OMB No. 2120-0020 Electronic Tracking Number MAJOR REPAIR AND ALTERATION Exp: 5mm gganEESan?iw (Airframe, Powerplant, Propeller, or Appliance) For FM Use Only Federal Aviation Administration INSTRUCTIONS: Print or type all entries. See Title 14 CFR ?43. 9 Part 43 Appendix and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report' IS required by law (49 U. S. C. ?44701). Failure to report can result in?a civil penalty for each such violation. (49 S. C: ?46301(a)) Nationality and Registration Mark: N51 PR Serial No.: 1425 1. Aircraft . . Make: Model: GIV SP Series: GIV Name (As shown on registration certi?cate) . Address (As shown on registration certificate) AC-1425 Address: 3420 3 Ocean ii 10 2. Owner . . . . City Highland Beach State: Florida Zip: 334874703 Country: United States of America 3. For FAA Use Only 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model SeriaI Number AIRFRAME (AS described in ?em 1 above) POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agencys Name and Address B. Kind of Agency Name S?evens Aviation. mc' El U.S. Certi?cated Mechanic [Manufacturer Address 600 Delaware St. Foreign Certi?cated Mechanic C. Certi?cate No. City GreenVille State 3mm cam'ina Certi?cated Repair Station Zip 29605 Country United States of America Certi?cated Maintenance Organization R368K D. I certify that the repair and/or alteration made to the unit(s) identi?ed in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the US. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge I, Extended range fuel Signature/Date of Au per 14 CFR Part 43 App. 7*7-48? . 7. Approval for Return to Service Pursuant to the authority given persons speci?ed below, the unit identi?ed in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is APPROVED REJECTED FAA Fit Standards . . . . Person Approved by Canadian inspector Manufacturer MaIntenance OrganIzatIon Department of Transport BY Other (Specify) FAA Designee Repair Station Inspection Authorization Certi?cate or Signature/Date of Authori Designation No. 01 7 FAA Form 337 (10-06) NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description ?of Work Accomplished . . . (if more space is required, attach additional sheets. identify with aircraft nationality and registration mark and date work completed.) N51PR 9/7/2018 Nationality and Registration Mark Date Removed #2 VHF antenna. Performed Eddy Current inspection to identify damage locations. Removed damage section of fuselage skin. Fabricated repair components. located and drilled. Performed Eddy Current inspection of repair components and adjacent structure. Installed repair components. Installed New VHF #2 antenna. VHF #2 antenna structural repair performed in accordance with Aery Aviation Engineering Order 1848-EO-2310 Rev. R. Dated 09/07/2018. XL . Additional Sheets Are Attached FAA Form 337 (10-06) GB US Department of Transportation Federal Aviatlon Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) OMB No. 2120-0020 Tracking Number Exp: 51311201 8 I or FAA Use Only such violation. (49 U.S.C. ?46301(a)) INSTRUCTIONS: Print or type all entries. See Title 14 CFR ?43.9, Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. ?4470?l). Failure to report can result in a civil penalty for each Nationality Mark N5l PR Serial No. erF 1 . Aircraft Make s?l?r?Qom Model Series as Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) Address C. t" P: 2' Owner A HlQhIC-l?d 910 C-h State LI 2 5 Zip Country 3. For FAA Use Only 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model Serial No. (As described in Item 1 above) POWERPLANT El AIRFRAME El PROPELLER Type APPLIANCE Manufacturer El 6. Conformity Statement A. Agency?s Name and Address B. Kind of Agency Hams $10. in :15 Av io?H on U. S. Certi?cated Mechanic Manufacturer Address 31 . cuy Grrernutllc mike?. a. 2959; ?gt?r?llt Foreign Certi?cated Mechanic C. Certi?cate No. t/ Certi?mted Repair Station Certi?cated Maintenance Organization D. I certify that the repair and/or alteration made to the unit(s) identi?ed in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the US. Federal Aviation Regulations and that the information fumished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 [3 App- Signature/Date of Aut riz 7. Approvat for Retum?t'o Service 9/71/2019 Pursuant to the authority given persons speci?ed below, the unit identi?ed in item 5 was inspected in the manner prescribed by the Designation No. Vtiasrrk SignaturelDate U/Wdual v/I Administrator of the Federal Aviation Administration and is DApproved [j Rejected FAA Flt. Standards - . . Persons Approved by Canadian In spect or Manufacturer Maintenance Organizatlon Department of Transport BY Other (Spec?y) FAA Designee Repair Station inspection AUthOI'ization Certi?cate or FAA Form 337 (10/06) Page 1 9/75/20)? NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable aimorthiness requirements. 8. of Work Accomplished {if more space is required, attach additional sheets. identify with aircralt nationality and registration mark and date work completed.) usur? 9/7/2018) Nationality and Registration Mark Date wacd 1* VHF an?fmna. Cum-tern inspco?Hon '1?0 lakn?fitf?x, damage Iotq?liang? Ramada, Jamaggco Sco?h?on 010 'Pusdaac :Ict'n. Fqbtiaq?lta? impair components, [cachet am) Jrintj. I?M-Format) Eddy iag'mc?tiort VF l?tpdt?l? eom'aonca?t'; CMJ a jewel!" S?h?uc?l?uf? Im?f?auvj Nf?qir compontn?lls. :Im?lelltai UHF 1?3 On?lmnol- in 2 Pm?hnna .S'?ud?ul?al qulah' Ptr-FarmeJ In Accel?cpamf kl?n?ln Ann, Avie-lion maintains Ufckf telle-vEd- 3340 Re. IR. DAdditional Sheets Are Attached FAA Form 337 (10/06) Page 2 FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Form Approved OMB. No. 2120-0018 Expiration Date 01/31/2021 0 APPLICATION FOR - Printaior type. Do not write in shaded areas; these are for FAAI . Re resentative. if additi a 3i $312532; Rwo RTHI NESS going [62:03.03 stra?ng?" 13:: 2:23; :GAht pe?nits complete Sectiogrsi1 Federal Aviation CERTIFICATE Ii. VI. and VII as applicable. Administration 1. REGISTRATION MARK 2. AIRCRAFT NAME (Make) 3. AIRCRAFT MODEL DESIGNATION 4. YR. MFR. FAA CODING N51 PR Aerospace G-IV 2000 5. AIRCRAFT SERIAL NO. 6. ENGINE NAME (Metro) 7. ENGINE MODEL DESIGNATION 1425 Rolls Royce Tay Mark 611-18 f. 0. NUMBER OF ENGINES 9. PROPELLER NAME (Metro) 10. PROPELLER MODEL DESIGNATION 11. AIRCRAFT Is (Checkifapplicebie 2 NIA NIA IMPORT IS HEREBY MAD FOR: (Check a unaut- items) A 1 STANDARD AIRWORTHINESS CERTIFICATE {Indicate mm norm 1mm moon I omen .1 SPECIAL AIRWORTHINESS CERTIFICATE (Check We items} 7 PRIMARY 9 LIGHT-SPORT pm. I Airplane I I Power-Panachute I Giider Lighter than Air 2 LIMITED 5 PROVISIONAL (Indicate class) 1 2 CLASS II 1 AGRICULTURE AND PEST CONTROL 2 AERIAL SURVEY 3 AERIAL ADVERTISING 3 Dr) "ma? 4 FOREST (mm conservation) 5 PATROLLING 6 WEATHER CONTROL c3! 0 OTHER (Speem 1 Ir RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION 4 AIR RACING 5 CREW TRAINING 6 MARKET SURVEY 0 To SHOW COMPUANCE WITH THE CFR 7 OPERATING (Primary Category) KIT BUILT AIRCRAFT EXPERIMENTAL (mm mason?) BA Existing aircraft without an airworthiness certi?cate 5 do not meet 5 103.1 I- 4 b, MW OPERATING BB Operating Light?Sport Kit-built SC Operating light-sport pre?cusly issued spatial light-Sport category aimorthiness Certifloate under 21.190 9 UNMANNED 9A RESEARCH AND DEVELOPMENT I 90 I CREW TRAINING AIRCRAFT 913 MARKET SURVEY 1 FERRY FLIGHT FOR REPAIRS. ALTERATIONS, MAINTENANCE, OR STORAGE . SPECIAL FLIGHT PERMIT (1mm 2 EVACUATE FROM AREA OF IMPENDING DANGER a ma?mfmm We) OPERATION IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT DELIVERING OR EXPORTING I 5 PRODUCTION FLIGHT TESTING 6 CUSTOMER DEMONSTRATION FLIGHTS I MULTIPLE AIRWORTHINESS CERTIFICATE (Cheek ABOVE 'Restricted Operaiian'end 'Standenfor 'Limitad'ae applicable) A. REGISTERED OWNER (As sham or.- certi?cate oleircrai'i registration) IF DEALER. CHECK HERE I LLC S. OCEAN BLVD #10 HIGHLAND BEACH, Ft. 33487 2 WCRAFT CERTIFICATION (crock aw Hacks and we items as inoiceter? ?35m: SPECIFICATION 0R TYPE CERTIFICATE DATA SHEET (Give ND. and Fwam?mmw term age give the number ?1 IZEA REV 22 0310112013 AIRCRAFT LISTING (Give page mmberfs}; SUPPLEMENTAL TYPE CERTIFICATE (List numberoi?each STC armoured} 3 c. AIRCRAFT OPERATION AND MAINTENANCE RECORDS 5 CHECK IF RECORDS IN TOTAL AIRFRAME HOURS EXPERIMENTAL ONLY (Enter hours ?own since first certificate Issued COMPLIANCE WITH 4465 1 3 rammed) 9 5 14 CFR section 91.41? - - D. CERTIFICATION - I hereby certify that I am the registered owner (or his agent) ofthe aircraft described above. that the aircraft is registered with the Federal Aviation Administration in accordance with Title 49 of the United States Code 44101 m. and applicable Federal Aviation Regulations. and that the aircraft has been inspected and is airworthy and eligible for the airworthiness certi?cate requested. DATE OF APPLICATION NAME AND TITLE (Pnnrortype) SIGNATUR 1 08/06/2018 Neil Collins, Agent For Service UM A. THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY: (Complete the section only I 14 CFR part 21.1mm) engine; 3 2 14 CFR part 121 CERTIFICATE HOLDER (em I 3 I CERTIFICATED MECHANIC (Gm Certi?cate NO.) 6 I CERTIFICATED REPAIR STATION (Give Certi?cate 5 a 5 Certi?cate No.) No.) 5 AIRCRAFT MANUFACTURER name or?rm} 2- DATE TITLE SIGNATURE (Check ALLappIicabIablockitemsAendB) THE CERTIFICATE REQUESTED g. A- I ?nd that the aircraft described in Section I or VII ?eets requirements for 4 1? AMENDMENT OR MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE B. Inspection for a speciei permit under FAA INSPECTOR It FAA DESIGNEE 5 by. CERTIFICATE HOLDER UNDER 1 14 CFR part 65 I I 14 CFR part 121 OR 135 I I 14 CFR part 145 t; DATE MIDOIFSDO FAA INSPECTORS SIGNATU or IGNE FAA FILE REVIEW 0 7 A UG OFFICE 4 SIGNATURE AND NC. 1 SIGNATURE f/ff/f/ 20,3 A 8?1 2 Eric P. Minnie DA 628092562 FAA Form 8130-6 (04-2011) All Previous Editions Superseded Elecb'onic Format -PDF Page 1 of 2 oo peideoov VI. PRODUCTION FLIGHT TESTING A. MANUFACTURER NAME ADDRESS B. PRODUCTION BASIS (Check applicable item) PRODUCTION CERTIFICATE (Give production certificate number) TYPE CERTIFICATE OTHER: C. GIVE QUANTITY OF CERTIFICATES REQUIRED FOR OPERATING NEEDS DATE OF APPLICATION NAME AND TITLE (Print or type) SIGNATURE VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT TEST A. DESCRIPTION OF AIRCRAFT REGISTERED OWNER ADDRESS BUILDER (Make) MODEL SERIAL NUMBER REGISTRATION MARK 3. DESCRIPTION OF FLIGHT CUSTOMER DEMONSTRATION FLIGHTS El (Check ifappiicable) FROM To VIA DEPARTURE DATE DURATION C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EQUIPMENT I PILOT I I I I FLIGHT ENGINEER I I OTHER (specrry) D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS: E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION: (Use attachment if necessary) F. CERTIFICATION - I hereby certify that I am the registered owner (or his agent) of the aircraft described above; that the aircraIt is registered with the Federai Aviation Administration in accordance with Title 49 of the United States Code 44101 31359. and appiiwble Federal Aviation Regulations; and that the aircraft has been Inspected and is safe for the ?ight described. DATE NAME AND TITLE (Print or type) SIGNATURE A. Operating Limitations and Markings in Compliance With 14 CFR Section 91.9. G. Statement of Contormity, FAA Form 3130-9 (Attach when required) As Applicable 5 H. Foreign Airworthiness Certi?cation for Import Aircratt a a B. Current Operating Limitations Attached mm") E. c. Data. Drawings. Photographs. eta (Attach when required) Previous mess Cem?cate at! dance With DE 5 14 CFR Section CAR (Originalettached) D. Current Weight and Balance Information Availahie In Aircrait m, J. I 5 E. Major Repalr and Alteration. PM Form 337 (Attach when required) Current IrworthIness CerIIfIcete ssued rdanoe I :3 14 CFR Section 21-191 (Copy attached) F. This inspection Recorded In Aircra? Records K. Light-Sport Aircraft Statement of Compliance, FAA Form 8130-15 (Attach when required) FAA Form 8130-6 {044011) All Previous Editions Superseded Electronic Format - PDF Page 2 of 2 152110-12. ?imam? . m?smnmexceedm IFS. UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION - FEDERAL AVIATION ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE A EXPERIMENTAL PURPOSE RESEARCH AND DEVELOPMENT MANU- NAME FACTURER ADDRESS FROM FLIGHT TO I A N- 51PR SERIAL NO. 1425 BUILDER AEROSPACE MODEL G-IV DATE OF ISSUANCE 24 JUN 2013 EXPIRY 24 JUN 2019 LIMITATIONS DATED ARE PART OF THIS CERTIFICATE IGNATURE 0 REPRESENTATIVE DESIGNATION OR OFFICE NO. DART-200064EA imprisonm not exce mg 3 years. 0 th. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT Any ow?isusg th? certi?cate may be punishable by a ?ne not exceeding $1,000 or IN ACC DANCE WITH APPLICABLE TITLE 14. CODE OF FEDERAL REGULATIONS (CPR). FAA Form 8130-7 (04/2011) Previous Edition 071'04 May be Used until Depleted SEE REVERSE SIDE 0052-00-693?4000 This ainrvorthiness certi?cate is issued under the authority of Public Law 104-6, 49 United States Code (USC) 44704 and Title 14 Code of Federal Regulations (CFR). The airworthiness certi?cate authorizes the manufacturer named on the reverse side to conduct production ?ght tests, and only production ?ight tests, of aircraft registered in his name. No person may conduct production ?ight tests under this certi?cate: (1) Carrying persons or property for compensation or hire: and/or (2) Carrying persons not essentiai to the purpose of the ?ight. This airworthiness certi?cate authorizes the ?ight speci?ed on the reverse side for the purpose shown in Block A. This airworthiness certi?cate certi?es that as of the date of issuance, the aircraft to which issued has been inspected and found to meet the requirements of the applicable CFR. The aircraft does not meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention On International Civil Aviation. No person may operate the aircraft described on the reverse side: (1) except in accordance with the applicable CFR and in accordance with conditions and limitations which may be prescribed by the FAA as part of this certi?cate; (2) over any foreign country without the special permission of that country. Unless sooner surrendered, suspended, or revoked, this airworthiness certi?cate is effective for the duration and under the conditions prescribed in 14 CFR, Part 21, Section 21.181 or 21.217. U.S. Department of Transportation Federal Aviation Administration Operating Limitations for N51PR Aerospace 1425 Issue Date Aug 09, 2018 FAA Order 8130.21 Appendix 1) This aircraft does not meet the airworthiness standards of Annex 8 to the Convention on International Civil Aviation. Operations in airspace outside of the United States will require the permission of the applicable foreign authority. That permission must be carried aboard the aircraft together with this U.S. airworthiness certificate and, upon request, be made available to an FAA inspector or the applicable foreign authority in the country of operation. Operations may be further restricted by the applicable foreign authority. This may include not allowing use of an airport, requiring specific routing, and restricting flight over specific areas. The operator must comply with any additional limitation prescribed by the applicable foreign authority when operating in its airspace. (1) 2) These operating limitations do not provide any relief from any applicable law or regulation. This aircraft must be operated per applicable regulations and the additional limitations prescribed herein. Note that a clearance from air traffic control (ATC) is not authorization for a pilot to deviate from any rule, regulation, operating limitation, or minimum altitude, or to conduct unsafe operation of the aircraft. If ATC issues a clearance that would cause a pilot to deviate from a rule, regulation, or operating limitation, or in the pilot?s opinion, would place the aircraft in jeopardy, it is the pilot's responsibility to request an amended clearance. These operating limitations are a part of FAA Form 8130-7 and are to be carried in the aircraft at all times and to be available to the piiot in command of the aircraft. (2) 1 Page 3) This special airworthiness certificate is not in effect during public aircraft operations (PAO). Concurrent public/civil operations are not permitted; the aircraft cannot be operated as a civil aircraft and as a public aircraft at the same time. No weapons or special military mission systems may be added to the aircraft. This airworthiness certificate is not in effect during flights related to providing military services (that is, air combat maneuvering, air?to-air gunnery, target towing, electronic countermeasures simulation, cruise missile simulation, and air refueling). These activities are inherently military, not civil activities. The FAA makes the distinction between the authorized flights for experimental purposes, and PAO. Before operating this aircraft under this special airworthiness certificate following a PAO, the aircraft must be returned to the condition and configuration at the time of inspection for the issuance of this airworthiness certificate. The operator must have written procedures for returning the aircraft to the civil configuration. This action must be documented in the maintenance records. The maintenance records and entries must clearly differentiate between a civil experimental flight per this certificate and any other flights. (3) 4) Application to amend this certificate must be made to the local Flight Standards District Office (FSDO) or Manufacturing inspection District Office (MIDO). (4) 5) Not Applicable 6) Not Applicable 7) Not Applicable 8) The pilot in command must hold? An appropriate type rating (if one has been established); or An experimental aircraft authorization, by make and model, on their pilot certificate; or A temporary letter of authorization (LOA) issued by an FAA Flight Standards Operations inspector. (8) 9) Not Applicable 10) Additional required members must hold the appropriate airman certificate. (10) 11) When filing a flight plan, the experimental nature of this aircraft must be listed in the remarks section. (11) 12) Not Applicable 13) This aircraft must not be used for towing, including, but not limited to glider towing, banner towing, target towing, or towing electronic receivers or emitters. This aircraft must not be used for intentional parachute jumping. (13) 2 Page 14) If aircraft, engine, or propeller operating limitations are exceeded outside of planned test conditions, an appropriate entry will be made in the maintenance records. (14) 15) No person may operate this aircraft unless it is maintained per an inspection program meeting the scope and content described in The operator must select and identify in the aircraft maintenance records one of the following programs for the inspection of the aircraft: For type-certificated aircraft, a current inspection program recommended by the manufacturer; or For former-military aircraft, an inspection program recommended by the manufacturer or North Atlantic Treaty Organization (NATO) military service; or An FAA-approved inspection program. Note: To extend an inspection interval, the owner/operator must submit a request for that extension with supporting documentation and data to the local F500 and obtain concurrence from that FSDO. Inspections must be recorded in the aircraft maintenance records showing the following, or a similarly worded, statement: certify that this aircraft has been inspected on (insert date] per [identify applicable inspection program] and found to be in a condition for safe operation.? (15) 16) Not Applicable 17) Not Applicable 18) Not Applicable 19) Only FAA-certificated repair stations, FAA-certificated mechanics with appropriate ratings, or a manufacturer as authorized by 43.3 may perform inspections required by these operating limitations. (19) 20) The aircraft may not be operated unless the replacement for life-limited articles specified in the applicable technical publications pertaining to the aircraft and its articles are complied with in one of the following manners: Type-Certificated Products: Replacement of life-limited parts required by 91.409(e) applies to experimental aircraft when the required replacement times are specified in the U5. aircraft specifications or type certificate data sheets. Non?Type? Certi?cated Products: All articles installed in non-type-certificated products operated under an airworthiness certificate issued for an experimental purpose, in which the manufacturer has speci?ed limits, must include in their program an equivalent level of safety for those articles. These limits must be evaluated for their current operating environment and addressed in the approved inspection program. All articles installed in non-type-certificated products in which the manufacturer has specified limits, must include in their program an equivalent level of safety for those articles. The article must be inspected to ensure the equivalent level of safety still renders the product in a serviceable condition for safe operation. (20) 21) For aircraft originally incorporating fatigue life recording systems, the owner/operator must maintain and use the system as prescribed by the aircraft manufacturer and comply with the manufacturer's fatigue life limits. (21) 3 Page 22) Not Applicable 23) Not Applicable 24) Not Applicable 25) Not Applicable 26) When changing between experimental operating purposes, the operator must determine that the aircraft is in a condition for safe operation and appropriate for the purpose intended. A record entry will be made by an appropriately rated person to document that finding in the maintenance records. (26) 27) Not Applicable 28) Not Applicable 29) Not Applicable 30) Not Applicable 31) Not Applicable 32) Not Applicable 33) Not Applicable 34) Not Applicable 35) Not Applicable 36) Not Applicable 37) Not Applicable 38) Not Applicable 39) Not Applicable 40) Enhanced Flight Vision System (EFVS) operations for the purpose of research and development and/or showing compliance with regulations are not authorized if any component associated with the instrument approach procedure being flown, or any component of the approach lighting system associated with the instrument approach, is inoperative. (40) 4 Page 41) Not applicable 42) Not Applicable 43) Not Applicable 44) Not Applicable 45) Not Applicable 46) Not Applicable 47) Kinds of operations authorized: Day VFR flight operations are authorized. (47) 48) Night flight operations are authorized if the instruments specified in 91.205(c) are installed, operational, and maintained per the applicable requirements of part 91. (48) 49) instrument flight operations are authorized if the instruments specified in 91.205(d) are installed, operational, compliant with the performance requirements of, and maintained per the applicable regulations. All maintenance or inspection of this equipment must be recorded in the aircraft maintenance records and include the following items: date, work performed, and name and certificate number of person returning aircraft to service. (49) SO) instrument flight operations are authorized if the instruments specified in 91.205id) are installed, operational, compliant with the performance requirements of, and maintained per the applicable regulations. The pilot in command must have a method to comply with the 91.319(c) prohibition from operating over densely populated areas or in congested airways. All maintenance or inspection of this equipment must be recorded in the aircraft maintenance records and include the following items: date, work performed, and name and certificate number of person returning aircraft to service. (50) 51) Not Applicable 52) Not Applicable 5 Page 53) All flights must be conducted within the geographical area described as follows. 2100 Nautical mile radius (1/2 fuel range) from one of the following home bases: *Manassas, VA (KEHF) *Twin Falls, lD (KTWF). Flights for maintenance, as defined in 1.1, of the aircraft are permitted outside the defined area. (53) 54) Not Applicable 55) Flight over a densely populated area or in a congested airway is authorized per 91.319lc) only for the purpose of takeoff and landing. The area on the surface described by the term ?only for the purpose of takeoff and landing? is the traffic pattern. For the purpose of this limitation, the term ?only for the purpose of takeoff and landing" does not allow multiple traffic patterns for operations such as training or maintenance checks. This does not restrict a go around/rejected landing for safety reasons. When avoiding populated areas, aircraft speed and weight must be considered. The information in FAA Order 8900.1, Flight Standards Information Management System (FSIMS), regarding set-back distances from spectator areas for aviation events such as air shows or air races may assist in determining a suitable space to fly the aircraft. (55) 56) Not Applicable 57) Operations in RVSM-designated airspace may be allowed under 91.180(b) for climbing/descending through RVSM flight levels without intermediate level?off to or from flight levels above RVSM airspace. Refer to part 91 and the Aeronautical Information Manual. (57) 58) Not Applicable 59) Not Applicable 60) Not Applicable 61) No person may be carried in this aircraft during flight unless that person is essential to the purpose of the flight. (61) as. 7?s P. DAR-F 628092562 6 Page PRIORITY 1 HOLDINGS, LLC 7900 Westpark Drive Tysons Corner, VA 22102 Aug 8, 2018 To Whom it may concern, This letter certifies that Aerospace Corporation GIV, serial number 1425, FAA registration number N51PR is owned by Priority 1 Holdings, LLC AC-1425, LLC. Priority 1 Holdings, LLC AC-1425, LLC has contracted with Aery Aviation to manage the modification of this aircraft. The modification contract includes maintenance, inspections, alterations, and repairs. This letter certifies that Jon Kiser, Ed Spirko and Neil Collins are Priority 1 Holdings, LLC AC-1425, LLC representatives authorized to approve changes in aircraft configuration and certifications. If there are any questions regarding their authority to represent Priority 1 Holdings, LLC AC-1425, LLC on issues regarding Aerospace Corporation 6 IV, serial number 1425 with registration N51PR, please do not hesitate to contact me. Sincerely, WW Andrew Palowitch, CEO Priority 1 Holdings 571 335 2631 STATE OF MARYLAND COUNTY OF ST MARYS Personally appeared before me, a Notary Public, in and for said county and state, on this El day 2,0 i?b, the within named 2 2g \Qgg} Ii: known to me, or satisfactorily proven, to be the person whose name is subscribed to the within instrument and who acknowledges that he executed the same for the purposes therein contained. emu) NOTARY PUBLIC Print Name: A?uAkvv?f?i? My Commission Expires: '10?22. 2? a EC 57 gar Date: 06 Aug 2018 Attn: Mr. Eric Minnis, DAR-F Experimental Research and Development Program Letter, Revision 2 N51 PR SIN 1425 1) Project Description: a. N51PR is being used to determine compatibility and operational functionality of the following systems: i. Tracer Radar ii. Hdi Camera Viasat Sat-com b. STC Program Number ST00464MC-T has been initiated with the FAA MCO. This experimental ?ight test program will be accomplished in accordance with Aery document SYSTEM FLIGHT TEST rev IR or latest revision; and TEST rev IR or latest revision. 2) Number of aircraft required: a. N51PR is the only aircraft required for this project. 3) Duration: a. 1 year Experimental RD certi?cate is requested. 4) Number of ?ights and or hours: a. Estimate of 1200 hours b. Estimate of 100 ?ights 0. Estimate does not include positioning time to and from ?ight test location. 44174 Airport Rd, Suite 300, Califomia, MD 20819 - I 3 301-373-2101 Telephone 301-373-2154 Facsimile 5) Geographic area of Experimental RD ?ight test to check compatibility and operational functionality of STC is described as follows: a) A radius that consists of V2 aircraft fuel range around the following base(s) i. Manassas, VA (KEHF) ii. Twin Falls, ID (KTWF) Contact person during Experimental RD Flight Test period is Mr. Neil Collins 719-425-0215 Thank You, Neil Collins 44174 Airport Rd, Suite 300, California. MD 20619 301-373-2101 Telephone 301-373-2154 Facsimile OMB No. 2120-0020 Electronic Tracking Number MAJOR REPAIR AND ALTERATION Ex?: 5?31?2018 (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Federal Aviation Administration INSTRUCTIONS: Print or type all entries. See Title 14 CFR ?43.9. Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. ?44701). Failure to report can result in a civil penalty for each such violation. (49 U.S.C. ?46301(a)) Nationality and Registration Mark: N51 PR Serial No.2 1425 1. Aircraft .7 Make: Aerospace Model: SeneS- Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) 2? Owner LLC Address: 3420 S. Ocean BLVD #10 City: Highland Beach State: FL Zip: 33487-4703 Country: U.S.A. 3. For FAA Use Only 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model Serial Number AIRFRAME (As described in Item 1 above) El POWERPLANT El PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agench Name and Address B. Kind of Agency Name Stevens Aviation Inc. El us. Certi?cated Mechanic El lManufacturer Address 600 Delaware St. El Foreign Certi?cated Mechanic C- Certi?cate No- City 31316 .39. Certi?cated Repair Station VI BR368K Zip_2_9_6_0_5_ Country USA El Certi?cated Maintenance Organization D. I certify that the repair and/or alteration made to the unit(s) identit? ed in item 5 above and describ on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U. 8. Federal Aviation gulations and that the information furnished herein' is true and correct to the best of my knowledge. Extended range fuel Signature/Date of Authorized Individual per 14 CFR Part 43 Scott Hansel App. 7. Approval for Return to Service Pursuant to the authority given persons speci?ed below, the unit identi?ed in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is APPROVED El REJECTED FAA Standards . . . Person Approved by Canadian In Sp ct or Manufacturer Maintenance Organization Department of Transport BY Other (Specify) FAA Designee Repair Station Inspection Authorization Certi?cate or Signature/Date of Authorized Individual Designation No. . VIBR368K Michael J. Ramsey FAA Form 337 (10-06) NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. identify with aircraft nationality and registration mark and date work completed.) N51 PR Nationality and Registration Mark Date MAJOR ALTERATION: Aircraft Total Time 8,262.3 Aircraft Total Cycles 5,283 1) Accomplishment of Chicago Jet Group. LLC. STC ST033690H. Certi?cation of the aircraft data link system used for communication supporting Air Traf?c Services (ATS) and installation of an ICG Iridium Satcom, installation of the Universal Avionics UniLink UL-801 Communications Management unit. and Flight Management system(s) in accordance with the Chicago Jet Group Master Drawing list Doc. No. DB1211002 Revision D. dated August 5, 2015. or later FAA approved revision. Major Parts/Components Installed- 10801-01 UL-801 Unilink Processor K12030-1 UniLink Install Kit 108009 UL-801 Con?g Module K12080 Antenna Kit 10708 GPS Antenna for WAAS FMS Solid State DTU Install Kit K12025 UNS-1CSPI1 ESP INSTALLATION KIT 30191 Con?g Module. CONFIG MODULE. UNS-1ESPW 3192-00-111106 FMS 16301-02 Area Mic CCU Instal! Kit 1641-110?02 Control Unit 1606?01-00 CVR Annunciator, LED-40-17-HE-EORXT I428-A-0010-02 AMT-700 HGA K12083-1 Install Kit 1242-A-0006 LNA (LOW NOISE AMPLIFIER) DIPLEXER (TYP F) 1428-F-0911 AMT-TOO-G -04 PLATFORM 7516222?901 RFU INTERFACE ADPATER (RFUIA) 7516118-27010 SATELLITE DATA UNIT SD-TOD 2) Compiled with Stevens Aviation Inc.. Engineering Order. MOS-7000 Equipment Integration Document 06-602-005 Rev IR dated 04/10/2018. 31 DER approved minor deviations are documented on Aery Aviation Drawings; IDwg ?Title ?Rev ?Rev Date I [174923309001 DIAGRAM, UNILINK [6/2/2018 L174ea460-9001 - FMS ? 5l312018 174ea4so-9002 - WIRING DIAGRAM. FMS ?6/1 3l2018 Reference attached 8110-3, Dated June 29?11 2018. 4) Details of this Major Alteration are on ?le at Stevens Aviation, Inc ref work order GYH-WO-9569. Aircraft log entry recording this Major Alteration was completed. Aircraft was reweighed at this time. Equipment list updated to re?ect atteration. Aery Engineering Document Number 1749-ED-1013. Rev IR, Dated June 29th. 2018 includes the electrical loads changes from this alteration. . Instruction's for Continued Ainlvorthiness: Chicago Jet Group, LLC ICA Document Number DB4109010 Rev. IR. dated 10-17-2014. 0 Aircraft was secured for ?ight. END IZI Additional Sheets Are Attached FAA Form 337 (10-06) US. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1. DATE STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS (17/25/20 8 I I I AIHUHAH UR COMPUNENTIDENTIFICATI 2. MAKE 3. MODELNO. 4. TYPE (Aircraft, Engine, Propeller: 5. NAME OF APPLICANT GU EAM IV etc.) AERY AVIATION AIRCRAFT LIST OF DATA I a. IDENTIFICATION . TITLE 1749-2330-9001. REV A OD-WIRING DIAGRAM. UNILINK 6I2l2018 1749-3450-9001. REV MOD WIRING DIAGRAM ADS-B UPGRADE orzma 1749-3460-9001. REV A IMOD - FMS 51312018 1749-3460-9002. REV a MOD - WIRING DIAGRAM. FMS 6I1312018 1749?1504013. REV IR - ELECTRICAL LOAD 7125/2018 NOTES: 1. This approval Is for Engineering design data only. It inc?cates the data listed above demonstrates comp?ance with the regulations speci?ed by paragraph and subparagraph below as Applicable Requirements. Compliance with additionat regulations not listed here is required. Only the electrical systems aspects of the above I?Ismd data are approved herein. to TCDS #At 2EA. 8. PU RPOSEOF DATA In support of deviations to APPROVED MODEL LIST STC STOSSB9CH and 31113424c1-1 on GIV Serial Number 1425. 9. APPLICABLE REQUIREMENTS (List speci?c sections) 14 CFR Part 25 Paragraphs. (Amendment Level Donated by 25400: [Amdt 25-123}; 25.1 135(1)) {Am 721; 25.13011AII) {Amdt 25?123]: {Amdt 25.1231; 25.1357 [Amdt 25-123}; 25.1431 (All) [Amdt 25-113] to. CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limltations of appointment under 14 CFR Part 183. data Itsmd above and on attached sheets numbered have been examined in accordance with established procedures and found to comply with applicable requirements of the Standards listed. Recommend approval of these data IGNOITherefore Approve these data I WW Leslie 3_ (STEVE) Walton <1 2 BERT-810179-NE Electrical Systems . I FAA 3110-3 (03110) SUPERSEDES PREVIOUS EDITION ?nite}; 51.21125 nf arteries nf g??eheral ?irtation ?nnplemerttal (@ng alertificate MW ST03369CH WW Mb Chicago Jet Group LLC 43 W522 Route 30 Sugar Grove, IL 60554 WM 25 Federal AViation gm See attached Federal Aviation Administration (FAA) Approved . Model List (AML) number for approved aircrait models and applicable airworthiness regulations. Jam/a! We g?zya- Certi?cation of the aircraft data link system used for communication supporting Air Traf?c Services (ATS) and installation of an ICG Iridium Satcom, installation of the Universal Avionics UniLink"D Communications Management Unit; and Flight Management System(s) in accordance with the Chicago Jet Group Master Drawing List Doc. No. DB1211002 Revision D, dated August 5, 2015, or later FAA approved revision. 32W (ma/KW: l. The installer must determine whether this design change is compatible with previously approved modi?cations. 2. If the holder agrees to permit another person to use this certi?cate to alter a product, the holder must give that person written evidence of that permission. 3. FAA approved Airplane Flight Manual Supplement as listed on AML number STO3369CH, or later FAA approved revision, is required on board the modi?ed aircraft. 4. Additional Limitations and Conditions may be listed on AML number ST03369CH. ?2 . . 5 @a/ag/WW'November 16, 2012 Pia/am I 'August 14, 2014 September 10, 2015 gnature) Steven L. Lardinois L- Manager, Systems and Flight Test Branch Chicago Aircraft Certi?cation Of?ce (Title) Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both. PM Form PAGE I of 2 PAGES This certificate may be transferred in accordance with FAR 21.47. Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03369CH Chicago Jet Group FOR Certi?cation of the aircraft data link system used for communication supporting Air Traf?c Services (ATS) and installation of an ICG Iridium Satcom, Universal Avionics UL-801 Unilink System and Universal Flight Management System(s). FAA APPROVED AIRCRAFT FLIGHT MANUAL SUPPLEMENT FAA APPROVED MASTER DRAWING LIST AML REV DATE AIRCRAFT MAKE AIRCRAFT TCDS ITEM MODEL NO. Date Approved 8-28-2015 Number/Rev" Number Rev*/Date 1. Dassault Mystere-Falcon 900 A46EU 8-5-2015 Aviation Falcon 900EX DB 1405006 A DB 1405007 IR 8-28-20] 5 8-14-2014 Aerospace G-IV A12EA DB1211004 lA [3131409011 IIR 8-28-2015 8-28-2015 DB1211002 The Boeing Company 767-200 Series AINM 1331211004 IA DB1409018 IR 8-28-2015 8-28-2015 DBIZIIOOZ 8-5-2015 8-5-2015 *Or later FAA-Approved Revision FAA Approved Steven L. La inois Manager, Systems and Flight Test Branch Chicago Aircraft Certification Of?ce Date Issued: September 10, 2015 Page 1 of 3 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03369CH Chicago Jet Group FOR Certification of the aircraft data link system used for communication supporting Air Traf?c Services (ATS) and installation of an ICG Iridium Satcom, Universal Avionics UL-801 Unilink System and Universal Flight Management System(s). AML Item I a. The aircraft must be maintained in accordance with the Instructions for Continued Airworthiness (ICA), Section 15.0 Airworthiness Limitations, identi?ed in Chicago Jet Group Document DB 121 1005, revision B, FAA Approved September 10, 2015 or later FAA approved revision. b. With the added single, standalone Universal Avionics Flight Management System installed, Airplane Flight Manual Supplement as listed on this AML is required on board the modi?ed aircraft. c. With the dual Universal Avionics Flight Management Systems installed, Airplane Flight Manual Supplement 081405007 as listed on this AML is required on board the modi?ed aircraft. Note: ?Triple con?guration requires both Airplane Flight Manual Supplements DB 1405006 and DB 1405007 on board the modi?ed aircraft. AML Item 3 a. The aircraft must be maintained in accordance with Instructions for Continued Airworthiness (ICA), Section 15 Airworthiness Limitations, identi?ed in Chicago Jet Group Document 031409017, Revision IR, FAA Approved September 10, 2015 or later FAA approved revision. SEQ/game? ?aw AML Item 1 The certi?cation basis for the changed Dassault Mystere-Falcon 900 and 900EX as described in this AML is as follows: a. The type certi?cation basis for the Mystere-Falcon 900 and 900EX aircraft is shown on TCDS A46EU for parts not changed or not affected by this change. i b. The certi?cation basis for parts changed or affected by this change since the reference date of application, December 8, 2014, is shown on TCDS A46EU. In addition, the applicant has complied with 14CFR Part 25 as amended by Amendment 25-123 as noted: [25.1353 I AML Item 2 The certi?cation'basis for the changed G-IV as described in this AML is as follows: a. The type certi?cation basis for the G-IV aircraft is shown on TCDS A12EA for parts not changed or not affected by this change. b. The certi?cation basis for parts changed or affected by this change since the reference date of application, December 8, 2014, is shown on TCDS A12EA. Page 2 of 3 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03369CH Chicago Jet Group FOR Certification of the aircraft data link system used for communication supporting Air Traf?c Services (ATS) and installation of an ICG Iridium Satcom, Universal Avionics UL-801 Unilink System and Universal Flight Management System(s). 59%mm .x?/?emdm: (continued) AML item 3 The certi?cation basis for the changed Boeing 767-200 Series as described in this AML is as follows: a. The type certi?cation basis for the Boeing 767-200 Series aircraft is shown on TCDS AINM for parts not changed or not affected by this change. b. The certi?cation basis for parts changed or affected by this change since the reference date of application, December 8, 2014, is shown on TCDS AINM. In addition, the applicant has complied with 14 CFR Part 26 as amended by Amendment 26-1 as noted: I 26.11(c) I 26.47(c) END Page 3 of 3 Chicago Jet Group LLC Master Drawing List 43W522 Route 30 Document No. 031201002 Revision Sugar Grove IL 60554 Master Drawing List Document Number: Luke: Arr Tra rvicesA Installation of a Dang glernunicap?t?S $yste?porting QML ?5583? WW 00 FAA APPROVED - 7c.2_ FEB 22 2018 CHICAGO AGO amen a. A Page 1 of 7 Chicago Jet Group LLC 43W522 Route 30 Sugar Grove IL 60554 Master Drawing List Document NO. 081201002 Revision ?e REVISIONS Ii LEVEL DESCRIPTION APPROVED DATE IR Initial ReIease DL3 7-27-12 Revised: A DB1108003 9443 331204010 031207012 DB1111026 331201005 D31204012 Added: 031308006 A . 3 Added 02 Con?gurahon ,kk 9-29-14 Revised (Eagle 2-17-15 0 Added 03 04 (EN 01.3 (3U 9-17-15 Con?gu AddedOWOOn (2x 11-25-15 FMS 2-26-16 :Qgirjgura?on narrow . 03 031509006 any Inswwonmgn?nued 04 031509003 5W1 04 031509007A Suppleni?nt. 04 IR New Con?guration Universal 04 caeisylnor IR Datelinlrl? Con?gliliratianUniversal Avionics UL-801 04 Instru?titionsjorngtinried Airworthiness 05.06. 07 ,oeisogpif IR Elecuioarifoadnjnaly?sis 05.06 (031593013 lR Airplane FIiLgh?tAManual Supplement. Dual 05 A Universal Avionids UL-801 05 CJG14W011 3 ?glaIWSKCon?gura?on Universal UNS-1 Ew 05 (Aircra? .F2000 SIN 028 1 only) CJG14W029 ?B?al FMS Con?guration Universal 05 081503011 ARR Wmlane Flight Manual Supplement, Single 06. 07 CJG15W038Q IR No. 3 FMS Con?guration Universal 06, 07 CJG15W040 f\ Datalink Con?guration Universal Avionics UL-801 06, 07 031511009U Airplane Flight Manual Supplement. FANS g: 04. 05.06. 07. DB1602004 IR Eiecirioai Load Analysis 08 031602003 A Instructions for Continued Airworthiness 08 031609009 A Con?guration Report 08 Page 4 of 7 Chicago Jet Group LLC 43W522 Route 30 Sugar Grove IL 60554 Master Drawing List Document No. 081201002 Revision INSTALLATION DOCUMENTS ,1 Reports: . Rev Description con?g 1: 031705005 Ground Test Plan. ATN 31 4301143 081705009 IR a A For the installation the following drawings in Table 1 should be Table 1 INSTALLATION DESIGNQATA Drawings Rev Description Wiring Diagrams A ICG Iridi in" ta! on Will 0' ram 01 031103002 'lgiand dag) lag ICG, 12 Iridium Installation Vl?rin 01 031303006 (Nag-trains? data ?lnction only. no ?$33935" 081108003 titriversaltlnilink lnstalla?oi?rVI??itg?Di?agtam 01 031206015 IR tritii?tr?rna?nd 01 Iridium lnstat \Mn? 0' 02 051406004 081406003 X13 ?UniverSaI?Bni?hk \Mring Diagram 02 081406005 :7 Iridiurr?ahiixljnilink SyStemwt?e Routing Diagram 02 031503003 universal Wiring Diagram 03 lag >I/?/dium I tion Win? 0? ram 03 031503004 ?Kr/f 11% ?ush "g as 031503005 IR #33 stadium System Wire Routing Diagram 03 ouotswomm 1M 1} WID 04 WID Dataiitilt?s'ystem Universal Avionics UL-801 04 c.131swois\\ (tr/mm System ICG ICS-120N220A 04 031500009 \\le NFMSASDU. Unilink System erle Routing Diagram 04 \WLDgoual FMS Upgrade to 05 mutton yxwro Datalirlk System Universal Avionics UL-301 05 cJe?ittv?iloza A ,wer Iridium Phone System ICG ICS-120N220A 05.06 wro No. 3 FMS Universal UNS-1ESPW 06. 07 5W039 f? WID Datelink System Universal Avionits UL-801 06 081503014 0 VA FMS. Iridium Unilink System Wire Routing Diagram 05.06. 07 c.1315w041 A WID Datelink System Universal Avionics UL-801 07 3 we Datelink System (Unilink UL-801) 03 CJG-GEBDSOJW A WID Iridium (ICS-120A or lcs-220A) 03 0816013003qu 4\ 1R Iridium 81 Unilink System Wire Routing Diagram 08 DB1111026W Iridium Transceiver and Unilink Installation 01 081111025 IR 2 Bracket 01 081203019 IR Relays Mount Plate Installation 01 031203020 lR Relays Mount Plate 01 031204010 iR Cordless Phone Installation 01 031204009 IR "Cordiess Phone Bracket 01 Page 5 of 7 Chicago Jet Group LLC Master Drawing List 43W522 Route 30 Document No. 081201002 Revision Sugar Grove IL 60554 Table 1 (Continued) INSTALLATION DESIGN DATA a Drawings Rev Description Con?g Structural 031203023 IR Annunciators Installation 01 031203022 IR Dialer installation 01 031203021 IR Circuit Breakers Installation 01 DB1201012-A NIC 867-1 575-165 ltidiumIData nnel Antenna 01 Doubier Design and lnstal DB1201012-B NIC Antenna Removal and Rep?tht with 665- 01 3230-1 3 VHF Antenna NIC Pressurized Floor Connector (PE-9154) 01 031409024 IR ICS-120A1220A angcm Installation 02 031409025 IR Unilink mengtalla?on 02 031409027 IR Hat 02 031409034 IR Anna?noiators installation 02 031409035 IR @3113me instelation MW 02 031405010 IR A I?tli?ri?tntenna iraalia?lian t\ )i 02 031509003 IR 1:1de Antenna limitation Aim) 03 081509004 IR UE-801 Unilin CPU 108-120 03 ?1anth 081509011 ($111127 WF Emmana 03 0315090114101 3% 03 D81509011-002 A it EE A 03 031509011003 IR WWet 03 031509011004 IR Wt? A 03 031503008 REL detpit??q?i?tne?t Layout 03 [1119 GPS Anht?lna Installation 04 JW mini Amhna Instl. 04 Y3 Panel and Pedatal Mod 04 0.163ng ?6,413 Wk System (UL-801) 04 mats-M07 mg \Il'idium InstI. or ice-220A) 04 Antenna Installation (365-8280) 04 mm, indium (lcs?1zonotlcs-220A) 05.05 \Nc Indium Antenna 05.06 it 9 NC Datalink System (UL-801) 05.05.07 NC Cockpit Mod. 05,06. 07 NC GPS Antenna 05. 07 A indium Antenna Installation 03 - CJG-GEBD6011M033 NC VHF Antenna Installation 08 NC UL-801 and Inst! 08 NC Flight Instrument Panel Mod 08 NC VI-IF F8621 Bulkhead Feedthru 08 Page 6 of 7 D?mm? ?Ea MQQ GIV Stevens Aviation, Inc. STEVENS 600 Delaware St. MOS-7000 Equipment Integration AV AT ON Greenville, SC 29605 Document Number: 06-602-005 ENGINEERING ORDER HONEYWELL MCS-7000 Equipment Integration GIV N51PR 1425 DOCUMENT NUMBER: 06-602-005 Revision: IR Date: 04/10/18 PROPRIETARY DOCUMENT The technical Data and design enclosed are the exclusive property of Stevens Aviation Inc. and the recipient of this document agrees to hold in con?dence the technical data and design contained herein. Reproduction by written permission only. Revision: IR Page i CQEEXZMNAJION STEVENS Stevens Aviation, Inc. 600 Delaware St. Greenville, SC 29605 GIV Equipment Integration Document Number: 06?602-005 LOG OF REVISIONS Prepared Reviewed Rev Description By Date By Date IR Initial Release R. Hessel 04/10/18 B. Carr 04/10/18 Revision: IR Page ii i Stevens Aviation, Inc. GIV STEVENS 600 Delaware St. Equipment Integration AV AT ON Greenville, SC 29605 Document Number: 06-602?005 TABLE OF CONTENTS Section Topic Page LOG OF REVISIONS ii TABLE OF CONTENTS 1 Scope 1 2 Description 1 3 Effectivity 1 4 Locator Diagram 1 5 Component Removal/Installation Chart 2 6 Gaining Access 2 7 MOS-6000 SDU Removal 2 8 MOS-7000 SDU Installation 2 9 MOS-6000 RFU Removal 2 10 MOS-7000 RFU Installation 2 11 Close Up 3 12 Sign Off 3 Revision: IR Page Stevens Aviation, Inc. GIV STEVENS 600 Delaware St. MOS-7000 Equipment Integration AV AT ON Greenville, SC 29605 Document Number: 06-602-005 1 Scope The purpose of this document is to de?ne the step-by-step instructions and provide a certi?cation path for the integration of a Honeywell-Thales MOS-7000 SATCOM system. 2 Description of Modification The integration consists of the removal of the existing MOS-6000 SATCOM system and the installation of a MOS-7000 SATCOM system. NOTE: Reference Honeywell Sales Bulletin HSB 2018-16 3 Effectivity N51PR 1425 4 Locator Diagram SATELLITE DATA UNIT FS 723.0 LBL 15.0 RADIO FREQUENCY UNIT FS 723.0 LBL 22.0 Revision: IR Page 1 Stevens Aviation, Inc. GIV i STEVENS 600 Delaware St. MOS-7000 Equipment Integration AV HAT ON Greenville, SC 29605 Document Number: 06-602-005 5 Component Removal I Installation Chart Outlln Description Part Number Serial Number Out Satellite Data Unit 7516100-60-060 00082355 18.0 Out Radio Frequency Unit 7516240-60-060 00071621 24.0 In Satellite Data Unit 7516118-27010 67004151 21.4 In Radio Frequency Unit 751622-901 40507074 3.4 6 Gaining Access 1) Access to the existing Honeywell Radio Frequency Unit and the Honeywell Satellite Data Unit is obtain through the aft tailcone maintenance door located between FS 682.0 and FS 713.0 7 MCS-6000 SDU Removal 1) Locate the existing SDU labeled 2) Loosen the two rack knobs securing the SDU in the ECS mount rack (PIN 6045-109). 3) Remove SDU, protect connectors and tag as ?Serviceable". 4) Return unit to Honeywell. 8 MOS-7000 SDU Installation 1) Place new Honeywell Satellite Data Unit in existing ECS rack (ensure unit is seated fully forward into rack connectors). 2) Tighten the two knobs securing unit in rack. 9 MCS-6000 RFU Removal 1) Locate the existing RFU labeled 2) Loosen the two rack knobs securing the RFU in the ECS mount rack (PIN 6302-101). 3) Remove SDU, protect connectors and tag as "Serviceable". 4) Return unit to Honeywell 1O MCS-7000 RFU Installation 1) Place new Honeywell Radio Frequency Unit in existing ECS rack (ensure unit is seated fully into rack connectors). 2) Tighten the two knobs securing unit in rack. Revision: IR Page 2 STEVENS Stevens Aviation, Inc. GIV S: 600 Delaware St. MOS-7000 Equipment integration AV i ON Greenville, sc 29605 Document Number: 06-602-005 11 Close up 1) Ensure all tools used performing this E0 are accounted for. 2) Stow ladder and close the aft tail cone maintenance door. 3) Record accomplishment of this E0 in the aircraft records as required. 12 Sign Off Accomplished By: Signed: Date: inspected By: Signed: Date: Revision: IR Page 3 jaw-Mr 305 Cherokee Drive, Nev/port News, VA 23602 Phone: 757. 709.0077 ELECTRICAL LOAD ANALYSIS 1 749-ED-1013 REV: IR MISSION SENSOR AND COMMUNICATIONS SYSTEMS For Guifstream GIV-SP Aircraft - Serial Number 1425 FAA PROJECT ST00464MC-T Name Signature Date IR Prepared by R. Roytas 07/25/18 IR Checked by R. Roytas ZK 07/25/18 IR Approved by s. Walton 4 1% 07/25/18 PROPRIETARY NOTICE All data contained herein is the sole property of Aery Aviation, LLC. Disclosure, release or reproduction in whole or part of this proprietary document in any format or convention is not permitted without express written consent from Aery Aviation, LLC. For details and requests contact: guatitv@aeggaviation.com Aery Aviation, LLC. 305 Cherokee Drive, Newport News, VA 23602 Aery Aviation, LLC 1749-ED-1013 Electrical Load Analysis Rev IR 5: Page20f8 FAA STOO464MC-T Record of Revisions REV DATE APPROVED BY OF CHANGE IR See Cover See Cover INITIAL RELEASE Aery Aviation, LLC 1749-ED-1013 Electrical Load Analysis Rev IR Page 3 of 8 FM PROJ STOWMC-T Tablg of ngtents Section . . . Pagg 1.0 INTRODUCTION . .. 4 1.1 Purpose 4 1.2 Modi?cation Descriptlon 4 2.0 SYSTEM CHARACTERISTICS .. -. . . 5 Aery Aviation, LLC - Electrical Load Analysis Rev lR . Page 4 of 8 ?mk FAA srocmmc-T 1.0 INTRODUCTION 1.1 Purpose The purpose of this document is to define the engineering and certification services for installations of mission systems provisions and equipment on a Guifstream Serial Number 1425 Registration N51 PR Aircraft. This document. 1749-ED-1013, Electrical Load Analysis. will show that these modi?cations are within the capacity of the aircraft electrical generating and power systems and the modifications are compliant with the requirements of 14 CFR 25. 25.1165(b) [Amdt 72], 25. 1301 (all) [Amdti 23], 25.1351 [Amdt 72] and 25.1431 [Amdt This report shall be approved by the Project Electrical Systems DER. 1.2 Modification Description Aery Aviation has been authorized by the applicant, AIRTEC Inc., and contracted to provide engineering and certi?cation services to install special mission modi?cations into a Guifstream Aircraft serial number 1425. The modification will be comprised of the following: 1. Installation of Zea and ?lea mission transceivers. installation of a bottom mounted Lockheed Martin Tracer radar system. installation of a tap mounted 18? Viasat Arclight Ku Satcorn system. installation of a Wescam MX15 EOIIR camera to lower fuselage. Installation of a cockpit to mission operator internal communications system. Installation of a 28VDC Mission Power Distribution and Loadshed System. Addition of an Eldec installation 28vdc, 200amp mission power transformer rectif er unit (T RU) Replacement of an existing Honeywell SATCOM system with more current system. Removal of the existing Honeywell AFIS system. 10. Replacement of the VHF 3 communications transceiver cockpit interfaces with the 182. 11. Installation of Zea PRC-117 antennas and 1ea GPS antenna. 12. Deactivation of the Magnastar transceiver RF system. (Cabin LAN and Handsets are being retained). Aery Aviation, LLC Electrical Load Analysis me 3 Rev Page 5 of 8 FAA PROJ STOWMC-T 2.0 SYSTEM CHARACTERISTICS See appendix A for the pre~modi?cation electrical load analysis document 16 Revision R. The loads calculated below are related only to those items removed or added as part of the mission and sensor system modi?cation. The DC loads stated to be on the mission bus are powered by the ELDEC 81-107 TRU. The TRU is power by the aircraft 115/400Hz 3-Phase AC system. The max nomimnal load of the TRU on the aircraft AC system has been calculated. The overall capacity of the Aircraft AC system is 46000 VA. This TRU will add 3983' to the overall load on the aircraft AC system. Per the ELA referenced in Appendix A the capacity is as follows: Electrical . Emil) mm were 46 Pronunciation: WAG I: $146987? MI: tam-01 SUMRY a? . sexes LEFT AND ESSENTIAL AG LOAD . mu! II II II II I 28,Mwm (ESSENTIAL A0). (Revised page 09) 280.00 ?1 Demnd (LEFT. MAIN A0). (am page 42) 15,099.60 t" Reserve 7.02040 VA Rial-l7 mun Ac LOAD "nu-Inn u- Kim comm: (am page 45) 1433920 Hm . . .. . 0,200.00 til-A no LOAD GRAND TOTAL Tole! AC capacity . . 48,000.00 Total Durand 30,118.00 Reserve 15,801.20 VA (Rel: AMEN-8436.16. Page 1 and 140.) Aery Aviation. LLC Electrical Load Analysis ?ea-1m 1749-ED-1013 Rev IR Page 6 of 8 FAA PROJ ST00464MC-T MISSION SYSTEMS AND LOAD CHART (ITEMS IN YELLOW ARE POWERED BY THE MISSION SYSTEM TRU AND ARE PART OF THE TOTAL LOAD CALCULATOIN FOR THE AIRCRAFT AC SYSTEM). DC LOAD AC LOAD CIRCUIT INPUT SYSTEM (AMPS) (VA) BREAKER VOLTAGE BUSS STATUS #1 K6250 0.CARRY-ON 32 K6250 COMINT 0.OARRV-ON MISSION ICS 1.ACTIVE GPS 0.ACTIVE EGI BARO ALT 5.ACTIVE TRACER PDU 1:1 75.00 - 75ACTIVE ARC-132 4.DEACRVATED PRC-117G #DEACTIVATED PRC-117G 32 2.DEACTIVATED HPA 14.00 - 20DEACTIVATED TRACER P00 #2 50.00 - 50ACTIVE POWER CONVERTER (23- 12 VDC) 5.DEACTIVATED COMINT 1200 - 15.0 23VDC MSN PWR23VDC 3053 ACTIVE VIASAT MODEM 12.00 - 15.0 23VDC MSN PWR 23 VDC BU53 VIASAT 5.DEACTIVATED VIASAT ACU 1250 - 20.0 23VDC MSN PWR23VDC BU53 DEACRVATED VIASAT SERIAL CONVERTER 003 - 1.0 28VDC MSN PWR 23v0c 3053 DEACTIVATED was 32.5 - 35.0 23VDC MSN PWR23VDC 3u5 3 TRU - 3933.0 20.0 115/400 Hz Ac AIRCRAFTACBUSS ACRVE MISSION SYSTEM NO AC LOADS - CHANGE 15.0 115/30 Hz NON 115/60 Hz ACTIVE MISSION SYSTEM NO Ac LOADS - CHANGE 15.0 115/60 Hz NON ESSENTIAL 115/60 Hz ACTIVE NO RH 3AGGAGE - CHANGE 15.0 115le NON 115/50 Hz ACTIVE FANS LOADS DC 2.3 23 VDC FANS LOADS Ac - -2 115/400 ADSB LOADS 0.3 23VDC 4 Dc LOAD TOTAL ADDED LOADS 3331.0 Aery Aviation. LLC 1749-50-1013 Electrical Load Analysis Rev IR E: 1, Page 7 of 8 FAA PROJ STOWMC-T The added systems will increase the load on the AC system by 3983 VA. This increase creates a total demand of 34101 VA on the AC system. The new remaining capacity is 11899 VA. The total added load on the AC system increases the load percentage to 74%, which is increased from 65%. The increased loading on the AC system still keeps under the 80% leading threshold; therefore the increased electrical load is within limits based on this analysis. FANS-1A and Out STC Installation Total Loads Two prior approved STCs for FANS-1A and ADS-B out were performed concurrently with the aircraft modi?cation. The total added loads are as follows: 1. The added DC load for the FANS DC System is 2.3 AMPS. The existing SATCOM system installed In the aircraft is being used for the FANS-1A messaging function. therefore the iridium Load that is part of the STC is not included in this DC Load Calculation. This addition of 2.3 AMPS to the aircraft DC Buss does not impact the current compliance of the aircraft DC electrical system. 2. The changed AC Lead for the FANS system, reduces the tOtaI load on the AC system by 2 VA. This is negligible and does not impact the aircraft AC System loading compliance. 3. The changed DC Lead for the ADS-B system increase the DC current draw by 0.6 AMPS. This added load is considered negligible and does not have an impact to compliance of the aircraft DC System. 3.0 CONCLUSION The mission systems added as part of this modi?cation are on the cabin ioadshed bus and do not impact the battery capacity in the event of a generator failure. The added load from the modi?cation will not increase the overall essential systems load on the battery system and the batteries remain adequate for 20 minutes of operation. Therefore this analysis ?nds that the added systems do not impact compliance to the applicable requirements. nun-mm- Aery Aviation, LLC 1 Electrical Load Analysis Rev IR 5.1389680f8 FAA APPENDIX A . ?gamma?. .. bk . AIRCRAFT REPORT NUMBER (304146961 16 ELECTRICAL LOAD ANALYSIS SUPPLEMENT FOR Aero Mundo Ejecuuvo AEROSPACE G-N AIRCRAFT (A12EA) SERIAL NUMBER 1426 PREPARED BY: 7 APPROVED BY: 0%.0 12-May-01 Data Avionics/Electrical Engineer Eng nearing Manager! DER List of Revisions Bapor?lumber: 60414296116 By Besc?p?on of ?gvlsion Date Approved Rev. Chris Tan NEW 12-May-01 (see cover) - amni??'racmcal - LOAD ANALYSIS Page: 1 I Prep. By: TABLE OF CONTENTS Reporl (30414696116 Date: 12-May?01 Model: Page Number LIst of Revisions . 1 Table of Contents . 1 Introduction . . . 3 System Characte?etics . . 4 General Notes . 6 ESSENTIAL. 28V Dc PILOT (P600) .. 8 PILOT (P602) ., 9 PILOT (P609) .. . 10 COPILOT (P605) . . . 11 COPILOT (P606) . . 12 COPILOT (P613) 13 ACCESS . . 14 ESSENTIAL DC Summary . . 15 LEFT MAIN, 23V DC PILOT (P604) . . 16 PILOT (P652) 17 COPILOT (P606) 18 COPILOT (P645) .. 19 COPILOT (P621) 20 r' ACCESS (PX102) . . 21 LEFT MAIN DC Summary 22 RIGHT MAIN, 28V DC - PILOT #1 . (P603) . A 23 PILOT (P615) . 24 GOPILOT (P607) . 25 COPILOT (P650) . . .. 26 COPILOT (P616) . . . 27 ACCESS (PX202) . 26 RIGHT MAIN DC Summary 29 AIRCRAFT DC SUMMARY . . - 30 MAIN BATTERY CAPACITY ANALYSIS 31 EMERGENCY BATTERY ANALYSIS . (1 PU1129) (1PU1130) (1 PU1131) (IPU1141) (1 PU1142) 32 (2PU1129) (2PU1130) (2PU1131) (2PU1141) (2PU1142) 33 (3PU1205) THFIU (3PU1235) (1 PU1129) (1PU1130) (1PU1131) 34 (4PU1205) THFIU (4PU1235) (2PU1129) (2PU1130) . 35 28V DC AUX CONVERTER SUMMARY 36 115V AC 601-12 CONVERTER SUMMARY .. . .. 37 I (can .2- napo?nflectmm ANALYSIS JP?ago: 2 Prep. By: Gh?s Tan TABLE OF CONTENTS Report 60414696116 Daio: 12-May-01 Model: G-IV Page Number 15V AC COPILOT PHASE-B, (X615) 38 ESSENTIAL AC Summary . . . 39 LEFT MAIN, 115V Ac - PILOT PHASE-C, 4O ACCESS (1XX101) . . . 41 LEFT MAIN AC Summary . . 42 RIGHT MAIN, 115V Ac COPILOT PHASE.A1 (ZXWZ) In? a a 43 ACCESS . 44 RIGHT MAIN Ac Summary 45 AIRCRAFT Ac SUMMARY . . 46 .f 'r-H mm?: nil-null I.- mom Electrical ANALYSIS 15331: a Imooucnou Reportt: 60414696116 Model: G-W This ELECTRICAL LOAD ANALYSIS has been prepared as a SLIpplement to the AEROSPACE CORPORATION REPORT NO: AC DC LOAD EFFECTIVITY NC SIN 1390 and SUBQ. In accordance with FEDERAL AVIATION ADMINISTRATION ADVISORY CIRCULAR 43.13-2A (Para 27d) and FAR 25. It is the summary of the factory loads and the outfitter installed avionics and electrical equipment system loads for the aircraft speci?ed herein. The following tabulation of AC and DC loads have been extracted from this repon: (A) CRUISE Dc LOAD (Page 30) 464.52 A (B) CRUISE Ac LOAD (Page 46) 30118.80 VA (0) MAIN BATTERY LOAD (Page 31) 167.35 A (0) FIND EMERGENCY BATTERY LOAD (Page 32) 195.75 VA (5) AFT EMERGENCY BATTERY LOAD {Page 33) 131.35 VA (F) FWD EMER LIGHTS BATTERY (Page 34) 153.90 VA (3) AFT EMER LIGHTS BAT-IE RY LOAD (Page 35) 153. ?x Electrical CAL Long ANAL are Page: 4 Prep. By: Chris Tan svsratr CHARACTERISTICS Report r: 60414696116 Date: 12-May-01 Model: r. MAIN Dc POWER The primary sources of DC power on the aircraft are two 28V Dc, 250 Amp outputs from the Left and Right DC converters (one output per converter). The converters receive their input power from their associated alternator (three phase and variable frequency). which then outputs Ac, three phase, feted frequency (400Hz) and 28V DC (regulated voltage) power. The DC output voltage of a converter Is regulated to 28V DC and maintained from no load to a full load condition. The two converters share the system loads during normal operations as follows: 0 Left converter DC output shall power the LEFT MAIN DC BUS and ESSENTIAL DC BUS. 0 Right converter DC output shall power the RIGHT MAIN DC BUS. With the loss of either converters DC output and when the AUX Transionner-Rectifier is de?energized, the remaining operating converter will automatically assume the total aircraft load. Some load shedding may be required depending upon the systems in use. ll. AUXILIARY DC POWER In the event of the loss at either or both converter DC source(s) and/or during APU operation, 300 Amps at 28V DC power is available from the Auxiliary Transformer?Recti?er (THU). Power for the AUX THU is supplied by the LEFT or RIGHT MAIN AC BUS. lit. DO BATTERY POWER The DC power system is supplemented by two 24V DC. 40 Amp-Hour NI-CAD batteries. These batteries provide power for APU start and tor emergency power lor emergency operation under the loading conditions summarized in Table 4. (Ref; Report No.: Page 149, Figure 4). IV. EMERGENCY BATTERIES Four 24V DC, sealed-cell. lead acid emergency battery packs are Installed in the SW aircraft and are charged from the ESSENTIAL DC BUS. In the event of loss of all electrical power. the emergency batteries supply DC power to most essential Instruments and the emergency light system as long the ESSENTIAL DC BUS is less than 18 VOLTS DC. A fully charged emergency battery is capable of supplying 200 WATTS at a voltage between 19 to 28.5 VDC for a minimum of 30 minutes. (can a -- .Iuh nepon: Earnest ?'E?E?cranA'ut. LOAD ANALYSIS Page: 5 Prep. By: Chris Terr SYSTEM CHARACTERISTICS . R3211 90414696116 Date: 12-May~01 (Continued) . Model: any W. V. APU POWER APU power is primarily used during ground operation but is also available as a back-up for the and RIGHT converter sources during ?ight. The APU is rated for airborne operation at altitudes up to 30 .000 feet. The APU is equipped with an alternator which provides 115V AC, 400 Hz. 3-phase power DC power is available during APU operation using the Auxiliary Transfonner-Fiecti?er Unit (THU). Vt. STANDBY ELECTRICAL POWER Standby electrical power is provided by a hydraulically dn?ven motor/generator (ABEX) capable of supplying Amps at 28V DC. Hydraulic power for the ABEX is derived from the Combined Hydraulic System. The 5 KVA AC output of the. ABEX is recti?ed by the AUX to provide 163 Amps DC power to the ESSENTIAL DC BUS. The 50 Amps 00 output of the ABEX is utilized to poWer the Emergency Inverter, to supply ESSENTIAL AC loads In the event of the loss of all three power sources (Left. Right and APU altemators), 163 Amps ot 28V DC to available at the ESSENTIAL DC BUS thereby further delaying the depletion of the batteries. In addition. 800 VA of Ac power (Phase A only) is available at the ESSENTIAL AC BUS. VII. MAIN Ac POWER The primary sources of AC power (constant frequency), 3-phase converters. The system load during normal operation is as follows: 0 Left converter AC output shall power the MAIN AC BUS and ESSENTIAL AC BUS. 0 Right converter AC output shall power the RIGHT MAIN Ac BUS With the loss oi either converters AC output the remaining Operating converter will automatically assume the total aircraft load. some load shedding may be required depending upon the systems in use. ESSENTIAL Ac POWER 115V AC, 400 HZ. 3-phase power for the ESSENTIAL BUS is normally supplied treat the LEFT or RIGHT MAIN AC BUS. However. in emergency conditions (failure of three sources LEFT, RIGHT. and APU sources), ESSENTIAL AC power is supplied by an 800 VA E-INVEFITEFI (only PHASE A BUS ls energized). The Input power for the E- INVERTER 13 derived from the ESSENTIAL DC BUS or from the Standby Electrical Power Motor/Generator. IX. ENGINE INSTRUMENT 26V Ac POWER Engine instrument power is provided by two 200 VA transformers powered by the ESSENTIAL AC BUS. x. mm 23v Ac Powaa MAIN 23v AC POWER IS provided by two 1000 VA transformers powered by the LEFT MAIN Ac BUS and RIGHT MAIN AC eus eminence Leno ANALYSIS 9' 6 Prep. DEChris Tan GENERAL NOTES Report 5310414696116 Date: 12-May-01 Model: ow . 1- LOADS All have been obtained from Guifstream Aerospace Report No.: Gulistreamdv AC DC LOAD Dated 1 SEPT, 1999; Eitectivity NC SIN 1390 and SUBQ.: PRODUCTION CONFIGURATION. 2 - COMPLETION CENTER ADDED LOADS The added loads listed in this report are calculated from vendorpublished data which are usually conservative. The actual loads are normally less than the calculated load. GREENIE AND ADDED LOADS. All and added loads listed In this report are for a night cruise condition and continuous operation unless otherwise noted. 4 - NORMAL onemmnc conomon During conditions of normal operation with both converters power. the approximate DC load of the Left converter is 93.06% . and the Right ls 92.74% This assumes that the Lott Converter is supplying power for the LEFT MAIN and ESSENTIAL DC BUS. 5 - EMERGENCY SINGLE SOURCE OPERATION - For a conditionln which one converter DC source is inoperative. the will automa?cally come on line and power the DC loads of the de?energized source. There shall be no reduction in aircraft load requirements and it is assumed that all systems will be operating normally. However, it the TRU is inoperative (is. dual failure), the remaining operating converter 00 source shall assume the total aircraft load,- and some load shedding maybe required. In the event of an? emergency condition (is. dual failure) in which the Auxiliary Transformer-Rectifier is on line, the total load may, under certain condidons, exceed the capacity of the Auxiliary Transformer-Rectifier and manual load shedding will be required to limit the load to 300 Amps or less. a - BATTERY 8. STANDBY ELECTRICAL POWER OPERATTON This summary considers an emergency condition in which the two main batteries and standby electrical power system are the only sources of power at altitudes of up to 45,000 feet. Adequate electrical power isavailable to the essential DC and AC busses to supply all the loads listed. 7 BATTERY This summary considers an emergency a condition in which the two main batteries are the only source of DC power during a forced descent and landing. Adequate battery Capacity is available to supply allot the loads listed during such a condition ct Operation. However, it during the period at failed DC power the AC portion is functional, the battery charger will operate as a Transtonnen Recti?er. in this mode of operation, the TransionneruRectt?er wilt parallel with the batteries and provide up to 55 Arms each at 27.75 Volts'DC to the DC ESSENTIAL BUS and thereby further delay the depletion of the batteries. (can?t) - am; w?Ai-ln u. m. Report: Electrical ELECTRICAL LOAD Page: 7 Prep. By: cm?. Tan GENERAL NOTES Report a: (30414se6116 . Date: 12-May-01 (Continued) Model: G-IV e- EMEFIGENCY BATTERY OPERATION This summary considers an emergency condition involving multiple failures of all power sources (Left, Right, APU and Standby Electrical Power) in Which the existing FWD and AFT emergency batteries will supply power to the most essential instruments plus the additional FWD and AFT emergency lighting batteries supplying power to the interior and exterior emergency lighting system. CAUTION it may be necessary to make load adjustments when powered under emergency conditions, as is required under normal conditions. if aircraft total Ac or DC power requirements exceed total available power. unload the respective electrical system to maintain a total load at less than 100%. As a reminder these load values may be read on the Standby Electrical Power Panel as a percentage of available power. The hydraulically driven ABEX emergency generator provides raw AC to the Transionner-Ftecti?er Unit (THU) converting it to a regulated Dc. This output in turn is provides to the supplying constant frequency emergency Ac electrical power. Knowing this. the DO load must be reduced to lower the (Ac PWH reading, and conversely the AC load must be reduced to lower the (DC PWR reading. REFER TO THE FLIGHT MANUAL FOR COMPLETE OPERATING PROCEDURES. ?nun-u .. an. un- 'um Luann hiya?. RammeancaI L04 ALY IS T?s?ea 3 Prep. an em Tan 2131! Do ESSENTIAL 11% at: (30414896118 Date: 12-May-01 PILOT 1 (Pace) I: (3- 1 2mg: 9m 00- LIME DELETED: WHEEL WELL US 3140131 43 PLT MAIN 3.06 1.3 TOTAL DELEED CI-Ibiilbo U. I. aim A ADDED: FWD EMER LTS BAT 139031 PLT AUX 0.15 2 FWD EMER LTS IMPACT 189032 PLT Aux 0.10 MASTER 195031 PLT Aux 0.90 3 FMS MASTER 295031 PLT Aux 0.40 3 CABIN MASTER 390031 PLT Aux 0.30 GALLEY MASTER 3900132 PLT Aux 0.4a . TOTAL ADDED . . 1.03 A EXISTING: (Rah: Page 22.) (50 AMP FEEDER) ESSENTIAL Dc PILOT 11, (P600) 20.62 A REVISED TDTAI. . "??2155?1 NOTES: 1.) Production system rebussed to 28VDC ESSENTIAL ACCESS. reference page 14 2.) Nome! load is 0.15 Amps. 20.0 Amps maximum. 3.) Ground operation only and is not added to load. WTE'IectrIcaI E?LEcLl-?llc_ AL LOAD ANALYSIS Fags: 9 Prep. By: Chris Tan 20v 00 ESSENTIAL Repo?ii: (30414696116 'oatez12-May-01 (P602) Model: G-IV gum; 013 No, 03 L00, LOAQ Fons-ran: UTILITY LTS 31403355 PLT MAIN 5.30 1.4 TOTAL DELETED . 0.00 A ADDED: AFT EMER LTS BAT 139033 PLT Aux 0.15 2 APT LTS 109034 PLT Aux 0.10. CKPT LIGHT- Aux PED 2790131 PLT Aux 2.50 CKPT Aux ANN 336031 PLT Aux 1.20 3 I TOTAL ADDED .. A EXISTING: (Flat: Av-er-n-425.1s, Page 26.) (50 AMP FEEDER) ESSENTIAL 00 PIL0T112 (P602) 10.44 A TOTAL '2230' NOTES: 1.) Production system to ESSENTIAL ACCESS. telerenoe pagel 4. 2.) Normal load is 0.15 Amps charged. 20.0 Amps maximum. I 3.) Normal load is 1.20 Amps, 4.00 Amps maIdmum. 4.) Ground operation only and ls not added to elect?cal load. baa-"Mam . Repo?: Electrical ELECTRICAL LOAD Page: 10 Pmp. By: zavqc ESSENTIAL at: (30414696116 Date: 3 (P609) Emanuel: a-Imv ca mg QB ND. . 9119.2; LOAD NO 3 DELETED: NONE TOTAL DELETED 0.00 A ADDED: NONE TOTAL ADDED .. 0.00 A (Rot: Page 34.) (20 AMP FEEDER) Dc PILOT 3 (P609) 0.12 A REVISED TOTAL 41.12 A NOTES: None -.- - .. ?-11.45 um hulk-v u. .4 - -.-. I?u-w ?"n'epon 'ricaa""' ELECTRICKL LOAD ANALYSIS :11 Prep. By: Chris Tan 28V DC ESSENTIAL Report it: 6914696116 Date: 12-May-01 COPILOT 1 (P605) Model: G-IV - . ca TITLE ca 39? c3 L95. LOAD ?91532 NONE TOTAL DELETED . ADDED: NONE TDTAL ADDED.. (Rat: AV-GIV-R-426.16. Page 29.) (50 AMP FEEDER) (P605) 24.53 A REVISED TOTAL . . 24.53 A NOTES: None. a Electrical We ICAL LOAD ANALYSIS Page: 12 By: "?Tavbc? Report at: (30414696116 Data:12-May-01 comm? (P606) . ModelQC. L052 genes DELETED: NONE TOTAL DELETED . Too?A ADDED: ICE DET DC 446081 ch'r AUX 0.20 TOT AL ADDED . 0.20 A {Rem Page 32.) (50 AMP FEEDER) ESSENTIAL DC COPILOT 2 (P606) 23.48 A REVISED TOTAL 23.68 A NOTES: None NOTES: 1.) Rebussed to Pmduction Aft Emergency Battery. reference page 33. Report: Electrical ELECTRICAL LOAD LYS 5a 13 Prep. By: 28V Dc ESSENTIAL Report 6: 60414696116 (P613) - Model: G-IV TWLE 9m .4303 112m DELETED: nova 1 61506127 CPLT MAIN 0.70 DME 1 61606161 CPLT MAIN 1.08 TOTAL DELETED . . 1.78 A ADD-D: NONE TOTAL ADDED . . . 0.00 A EXISTING: (Ran: Page 36.) (20 AMP FEEDER) ESSENTIAL Dc COPILOT 11 6 (P813) - 14.43 A REVISED A maamawrummuham?. .-1. -- Report: Electrical LOAD Page: 14 pm or. con: zav be ESSENTIAL Repont: 66414696116 I. DELETED: NONE TOTAL DELETEDL. . . 0.00 A ADDED: WHEEL WELL LTS 31403148 PLT MAIN 3.06 UTILITY LTS 31403355 PLT MAIN 5.30 LAV AISLE LTS 584081 CABIN 0.60 CABIN PA 501081 CABIN 0.20 TOTAL ADDED Doll ??0.70 A EXISTING: 9.) (25 AMP FEEDER) ESSENTIAL cc ACCESS (PX304) coo A REVISED TOTAL 0.70 A NOTES: 1.) Production Load rebussed reference page 8. 2.) Production Load rebussed reference page 9. 3.) This load occurs during prestart and was not added to total. 4.) The Amplifier is normally powered from LH Main 115VAC bus. During Emergency operation the load Is 0.20 Amps nromalna! to 4.00 Amps Maximum and is not included in the column total. Date: 12-May-01 ACCESS Model: I. I ELEM 9.18.9; 0 EQLES 1 ,3 2.3 .u-r?w?a-Ip?h-M-u NOTES: None. i. Report: Elect?cai LOAD AN L"vs'Te Prep. By: onus Tan 28V DC Report 0: 60414696116 Date: 12-May~01 SUMMARY Model: DEMAND gem (AMPS) P600 PILOT 1 (Revised page 8) 21.65 P602 PILOT 2 (Revised page 9) 22.39 P609 PILOT 3 None added.Page 10 0.12 P605 COPILOT 1 None added.Page 11 24.53 P606 COPILOT 2 (Revised page 12) 23.68 P613 COPILOT II 3 (Revised page 13) 12.85 PX304 ACCESS (Added page 14) 0.70 V536 INVERTER FDR None added. 0.00 10126 MAIN FUEL FDR None added. 30.00 201126 MAIN FUEL FDR None added. 30.00 (REE: AV-G MIR-426.16, Page 53.) TOTAL REVISED ESSENTIAL Dc . 165.72 A lectrical We 67 ac LOAD ALYSIS Page: 16 Prep. By: ChriSTan 28V Dc LEFT MAIN Report 0: 60414696116 Dale: 12-May-01 1211.07 11 1 (P604) Model: G-IV QEIELE QB on Q0. 1.121% DELETED: NONE TOTAL DELETED . 0.06 A ADDED: CABIN EMER LTS SENSE RELAY 31406316 PLT MAIN 0.20 SIGN LTS 31408146 PLT MAIN 0.60 1 TOTAL ADDED . . ?Em" A EXISHNG: (661.: Page 39.) (66 AMP FEEDER) LEFT MAIN Dc PILOT 11 11.68 A REVISED TOTAL . A 1 None mm? . Report?L: Electrical LYSIS 71:95 17 Prgp. an arm Tan 28V Dc LEFT MAIN Report 6: 60414696116 Date:12~Mag~O1 (P652) Model: We. ca ILTLE gm ELSE.- LEE DELETED: NONE TOTAL .. . . 0.60 A ADDED: NONE TOTAL ADDED . . . . ammo: (Rat: Page 43.) (20 AMP FEEDER) LEFT MAIN Dc PILOT 2 (P652) 4.09 A REVISED TOTAL . . 4:06 NOTES: None. . "n a. i BMW ELECTRICAL 0A s: iago: 18 .B :ChusTan 28VDCLEFT MAIN Reporti: 60414696116 Date: 12-May-01 COPILOT #1 (P608) Model: (3an l( gem 9532: we I- - EAR ?53 DELETED: NONE TOTAL DELETED . 0.00 A ADDED: NONE I TOTAL ADDED 0.00 A HOSTING: (Ref; Page 40.) (50 AMP FEEDER) MAIN DC COPILOT #1 (P608) 2320 A REVISED TOTAL . 23.20 A None I. Report: ETectricai LOAD Fags. 19 Prop. By: Chris Tan 20v Dc LEFT MAIN Report 0: (30414696115 0m: 12-May-01 COPILOT 2 (P645) . nodal: G-IV ?6 9% 2.9.32: - .QLL BQEE LEFT mm '00 COPILOT at 2 (P645) LDELETED: NONE TOTAL DELETED 0.00 A ADDED: NONE TOTAL . . . . 0.00 A EXISTING: (Bat: mew-mama, P019042.) (20 AMP FEEDER) LEFT MAIN Dc COPILOT 2 (P645) 3.10 A REVISED TOTAL . . . . 3.10 A NOTES: None I x. Report: Electrical L1?'o ANALYSIS 511?99: 20 Prop. By: 1mm. 28V DC LEFT- NIAIN Report 80414696116 Data: 12?May-01 COPILOT 11 3 (P621) ModeI: a-sv may: cg No. on Lee. 5959 NOIES mI-?r MAIN Dc COPILOT 11 3 (P621) DELETED: HF com 11 1 03351 CPLT MAIN 0.60 1 TOTAL amp 0.60 A moan: NONE TOTAL men . . . . "nice" exams: (Flat: Page 41.) (50 AMP FEEDER) MAIN Dc communes (P621) 22.75 A REVISED TOTAL . . 22.15 A 1.) Pmduction' System Hemved. - I Report: Electrical ELECTRICAL LOAD Page; 21 . 28VDC MAIN Hem (30414696116 Date: 12-May~01 ACCESS (PX102) Model: G-IV QBJIILE 951:2. - DELETED: NONE TOTAL DELETED 0.00 A ADDED: LH mnwouo AIHSTAIR us 430031 CABIN 3.29 1 VEST us 432031 CABIN 1.92 SERVICE LTS 437cm CABIN 2.03 1,2 TOTAL ADDED WA 1303mm (new wow-mama, Page 9) (50 AMP FEEDER) LEFT MAIN DC ACCESS (9x102) 0.00 A newsren TOTAL . . . 1.92 A NOTES: 1.) Load used during ground operation only and are not added to the total. 2.) Average load is ?gured at 50% of the maximum load. .f'N Re Emma: LOAomF-sm Page: 22 Prop. By: Chris Tan 28V Dc LEFT MN Report 60414696116 I Date: 12-May-01, SUMMARY Model: DEMAND EEQER ELE MMPS) P504 PILOT a 1 (Revised Page 16) 12.48 P652 PJLOT 2 None added. Page 17 4.09 P608 COPILOT 1 None added. Page 18 23.20 P645 COPILOT 2 None added. Page 19 3.10 P621 COPILOT 3 (Revised Page 20) 22.15 9x102 Access (Revised Page 21) 1.92 (Rat: Page 54.) TOTAL REVISED MAIN A NOTES: None. 4 ..-.. - - Report: ?Electrical LOAD 23 Prep. By: OhdsTan 28V DC RIGHT MAIN Report 3: 60414696116 Date: 12-May-01 PILOT #1 (P603) Model: 04v CB mg, ca 1.00. 5959 DELETED: NONE TOTAL DELETED 0.00 A ADDED: CABIN SWITCHED CABIN EFFECT LTs CONT 581 0131 CABIN 0.55 1 FWD UPPER EFFECT LTS 501052 CABIN 4.20 1,2 FWD LOWER EFFECT LTS 551053 CABIN 3.15 1.2 AFT UPPER EFFECT LTS 581034 - CABIN 3.15 1.2 AFT LOWER EFFECT LTS 581085 CABIN 3.15 1,2 CREDENZA FANS 399051 CABIN 0.75 1 BAGG FANS 399052 CABIN 0.32 1 TOTAL ADDED 15-38 A 511311110: (Rat: Page 45.) (50 AMP FEEDER) RIGHT MAIN DC PILOT 11: 1 (P603) 6.16 A REVISED TOTAL . . . . 21.54 A NOTES: 1.) This load can be 5th from the cockpit by switching to the position. 2.) Average load Is ?gured at 70% 0f the maximum Ioad. . .1 If?f-U?l-?wgn? Report: ?ance! LOAD ANALYSIS 511?93: 24 Prep. 8155:1110 Tan 20V Dc HUGHT 3: 60414696116 Date: 12-May-01 (3315) ?r?flv TITLE o. 33.1.92. 32m 32m DELETED: NONE TOTAL DELETED .. . . . 0.00 A ADDED: MAP LTS - CKPT 179032 PLT Aux 1.75 03 PNL LIGHTS - OKPT 179031 PLT Aux 1.25 . PLT FLASHLIGHT . 432031 PLT Aux 0.44 PULSELITE 133031 PLT Aux 0.50 (WHO 03 PNL LTS 3300310 FLT AUX 2.50 VHF COMM 3 . 300031 CPLT Aux 0.31 2 SELCAL 423031 CPLT Aux 0.30 CPLT FLASHLIGHT 432032 CPLT Aux 0.44 SATCOM on 103034 0er Aux 029 SATCOMANT 103033 CPLT Aux 1.00 1 CKPT MON 504032 CPLT Aux 1.00 . CABIN EMER LTS SENSE RELAY 31403313 PLT MAIN 0.20 TOTAL ADDED . 3x13111110: Page 49.) (20 AMP FEEDER) RIGHT MAIN Dc P1LOT 3 2 (3315) 1.34 A REVISED TOTAL . 1?2 A NOTES: 1.) Normal load is 1.00 Amp. 4.50 Amps maximum. 2.) Normal load is 0.61 Amp. 4.91 Amps maximum when transmitting. . aha?.14.. .2 . .. Report: Electrical ELECTRICAL ANALYSIS Pagg: 25 Prop. By: Guts Tan 28V DC RIGHT MAIN Report 60414696116 Date: 12-May-01 COPILOT #1 (P607) Model: 23111;: Le No 9.84.99a um DELETED: NONE TOTAL DELETED . . . 0.00 A ADDED: NONE . TOTAL ADDED . 0.00 A EXISTING: (Hat: AV-GIV-R-426J 6, Page 48.) (50 AMP FEEDER) RIGHT MAIN DC COPILOT 1 (P607) 37.40 A REVISED TOTAL . - .. 37.40 A NOTES: None. WUd??n: ?iv-Isa? NOTES: 1.) Normal load is 2.00 Amp. 7.00 Amps maximum when transmitting Report: Electricai LOAD ANALYSIS Page: 26 Prep. By: CMs Tan 20?! DC RIGHT MAIN Report GQM 4696116 Date: 12-May-01 2 (P650) Model: G-IV (. CB TELE 00. LOAD 591:9; DELETED: NONE TOTAL DELETED . ?0.00 A ADDED: AFIS DMU 306031 CPLT AUX 2.00 1 AFIS PRINTER 306082 CPLT AUX 0.50 ?a TOTAL ADDED . 2.50 A FEXISTING: (Bet: AV-GIV-R-426.16, Page 52.) (20 AMP FEEDER) RIGHT MAIN DC COPILOT 2 (P650) 10.93 A REVISED TOTAL 13.43 A ELECTRICAL ANALYSIS P390: 27 Prep. By: 01me 20v Dc mam MAIN Report 0: 60414696116 Dato:12-May-O1 (P010) Modal: e-w 91mg: cat-0c. L952 MES DELETED: TDRICAD 11 2 CS1 79 CPLT MAIN 1.25 1 HF com 2 cases CPLT MAIN 0.00 1 TOTAL DIIDI OI I I 0 I'llADDED: #2 00170 CPLT MAIN 1.00 2 TOTAL ADDED . . EXISTING: (991.: Page 51.) (50 AMP FEEDER) RIGHT MAIN Dc 40.05 REVISED '41-.20' A . NOTES: 1.) Production system removed. 2.) Production system addition. Report: 313031331 ELECTRICAL $339: 23 Prop. By: 011.14 Tan 2311 00 NIGHT MAIN 3: 304141393113 0414: 12-May-01 ACCESS (PX202) WET?Model: G- I 23% CB "11- 21mg 3913.3. ADDED: CABIN RADIO TEL ARTU 104031 CABIN 4.40 3 RADIO TEL CONT 104032 CABIN 1.33 504031 CABIN 1.75 CABIN SPKR PREAMP 501033 CABIN 0.20 GALLEY DATA 303 539035 CABIN 0.40 CBN FLASHLICHT 432033 CABIN 0.44 CABIN DATA BUS 2 539032 CABIN 0.30 1 CABIN DATA Bus 3 339033 CABIN 3.40 1 CABIN DATA BUS 4 539034 CABIN 0.30 1 VEST EFFECT LTS 434031 CABIN 1.10 1 CLOSET LTS 537031 CABIN 1.53 1 FWD LAV 00 503031 CABIN 2.71 1 CALLEY LTS 343031 CABIN 0.22 1 CABIN TEMP FANS 453031 CABIN 0.30 1 CABIN TEMP CTL 457031 CABIN 0.40 1 30112 CONT. 493032 CABIN 0.04 1 AFT DC 393032 CABIN 3.30 1 CALI. SYSTEM 107031 CABIN 0.50 1 GALLEY - RH MAIN DCIGND SVC GALLEY DC FDR 1 394032 CABIN 0.00 1 ,4 GALLEY DOME LTS 590031 GALLEY 1.29 1 GALLEY CONT 573031 SALLEY 0.70 1 WATER LEVEL 550031 GALLEY 0.30 1 GALLEY - RH MAIN DCICND GALLEY 00 FOR 2 394031 CABIN 0.00 1.4 GALLEY WORK 590033 GALLEY 4.31 1.2 GALLEY EFFECT LTS 590032 GALLEY 4.31 1.2 WATER SYS D0 543031 GALLEY 3.52 1.2 DRAIN CONT 549031 GALLEY 0.92 1.2 TOTAL ADDED .. . . . 40' .17 A 3x13111131 Page 9.) (50 AMP FEEDER) RIGHT MAIN DC ACCESS (szoz) 0.00 A REVISED TOTAL . . . . . 40.17 A NOTES: 1.) This load can be Shed (mm the cockpit by Switching to the position. 2.) This load can be shed from the cockpit by swim-ling to the position. .. 3.) Normal load is 4.40 Amps, 9.60 Amps maximum when transmitting. I '3 4.) GALLEY FDR DC. loads shown as GALLEY SWITCHED and UNSWITCHED. mm?hh?wme?K" u. . -. nopo?lectrica: rum? AL ANALYSIS 8: 29 Prep. By: um Tan 28V DC RIGHT MAIN Repeat! if: (50414696116 I Date: 12.May-O1 SUMMARY G-IV DEMAND TITLE P603 PILOT ?l (Revised page 23) 21.54 P615 PILOT 2 (Revised page 24) 12.12 P607 COPILOT 1 None added. page 25 37.40 P650 COPILOT 2 (Revised page 26) 13.43 P616 COPILOT 3 (Revised page 27) 47.20 szoz ACCESS (Added page 28) 40.17 10127 ALT PUMP FDR None added. 30.00 20127 3 ALT PUMP FDR None added. 30.00 (Rat: Page 55.) TOTAL REVISED RIGHT MAIN DC . 231.86 A Nari-ES: None. . . .-. I Report: Electrical ELEOTBIEAL EOAD ANALYSIS 30 604146961 16 G-IV Ira MAIN AND ESSENTIAL DC LOAD Capacity 250.00 Demand (ESSENTIAL DC) (Revised page 15) -165.72 Demand (LEFT MAIN DC) (Revised page 22) 68.94 Reserve 17.34 A RIGHT MAIN DC LOAD Capaclty 250.00 Demand (Revised page 29) -231.86 Reserve 18.14 A DC LOAD GRAND TOTAL Total DC Capacity 500.00 Total Demand 464.52 Total Reserve - 35.48 A NOTES: 1.) ESSENTIAL DC load ls Included In the LEFT MAIN DC total. . Pa I P_r_e& Chris Tan AIRCRAFT DC Report t: Date: 12-May-01 SUMMARY Model: OTE 1 1 . pm (Bet: Page 149. Figure 4.) NOTES: 1.) Average Demand is a quantity of continuous current, expressed in Amps. 2.) Values are expressed in Amp-Minutes for a 30 minute period. 3.) Simultaneous Demand is a quantity of current required at a given moment. 4.) Calculated value is approximate, actual time may vary. Heport: Electrical Page: 31 Prep. By: Chris Tan BATTERY CAPACITY ANALYSIS REM 60414696116 Date: 12-May-01 28V DC ESSENTIAL Model: G-IV DEMAND DEMAND EgngR TEL: (AMPS) (AMP-MIN) meme: AVERAGE DEMAND 163.25 4397.40 (Bet: Page 92.) SIMULTANEOUS DEMAND 334.52 13? NIA (Rat: Page 92.) ADDED: P600 (Revised page 8) 1.03 30.90 P602 5 (Revised page 9) 3.95 118.50 P609 None added. page10 0.00 0.00 P605 None added. page 11 0.00 0.00 P606 (Revised page 12) 0.20 6.00 P613 (Revised page 13) -1 .73 53.40 PX304 (Added page 14) 0.70 21.00 . V536 None added. page 15 0.00 0.00 10126 None added. page 15 0.00 0.00 20126 None added. page 15 0.00 0.00 . REVISED AVERAGE DEMAND TOTAL 5020.40 AMP-MIN 5,020.40 AVERAGE DEMAND x: 167.35 A 30 minutes Period: 30 MINUTES Battery Capaclty in Amp-Hours 40 Number of Batteries :2 2 BATTERY DEPLE110N 23.33 MINUTES - -uu. - vans?mu. .2. mw?d??u Re A: Electrical cm cA LOAD ANA YSIS _F_a9e: 32 I 9""rep' By: c1111; 1m? ANALYSIS new?: (30414696116 Model: Date: 12-May-01 (1PU1129) (1 PU1130) (1 PU1131) (1 PU1 141) (1PU1142) G-IV PRODUCTION FORWARD EMERGENCY BATTERY (Existing Securapiane 6.0 AMP-HOUR Battery) 21mg .3.th o. - meme DELETED: 1 08177 CPLT MAIN 1.09 2 OVERWING EMERG LTS 1PU1129 0.60 3 OVERWING EMERG LTS 1PU1130 0.60 3 OVERWING LTS 1PU1131 0.60 3 TOTAL DELETED .. 2.89 A ADDED: 1 . 03177 CPLT MAIN 1.00 4 423081 (1 PU1 142) CPLT AUX 0.35 TOTAL ADDED . . .. 1.35 A REVISED TOTAL . . . - 1.54 A DEMAND DEMAND (AMPS) rap-um EXISTING: (Bet: Page 94.) 10.24 307.20 1 TOTAL DELETED . 2.89 88.70 TOTAL ADDED . 1.35 40.50 BATTERY LOAD . 0.70 A 261.00 AMP-MIN 261.00 AVERAGE DEMAND 8.70 A 30 8.70 A 225VDC 195.76 VA Page 149, Figum 5.) T0 18VDC 41.38 MINUTES NOTES: 1.) This value re?ects shared exterior lamp loads between forward and aft emergency batteries. 2.) Production system removal. 3.) System rebuesed to Emergency Lights Battery, reference page 34. i- 4.) Production system addition. u-u-u . i 832011: ?ecMcaI ANALYSIS 1 5356: 33 Prep. By: Chris Tan BATTERY ANALYSIS 33% II: 00414696116 Date: 12-May01 (ZPU1129) (2PU1130) (2PU1131) (2901141) (2PU1142) G-IV . PRODIJCTION AFT EMERGENCY BATTERY (Existing Securaplans 6.0 AMP-HOUR Battety) QB cg No. cg L00, Log 591g OVER WING EMERG LTs 2PU1129 0.60 2 OVER WING LTs 2PU1130 0.60 2 OVER WING EMERG LTS 2PU1131 0.60 2 TOTAL DELETED . . . '1 .60' ADDED: NAV RCVR 1 31503127 (2901142) CPLT MAIN 0.70 6 DME1 61506161 CPLT MAIN 1.06 6 TOTAL ADDED REVISED TOTAL . .. -0.02 A DEMAND DEMAND (AMPS) AMP-MI manna: (Bet: Page 95.) 6.06 242.40 1 TOTAL DELETED .. . 1.60 54.00 TOTAL ADDED . 1.78 56.40 BATTERY LOAD .. 6.06 A 241.60 AMP-MIN 241.60 AVERAGE DEMAND . 6.06 A 60 8.06 A 181.35 VA (Rat: Page 149, Figure 5.) TIME TO 18.0V Dc 2 44.67 MINUTES NOTES: 1.) This value re?ects shared extedor lamp loads between and aft emergency batteries. 2.) Production system rebuesed to Aft Emergency Lights Battery, reference page 35. 3.) Production system rebussed to Aft Emergency Lights Battery, refereme page 13. ?Maud-Inna -. . - . . . . . m. .- .I w- TIME TO 18.0V D0 NOTES: 1.) This value reflects shared lamp loads between and alt emergency lighting batteIies. 2.) This value reflects 25% max load clue to ground operation 'only. 3.) Production system rebussed, reference page 32. i Repor?lecmcar We Lo ANALYSIs 5696: 64 Prep. By: Chris Tan BATTERY ANALYSIS Rem 6: 60414696116 0m: 12-May-01 (1PU1129) (1PU1130) (1PU1131) (3PU1204) THRU (3PU1234) Model: G-IV FWD EMERGENCY LIGHTS BATTERY (Added Secu raplane 6.0 AMP-HOUR Battery) 05 mg 66 No. cg Loo. LQAD mg ADDED: CABIN EMERGENCY LIGHTS 2.75 AIRSTAIR LIGHTS 0.65 1.2 CABIN EMERGENCY Exrr SIGNS 0.36 1 VE6T 0.64 1 GALLEY DOME LIGHT 0.64 1 OVER WING EMERG LTs 1PU1129 0.60 3 OVER WING EMERG LTS 1PU1130 0.60 6 OVER WING EMERG LTs 1PU1131 0.60 3 TOTAL ADDED . . 6.64 DEMAND DEMAND . . (AMPS) - None 0.00 0.00 TOTAL DELETED 0.00 0.00 TOTAL ADDED 6.64 205.20 REVISED LOAD 6.64 A 205.20 AMP-MIN 205.20 . AVERAGE DEMAND: .. 6.64 A 30 . 6.64 A 22.5 153.90 VA 5263 MINUTES . 4 .. ,2 .I-u . . . . Report: ectrIcal ELECTRICIL ANALYSIS Page: 35 Prep. By: Chris Tan EMERGENCY BATTERY ANALYSIS Report It: ?414696118 om: 12-May?01 (2120129) (2P0130LL2PU131) (4PU1204) THFIU (4PU1234) Model: G-IV I EMERGENCY uoms BATTERY (Added Socumplane 8.0 AMP-HOUR Battery) 130- ADDED: CABIN EMERGENCY LIGHTS 2.75 1 AIR LIGHTS 0.85 1.2 CABIN EMERGENCY EXIT SIGNS 0.30 I VESTIBULE DOME 0.64 1 GALLEY DOME LIGHT 0.64 1 OVER WING EMERG LTS 2PU1129 0.60 3 OVER WING EMERG LTS 2PU1130 0.60 3 OVER WING EM ERG LTS 2PU1 131 0.60 3 DEMAND DEMAND (AMPS) EXISTING: None 0.00 0.00 TOTAL DELETED 0.00 0.00 TOTAL ADDED 6.84 205.20 - REVISED BATTERY LOAD. 6.84 A 205.20 AMP-MIN 205.20 AVERAGE DEMAND 6.04 A 30 6.84 A 22.5 153.90 VA TIME TO 18.0V DC 52.63 MINUTES NOTES: 1.) This value reflects shared lamp loads belwaen and aft emergency lighting batteries. 2.) value re?ects 25% max load due to ground operation only. 8.) Production system rebussedgeferenoe page 33. . .. .. .. Report: ELECTRICAL LOAD Page: 36 Prep. By: Chris Tan 28V DC AUX CONVERTER Report 5: 60414696116 Data: 12-May-01 SUMMARY Model: IV I . 9mg cg No, L00. LOAD NOTES ADDED: SWITCHED AUX DCIGND SVC FWD LAV TOILET 598082 CABIN 4.00 1.4 LAV TOILET 696082 CABIN 4.00 1,4 AFT LAV DOME LTS 896081 CABIN 1.92 1 CABIN DATA BUS 1 569081 CABIN 0.80 1 CABIN AISLE LTS 584082 CABIN 2.00 1 BAGG LTS 488081 CABIN 1.08 1 CABIN Aux Dc (mac) . RH SPOT LTS 682081 CABIN 3. 92 1,5 LH SPOT LTS 582082 CABIN 3.14 1.5 AFT LH SPOT LTS 582083 CABIN 2.35 1.5 ENT 28V DC 502081 CABIN 2.00 1 DIVAN MONITOR 502084 CABIN 1.50 1 MONITOR 502083 CABIN 3.10 1 CREDENZA MONITOR 502087 CABIN 1.60 1 TOTAL ADDED 23.41 A 2 Exceeded output capaclty by . 0.00 A Reserve power available . 19.45 A Percentage of capacity In use 0.55 Output power at 28V DC . 855.48 AUX D0 Converter ef?ciency rating 0.80 Converter maximum output load 42.88 A Calculated load Input current at 115V AC 7.12 A Converter ?Neload' operation current 0.35 A Calculated Input current .. 7.47 A Calculated input power at 115V AC . 859.80 VA Calculated input cun'ent per phase . . 2.49 A - Input VA per phase 288.53 VA 3 NOTES: 1) This load can be shed from the cockpit by switching to the positlon. 2.) Represents maximum load. not to exceed 42 0 Amps. 3.) Load values transferred to page 44. 4.) This lead is momentary use and not added to the total. 5.) Average load ls ?gured at 70% of the maximum load. "Wm: act I WELECTRICAL LOAD ANALYSIS 5.) This load can be shed from the cockpit by switching to the position. "Rage: 3'7 Prop. By: Chas Tan 1161! AC 60 HZ CONVERTER Bogart (194146961 16 Date: 12-May? SUMMARY Model: G-IV 93 mm cg no. cg mg. 1.950 3035 ADDED: CABIN CONVERTER 60 HZ CONV OUTPUT (35A) (3500 VA) 493081 BAGG COMPT 0.00 60 HZ - LH CABIN 493084 BAGG COMPT 172.00 1.5 60 H2 - RH CABIN 493085 BAGS COMPT 172.00 1.5 60 HZ - FWD LAV 493086 BAGG COMPT 172.00 1.5 60 H2 - AFT LAV 493087 BAGG COMPT 172.00 1.5 60 HZ - FAX 493088 BAGG COMPT 172.00 1.5 60 HZ - MICROWAVE 493089 BAGG COMPT 1200.00 4.5 60 HZ - ENTERTAINMENT 4930810 BAGS COMPT 172.00 1,5 60 H2 - RH GALLEY ANNEX 4930811 BAGS COMPT 172.00 1.4.5 60 HZ - LH GALLEY 4930812 BAGS COMPT 172.00 1,4,5 60 HZ BAGGAGE COMPT. RH 4930813 BAG-G COMPT 172.00 1.5 (. TOTAL LOAD. 2740.00 VA BUS INPUT LOADING . . 3534.50 2 PER PHASE . 1194.83 VA 2.3 NOTES: 1.) Calculated at 10% of maximum input load. 2.) Represents Input load, at TOTAL LOAD shown 3.) Load values transferred to page 41. 4.) This load can be shed from the cockpit by switching to the position. n?mwu. us. .. None. Electn'?ca HICAL LOAD YSIS Egg: as Prep. By: mm 115v Ac ESSENTIAL II: 60414696116 . Date: 12-May-01 OOPILOT PHASE-I3 (X615) Model: 03 ES 9339,, LOO. LOAD DELETED: NONE. TOTAL DELETED . ADDED: ICE 051? AC 445032 CPLT Aux 280.00 I TOTAL ADDED . . .. . moo'VA ems-nun: (Hen: AV-GIV-R-426.1B. Page 107.) (75 AMP FEEDER) ESSENTIAL Ac COPILOT PHASE-B (xe15) o.oo VA REVISED TOTAL. . "?230.00? .m In" u-y- u. .1. - 0123: None. Roped-Edam 39 Prep. By: 0an Tan 115V Ac ESSENTIAL Report I: (30414696116 Data: 12-May-01 SUMMARY Model: . G-IV (N DEMAND PHASE-A: (Rat: Page 131.) x010 PILOT None added. 136.60 x011 COPILOT None added. 573.32 REVISED TOTAL (PHASE A) 709.92 VA PHASE-B: Page 132.) mm PILOT None added. 0.00 x015 COPILOT (Revised page 30) 280.00 REVISED TOTAL (PHASE B) . 200200 VA (Flat: P090133.) x014 PILOT None added. 0.00 x013 COPILOT None added. 0.00 REVISED TOTAL (PHASE 0) . 0.00 VA r" TOTAL REVISED ESSENTIAL Ac . . . 900.92 VA 1 4- mnemn: Electrical ?Elma ?gs: 40 Prep. By: 115V AC LEFT MAIN Reporlt: 60414696116 EXISTING: (Raf: Page 117.) MAIN AC PILOT PHASE-C (1 REVISED TOTAL None. (35 AMP FEEDER) 0.00 VA 0.00 VA om: 12-May-01 PHASE-C (1xeos) Model: 34v 911E: cg Hg. ca LOO. LOAD ugnas DELETED: NONE TOTAL DELETED mom VA mango: NONE TOTAL ADDED . . . "?o.oo VA Ww- "E"iectrsoaI 1:393: 41 Prep. By: 01113131. 113V AC LEI-T MAIN Reporu: 30414393113 0313: 12-May-01 (1xx101) Model: 34v 93mg 03 N9. 93 (.00. LOAD NOTES ADDED: ACCESS Bus (PHASE A) (1101101) (35 AMP FEEDER) CABIN 9191101130 301-12 CONVERTER 493031 CABIN 1194.33 1.3 GALLEY 31114101130 OVEN 541031 GALLEY 1000.00 2 COFFEEMAKER 1 543031 GALLEY 333.00 2 GALLEY WTR HTR 543033 GALLEY 750.00 2 TOTAL ADDED (PHASE A) . . 3277.33 VA 19003019100393 Bus (PHASE B) (1101101) (35 AMP FEEDER) CA3IN 9111101130 3032 CONVERTER 493031 CABIN 1194.33 1.3 CABIN SPEAKER AMP 501032 CABIN 345.00 1.4 GALLEY 91111101420 OVEN 541031 GALLEY 1000.00 2 COFFEEMAKER 1 343031 CALLEV 333.00 2 . TOTAL ADDED (PHASE 3) mun?Wm . 40030: Access 309 (93493 0131011011 (35 AMP FEEDER) CABIN 9111101130 60HZ CONVERTER 493031 CABIN 1194.33 1.3 RH FLOOR HTRS 349031 CABIN 234.00 1 LR FLOOR HTRs 349032 CABIN 220.00 1 CREW HOT 343032 CABIN 120.00 1 GALLEV OVEN 541031 GALLEY 1000.00 2 COFFEEMAKER 1 543031 GALLEY 333.00 2 TOTAL ADDED (PHASE 0) 3131.33 VA NOTES: 1.) This load can be shed from the (:00ka by switching the MAST to the position. 2.) This load can be shed from the 000ka by switching the GALLEY MAST to the position. 3.) For 60 HZ Converter loads, roierence page 37. 4.) Is 345 VA. 1150 VA maximum. - .11. i Report: Electrical LO DANALYSIS 35:42 mewcmenn MAIN AC Reporte: (30414696116 Date: 12-May-01 SUMMARY MOM: G-IV . DEMAND TELE (CRUISE) PHASE A: (Ref: Page 134.) 1X560 BATT CHARGER None added. 464.20 ?(605 PILOT None added. 271.50 1X606 COPILOT None added. 2129.00 1XX101 ACCESS (Revised page 41) 3277.83 TOTAL ADDED (PHASE A) . 6142.53 VA PHASE 8: (Ref: Page 135.) ?(561 BATT CHARGER None added. 464.20 PILOT None added. 0.00 1XB08 COPILOT None added. 1877.00 ?0?1 01 ACCESS (Revised page 41) 2872.83 TOTAL ADDED (PHASE B) 5214.03 VA PHASE c: (Ref: Page 136.) - 1X562 BATT CHARGER None added. 464.20 1X609 PILOT None added. 0.00 ?(020 COPILOT None added. 147.00 1XX101 (Re?Vised page 41) 3131.83 TOTAL ADDED (PHASE 0) 3743.03 VA TOTAL REVISED LEFT MAIN AC . 15096.60 VA was: None. nun?1am. -. I Report: ?le-Erica! LORD ml. PLago: 43 Imp. By: 0mm 115v Ac RIGHT MAIN Report 0: 60414698116 I OOPILOT Model: . (34V ca 1915 ca no. ca 1.00. LOAD DELETED: NONE TOTAL DELETED .. . . . 0.00 VA ADDED: SATCOM PHI 103031 OPLT Aux 621.00 1 SATCOM FAN 103032 CPLT Aux 100.00 1 TOTAL ADDED - . . . .. 001.00 VA mama: (Ref: Page 124.) (35 AMP FEEDER) RIGHT MAIN Ac OOPILOT PHASE-A (2X602) 407.00 VA REVISED TOTAL . . 1200.00 VA 91158: 1.) Nomal load Is 621 VA, 800 VA maximum. . .l-u?u ?mvu-a? ?opon: Eleot?cat LOAD ANALYSE NOTES: 1.) For AUX DC CONVERTER loads, reference page 36. 3.) Average load is ?gured at 50% of maximum load. 4.) Normal load is 460VA, 575VA Maximum Fags: 44 Prep. By: cm Tan 115V AC RIGHT MAIN Report II: 30414595115 0m 12-May-01 ACCESS I 2xx101 Modal: 93 mg; 03 I39, 03 CC. LQAQ NOTES ADDED: ACCESS BUS (PHASE A) (M101) (35 AMP FEEDER) Aux Dc CONVERTER 594035 CABIN 255.55 1 GALLEY AIR COMPRESSOR 545034 GALLEY 52.00 2 COFFEE MAKER 2 545032 GALLEY 555.00 2 FWD DRAIN +335 549032 GALLEY 570.00 2 AFT DRAIN HTRS 545035 GALLEY 975.00 2 TOTAL ADDED (PHASE A) . 'f "2'5 '25" .55" VA ADDED: ACCESS BUS (PHASE B) (M101) (35 AMP FEEDER) Aux DC CONVERTER . 594035 CABIN 255.55 1 GALLEY SWITCHED AIR COMPRESSOR 545034 GALLEY 52.00 2 COFFEE MAKER 2 545032 GALLEY 555.00 2 GALLEY 400HZOUTLETS 545031 GALLEY 552.00 2.9 FWD WATER HTR 545032 GALLEY 540.00 2 TOTAL ADDED (PHASE 3) 2555.55 VA ADDED: ACCESS 305 (95.4530) (MIN) (55 AMP FEEDER) Aux DC CONVERTER 594035 CABIN 255.55 1 GALLEYSWITOHED . AIPI COMPRESSOR 545034 GALLEY 52.00 2 COFFEE MAKER 2 545032 GALLEY - 555.00 2 ANNEX 4OOHZ OUTLETS 545032 GALLEY 552.00 2.5 THERMAL COOLING UNIT . 745031 GALLEY 450.00 2.4 TOTAL ADDED (PHASE 0) . . 2005.55 VA 2.) This load can be shed from the cockpit by selecting the to the position. M.uw.m. ?om-4w. ?x TIES: Nona. Report: Electrical LECTRICAL AD ANAL SIS jme: 45 Prep. By: cues Ten RIGHT MAIN AC Report 60414696116 Date: 12-May~01 SUMMARY Model: DEMAND PHASE A: (CRUISE) (Flat: 6. Page 137.) CHARGER None added. 464.20 2X605 PILOT None added. 120.00 ?(602 COPILOT (Revised page 43) 1288.00 2XX101 ACCESS (Added page 44) 2526.53 REVISED TOTAL (PHASE A) . 4398.73 VA PHASE 8: (Rat: Page 138.) 2xee1 a BATT CHARGER None added. 464.20 2X624 PILOT None added. 0.00 ZXSOS COPILOT None added. 2267.00 201101 ACCESS (Added page 44) 2383.53 REVISED TOTAL (PHASE B) . 5114.73 VA PHASE O: (Bet: AV-GIV-R-426.16, Page 139.) 2X562 CHARGER None added. 464.20 PILOT None added. 414.00 2X604 COPILOT None added. 2344.00 2XX101 ACCESS (Added page 44) 2003.53 REVISED TOTAL (PHASE 0) . . 5mm: VA REVISED RIGHT MAIN Ac TOTAL . 14739.20 VA . as.- a .0 I alert: Etactrical . ?95 46 Prop. By: owls Tan AIRCRAFT AC Report i: 60414696116 I Date: 12-May-01 SUMMARY Model: ETES LEFT MAIN AND ESSENTIAL Ac LOAD Capacity" .. 23,000.00 Demand (ESSENTIAL (Revised page 39) 200.00 ?0 Demand (LEFT MAIN AC) (Revised page 42) 15,099.60 Reserve . 7,620.40 VA RIGHT MAIN Ac LOAD Capacity 23.000.00 Demand (Revised page 45) 14,739.20 Reserve .. 8,200.80 - VA Ac LOAD GRAND TOTAL Total AC Capac?y . 46,000.00 Total Demand 30 118.80 Reserve 15,881.20 VA 1L- (Ref: Page 1 and 140.) NOTES: 1.) Existing ESSENTIAL AC loads are included In the LEFT MAIN AC total. 0MB 2120-0020 Electronic Tracking Number MAJOR REPAIR AND ALTERATION Ems/3112015 U.SD - (Alrframe, Powerplant, Propeller, or Appliance) For FAA Use Only Federal Aviation Administration INSTRUCTIONS: Print or type all entries. See Title 14 CFR ?43.9. Part 43 Appendix B. and AC 43.9?1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. ?44701). Failure to report can result in a civil penalty for each such violation. (49 U.S.C. ?46301(a)) Nationality and Registration Mark: N51 PR Serial No.: 1425 1. Aircraft - 5. Make: Aerospace Model: G-IV - Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) Address: 3420 8. Ocean BLVD #10 2. Owner - AC 1425 LLC City: Highland Beach State: FL Zip: 33487-4703 Country: U.S.A. 3. For FAA Use Only 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model Serial Number El POWERPLANT PROPELLER Type El APPLIANCE Manufacturer 6. Conformity Statement A. Agency?s Name and Address B. Kind of Agency Name Stevens Aviation Inc. El us. Certi?cated Mechanic El Manufacturer Address 600 Delaware St. El Foreign Certi?cated Mechanic C- Certi?cate No- City Greenville State 3 Certi?cated Repair Station VIBR368K 219% Country El Certi?cated Maintenance Organization D. I certify that the repair and/or alteration made to the unit(s) identi?ed In item 5 above and described on the reverse or attachmentsn hereto have been made' In accordance with the requirements of Part 43 of the U. 8. Federal Aviation Regulations and that the info furnished herein Is true and correct to the best of my knowledge. Extended range fuel Signature/Date of Authorized Individual per 14 CFR Part 43 App. 7. Approval? Return to Service Pursuant to the authority given persons speci?ed below, the unit identi?ed In item 5 was inspected In the manner prescribed by the Administrator of the Federal Aviation Administration and is APPROVED REJECTED FAA Standards . . . Person Approved by Canadian Inspector Manufacturer Maintenance Organization Department of Transport BY Other (Specify) FAA Designee Repair Station Inspection Authorization Certi?cate or Signature/Date of Authorized individual Designation No. VIBR368K FAA Form 337 (10?06) NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. identify with aircraft nationality and registration mark and date work completed.) N51PR Nationality and Registration Mark Date Major Alteration: 1. Accomplishment of CMD Flight Solutions, LLC. STC ST03424CH, Certi?cation of Automatic Dependent Surveillance Broadcast (ADS-B) Out System with Rockwell Collins Transponders in accordance with Dan Buzz 8: Associates Master Data List. Document No. DB1409001. Revision dated July 20. 2015, or later FAA approved revisions. Major Component List TDR94D 622-9210-501 SN 1MPXJ TDR94D 622-9210-501 SN 1W23M DDA 08090021-6 SN 541 Annunciator 2. AFM Supplements 031409004 Rev. (ADS-B) have been added to the Aircraft Flight Manual. 3. DER approved minor deviations are documented on Aery Aviation Drawing 1749-3450-9001. WIRING DIAGRAM, ADS-B Rev C, Dated June 2018. Reference attached 8110-3. Dated June 29??1 2018. 4. Details of this Major Alteration are on ?le at Stevens Aviation. Inc. ref work order GYH-W0-9569 Aircraft log entry recording this Major Alteration was completed. Aircraft was reweighed at this time. Equipment list updated to re?ect alteration. Aery Engineering Document Number 1749-ED-1013. Rev IR, Dated June 2018 includes the electrical loads changes from this alteration. for Continued Ainivorthiness: Report No. 031409003 Rev. C. Aircraft was secured for flight. END Additional Sheets Are Attached FAA Form 337 (10-06) U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1. DATE STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS (17/2/5/20 Amm . 2. MAKE 3. MODELNO. 4. TYPE (Aircraft. Engine. Propeller; 5. NAME OF APPLICANT GU IV ere-I AERY AVIATION AIRCRAFT LIST OF DATA 6. IDENTIFICATION . TITLE 1749-2380-9001. REV A D-WIRING DIAGRAM. UNILINK armors . 1749-3450-9001, REV MOD WIRING DIAGRAM ADS-B UPGRADE BBOIZM 8 1749-3460-9001. REV A Woo FMS 5131201 8 1749-3460-9002. REV 8 OD . WIRING DIAGRAM. FMS 811 3I201 1749-ED-1013. REV IR - ELECTRICAL LOAD 7125(201 8 NOTES: 1. This approval Is for Engineering design data only. It indicates the date listed above demonstrates compliance with the regulations speci?ed by paragraph and subparagraph below as Applicable Requlremente Compliance with additional regulations not tisted here is requlred. 2. Only the electrical systems aspects of the above listed data am approved herein. 3. Applicable to TCDS a. PURPOSEOF DATA In support ofdeviaticns to APPROVED MODEL LIST STC and ST03424CH on GIV Sedal Number 1425. 9. APPLICABLE REQUIREMENTS (List speci?c sections) 14 CFR Part 25 Paragraphs. (Amendment Level Denoted by 25-100: [Amdt 25-123]; 25.1 165(1)) [Amdt 72]; 25.1301IAII) [Arndt 25-123}; [Amdt 25.123]; 25.1357 [Amdt 25-123]; 25.1431 (All) 25-113] to. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Part 183. data listed above and on attached sheets numbered MA have been examined in accordance with estabtished Mares and found to comply with applicable requirements of the Airworthiness Standards listed. I: Recommend approval of these data I (We) Therefore Approve these data MENS) 13. CLASSIFICATIONS) FAA Form 3110-3 (03110) SUPERSEDES PREVIOUS EDITION ?niteh 5mm of America of Wranapnrtatinn -- general (A?ia?on ?tministra?nn @1ng Q'Lcri'ificatc FQR use on sros424cn Enlistment) (er-WP 9?11 CMD Flight Solutions LLC mber 1425 9199 Cotters Ridge Richland, MI 49083 LY We?! 25 4/163 Federal Aviation ?ya??m 19%? g?wm See attached Federal Aviation Administration (FAA) Approved (12$ Model List (AML) number ST03424CH for approved aircraft models and applicable airworthiness regulations. ?ow gm gauge- Certi?cation of Automatic Dependent Surveillance - Broadcast Out System with Rockwell Collins Transponders in accordance with Dan Buzz Associates Master Data List, Document No. 081409001, Revision F, dated July 20, 2015, or later FAA approved revision. 3mm- - l) The installer must determine whether this design change is compatible with previously approved modi?cations. 2) lf the holder agrees to permit another person to use this certi?cate to alter a product, the holder must give the other person written evidence of that permission. 3) The existing Rockwell Collins Transponder installation must be previously FAA Approved. 4) FAA Approved Airplane Flight Manual Supplement (AF MS) as listed on the AML number ST03424CH, or later FAA approved revision, is required on board the modi?ed aircraft. 5) Additional Limitations and Conditions are listed on AML number ST03424CH. @aAmea-Sepmber 12, 2014 August 28, 2015 23, 2015 mm Steven L. Lardinois Manager, Systems and Flight Test Branch Chicago Aircraft Certi?cation Of?ce (Title) Any alteration of this certificate is punishable by a fine of not exceeding $11,000, or imprisonment not exceeding 3 years, or both. PM Form 8110-2l10-68) PAGE 1 of 2 PAGES This certificate may be transferred in accordance with PAR 21.47. Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins TDR-94DI-94 Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Issue Date: February 23, 2015 ink-940194 Transponder CPS Approved Part SOURCE Numbers AML AMENDMENT DATE FAA APPROVED FAA APPROVED AIRCRAFT FLIGHT MASTER DRAWING ?Rem" AIRCRAFT MODEL TCDS NO. MANUAL SUPPLEMENT LIST MAKE NumberIRev Date Improved Number [Date . Airbus Defense and Space SA. Chi-235400 AZINM DBI409004. 3-7-30? 08140900! RockweilColiins 3-9-20? (IN-235400 2-22-2m7 622-9352-501 (H?s-40005 (314-235-309 or Universal Avionics UNS- i l-iw FMS or Freel? light Systems Model l2t)3C GPS bi Beecherutl Mil-300 DBI409004. 3-7-20l7 622-92l0-50l Rockwell Collins 3-9-20? Corporation (Diamondlondlm 2.23.3917 622-9352-50l (BPS-40005 or Universal Avionics FMS or a" FrceFlight Systems Model OPS 622-92l0-50l Rockwell Collins 3-9-2017 2-2017 622-9352?50l OPS-40005 3. Commotion MU-SOO409004. 3-7-20! 7 (Diamond ii i. 400 400A (l-lmvker 4001? or Universal Avionics UNS- FMS or FreeFlight Systems Model I203C GPS Page I of l3 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins TDR-94DI-94 Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Issue Date: February 23, 2015 ITEM MAKE AIRCRAFT AIRCRAFT MODEL TCDS NO. FAA APPROVED AIRCRAFT FLIGHT MANUAL SUPPLEMENT FAA APPROVED MASTER DRAWING LIST Transponder Approved Part Numbers Date NumberIRev Approved Number Rev'lDate CPS SOURCE AM AMENDMENT DATE 4. Beechcra? Comoratiott HS. l25 Series 700A ?8.125 Series 7008 Series 800A 125 Series 8008 l-lawker 800x Hawker SEUXP lawker l? l'lawlzer 750 A3EU DB ?09004. 3-7-20] 7 Dill-1090M 2-22-20 l7 622-92 l0-50l 622-9352-50l Rockwell Collins GPS-40003 or Universal Avionics UNS-il-lw FMS Of Free? light Systems Model i203C 0r Honeywell ?(3202 [600? GNSSU 3-9-20! 7 5. The Boeing Company 727 Series 727- Series 727-200 Series A3 WE DB 1409004. 3-7-20I 7 DB l40900 2-22-20 I 7 622-92 l0-50 I 622-9352-50 I Rockwell Collins UPS-40008 or Universal Avionics UNS-ll-lw FMS or l-?reeF light Systems Model l203C 3-9-20I 7 6. The Boeing Company DC-9-87 (MD-87) A6Wli DB ?09004. 3-7-20? l40900l 2-22-20 I 7 622-92 l0-50I 622-9352-50] Rockwell Collins OPS-40005 or Universal Avionics UNS-lt-lw FMS or I?rcel?light Systems Model l203C OPS 3-9-20 7 Page 2 of 13 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Issue Date: February 23. 201 5 ITEM AIRCRAFT MAKE AIRCRAFT MODEL TCDS NO. FAA APPROVED AIRCRAFT FLIGHT MANUAL SUPPLEMENT FAA APPROVED MASTER DRAWING TOR-940194 Transponder Approved Part Numbers Number/Rev Approved Date CPS SOURCE AMI. AMENDMENT DATE Boeing Company 73 7-200 737-200C A I6WF. I 409004. I) 3-7-20l 7 DB l409ll0l 622-92 Ill-50 I 622-9352-50] Rockwell Collins OPS-40008 or Universal Avionics UNS- FMS or Freci-?light Systems Model I203C GPS 6-2l-2017 Bombardier Inc. Series Dl-lC-8-200 Series Dl-lC-8-300 Series Dl-iC-8-400 Series AI3NM 031409004. I) 3-7-2017 DB 1 40900 I 2 0 PI PI 622-92 Iii-50 I 622-9352-50l Rockwell Collins CPS-40003 or Universal Avionics UNS-it-iw FMS or Freel-?light Systems Model 1203C GPS 3-9-20! 7 Page 3 of [3 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins TDR-94DI-94 Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Issue Date: February 23, 20l5 ITEM AIRCRAFT MAKE AIRCRAFT MODEL FAA APPROVED AIRCRAFT FLIGHT MANUAL SUPPLEMENT FAA APPROVED MASTER DRAWING LIST Transponder Approved Part Numbers NumberIRev Date Approved Number Rev"/Date CPS SOURCE AML AMENDMENT DATE Bombardier Inc. 600) CLGOO-ZAIZ (1600- 21! I6 iCl.-60l-3A Variant. CL-(itll-JR Variant. Variant} (Regional Jet Series IOO 440) (Regional Jet Series 700. 70l 702) (Regional Jet Series 705) (Regional Jet Series 990) CL-600-2E25 {Regional Jet Series "300) 409i 104. 3-7-20l 7 DB 22-20 I 7 622-92 I 0-50 I Rockwell Collins OPS-40008 or Universal Avionics UNS- FMS or i-?reel?liglu Systems Model l2tl3C (it?s 3-9-20! 7 I0. Bombardier lac. BD-IUIMAIO DB ?09004. 3-7-20I 7 DB I 4090i? 2-22-20l 7 622-92 0-50! 622-9352-50l Rockwell Collins or FreeFlight Systems Model I203C OPS 3-9-20] 7 Page 4 of l3 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins TDR-94DI-94 Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Issue Date: February 23, 2015 Transponder GPS Approved Part SOURCE. Numbers AML AMENDMENT DATE FAA APPROVED FAA APPROVED AIRCRAFT FLIGHT MASTER DRAWING AIRCRAFT MODEL TCDS NO. MANUAL SUPPLEMENT LIST ITEM AKE Date Number Rev?VDate Approved i. Dassault Fan Jet Falcon ATEU 013 ?09064. 3-7-20l 7 031409001 622-930-501 Rockwell Collins 3-9-2017 Aviation Fan Jet Falcon Series 2.22.2017 622-9352-50! C. D. E. or Mysterc-Falcon 20- Universal Avionics C5. UNS-lt-jw FMS 20-05. ZO-Es. 20-l-?5 or Mysterc-l?alcon 200 Freel-?light Systems Model IZOJC OPS l2. Dassaull Falcon l0 A33lil) 3-7-2017 01314990!" RockwellCoIlins 3-9-2017 Malina 2-22-2on 622-9352-50I OPS-40003 or Universal Avionics FMS or light Systems Model 1203C l3. Dassault Mysterc-Falcon 50 Dill-109004. 3-7-20I7 DBI40900I 622-930-501 Rockwell Collins 3-9-20? Aviation (Falcon 50EX) 2-22-20I1 622-9352-501 (BF-9.40005 Mystere-Folcon 900 or Falcon 900EX Universal Avionics UNS- I Hw FMS or FreeFlight Systems Model l203C GPS Page 5 of 13 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Issue Date: February 23. 20l5 Transponder CPS Approved Part SOURCE Numbers AMI. AMENDMENT DATE FAA APPROVED FAA APPROVED AIRCRAFT FLIGHT MASTER DRAWING ?Rem" AIRCRAFT MODEL TCDS no. MANUAL SUPPLEMENT LIST ITEM MAKE NumberlRev Date a i Approved Nnmh" Rev {Date l4. Dassault Falcon 2900 ASONM DBI409004. 3-7-2017 0131409001 ?zz-9210.50: Rockwell Collins 3-9-20? Aviation Falcon zoom-1x 2-22-2017 622-9352?501 OPS-40005 or Universal Avionics uns-uow ms or Freel-?light Systems Model I203C ops l5. Fokker F.27 A-8l7 [)8l409004. 3-7-20? Dill-10900! 622-92l0-50l Rockwell Collins 3-9-2017 Services (l?okkchOl 2. m7 622-9352-50I OPS-40005 B. V. or Universal Avionics FMS or FrecFiight Systems Model (3P5 0! 16. l 25 Astra Dill-imam. 3-7-2017 l)li 40900l 622-9210-50! Rockwell Collins 3-9-20? Aerospace? Astra 2. 622-9352-50I UPS-40008 100 or (iull'szream OISE Universal Avionics UNS-ll-lw FMS or FreeFlight Systems Model l203C GPS Page 6 of 13 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out issue Date: February 23, 20! 5 ITEM AIRCRAFT MAKE AIRCRAFT MODEL FAA APPROVED AIRCRAFT FLIGHT TCDS NO. MANUAL SUPPLEMENT FAA APPROVED MASTER DRAWING LIST TOR-940194 Transponder Approved Part Numbers Number/Rev Date Approved Number Rcv?lDatc GPS SOURCE AML AMENDMENT DATE l7. Aerospace LP Galaxy 200 A53NM DB I 409004. 33-7-2017 1) [33140900] 2-22-20 I 7 622-92 Ill-50 I 622-9352-50I Rockwell Collins OPS-40005 or Universal Avionics UNS-lt-lw FMS or Freel?ligln Systems Model 1203C GPS 3-9-20l 7 l8. G-l I 59 I 59A 1598 C-IV OV OV-SP A I 2EA OBI-109004. 3-7-20] 7 OH I 4090i" I) 2-22-20 i 7 622-92 Ill-50 I 622-9352-50l Rockwell Collins OPS-40005 or Universal Avionics FMS or Free-Flight Systems Model 1293C GPS Or l-loneywell H6202 GNSSU 3-9-20l 7 l9. lsrael Aircrali Industries Ltd. H23 1124 AZSW DB ?09004. 3-7-20! 7 DB I 40900! I) 2-20 I 7 622-9219-501 622-93 52-50 I Rockwell Collins OPS-40005 or Universal Avionics UNS-ll-lw FMS or Free? I ight Systems Model I203C GPS 3-9-20! 7 Page 7 of l3 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Issue Date: February 23, 2015 ITEM MAKE AIRCRAFT AIRCRAFT MODEL TC 05 N0. FAA APPROVED AIRCRAFT FLIGHT MANUAL SUPPLEMENT FAA APPROVED MASTER DRAWING LIST TOR-94 0194 Numbers Transponder Approved Part Numberl?ev Date Approved horn her Rev?IDate CPS SOURCE AML AMENDMENT DATE 20. Kelowna Flightem? Tmeor tConvair) Ltd. 340 440 6A6 DB I 409004. 3-7-20l 7 DB 622-92 I 0-50 2-22-20 I 7 622-9352-50l Rockwell Collins OPS-40005 or Universal Avionics UNS-lt-lw FMS or l-?reeFlight Systems Model 1203C CPS 3-9-20l 7 2 l. Learjet lne. 2-1. 24A. 248. 248- A. 24C. 24D. 24D-A. 24E. ZJF-A 25. 25A. 25?. 25C. 250. 25F. 28. 3 I. JIA 35. 36. 36A. 55. 553. 55C 60 A Dill-109004. 3-7-20 7 DB I 40900! 622-92 2-22-20] 7 622-9352-50 Rockwell Collins OPS-40005 or Universal Avionics FMS or l?reeFlight Systems Model 1203C OPS 3-9-2017 22. Learjet Inc. 45 I Learjet 40. Learjet 45. lxarjet 70. Learjet 75) 3-7-2017 DB I 40900! 622-92 Ill-501 622-9352-501 2.. Fl 2-20 I 7 Rockwell Collins (BPS-40005 or Universal Avionics FMS or FreeFiight Systems Model l203C (il?S Or I loneywell ?6202 I (3007 GNSSU 3-9-20l 7 Page 8 of 13 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Issue Date: February 23, 20 5 TOR-940194 Transponder Approved Part Numbers FAA APPROVED MASTER DRAWING LIST AM 1.. AMENDMENT DATE FAA APPROVED AIRCRAFT FLIGHT MANUAL SUPPLEMENT GPS AIRCRAFT SOURCE MAKE AIRCRAFT MODEL TCDS NO. Number/Rev Date Number Rev?IDatc Approved Lockheed Martin Corporation l329?23A ?29-231) 329-23E I 329-25 2AIS DB 1409004. 0 3-7-20l 7 0814090!" I 2-22-20] 7 622-92 0-50 1 622-9352-50l Rockwell Collins OPS-40008 or Universal Avionics UNS- -lw FMS or l-?rcci-?light Systems Mode! IZGJC (BPS 3-9-20l 7 Saab All. Saab Aeronautics 340A 3403 A52EU DIN-100004. I) 3-7-20l 7 DB I 40900! \i 2-22-20 I 7 $22-92 Ill-Sill 622-9352-50I Rockwell Collins OPS-40003 or Universal Avionics FMS or Systems Model 1203C GPS 3-9-20! 7 Sabreliner Aviation LLC NA-265-65 NA265-80 AZWE 409004. 3-7-20i 7 2-22-20 622-92l0-50l 622-9352-50l Rockwell Collins OPS-40003 or Universal Avionics UNS-lt-lw FMS or Systems Model l203C GPS 3-9-20l 7 Page 9 of 13 Federal Aviation Administration (FAA) Approved Model List (AML) Number CMD Flight Solutions LLC FOR Rockwell Collins TDR-94DI-94 Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out issue Date: February 23. 2015 Transponder GPS Approved Part SOURCE Numbers FAA APPROVED FAA APPROVED AIRCRAFT FLIGHT MASTER DRAWING AIRCRAFT MODEL TCDS N0. MANUAL SUPPLEMENT LIST AMI. AMENDMENT ITEM DATE Number/Rev Date . Approved Number Rev'IDate 26. Short $03-30 AMI-2U Dill-109004. 3-7-20? DIJHDWOI 622-92l0-50I Rockwell Collins 3-9-20]? Brothers 503-60 1) 2.22.20? 622-9352-59] OPS-40008 SD3-SIIERPA or $03-60 Universal Avionics UNS-lt-lw FMS or l?rceFlight Systems Model l203C Gl's 27. 'l'estron 650 AONM DBHWUIH. 3-7-2111? Dill-30900] 622-92l0-50l Rockwell Collins 3-9-2017 Aviation Inc. D. li. F. Gill. VI and 2.33.2017 522435240] OPS-40005 or Universal Avionics UNSoll-lw FMS or Frecl? light Systems Model IEOJC 0r Honeywell ?620210007 GNSSU Page l0 of 13 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins TDR-94DI-94 with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Issue Date: February 23. 2015 AIRCRAFT ITEM MAKE AIRCRAFT MODEL FAA APPROVED AIRCRAFT FLIGHT MANUAL. SUPPLEMENT FAA APPROVED MASTER DRAWING LIST Transponder Approved Part Numbers Number/Rev Date Approved Number Rev?antc AML AMENDMENT DATE GPS SOURCE 28. Testron Aviation lnc. 500 550 5550 552 560 5602?. DB I 409004. 3-7-2017 DB 4090M 2-22-20 I 7 62 2-92 622-9352-50! Rockwell Collins 3-9-20? OPS-40008 or Universal Avionics UNS-lt-)w or FreeI-?light Systems Model l203C GPS Or I?loneyn'cil ?6202 16007 GNSSU 29. Textron Aviation Inc. 750 DB I 409004. I) 3-7-2017 2-22-20! 7 622-92 I 0-50 I 622-93 52-50! Rockwell Collins 3-9?20? CPS-40008 or Universal Avionics UNS-lt-lw or Free-Flight Systems Model l203C Or l-loneyweli GNSSU *or later FAA-Approved Revision Page ll ofl3 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Date: Februaiy 23, 2015 FAA Approved: A Steven L. Lardinois Manager. Systems and Flight Test Branch Chicago Aircraft Certi?cation Office Date Reissucd: August 28. 2015 Date Amended: June 22. 2015: August 28. 2015 Dece ber l6 20 9 20l6 a a a . (anti/Imus NI. 1) Successful completion of Ground Test Plan l00 7 Revision 1) dated April 4. or later FAA approved revision. must be accomplished following of this STC. Page 12 of 13 Federal Aviation Administration (FAA) Approved Model List (AML) Number ST03424CH CMD Flight Solutions LLC FOR Rockwell Collins Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Issue Date: February 23. 2015 Zh??iw?'rw Jams/l1 . temsl hrou The certi?cation basis for the changed aircraft as described in this AMI. is as follows: a. The type certification basis for the aircraft listed on the FAA Approved Model List. is shown on TCDS listed on the PM Approved Model List for parts not changed or not all?ected by this change. b. The certi?cation basis for parts changed or a??ected by this change since the reference date of application. October 23. ZOIS. is as follows: Regulations at the amendment level: 14 CPR 25.301 [25-23]. 25.5mm [25-91]. 25.605tnll25-46I. 25.6117 [25-23]. 25.61 Ito) [25-123]. 25.619 [25-23]. 25.7mm) [25-46]. 25.l327(o) 25.1351 [25-72]. 25.1431 tattbueud) [25-113] . 25.1501 [25-42]. 25.1525 (ORIG). 21152912564]. 25.1581 [25-72]. 25.1585ta) [25-105]. Additional regulations for AMI. Item: I. 5. 6. 8 [Rd Series only). 14. and 24: I4 CPR 26.l I) Page 13 of 13 Dan Buzz Associates LLC Master Data List 9199 Cotters Ridge Report No: DB1409001 Richland Ml Revision 49083 FQR USE GIN Gu?fstream, 64% serial] number 1425 (MW Master Data List Document Number: DB1409001 Revision: [3 Rockwell Collins Transponders with Automatic Dependent Surveillance - Broadcast (ADS-B) Out Approved Model List Supplemental Type Certi?cate ST03424CH Approved By 2; Date November 29, 2017 Page 1 of 6 Dan Buzz Associates LLC Master Data List 9199 Cotters Ridge Report No: DB1409001 Richland MI Revision 49083 REVISIONS LEVEL DESCRIPTION APPROVED DATE IR Initial Release DLB 11-25-14 A Minor Revisions DLB 2-2-15 Added Con?g 02 DLB 3-17-15 Minor Revisions DLB 5-28-15 Minor Revisions DLB 6-4-15 Corrected typo in GTP document number . DLB 6-27-15 Minor Revisions. DLB 7-20-15 Revised electrical drawings DB1410011 DB1411010 DLB 10'9'15 Added Model Qual Report DB1510005. Revised electrical drawings DB1411010 Revised Report DB1411004. DLB 2-1?2016 Added RVSM Report Revised electrical drawings DB1410011 and DB1411010. DLB 4'5'2016 Added Model Qual Report DB1602001. Revised the following Reports: DB1409003 031409004 031411005 Revised electrical drawings DB1410011 and DB1411010. DLB 842016 Added Model Qual Report 031607009, GTP 1607010, and manufacturing data section. Revised the following Reports: DB1409004 DB1411004 DB1411005 Revised electrical drawing DB1411010. Removed GTP DB1607010. DLB 8'26'2016 Added Shadin AFID. DLB 12-22-2016 Added and revised documents as indicated by revision bars. DLB 1-31-2017 Page 2 of 6 Dan Buzz Associates LLC Master Data List 9199 Cotters Ridge Report No: DB1409001 Richland MI Revision 49083 REVISIONS (Continued? LEVEL DESCRIPTION APPROVED DATE documents as Indicated by revusuon DLB 2222017 Added Model Qual Report DB1704001. 0 Revised system wiring diagrams. DLB 5'23'2017 Revised manufacturing drawings as indicated by revision bars. Minor change to system wiring diagrams. Minor change to installation instructions. DLB 11 29 2017 Minor change to strapping instructions. Latest changed areas are indicated by ?ea text. Page 3 of 6 Dan Buzz Associates LLC Master Data List 9199 Cotters Ridge Report No: 081409001 Richland Revision 49083 Approved Aircraft Con?gurations Aircraft Model Serial Number Description Config See approved Model List ALL Rockwell Collins TOR-941940 Transponders 01 ST03424CH with Rockwell Collins GPS-40008 GPS Receiver. (Collins Proline IV, ProIine 21 or Fusion equipped aircraft) See approved Model List ALL Rockwell Collins Transponders 02 ST03424CH with Federated (Universal Avionics FMS. dedicated Collins GPS-40008, Freeflight 12030 GPS or Honeywell H62021G007 GNSSU equipped aircraft) CERTIFICATION DOCUMENTS Rev Description Con?g Reports: 081409002 IR Project Specific Certi?cation Plan 01 081502036 IR Certi?cation Plan, STC Amendment 02 081510002 IR Certi?cation Plan, STC Amendment, FreeFlight 1203C GPS 02 081606012 Certi?cation Plan, STC Amendment, Honeywell GNSSU 02 081609010 Certi?cation Plan, STC Amendment, AFID 01, 02 081409008 A ADS-B Flight Test Plan 01,02 081411011 ADS-8 De-mod Instructions 01,02 081510005 IR Model Quali?cation Report 01,02 081602001 IR Model Quali?cation Report 01,02 081607009 IR Model Quali?cation Report 02 081701003 IR Model Quali?cation Report 01, 02 081704001 IR Model Quali?cation Report 02 MANUFACTURES DATA Document No. Rev Description Con?g 14080001 3 Skylight Avionics Digital Discrete Adapter, 01, 02 PIN 08090021-6 833613-00 - ADS-B Flight ID Adapter 01, 02 833613-10 - Digital Discrete Adapter (00A) 01, 02 INSTALLATION DOCUMENTS Rev Description Config Reports: 081409003 Instructions for Continued Airworthiness 01, 02 081409004 0 Airplane Flight Manual Supplement 01, 02 081409005 A Electrical Load Analysis 01, 02 081409007 IR EMI Test Procedure 01, 02 081410017 0 ADS-B Ground Test Plan 01, 02 081411004 ADS-B Strapping Instructions 01, 02 081602005 IR RVSM Substantiation Report 01, 02 Page 4 of 6 Dan Buzz Associates LLC 9199 Cotters Ridge Richland MI 49083 Master Data List Report No: DB1409001 Revision For the installation the following applicable drawings/documents in Table 1 should be used for the applicable configuration: Table 1 INSTALLATION DESIGN DATA Drawings Rev Description Config Wiring Diagrams 031410011' Collins ADS-B Upgrade o1 Wiring Diagram DB1411010 Collins Federated Upgrade Wiring 02 Diagram Installation Instructions DB1411005 Digital Discrete Adapter (DDA) and ADS-B Annunciator 01, 02 Installation Instructions MANUFACTURING DATA Drawing Rev Description Config DB1602009 A TDR Bracket DDA Mount Assembly 01, 02 DB1602008 A Bracket DDA Mount 01, 02 031602007 A Harness ADS-B Out Wire Diagram 01 443613-00 A Harness, 833613-00 01, 02 443613-10 - Harness, DDA 01, 02 613603-00 Bracket, AFID RA Mount 01, 02 613604-00 Bracket, AFID Side Mount 01. 02 613605-00 A Bracket, AFID Top Mount 01, 02 613606-00 Bracket, AFID Under Mount 01, 02 KIT DATA LISTS DB1602010 IR ADS-B Out Beechcraft 400A with Proline IV Avionics 01 DB1602011 IR ADS-B Out Beechcraft 400A with Proline 21 Avionics 01 (without Luma Technologies Annunciator Panel LT-4515) DB1602012 lR ADS-B Out Beechcraft 400A with Proline 21 Avionics (with 01 Luma Technologies Annunciator Panel LT-4515) DB1602013 IR ADS-B Out Federated Aircraft 02 Page 5 of 6 Dan Buzz Associates LLC Master Data List 9199 Cotters Ridge Report No: DB1409001 Richland MI Revision 49083 SUPPORTING DATA Rev Description Reports: SD-160100 2 Quali?cation Test Procedures 4 ADS-B Flight ID Adapter (AFID), Quali?cation Test Results SD-170001, SCI.5 2 Test Report, ADS-B Flight ID Adapter (AFID), Quali?cation Test Report Shadin Artifacts SD-170002, SCI.5 2 Test Report, ADS-B Flight ID Adapter (AFID), Quali?cation Test Report Element Artifacts SD-160090 4 Software Change Impact Analysis SCI403613-01 3 Flight ID Adapter (AFID), Software Con?guration Index/ Lifecycle Environment Con?g Index 2 833613-00 ADS-B Flight ID Adapter (AFID), Software Accomplishment Summary 4 Plan for Software Aspects of Certi?cation Page 6 of 6 305 Cherokee Drive, NeWpon? News, VA 23602 Phone: 757. 709. 0077 ELECTRICAL LOAD ANALYSIS 1 749-ED-1013 REV: IR MISSION SENSOR AND COMMUNICATIONS SYSTEMS For GIV-SP Aircraft - Serial Number 1425 FAA PROJECT Name Signature Date IR Prepared by R. Roytas omens IR CheCked by R. Roytas Zig 07/2518 tR Approved by s. Walton (the) 07/25/13 PROPRIETARY NOTICE data contained herein is the sate property of Aery Aviation, LLC. Disclosure, release or reproduction in whole orpert of this proprietary document in any format or convention is not permitted without express written consent from Aery Aviation, LLC. For details and requests contact: ggalitz@agryaviation.com Aery Aviation, LLC. 305 Cherokee Drive. Newport News, VA 23602 Aery Aviation, LLC 1749-ED-1013 Electrical Load Analysis Rev IR 5; Page20f8 FAA STOWM C-T Record of Revisigns REV DATE APPROVED BY DESCRIPTION OF CHANGE IR 399 Cover See Cover INITIAL RELEASE Aery Aviation, LLC 1749-ED-1013 Electrical Load Analysis Rev IR jgy. E. Page 3 of 8 FAA PROJ STOWMC-T Table of Contents Section . . Pagg 1.0 INTRODUCTION . . . 4 1.1 Purpose 4 1.2 Modi?cation 4 2.0 SYSTEM . . . . 5 Aery Aviation. LLC - 1749-ED-1013 Electrical Load Analysis Rev IR Page 4 of 8 ZZ/m?m% FAA srommc-r 1.0 INTRODUCTION 1.1 Purpose The purpose of this document Is to define the engineering and certi?cation services for installations of mission systems provisions and equipment on a Serial Number 1425 Registration N51 PR Aircraft. This document. 1749-ED-1013. Electrical Load Analysis. will show that these modi?cations are within the capacity of the aircraft electrical generating and power systems and the modifications are compliant with the requirements of 14 CFR 25. 25.1165(b) [Amdt 72], 25.1301(all) [Amdt123], 25.1351 [Amdt 72] and 25.1431tc) [Amdt This report shall be approved by the Project Electrical Systems DER. 1.2 Modi?cation Description Aery Aviation has been authorized by the applicant, AIRTEC Inc., and contracted to provide engineering and certi?cation services to instali special mission modi?cations into a Guifstream GMSP Aircraft serial number 1425. The modi?cation will be comprised of the following: 1. Installation of Zea and ice ARC-182210 mission transceivers. lnstaliation of a bottom mounted Lockheed Martin Tracer radar system. Installation of a top mounted 18" Viasat Arclight Ku Satcom system. installation of a Wescam MX15 camera to lower fuselage. Installation of a cockpit to mission operator internal communications system. Installation of a 28VDC Mission Power Distribution and Loadshed System. Addition of an Eldec Installation 28vdc, 200amp mission power transformer rectifier unit (T RU) Replacement of an existing Honeywell SATCOM system with more current system. Removal ofthe existing Honeywell AFIS system. 10. Replacement of the VHF 3 VHF-422 communications transceiver cockpit interfaces with the ARC- 182. 11. Installation of Zea PRC-117 antennas and 1ea GPS antenna. 12. Deactivation of the Magnastar transceiver RF system. (Cabin LAN and Handsets are being retained). 5999?:9?9991?3 Aery Aviation, LLC Electrical Load Analysis 2am Rev IR Page 5 of 8 FAA PROJ 2.0 SYSTEM CHARACTERISTICS See appendix A for the pre~modi?cation electrical load analysis document #60414696116 Revision R. The loads calculated below are related oniy to those items removed or added as part of the mission and sensor system modi?cation. The DC loads stated to be on the mission bus are powered by the ELDEC 81-107 TRU. The TRU is power by the aircraft 3~PhaSe AC system. The max nomimnal load of the TRU on the aircraft AC system has been calculated. The overali capacity of the Aircraft AC system is 46000 VA. This TRU will add 3983' to the overall load on the aircraft AC system. Per the ELA referenced in Appendix A the capacity is as follows: Electrical . a one 4s Tamas ?fmi is an.? 12-May-01 sumav a. If,? . i LEFT mo 2mm ac LOAD %;msm oemmressemw Ac. (Revisedpageati) 230.00 "i DemnerEFT mm AG) (Revised page 42) 15,099.60 4" Reserve .. . 1.32140 VA nicer mun ac LOAD Capacity. . 23.0mm 90mm! (Revised page 45) 4 739.20 Hm ., 03a? VA At: Low mo Tom. Total AC Capacity - 48,000.00 Total cum 30.11am Receiver -. . A . 15.30120 VA (Ref: mew-masts. Feast and 14a.) Aery Aviation. LLC 1749-ED-1013 Electrical Load Analysis Rev IR 5. 32%; PageSofB FAA PROJ ST00464MC-T MISSION SYSTEMS AND LOAD CHART (ITEMS IN YELLOW ARE POWERED BY THE MISSION SYSTEM TRU AND ARE PART OF THE TOTAL LOAD CALCULATOIN FOR THE AIRCRAFT AC SYSTEM). DC LOAD AC LOAD CI RCUIT INPUT SYSTEM (AMPS) (VA) BREAKER VOLTAGE BUSS STATUS #1 K6250 0.CARRY-ON #2 K6250 COMINT 0.CARRY-ON MISSION ICS 1.ACTIVE GPS SPUTTER 0.ACTIVE EGI BARO ALT 5.ACTIVE TRACER PDU #1 75.00 - 75ACTIVE ARC-182 4.DEACTIVATED #1 2.DEACTIVATED PRC-117G #2 2.DEACTIVATED HPA 14.00 - 20DEACTIVATED TRACER PDU #2 50.00 - 50ACTIVE POWER CONVERTER (28- 12 VDC) 5.DEACTIVATED COMINT 12.00 15ACTIVE VIASAT MODEM 12.00 - 15DEACTIVATED VIASAT INU 5.DEACTIVATED VIASAT ACU 12.50 - 20DEACTIVATED VIASAT SERIAL CONVERTER 0.DEACTIVATED MX15 32.5 - 35DEACTIVATED TRU - 3983.0 20.0 115/400 HZ AC AIRCRAFT AC BUSS ACTIVE MISSION SYSTEM NO AC LOADS - CHANGE 15.0 115/60 HZ NON ESSENTIAL 115/60 Hz ACTIVE MISSION SYSTEM NO AC LOADS - CHANGE 15.0 115/60 HZ NON ESSENTIAL 115/60 Hz ACTIVE NO RH BAGGAGE - CHANGE 15.0 NON ESSENTIAL 115/60 Hz ACTIVE FANS LOADS DC 2.3 28 VDC FANS LOADS AC -2 115/400 ADSB LOADS 0.5 28 VDC - newton .1519; TOTAL ADDED LOADS Lg ?281.11 Aery Aviation. LLC 1749-ED-1013 Electrical Load Analysis Rev IR 75/. E: Page 7 of 8 FAA PROJ STOWMC-T The added systems will increase the load on the AC system by 3983 VA. This increase creates a total demand of 34101 VA on the AC system. The new remaining capacity is 11899 VA. The total added load on the AC system increases the toad percentage to 74%, which is increased from 65%. The Increased loading on the AC system still keeps under the 80% leading threshold; therefore the increased electrical load is within limits based on this analysis. and ADS-B Out STC installation Total Loads Two prior approved STCs for FANS-1A and ADS-B out were performed concurrently with the aircraft modi?cation. The totai added loads are as follows: 1. The added DC load for the FANS DC System is 2.3 AMPS. The existing SATCOM system installed In the aircraft is being used for the FANS-1A messaging function, therefore the iridium Load that is part of the STC is not included in this DC Load Calculation. This addition of 2.3 AMPS to the aircraft DC Buss does not impact the current compliance of the aircraft DC electrical system. 2. The changed AC Load for the FANS system. reduces the total load on the AC system by 2 VA. This is negligible and does not impact the aircraft AC System loading compliance. 3. The changed DC Load for the ADS-B system increase the DC current draw by 0.6 AMPS. This added load is considered negligible and does not have an impact to compliance of the aircraft DC System. 3.0 CONCLUSION The mission systems added as part of this modi?cation are on the cabin ioadshed bus and do not impact the battery capacity in the event of a generator failure. The added load from the modi?cation will not increase the overall essential systems load on the battery system and the batteries remain adequate for 20 minutes of operation. Therefore this analysis ?nds that the added systems do not impact compliance to the applicable requirements. mun?n. Aery Aviation. LLC Electrical Load Analysis Rev IR j?f' vb?? Page 8 of8 FAA PROJ ST00464MC-T APPENDIX A . . 41 . .m?uF-wwm, AIRCRAFT INCORPORATED REPORT NUMBER (304146961 16 ELECTRICAL LOAD ANALYSIS SUPPLEMENT FOR Aero Mundo Ejecuuvo AEROSPACE G-IV AIRCRAFT (A12EA) SERIAL NUMBER 1426 PREPARED BY: APPROVED BY: 742/ 12~May-01 Christopher?l'an Date AvionicleIectdcaI Engineer Englneen'ng Manager! DER List of Revisions RWumber: 6041456361 16 By Eesc?ptlon of ?gvis?lon Date Approved Rev. Ch?s Tan NEW 12?May-01 (see cover) .. 1 Report- Electrical ELECTRICAL ?m AD ANALY IS Page: 1 Prep. By: GirlsTan TABLE OF CONTENTS Report II: (30414696116 Date: 12-May-01 Model: E-IV Page Number List of Revisions . i Table of Contents . . 1 Introduction . . . 3 System Characteristics 4 General Notes . .. . 6 ESSENTIAL. 26V DC PILOT (P600) . 8 PILOT (P602) . . . 9 PILOT (P609) . 10 COPILOT (P605) . . - 11 COPILOT (P606COPILOT (P613) 13 ACCESS (PX304) . V. . . 14 ESSENTIAL DC Summary . . . 15 LEFT MAIN, 26V DC PILOT (P604) 16 PILOT (P652) .. . . . 17 COPILOT (P606) . 18 COPILOT (P645) .. . 19 COPILOT (P621) . 20 ACCESS (PX102) . . 21 LEFT MAIN DC Summary 22 RIGHT MAIN, 28V DC PILOT (P603) .- 23 PILOT (P615) . . 24 COPILOT (P607) 25 COP ILOT (P650) . . 26 COPILOT (P616) . 27 ACCESS (PX202) . 26 RIGHT MAIN DC Summary 29 AIRCRAFT DC SUMMARY . 30 MAIN BATTERY CAPACITY ANALYSIS 31 EMERGENCY BATTERY ANALYSIS (1 PU1129) (1PU1 130) (1 PU1131) (IPU1 141) (1 PU1142) 32 (2PU1129) (2PU1130) (2PU1131) (2PU1141) (2PU1 33 (3PU1205) THFIU (3PU1235) (1 PU1129) (1PU1130) (1 PU1 34 (4PU1205) THFIU (4PU1235) (2PU1129) (2PU1130) (2P01131) 35 28V DC AUX CONVERTER SUNNARY . 36 1151! AC 60112 CONVERTER SUMMARY 37 (can?t) .1- 11.1.5 Tamra??mu. {Wu A $3 ?gs: 2 I Pmp. By: Chris Tan TABLE OF CONTENTS HM 60414696118 I Date: 12-May-01 Model: IV Page Number ESSENTIALJ 15V AC COPILOT PHASE-B, as ESSENTIAL AC Summary . . 39 MAIN, 115V Ac PILOT PHASE-C, (1X609) . -A . 4o ACCESS (1xx1o1) . 41 MAIN Ac Summary . 42 RIGHT MAIN, 115V AC COPILOT PHASE-A, (2xeoz) 43 ACCESS (2)0(101 . . 44 RIGHT MAIN A0 Summary . 45 AIRCRAFT AC SUMMARY . 46 f?u. - a *mooww?mr 9.. "r3- I "Wm El WEE ANALYSIS ?gs; 3 Prep. By: mam" INTRODUCTION Report a: 60414698116 Date:12-May-O1 Modal: G-IV This ELECTRICAL LOAD ANALYSIS has been prepared as a stipplernent to the AEROSPACE CORPORATION REPORT AC DC LOAD EFFECTIVITY NC SIN 1390 and In accordance with FEDERAL AVIATION ADMINISTRATION ADVISORY CIRCULAR 43.13-2A (Para 27d) and FAR 25. it is the- summary of the factory loads and the out?tter Installed avionics and electrical equipment system loads for the aircraft specified herein. The foliowing tabulation of AC and Dc loads have been extracted from this report: (A) CRUISE DC LOAD (BI CRUISE Ac LOAD MAIN BATTERY LOAD (D) FWD EMERGENCY BATTERY LOAD (E) AFT EMERGENCY BATTERY LOAD (F) FWD EMER LIGHTS BATTERY LOAD AFT EMER LIGHTS BATTERY LOAD (Page 30) (Page 46) (Page 31) (Page 32) (Page 33) (Page 34) (Page 35) 464.52)! 301 18.80 VA 16735 A 195.75 VA 181.35 VA 153.90 VA 153.90 VA ?me Electrical ELecr'riicAL are Page: 4 Prep. By: Ctuis Tan SYSTEM CHARACTERISTICS Report 60414696116 Date: 12-May-01 Model: r. MAIN oc POWER The primary sources of DC power on the aircraft are two 28V DC, 250 Amp outputs from the Left and Right DC converters (one output per converter). The converters receive their input power from their associated alternator (three phase and variable frequency). which then outputs AC, three phase, ?xed frequency (400Hz) and 28V DC (regulated voitage) power. The DC output voltage of a converter is regulated to 28V DC and maintained tram no load to a full load condition. The two converters share the system loads during nonnal operations as follows: 0 Left converter DC output shall power the LEFT MAIN DC BUS and ESSENTIAL DC BUS. a Flight converter DC output shall power the RIGHT MAIN DC BUS. With the loss of either converters Dc output and when the AUX Transformer-Rectifier Is rte-energized, the remaining operating converter will automatically assume the total aircrait load. Some load shedding may be required depending upon the systems in use. II. AUXILIARY DC POWER In the event at the loss at either or both converter DC source(s) anWor during APU operation, 300 Amps at 28V DC power is available from the Auxiliary Transformer-Rectifier (THU). Power for the AUX is supplied by the LEFT or RIGHT MAIN AC BUS. Ill. DC BATTERY POWER The DC power system is sepplernented by two 24V DC, 40 Amp-Hour batteries. These batteries provide power for APU start and for emergency power tor emergency operation under the loading conditions summarized in Table 4. (Fist: Report No: Page 149, Figure 4). IV. EMERGENCY BATIERIES Four 24V DC, sealed-cell. lead acid emergency battery packs are installed in the aircraft and are charged from the DC BUS. In the event of toss of all electrical power. the emergency batteries supply DC power to most essential instruments and the emergency light system as long the ESSENTIAL DC BUS is less than 18 VOLTS DC. A fully charged emergency battery to capable of supplying 200 WATTS at a voltage between 19 to 28.6 VDC for a minimum of 30 minutes. (can heap- ?.410 Wmm.sa e: - Report: Electrical I EECTRIEAL LOAD ANALYSIS Page: 5 Prop By: GhrlaTan CHARACTERISTICS Reportit: 9C414696116 Date: 12~May~01 (Continued) Model: . G-IV V. APU POWER APU power is primarily used during ground operation but is also available as a back-up for the LEFT and RIGHT converter sources during The APU is rated for airborne operation at altitudes up to 30,000 feet. The APU is equipped with an alternator which provides 115V AC, 400 Hz, 3-phese power. DC power Is available during APU operation using the Auxiliary Transionner-Recti?er Unit (TRU). Vi. STANDBY ELECTRICAL POWER Standby electrical power is provided by a motor/generator (ABEX) capable of supplying Amps at 28V DC. Hydraulic power for the ABEX is derived from the Combined Hydraulic System. The 5 KVA AC output of the, ABEX is recti?ed by the AUX TRU to provide 163 Amps DC power to the ESSENTIAL Dc BUS. The 50 Amps DC output of the ABEX is utilized to povver the Emergency Inverter, to supply ESSENTIAL AC loads In the event of the loss of all three power sources (Left, Right and APU altemators).163 Amps of 28V DC :8 available at the ESSENTIAL DC BUS thereby further delaying the depletion of the batteries. In addition, 800 VA of AC power (Phase A only) is available at the ESSENTIAL AC BUS. VIL HAIN Ac POWER The primary sources at AC power on the Guilstream-(constant frequency), 3-phase converters. The system load during normal operation is as follows: 0 Left converter AC output shall power the LEFT MAIN AC BUS and ESSENTIAL AC BUS. 0 Right converter AC output shall power the MAIN AC BUS With the loss of either converters AC output the remaining Operating converter will automatically assume the total aircraft load. some load shedding may be required depending upon the systems in use. ESSENTIAL Ac POWER 115V AC, 400 HZ. 3-phese power for the ESSENTIAL BUS is normally supplied from the or RIGHT MAIN AC BUS. However. in emergency conditions (iatlure at three sources RIGHT. and APU sources), ESSENTIAL AC power is supplied by an 800 VA E-INVERTEFI (only PHASE A BUS is energized). The input power tor the is derived from the ESSENTIAL DC BUS or from the Standby Ebctricai Power Motor/Generator. Ix. ENGINE INSTRUMENT 28V Ac POWER Engine Instrument power ls provided by two 200 VA transformers powered by the ESSENTTAL AC BUS. X. MAIN 28V AC POWER MAIN 28V AC POWER is provided by two 1000 VA transionners powered by the MAIN AC BUS and MAIN AC BUS. Bottom?Electrical AL OAD r. are Palm 6 magmas Tan GENERAL NOTES Report it: 60414696116 Date: 12-May-01 Nader: G-IV . 1- PRODUCTION LOADS . All have been obtained from Aerospace Report No.: AC 8: DO LOAD Dated 1 SEPT, 1999; Effecthity NO SM 1390 and PRODUCTION CONFIGURATION. 2 - COMPLETION CENTER ADDED LOADS The added loads listed in this report are calculated from vendor-published data which are usually conservative. The aetual loads are normally less than the calculated load. 3-- AND ADDED LOADS. All and added loads listed In this report are tor a night cmise condition and continuous operation unless otherwise noted. 4 . NORMAL OPERATING conomou During conditions of normal operation with both converters sUpplying power. the approximate DC load of the Left converter is 93.06% - and the Right Is 92. 74% This assumes that the Left Converter ls supplying power for the LEFT MAIN and ESSENTIAL DC BUS. 5 - EMERGENCY SINGLE SOURCE OPERATION - For a conditionin which one converter 00 source is Irreperative, the TRU will automatically come on line and power the DO loads of the de-energlzed source. There shall be no reduction in aircraft load requirements and It Is assumed that all systems will be operating normally. However. if the TRU is inoperative (Le. dual failure), the remaining operating converter 00 source shall assume the total aircraft load; and some load shedding maybe required. In the event of an emergency condition (to. dual failure) In which the Auxiliary Transformer-Rectifier is on line, the total load may, under certain conditions, exceed the capacity of the Auxiliary Transformer-Recti?er and manual load shedding will be required to limit the load to 300 Amps or less. a . BATTERY a STANDBY ELECTRICAL POWER OPERARON This summary considers an emergency condition in which the two main batteries and standby electrical power system are the only sources of power at altitudes of up to 45,000 feet. Adequate electrical power isavailable to the essential DC and AC bosses to supply all the loads listed. 7 - BATTERY OPERATION This surnmary considers an emergency a condition in which the two main batteries are the only source at DC power during a forced descent and landing. Adequate battery Capacity is available to supply all of the loads listed during such a condition of operation. However, if during the period of failed DC power the AC portion is functional, the battery charger will operate as a Transformer- Rectifler. In this mode of operation. the Transfonner-Rectl?er will parallel with the batteries and provide up to 55 Amps each at 27.75 Volts DC to the DC BUS and thereby further delay the depletion of the batteries. (can?t) nepo'rt' LO DANAL a ?nger: 7 Prep. By: our: Tan GENERAL NOTES Report it: (30414696116 . om: 12-May~01 (Continued) Model: e-rv e? EMERGENCY BATTERY OPERATION This summary considers an emergency condition involving multiple failures of all power sources (Left, Right, APU and Standby Electrical Power) in which the existing FWD and AFT emergency batteries will supply power to the most essential instruments plus the additional FWD and AFT ememency lighting batteries supplying power to the interior and exterior emergency lighting system. CAUTION it may be necessary to make load adjustments when powered under emergency conditions. as is required under normal conditions. it aircraft total AC or Dc power requirements exceed total available power. unload the respective electrical system to maintain a total load of less than 100%. As a reminder these load values may be read on the Standby Electrical Power Panel as a percentage of available power. The hydraulically driven ABEX emergency generator provides raw AC to the Transionner-Rectifier Unit (THU) converting it to a regulated Dc. This output in turn is provides to the E-INVERTER supplying constant frequency emergency AC electrical power. Knowing this, the DC load must be reduced to lower the (Ac PWR reading, and ccnvemely the AC load must be reduced to lower the (DC reading. . REFER TO THE FLIGHT MANUAL FOR comma-re OPERATING Pnoceounes. nun-p. and. .- .. .- REVISED TOTAL NOTES: 1.) Production system mbussed to 28VDC ESSENTIAL ACCESS. reference page 14 2.) Normal load ls 0.15 Amps, 20.0 Amps maximum. 3.) Ground Operation only and is not added to load. Rammecmal ANALYSIS ?1-792; 9 Prep. By: 011119 Tan 28V Dc ESSENTIAL Report it: 60414896118 0919: 12-May-01 PILOT 11 1 (P600) Modal: G-IV sang. 4?03 00- LAO um DELETED: WHEEL WELL LTs 31403148 PLT MAIN 3.00 1.3 TOTAL DELETED . 0.00 A ADDED: FWD EMER LTS BAT 199031 PLT Aux 0.15 2 FWD EMER LTs IMPACT 199092 PLT Aux 0.10 RADIO MASTER 195091 PLT Aux 0.90 3 FMS MASTER 295031 PLT Aux 0.40 a CABIN MASTER 390031 PLT Aux 0.30 GALLEY MASTER - 9900132 PLT Aux 0.49 . TOTAL ADDED 1.09 A 21051010: (1191.: Av-ew-H-42s.1s, Page 22.) (50 AMP FEEDER) ESSENTIAL Dc PILOT 11 1, (P600) 20.62 A 21.95 A 150"? . n?u?u?r?u-v?ahh. 9.1.1 .1 NOTES: 1.) Production system rebussed to 28VDC ESSENTIAL ACCESS, referenm 130901 4. 2.) Normal load is 0.15 Amps charged, 20.0 Amps maximum. 3.) Normal load is 1.20 Amps, 4.00 Amps madmum. 4.) Ground Operation only and is not added to electrical load. ?nepou_: Electrical VOA?hip ANALYSIS Pigs: 9 P101131: 0mm 20V 00 ESSENTIAL Repor?: 30414090110 Data: 12-May-01 PILOT 2 (P602) Modal: 00mg 0039. 03 L00. LOAQ DELI-JED: UTILITY LTS 31400355 PLT MAIN 5.00 1.4 TOTAL DELETED . .. . . . . 0.00 A ADDED: AFT EMER LTS BAT 139003 PLT AUX 0.15 2 AFT LTS IMPACT 100054 PLT AUX 0.10. CKPT LIGHT- AUX PED 270031 PLT AUX 2.50 OKPT LIGHT- AUX ANN 330031 PLT AUX 1.20 3 I TOTAL ADDED . . . . 0.05 A Page 20.) (50 AMP FEEDER) ESSENTIAL DC (P602) 13,44 A REVISED TOTAL . . . . '22. Repo?: Electrical ELECTRICAL LOAD AN LYSIS Fags: 10 Prep. By: 0mm 28VQCESSEN11AL 35mm (30414696116 Date: 12-WF01 PILOT 3 93609) odol: G-IV mg OB NO. . CB LOO. LOAD NO 5 DELETED: NONE TOTAL DELETED . . . . 0.00 A ADDED: NONE ?as TOTAL ADDED . . 0.00 A (Rat: AV-GIV-R-426.16, Page 34.) (20 AMP FEEDER) ESSENTIAL Dc PILOT 3 (P609) 0.12 A REVISED TOTAL 0.12 A NOTES: None .nu-m-n. . -.- -- A .. Report: Electrical Lo' iagg: 11 Prep. an onus Tan 20V 00 ESSENTIAL Report (30414698116 Dm=12-May-o1 Model: QB mm on 59. ca LOAD NOTES DELETED: NONE TOTAL DELETED .. . 0.00 A ADDED: NONE TDTAL ADDED ??0.00 A sxusma: Page 29.) (50 AMP FEEDER) ESSENTIAL Dc COPILOT 1 (P605) 24.53 A REVISED TOTAL . A NOTES: None. .Mumy-wl. i Report: fiance: We 1OAL Page: 12 amt: 1310414896116 Date: 12-May?01 COPILOT 11 2 (P606) Model: G-IV No m9; DELETED: NONE TOTAL DELETED D.oo"A ADDED: ICE DETDC 446681 CPLT Aux 0.20 TOTAL ADDED . . a 0.20 A EXISTING: (Den: AV-GIV-R-426.16, Page 32.) (50 AMP FEEDER) ESSENTIAL DC COPILOT 2 2 (P606) 23.48 A REVISED TOTAL nan A NOTES: None 1' L. I Report: Elm?'I Page: 13 Prop. By: Ch?sTan 20v Dc ESSENTIAL Report 4: 00414090116 Date: 12-May-01 COPILOT 11 3 (P613) Model: G-IV swig 9.0.02. $34-29. LQAQ EELS. DELETED: NAV nova 1 315013127 CPLT MAIN 0.70 1 ONE 1 315013101 CPLT MAIN 1.03 1 TOTAL DELETED . 1.78 A ADD :14: NONE TOTAL ADDED . 0.00 A EXISTING: (not: Page 36.) (20 AMP FEEDER) ESSENTIAL Dc COPILOT II 3 (P613) . 14.43 A REVISED TOTAL 12.05 A NOTES: 1.) Hebussed to Production Aft Emergency Ba?ety. reference page 33. w'awtvm?'a??uu 4-1. - - DELETED: NONE 0 00 A TOTAL I I no. ADDED: WHEEL WELL LTs 31400143 PLT MAIN 0.00 unuw LTS 31400355 PLT MAIN 5.30 AISLE LTS 504001 CABIN 0.50 CABIN PA . 501001 CABIN 0.20 I TCTAL . . . . 0.70 A 53031100: 9.) (25 AMP FEEDER) ESSENTIAL 00 ACCESS (PX304) 0.00 A names-:0 TOTAL . . #010 A NOTES: 1.) Production Load rebussed Ieference page 8. 2.) Production Load rebussed reference page 9. 3.) This load occurs during master! and was not added to total. 4.) The Ampli?er is normaIIy powered from LH Main 115VAC bus. During Emergency operation the load ls 0.20 Amps nmmalnal to 4.00 Amps Maximum and is not included in the column tote). 00000: E'iecmeaI L670 ANALYSIS $90: 14 Prep. By: Chas Tan 28V DC ESSENTIAL Report 60414696116 Date: 12-May-01 ACCESS (an04) Model: G-IV . 9m 2m 0- HELES 1 ,3 2.3 I. -. Wneport: El Was 1011 0A0 AN . Page; 16 Prep. By: Chris Tan - 26V Dc Regen 60414696116 Date: 12eMay?O1 SUMMARY Model: 1 DEMAND (AMPS: P600 PILOT 1 (Revised page 6) 21.65 P602 PILOT 2 (Revised page 9) 22.39 P609 PILOT 3 None added.Page 10 0.12 P605 COPILOT 1 None added.Page 11 24.53 P606 COPILOT 2 (Revised page 12) 23.68 P613 COPILOT 3 (Revised page 13) 12.65 PX304 ACCESS {Added page 14) . 0.70 V536 INVERTER FDR None added. 0.00 10126 MAIN FUEL FDR None added. 30.00 20126 MAIN FUEL FDR None added. 30.00 Page 53.) TOTAL REVISED ESSENTIAL DC 165.72 A NOTES: None. 1. :16 mas: None Report: ELECTRICAL LOADTANALYSIS Prop. By: Chris Tan 28V Dc MAIN Report (30414696116 Date: 12-Mayd01 PILOT #1 (P604) M06131: G-IV ERIE-.5. H.433 No A03 0 LQAD [221$ DELETED: NONE TOTAL DELETED 0.00 A ADDED: CABIN EMEFI LTS SENSE RELAY 81468316 PLT MAIN 0.20 SIGN LTS 31408146 PLT MAIN 0.60 TOTAL ADDED . 0.80 A msnue: Page 39.) (50 AMP FEEDER) LEFT MAIN DC PILOT 1 (P604) 11.88 A REVISED TOTAL 12.48 A -. . an." .- . Repo?_rt: Electrical LOAD A LYS 339.: 17 Pg?. By: cm: Tan 23v Dc LEFT mm Report (30414696113 Date:12-May-01 (P652) Mode): G-IV EEIELE. 918.2; 28.52% L-QAQ DELETED: NONE - TOTAL DELETED "Too A ADDED: NONE TOTAL ADDED . . . .. ??6361: EXIsnuo: (Rat: Page 43.) (20 AMP FEEDER) LEFT MAIN Dc PILOT 2 (P652) 4.09 A REVISED TOTAL . . NOTES: None. . . Report: E'iect?ca] OA s: 5899. 18 Prep. By: mm 2011 no LEFT MAIN Report #1 39414696116 0m: 12-May-01 COPILOT 11 1 (P608) Model: G-IV 1' 20m LLB a 9?018 - LQAQ TES DELETED: NONE TOTAL DELETED '0.00' A ADDED: NONE 1' TOTAL ADDED . . . 0.00 A mama: (not: Page 40.) (50 AMP FEEDER) LEFT MAIN Dc COPILOT 11 1 (P608) 23.20 A REVISED TOTAL . 23.20 A NOTES: None mu- -.. a NOTES: Nona B'ewport: Eiecmea' ANALYSIS ?age: 19 Prep. an em Tan zav Dc LEFT mm Report (304146961 16 .57 Date: 12-May?01 COPILOT 2 (P645) Model: G-IV 9.8.1.1155. "[12:08 - .QLL HOE LEFT MAIN Dc COPILOT 2 (P645) DELETED: NONE TOTAL DELETED 0.00 A man: NONE q! TOTAL moan . 0.00' A exusma: (20 AMP FEEDER) LEFT MAIN DC copnm 2 (P645) 3.10 A REVISED TOTAL 3.10 A ADDED: NONE TOTAL ADDED Report: Electrical ANALYSIS 5? 20 Prep. By: Chris Tan 28" DC LEFT MAIN . Egan 60414696116 om: 12-May-01 COPILOT 3 (P621) Model: e-zv gum; on No. on Lee, 5959 NOES LEFT MAIN Dc COPILOT (r 3 (P621) ammo: HF com 1 03331 CPLT MAIN 0.30 1 TOTAL DELETED 0.60 A 0.00 A Manna: (Hot: Page 41.) LEFT MAIN DC COPILOT 3 (P621) REVISED TOTAL (50 AMP FEEDER) 22.75 A 1.) Production System Removed. . 22.15 A El cm' LEE: ANALYSIS 3399; 21 . this'ran 28V Dc LEFT MAIN Rapon (30414696116 Date: 12-May-01 ACCESS (PX102) Model: G-IV 29.111145. 9.5.119. .1de oc was. DELETED: NONE moan: LH MAINIGND AIHSTAIR LTS 430031 CABIN 3.29 1 VEST LTS 432031 CABIN 1.92 sermons LTS 487031 CABIN 2.03 1.2 TOTAL . A manna: (391.: mama-426.16, Page 9) (50 AMP FEEDER) LEFT MAIN DC ACCESS (PX102) 0.00 A FIEWSED TOTAL . . NOTES: 1.) Load used dudng ground operation only and are not added to the total. 2.) Average Ioad Is ?gured 1115099 of the mazdmum load Bo Tam-moat Ei?s'?a'ic' Lo" 11' NET 13' 22 Prep. By: this Tan 28V Dc LEFT MAIN Report 60414696116 I Date: 12-May-01 SUMMARY Model: G-IV DEMAND FEEDER TEL: P604 PILOT 1 (Revised Page 16) 12.48 P652 PILOT 2 None added. Page 17 4.09 P608 COPILOT 1 None added. Page 18 23.20 P645 COPILOT 2 None added. Page 19 3.10 P621 COPILOT 3 (Revised Page 20) 22.15 PX102 ACCESS (Revised Page 21) 1.92 (Rat: Page 54.) . NOTES: None. shunt. - . EectrIcaI LOAD 23 Prep. By: 311.3 T311 231: 00 RIGHT NAIN Report 3: 30414393113 Date: 12-May-01 PILOT 3 1 @303) Model: G-IV Quill-E 23.32. 03 Loc- BEE DELETED: NONE TOTAL DELETED .. 0.00 A ADDED: CABIN SWITCHED CABIN EFFECT LTS CONT 331031 CABIN 0.35 1 FWD UPPER EFFECT LTS 531032 CABIN 4.20 1,2 FWD LOWER EFFECT LTS 531033 CABIN 3.15 1.2 AFT UPPER EFFECT LTS 531034 - CABIN 3.15 1.2 AFT LOWER EFFECT LTS 531035 CABIN 3.15 1,2 CFIEDENZA FANS 399031 CABIN 0.73 1 31303 FANS 339032 CABIN 0.32 1 l. TOTAL ADDED . . . . 3111311113: (331.: mew-3423.13. Page 43.) (50 AMP FEEDER) RIGHT MAIN Dc PILOT 3 1 (P303) 3.13 A REVISED TOTAL 21.? A NOTES: 1.) This load can be shed from the cockpit by switching t0 the position. 2.) Average Ioad is ?gured at 70% of the maximum load. 4 . nun. no . . NOTES: 1.) Normal load is 1.00 Amp, 4.50 Amps maximum 2.) Nomal load is 0.61 Amp. 4.91 Amps maximum when 113031316139. Report: Eiecmcal 313 Eggs: 24 P111061: 0311s Tan 28V Dc RIGHT MAIN Report 60414696116 Datoz1Z-May-01 311.0142 (3315) 110041: G-IV gamma 0 9.3390. 3% 3933 DELETED: NONE DELETED . . . 0.00 A ADDED: MAP LTS -CKPT 179032 PLT Aux 1.75 03 PNL LIGHTS - 01031 179031 PLT Aux 1.25 . PLT FLASHLIGHT . 432031 PLT Aux 0.44 PULSELITE 133031 PLT AUX 0.50 OVHD 03 3NL LTS 3900310 PLT Aux 2.50 VHF COMM 3 . 300031 03L1 Aux 0.31 2 SELCAL 423031 03L1Aux 0.30 CPLT FLASHLIGHT 462032 OPLT AUX 0.44 311100141 011. 100034 031.1 A071 0.29 SATCOMANT 103033 03LT AUX 1.00 1 01031 MON 504032 03LT Aux 1.00 CABIN EMEH LTS SENSE RELAY 31403313 PLT MAIN 0.20 1. TOTAL ADDED . A 3x13111141: (Hat: Av-er-3-420.13, Page 43.) (20 AMP FEEDER) RIGHT MAIN Dc 2 (3315) 1.04 A REVISED TOTAL . . ?'12.12 A .. WHOM Electrical Bags: 25 Prep. By: Chris Tan 23v Dc RIGHT MAIN Report (30414696116 Date: 12?Maym COPILOT 1 (P607) Model: SW 5331;: cg No. on Lo_c_, LOAD 391g DELETED: NONE TOTAL DELETED . . ADDED: NONE . TOTAL ADDED . . . 0.00 A EXISTING: (Flat: Page 48.) (50 AMP FEEDER) RIGHT MAIN DC COPILOT 1 (P607) 37.40 A REVISED TOTAL . NOTES: None. I NOTES: 1.) Normal load is 2.00 Amp, 7.00 Amps maximum when transmitting Report: Electrical ELECTRIC-KL ANALYSIS Page: 26 Prep. By: Chris Tan 23" DC RIGHT MAE-N Report 3: 6914696116 Date: 12-May-01 COPILOT 2 @650) Model: G-IV (. CB cg No. 03 L00, LOAD gang DELETED: NONE TOTAL DELETED 0.00 A ADDED: AFIS DMU 306081 CPLT AUX 2.00 1 AFIS PRINTER 306082 CPLT AUX 0.50 TOTAL ADDED 2.50 A EXISTING: (Ref; AV-GIV-R-426.16. Page 52.) (20 AMP FEEDER) RIGHT MAIN DO COPILOT 2 (P650) 10.93 A REVISED TOTAL 13.43 A who culin- NOTES: 1.) Production system removed. 2.) Production system addition. nepon: Eastman 27 Prep. By: Ohm Tan 28V Dc RIGHT MAIN 1-1 11: 60414696116 Date: 12-May-01 OOPILOT 11 3 (P316) ?xes!? 9.0.1111; CB LOO- DELETED: 11 2 03179 CPLT MAIN 1.25 1 HF 2 03333 CPLT MAIN 0.60 1 TOTAL DELETED . 1.35 A ADDED: 11 2 03179 CPLT MAIN 1.00 2 Ii TOTAL ADDED. . 1.00 A 5x15111113: (Hat: Page 51 .1 (50 AMP FEEDER) RIGHT MAIN DO (P616) 40.05 REVISED TOTAL 47.20 A -- n-n -n nu ?Alum A .I.- Report. Electrical LOAD 5599: 20 Prep. By: ChrIs Tan 28V Dc RIGHT MAIN Report {30414696116 Data: 12-May-01 ACCESS (PX202) MedalNo. CALDE- m0 110133 500301 CABIN 3.) Normal load is 4 .40 Atrips, 9.60 Amps maximum when transmitting. 4.) GALLEY FDR DC. loads shown as GALLEY SWITCHED and u. NOTES: 1.) This load can be shed irom the 000ka1 by switching to the position. 2.) This load Can be shed from the cockpit by Switching to me position RADIO TEL ARTU 104031 0A31N 4.40 3 RADIO TEL CONT 104032 CABIN 1.53 AIRSHOW 504031 CABIN 1.75 CABIN SPKR PREAMP 501033 CABIN 0.20 GALLEY DATA BUS 509035 CABIN 0.40 CBN FLASHLIBHT 402033 CABIN 0.44 CABIN DATA BUS 2 509032 CABIN 0.30 1 CABIN DATA BUS 0 509033 CABIN 3.40 1 CABIN DATA BUS 4 509034 CABIN 0.00 1 VEST EFFECT LTS 404031 CABIN 1.10 1 CLOSET LTS 537031 CABIN 1.53 1 FWD 00 590031 CABIN 2.71 1 CREW GALLEY US 040031 CABIN 0.22 1 CABIN TEMP FANS 453031 CABIN 0.30 1 CABIN TEMP CTL 457031 CABIN 0.40 1 BOHZCONT. 493032 CABIN 0.04 1 00 095032 CABIN 3.30 1 CALL SYSTEM 107031 CABIN 0.50 1 GALLEY - 311 MAIN DCIGND . GALLEY DC FDR 1 394032 CABIN 0.00 1.4 GALLEY DOME LTS 590031 GALLEY 1.29 1 CALLEY CONT 573031 BALLEY 0.70 1 WATER LEVEL 550031 GALLEY 0.30 1 GALLEY - RH MAIN DCICND GALLEY 00 FOR 2 394031 CABIN 0.00 1.4 GALLEY WORK 590033 GALLEY 4.01 1.2 CALLEY EFFECT LTS 590032 GALLEY 4.51 1.2 WATER SYS 00 540031 GALLEY 3.52 1.2 DRAIN CONT 549031 GALLEY 0.92 1.2 . . 40.17 A EXISTING: (351.: mew-3420.10, Page 9.) (50 AMP FEEDER) RIGHT MAIN DC ACCESS (PX202) 0.00 A REVISED TOTAL . 40.17 A I u, NOTES: None. Began: ?eece AL 1.ng mums Edge: 29 Prep. By: 011115 Tan 20V 00 RIGHT 11mm Report 2: 60414696116 Date: 12-May-01 SUMMARY Model: G-IV 11 DEMAND TITLE P603 PILOT 1 (Revised page 23) 21.54 P615 2 (Revised page 24) 12.12 P607 COPILOT 1 None added. page 25 37.40 P650 0011001112 (Revised page 26) 13.43 P616 OOPILOT 11 3 (Revised page 27) 47.20 PX202 ACCESS (Added page 28) 40.17 19127 ALT PUMP FDR None added. 30.00 20127 ALT PUMP FDR None added. 30.00 (Ref: Page 55.) TOTAL REVISED RIGHT MAIN 0c .. . .. 231.00 A . I. J's?Mr! mu. I: E: 1519th Earl AL LOAD NALYSIS ?agg: 30 AIRCRAFTDC HMO: 60414696116 I Date: 12-May-01 SUMMARY m; G-IV OTES LEI-T MAIN AND DC LOAD Capacity 250.00 Demand DC) (Revised page 15) -1 65.72 1 Demand MAIN DC) (Revised page 22) 66.94 1 Reserve 17.34 A RIGHT MAIN DC LOAD Capaclty 250.00 Demand (Revised page 29) ?31.86 Reserve 18.14 A Dc LOAD GRAND TOTAL . Total DC Capacily 500.00 Total Demand 464.52 Total Reserve - 35.48 A NOTES: 1.) ESSENTIAL DC load is Included in the LEFT MAIN DC total. . . Report: Eiectrical Pa 31 mp. Dr. Chris Tan . BATTERY cAPAcm ANALYSIS Report it: 60414696116 Date: 12-May-01 23v Dc Model: G-IV . DEMAND DEMAND (AMPS) (AMP-MIN) EXISTING: AVERAGE DEMAND 163.25 ?i 4897.40 Page 92.) DEMAND 334.52 (Fiat: Page 92.) ADDED: P600 (Revised page 8) 1.03 30.90 P602 5 (Revised page 9) 3.95 118.50 P609 None added. page10 0.00 0.00 P605 None added. page 11 0.00 0.00 P606 (Revised page 12) 0.20 6.00 P613 (Revised page 13) -1 .78 4.33.40 PX304 (Added page 14) 0.70 21.00 . V536 None added. page 15 0.00 0.00 10126 None added. page 15 0.00 0.00 20126 None added. page 15 0.00 0.00 REVISED AVERAGE DEMAND TOTAL 5020.40 AMP-MIN 5,020.40 AVERAGE DEMAND: a: 167.35 A 30 minutes Period: 30 MINUTES Battery Capacity in Amp-Hours a: 40 Number 01 Batteries =2 2 BATTERY DEPLETION mile?) a 20.66 MINUTES (Fiat: Page 149. Figure 4.) NOTES: 1.) Average Demand is a quantity of continuous current, expressed in Amps. 2.) Values are expressed in Amp-Minutes for 30 minute period. (.. 3.) Simultaneous Demand is a quantity of cement required at a given moment. 4.) Calculated value is approximate, actual time may vary. . . 1 11mm ??cmcal EWCTR A 11313 33911: 32 I_Prep. By: cm Ten EMERGENCY BATTERY ANALYSIS RM 00414696116 Date: 12-May-01 (1PU1129) (11901130) (11301131) (1PU1141) (1PU1142) Model: G-IV PRODUCTION FORWARD EMERGENCY BATTERY (Existing Securaplane 6.0 AMP-HOUR Battery) me LE 22292. 99.032. Lem 2491.22 DELETED: TDRICAD 1 08177 CPLT MAIN 1.09 2 OVERWING EMERG LTS 1PU1129 0.60 3 OVERWING EMERG LTS 1PU1130 0.60 3 OVERWING EMERG LTS 1PU1131 0.60 3 TOTAL DELETED .. 2.89 A ADDED: 1 08177 CPLT MAIN 1.00 4 ELTINAV INT EF 423031 (1 PU1 142) CPLT AUX 0.35 TOTAL ADDED 1.35 A REVISED TOTAL . . -1 .54 A DEMAND DEMAND (AMPS) (AMP-MIN) Page 94.) 10.24 307.20 1 TOTAL DELETED . 2.89 86.70 TOTAL ADDED 1.35 40.50 REVISED LOAD 8.70 A 261.00 AMP-MIN 261.00 AVERAGE DEMAND 8.70 A 30 8.70 A 22.5VDC 195.75 VA Page 149, Figure 5.) TIME TO 16VDC 4138 MINUTES NOTES: 1.) This value re?ects shared exterior lamp loads between forward and aft emergency batteries. 2.) Production system removal. 3.) System rebuesed to Emergency Lights Battery, reference page 34. t- 4.) Production system addition. mm? Wu I EIectnca 33 Prep. By: Chris Tan EMERGENOY 00414666116 Date: 12-May-01 (2PU1129) (2PU1130) (2PU1131) (21:01 141) (21361 142) . AFT EMERGENOV (Existing Securaplane 6.0 AMP-HOUR Battery) 061m; 05 No, cg LocI LQAQ Helge DELETED: OVER WING EMEHG LTS 2Pu1129 0.60 2 OVER WING EMERG LTs 2PU1130 0.60 2 OVER WING EMERG LTS 2Pu1131 0.60 2 TOTAL DELETED 1.60' A ADDED: ROVR 1 61506127 (2Pu1142) CPLT MAIN 0.70 3 DME1 31503181 (21301142) OPLT MAIN 1.06 3 TOTAL ADDED 1.76 A REVISED TOTAL -o.02 A DEMAND DEMAND (AMPS) (AMP-MIN) meme: (Bet: Page 95.) 6.06 242.40 1 TOTAL DELETED 1.60 54.00 TOTAL ADDED 1.78 53.40 REVISED BATTERY LOAD 6.06 A 241.60 241.60 AVERAGE DEMAND 6.06 A 30 8.m A 181.35 VA (Bet: AVGIV-R-426.16, Page 149, Figure 5.) TIME TO 18.0V DC 44.67 MINUTES NOTES: 1.) This value re?ects shared exterior lamp loads between and aft emergency batteries. 2.) Production system rebussed to Aft Emergency Lights Battery, reference page 35. 3.) Production system rebussed to Aft Emergency Lights Battery, reference page 13. I-wvr - - - 4 .- .1 ..-. . . NOTES: 1.) This value re?ects shared lamp loads between and aft emergency lighting bane?es. 2.) This value reflects 25% max load due to ground operation only. 3.) Production system rebussed. reference page 32. 1 Report: Electrical WLECTRICAL LO ANALYSIS 5390: 34 Prep. By: Chris Tan EMERGENCY BATTERY ANALYSIS Report at: 60414696116 Date: 12-May-01 (1PU1129) (11:01 130) (1 PU1 131) (3PU1234) Model: G-IV FWD EMERGENCY LIGHTS BATTERY (Added Secu raplane 6.0 AMP-HOUR Battery) cg TITLE ca No. GB LOO. LOAD mg ADDED: EMERGENCY LIGHTS 2.75 AIRSTAIR LIGHTS 0.65 1.2 CABIN EMERGENCY Exrr SIGNS 0.36 1 VEST DOME-EMERGENCY 0.64 1 GALLEY DOME LIGHT 0.64 1 OVER WING EMERG LTs 11mm 0.60 3 OVER WING EMERG LTS 1PU1130 0.60 3 OVER WING EMERG LTS 1PU1131 0.60 3 TOTAL ADDED . . DEMAND DEMAND - (AMPS) - EXISTING: None 0.00 0.00 TOTAL DELETED 0.00 0.00 TOTAL ADDED . . 6.04 205.20 REVISED BATTERY LOAD 6.64 A 205.20 AMP-MIN 205.20 . AVERAGE DEMAND: a 6.64 A 30 . 6.64 A 22.5 163.60 VA TIME TO 18.0V DC a 52.63 MINUTES a- .0- . .. .. WW human-r1.- up. .. . . .1-.. I Report: ELECTR LOAD LYSIS 5090: 35 pm By: 0mm. EMERGENCY BATTERY ANALYSIS Heponm 39414000110 0510: 12-May-01 (200120) (200100) (2PU131) (4001204) 0100 (4901204) Model: G-IV AFT LIGHTS BATTERY (Added Securaplane 6.0 AMP-HOUR Battery) QJILLE. NO- LOC- LQAQ ADDED: CABIN EMERGENCY LIGHTS 2.75 1 AIRSTAIR LIGHTS 0.05 1.2 CABIN EMERGENCY EXIT SIGNS 0.30 I VESTIBULE DOME 0.04 I GALLEY DOME UGHT 0.04 1 OVER WING EMERG LTS 2001129 0.00 0 OVER WING EMERG LTS 2001100 0.00 3 OVER WING EMERG LTS . 2PU1181 0.00 3 Tom. ADDED . . . A DEMAND . DEMAND (AMPS) (AMP-MINI EXISTING: None 0.00 0.00 TOTAL DELETED 0.00 0.00 TOTAL ADDED 0.04 205.20 . REVISED BATTERY LOAD. 0.04 A AMP-MIN 205.20 AVERAGE DEMAND 0 0.04 A 00 0.04 A 22.5 a 150.00 VA TIME TO 18.0V D0 52.03 MINUTES 2.) value re?ects 25% max load due to ground operation only. 8.) Production system rebussed,r0lerenoe page 33. NOTES: 1.) This Value re?ects shared lamp loads between and all emergency lighting batteries. .a-neu. vs. .4- .. 3.) Load values transferred to page 44. 4.) This load is momentary use and not added to the total. 5.) Average load Is ?gured 1117095 ol the maximum load. Report: Electrical ELECTRICAL LOAD Page: 36 Prep. By: Chris Ten 28V DC AUX CONVERTER Report 0: (30414696118 Data: 12-May-01 SUMMARY ModelL00g LOAD NOTES ADDED: SWITCHED AUX DCIGND SVC FWD LAV TOILET 596082 CABIN 4.00 1.4 LAV TOILET 696082 CABIN 4.00 1,4 AFT LAV DOME LTS 698081 CABIN 1.92 1 CABIN DATA BUS 1 569081 CABIN 0.80 1 CABIN AISLE LTS 584082 CABIN 2.00 1 BAGG COMPT LTS 488081 CABIN 1.08 1 CABIN AUX Dc RH SPOT LTS 582081 CABIN 3.92 1.5 LH SPOT LTS 582082 CABIN 3.14 1.5 AFT LH SPOT LTS 582083 CABIN 2.35 1.5 ENT 28V DC 502081 CABIN 2.00 1 DIVAN MONITOR 5020B4 CABIN 1.50 1 BLKI-ID MONITOR 502089 CABIN 3.10 1 CREDENZA MONITOR 502087 CABIN 1.60 1 1 TOTAL ADDED 23.41 A 2 Exceeded output capacity by 0.00 A Reserve power available . . 19.45 A Percentage of capacity In use 0.55 Output power at 28V DC 655.48 AUX DC Converter ef?ciency rating 0.80 Converter maximum output load . . .4296 A Calculated load Input current at 115V AC 7.12 A Converter 'No-Iaad' operation current 0.35 A Calculated Input current . . 7.47 A Calculated input power at 115V AC . 859.60 VA Calculated input current per phase 2.49 A Input VA per phase 206.53 VA 3 NOTES: 1.) ?We load can be shed from the cockpit by switching to the position. 2.) Represents maximum load. not to exceed 42.0 Amps. Nauru-.m- . LOAD ANALYSIS $9 0: a7 Prep. By: 011119 Tan 115v A0 00 H2 CONVERTER 0: 004141390110 0414: 124491101 SUMMARY Model: 0-111 00 LE 00 N9, 00 Log. LOAD 519100 ADDED: CABIN CONVERTER 00 HZ - 00Nv OUTPUT (35A) (3500 VA) 493001 01400 COMPT 0.00 00 HZ 4 LH CABIN 493004 01100 OOMPT 172.00 1,5 00 H2 - RH CABIN 499005 01100 COMPT 172.00 1.5 00 HZ - FWD 1.41! 490000 0000 GOMPT 172.00 1.5 00 H2 - AFT LAV 499007 01400 COMPT 172.00 1,5 00 H2 - FAX 493000 0400 COMPT 172.00 1.5 00 HZ - MICROWAVE 490009 0400 GOMPT 1200.00 4,5 00 HZ - ENTERTAINMENT 4930010 01400 COMPT 172.00 1,5 00 H2 - RH GALLEY ANNEX 4990011 04100 COMPT 172.00 1.4.5 60 H2 - LH GALLEY 4900012 0400 COMPT 172.00 1.4.5 00 HZ 014004100 COMPT. RH 4990019 01400 001407 172.00 1.9 1? TOTAL LOAD WM 0095 INPUT LOADING . . . 3504.50 2 PER PHASE .. . . 1194.09 VA 2.3 NOTES: 1.) Calcuiated at 10% of maximum input load. 2.) Represents input load, at TOTAL LOAD shown 0.) Load values transferred to page 41.. 4.) This load can be shed from the cockpit by switching to the position. 5.) This ioad can be shed from the cockpit by switching to the position. .- "i LO 50?90; as Prep. By: Chris?l?an 110v Ac ESSENTIAL . nepon 0: 00414090110 0m: 12-May-01 COPILOT PHASE-B (X615) Model: G-IV on me gm CB Loo Moms DELETED: NONE. TOTAL DELETED . . 000' VA ADDED: ICE DET Ac 440002 CPLT Aux 200.00 TOTAL ADDED . . 200.90 VA 03001100: (Rat: mew-0420.10, Page 107.) (7.5 AMP FEEDER) ESSENTIAL Ac coptLOT PHASE-B 00515) 0.00 VA newssn TOTAL 200.00' VA None. 1 Report: Eiect?cal E51915 Mums Page: 39 Prep. Dr. Chris Tan 115V Ac Report 0: 69414096116 Data: 12?May?01 SUMMARY ModeI: . G-IV DEMAND (GR. UISEI PHASE-A: Page 131.) x010 PILOT None added. 136.60 x011 COPILOT None added. 573.32 REVISED TOTAL (PHASE A) . 709.92 VA PHASE-B: (Rot: AV-OIV-R-426.16, Page 132.) X612 PILOT None added. 0.00 x015 COPILOT (RevIeed page 30) 230.00 REVISED (PHASE 0) .. 200.00 VA (Rat: Page 133.) 10514 PILOT None added. 000 X613 COPILOT None added. 0.00 REVISED TOTAL (PHASE 0) . . 0.00 VA TOTAL REVISED ESSENTIAL Ac 903.92 VA 1 0123: None. 1 4. A- hI-?leuhk . .. ..- None. Eiect?cal WE OA LOAD ANALYSIS 339;: 40 Prep. By: mum 115V Ac MAIN Reporm 60414896118 Date: 12-May-01 PILOT (1 xwe) Model: e-w cg N9. ca LOO. LOAD ugTEs DELETED. NONE TOTAL DELETED 0:00 VA ADDED: NONE TOTAL ADDED . . 0.00 VA EXISTING: (net: Page 117.) (35 AMP FEEDER) LEFT MAIN AC PILOT (1X609) 0.00 VA REVISED TOTAL . 0.Ma?a. I Report: Electrical ELECTRICAL LOAD ANALVSIS nge: 41 Prep. By: cm; Tan 115v Ac MAIN Reportk 60414696116 Date: 12-May-01 ACCESS (1xx1o1) Model: G-IV 221111.: .140 N- on Loo LQLD me. ADDED: Access BUS (PHASE A) (1xx1o1) (35 AMP FEEDER) CABIN SWITCHED SOHZ CONVERTER 493081 CABIN 11 94.83 1 ,3 GALLEY SWITCHED OVEN 541CB1 GALLEY 1000.00 2 COFFEEMAKER 1 5430131 GALLEY 333.00 2 GALLEY WTR HTFI 548033 GALLEY 750.00 2 TOTAL ADDED (PHASE A) . . 3277.83 VA ADDED: ACCESS BUS (PHASE 3) (1)0110? (35 AMP FEEDER) CABIN SWITCHED 60HZ CONVERTER 4936131 CABIN 1194.83 1.3 CABIN SPEAKER AMP 501082 CABIN 345.00 1.4 GALLEY SWITCH ED OVEN 541 CB1 GALLEY 1000.00 2 COFFEEMAKER 1 543031 GALLEY 333.00 2 1" . TOTAL ADDED (PHASE B) . 2872.83 VA . ADDED: ACCESS BUS (PHASE o) (1 x111 D1) (35 AMP FEEDER) CABIN SWITCHED 601-12 CONVERTER 493081 CABIN 1194.83 1,3 RH FLOOR HTRS 649081 CABIN 264.00 1 LH FLOOR HTRS 6490132 CABIN 220.00 1 CREW HOT LIQUID 6460B2 CABIN 120.00 1 GALLEY OVEN 541081 GALLEY 1000.00 2 COFFEEMAKER 1 543031 GALLEY 333.00 2 TOTAL ADDED (PHASE C) . 3131.83 VA NOTES: 1.) This load can be shed from the cockpit by switching the MAST to the position. 2.) This bed can be shed from the cockpit by switching the GALLEY to the position. 3.) For 60 H2 Converter ioads, reference page 37. 4.) Normal'load is 345 VA, 1150 VA maximum. 4.1. Roma: Electrleal ELECTRICAL LO VSIS Page; 42 IPrep. By: ChrisTan LEFT MAIN AC Repart (30414696116 Date: 12-May-01 SUMMARY Model: G-IV DEMAND LE (CRUISE) PHASE A: (Ref: Page 134.) 1X560 CHARGER None added. 464.20 1X605 PILOT None added. 271.50 1X606 COPILOT None added. 2129.00 01 ACCESS (Revised page 41) 3277.83 TOTAL ADDED (PHASE A) . . 6142.53 VA PHASE 3: (Ref: AV-GIV-R-426.16, Page 135.) 1X561 BATT CHARGER None added. 464. 20 PILOT None added. 0.00 1X608 COPILOT None added. 1877. 00 1xx1o1 ACCESS (Revised page 41) 2872. 83 TOTAL ADDED (PHASE B) ..- 5214.03 VA PHASE 0: (Ref: IV-R-426.16. Page 136.) l{ 4 ?(562 CHARGER None added. 464.20 1X609 PILOT None added. 0.00 ?(620 COPILOT None added. 147.00 1XX101 ACCESS (Revised page 41) 3131.83 TOTAL ADDED (PHASE C) 3743.03 VA TOTAL REVISED LEFT MAIN AC 15099.60 VA ores: None. -. 315 5:13.: 43 . 115v Ac RIGHT MAIN Report 0: 60414696116 Data: 12-May-01 COPILOT PHASE-A (2X602) Model: . G-IV cg 1111.5 ca ?at. ca 1.00. LOAD DELETED: NONE TOTAL . 0.00 VA ADDED: SATCOM PHI 103031 OPLT AUX 621.00 1 SATGOM FAN 103032 OPLT AUX 100.00 TOTAL ADDED . . 001.00 30511119: (F101: Page 124.) (35 AMP FEEDER) RIGHT MAIN AC COPILOT (2x002) 487.00 VA REVISED TOTAL 1288.00 VA 1.) Normal load Is 621 VA, 800 VA maximum. . 5.4-0-1- Report: ELECTRICAL ANALYSIS Fags: 44 Prep. By: Chris Tan 115V AC RIGHT MAIN Report G0414696116 Date: 12-May-01 ACCESS 2XX101 Model: G-IV 93 my; cg ca Loo. LQAQ NOTES ADDED: ACCESS BUS (PHASE A) (2)0001) (35 AMP FEEDER) AUX DC CONVERTER 394035 CABIN 286.53 1 GALLEY SWITCHED AIR COMPRESSOR 548034 GALLEY 62.00 2 COFFEE MAKER 2 543032 GALLEY 333.00 2 FWD DRAIN HTRS 549032 GALLEY 870.00 2 AFT DRAIN HTRS 549033 GALLEY 975.00 2 TOTAL ADDED (PHASE A) . 2526.53 VA ADDED: Access 303 (PHASE 3) (2)0(101) (35 AMP FEEDER) AUXDC CONVERTER 394035 CABIN 286.53 1 GALLEY SWITCHED AIR COMPRESSOR 548034 GALLEY 62.00 2 COFFEE MAKER 2 543032 GALLEY 333.00 2 GALLEY 400HZ OUTLETS 546031 GALLEY 862.00 2.3 FWD LAV WATER HTR 548032 GALLEY 840.00 2 TOTAL ADDED (PHASE B) . 2383.53 VA ADDED: Access BUS (PHASEG) (23m 01) (35 AMP FEEDER) AUX D0 CONVERTER 394035 CABIN 286.53 1 GALLEY AIR COMPRESSOR 546034 GALLEY 62.00 2 COFFEE MAKER 2 543032 GALLEY - 333.00 2 ANNEX 400HZ OUTLETS 546032 GALLEY 862.00 2.3 THERMAL COOLING UNIT 746031 GALLEY 460.00 2.4 TOTAL ADDED (PHASE 0) . 2003.53 VA NOTES: 1.) For AUX DO CONVERTER loads, reference page 36. 2.) This load can be shed from the cockpit by seiecting the to the position. 3.) Average load Is ?gured at 50% of maximum load. 4.) Normal load is 460VA, 575VA Maximum - up ?nn.m? pu?ld?-DWAJ awn?um? 1 Report: Electrical ANALHYSISL Bags: 45 Prep. By: ends Tan RIGHT MAIN Ac . Report II: 60414698116 Data: 12-May-01 SUMMARY Modal: G-IV II. DEMAND PHASE A: EEDER (Rat: Av-er-R-426.10, Page 137.) 2xsso BATT CHARGER None added. 464.20 mm PILOT None added. 120.00 2mm COPILOT (Revised page 43) 1288.00 21mm ACCESS (Added page 44) 2520.53 REVISED TOTAL (PHASE A) . 4300??.73 VA PHASE 8: (Rat: Page 138.) 2X561 BATT CHARGER None added. 434.20 2X624 PILOT None added. 0.00 210500 COPILOT None added. 2267.00 ?01101 ACCESS (Added page 44) . 2383.53 REVISED erI. (PHASE 3) . VA PHASE 0: (Bet: Page 139.) 2X562 CHARGER None added. 464.20 PILOT None added. 414.00 2X604 COPILOT None added. 2344.00 M101 ACCESS (Added page 44) 2003.53 REVISED TOTAL (PHASE 0) 5225.73 VA REVISED RIGHT MAIN AC TOTAL . .. 14739.20 VA 31158: None. a. Gui-Du. wmumt.m-4 i Report. E?Iectricel . 0' 3599; 46 IPre Prep. By: chrte Tan AIRCRAFT Ac Report i: 60414896110 I Date: 12-May-01 SUMMARY Model: LEFT MAIN AND ESSENTIAL Ac LOAD Capacity" .. 23,000.00 Demand (ESSENTIAL ?(Revised page 09) 200.00 Demand MAIN AO) (Revised page 42) 15,099.00 Resetve . . 7,620.40 VA RIGHT MAIN Ac LOAD Capacity 23,000.00 Demand (Revised page 45) 14,739.20 Reserve 8,260.00 . VA Ac LOAD GRAND TOTAL Total AC Capacity . 40,000.00 Total Demand 30 118.80 Reserve . . 15,801.20 VA . (Ref: Page 1 and 140.) . 1.) Existing ESSENTIAL AC toads are induded in the LEFT MAIN AC total. - .u FAA FORM 8130-6. APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Form Approved OMB. No. 2120-0018 Expiration Date09/30/2017 '3 APPLICATION FOR gamma; u.S. AIRWORTHINESS Federamvianon CERTIFICATE Administration INSTRUCTIONS - Prim or type. Do not write in shaded areas; these are for FAA use only. Submit original only to an authorized FAA Representative. It additional space is required. use attachment. For special flight permits complete Sections II. VI. and VII as applicable. 1. REGISTRATION MARK N51 PR 2. AIRCRAFT NAME (Make) AEROSPACE a. AIRCRAFT MODEL DESIGNATION 4. YR. MFR. FAA CODING G-IV 2000 5. AIRCRAFT SERIAL N0. 1425 6. ENGINE NAME (Make) ROLLS ROYCE 7. ENGINE MODEL DESIGNATION TAY MARK 611-8 I. AI RC RAFT DESCRIPTION 8. NUMBER OF ENGINES 2 9. PROPELLER NAME (Make) 10. PROPELLER MODEL DESIGNATION 11. AIRCRAFT IS (Chockifappiicabla) I IMPORT APPLICATION IS HEREBY MADE FOR: (Check applicable items) A 1 STANDARD AIRWORTHINESS CERTIFICATE (Indicate category} I I NORMAL I IUTILITY I IACROBATK: I ITRANSPORT I ICOMMUTER I IBALLOON I IOIHER SPECIAL AIRWORTHINESS CERTIFICATE (Check appropriate Items) PRIMARY LIGHT-SPORT (Indicate Class) I IAirpiane I IPower-ParachuteI IWeight?Shitt-Control I IGlider I ILighterthan Air LIMITED 5 PROVISIONAL (Indicate class) CLASS I CLASS to be conducted) 3 RESTRICTED (Indicate operation(s) AGRICULTURE AND PEST CONTROL 2 AERIAL SURVEY 3 AERIAL ADVERTISING FOREST (Wild?fe conservation) 5 PATROLLING 6 WEATHER CONTROL OTHER (Specity) to be conducted) ll. CERTIFICATION REQUESTED I 4 EXPERIMENTAL (Indicateoperation(s) RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION AIR RACING 5 CREW TRAINING 6 MARKET SURVEY Olh-?O-h?lM-e TO SHOW COMPLIANCE WITH THE CFR 7 OPERATING (PrimaIy Category) KIT BUILT AIRCRAFT OPERATING LIGHT-SPORT 8A Existing aircraft without an airworthiness certificate do not meet 103.1 813 Operating Light-Sport lat-built BC Operating light-sport previously issued special light-sport category airworthiness certi?cate under 21.190 UNMANNED AIRCRAFT 9A RESEARCHANDDEVELOPMENT IQCI ICREWTRAINING 98 MARKET SURVEY 8 operation to be conducted. then complete Section VI or VII as applicable on reverse side) 1 FERRY FLIGHT FOR REPAIRS. ALTERATIONS. MAINTENANCE. OR STORAGE SPECIAL FLIGHT PERMIT (Indisate 2 EVACUATE FROM AREA OF IMPENDING DANGER OPERATION IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT DELIVERING OR EXPORTING I 5 I PRODUCTION FLIGHT TESTING 6 CUSTOMER DEMONSTRATION FLIGHTS CI 6 MULTIPLE AIRWORTHINESS CERTIFICATE (Check ABOVE 'Restricted Operation? and 'Standam? or 'Umired' as applicable) A. REGISTERED OWNER (As shown on certificate of aircraft registration) IF DEALER, CHECK HERE I WAC-1425 LLC ADDRESS3420 8. OCEAN BLVD #10 HIGHLAND BEACH, FL 33487 B. AIRCRAFT CERTIFICATION BASIS (Chair applicable blocks and items as indicated) Revision No.) 1 2 A EV 22 AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET (Give NO. and AIRWORTHINESS DIRECTIVES (Check It all applicable ADS are complied with and give the number of the last AD SUP PLEMENTevaI?ieble' In the biweekly series as of the date of application) 06/1 #201 8 AIRCRAFT LISTING (Give page number(5)) SUPPLEMENTAL TYPE CERTIFICATE (List number bleach STC incorporated) .0 AIRCRAFT OPERATION AND MAINTENANCE RECORDS 14 CFR section 91.417 CHECK IF RECORDS IN TOTAL AIRFRAME HOURS COMPLIANCE WITH 4455.6 EXPERIMENTAL ONLY (Enter hours flown since Iast certI'fICaIe issued 3 orrenewed) 0 0 CERTIFICATION airworthiness certificate requested. 0. CERTIFICATION - I hereby certify that I am the registered owner (or his agent) of the aircralt described above. that the aircraft IS registered with the Federal Aviati Administration in accordance with This 49 ot the United States Code 44101 and applicable Federal Aviation Regulations. and that the alrcratt has been insperyy :5 8.1% and eligible tor the DATE OF APPLICATION NAME AND TITLE (Printartype) 11JUNE2018 ED SPIRKO, AGENT 5' A. THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND BY: (Complete 1er sectirm on (14' CFRpart21 I 2 Certificate No.) 14 CFR part 121 CERTIFICATE HOLDER (Give I a I I CERTIFICATED MECHANIC (om Certificate No.) I I WTMCATED REPAIR STATION (Give Certi?cate 5 AGENCY AIRCRAFT MANUFACTURER (Give name or?rrn) IV. INSPECTION VERIFICATION DATE TITLE SIGNATURE (Check ALL applicable block items A and B) THE CERTIFICATE REQUESTED A- ?nd that the aircraft described in Section I or VII meets requirements for 4 AMENDMENT OFI MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE B. Inspection tor a special ?ight permit under VII was conducted by: FAA INSPECTOR FAA DESIGNEE CERTIFICATE HOLDER UNDER 14CF I I I14CFRpart145 V. FAA REPRESENTATIVE CERTIFICATION 4 DATE EAA INSPECTOR OFFICE SIGNATURE AND NO. or 90?: ER 36 SIGNATURE 1 FAA CERTIFICATION FILE REVIEW I FAA Form 8130-6 (04-201 1) All Previous Editions Supersedea/ (- . /EIe?ronIc -PDF 0 Page 1 012 OO peldBOOV VI. PRODUCTION FLIGHT TESTING A. MANUFACTURER NAME ADDRESS B. PRODUCTION BASIS (Check applicable Item) PFIOD UCTION CERTIFICATE (Give production certi?cate number) TYPE CERTIFICATE OTHER: C. GIVE QUANTITY OF REQUIRED FOR OPERATING NEEDS DATE OF APPLICATION NAME AND TITLE (Print or type) SIGNATURE VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT TEST A. DESCRIPTION OF AIRCRAFT REGISTERED OWNER ADDRESS BUILDER (Make) MODEL SERIAL NUMBER REGISTRATION MARK B. DESCRIPTION OF FLIGHT CUSTOMER DEMONSTRATION FLIGHTS El (Check ifepplr?cabie) FROM TO VIA DEPARTURE DATE DURATION C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EQUIPMENT PILOT 1 CO-PILOT FLIGHTENGINEER D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS: E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION: (Use attachment 1109695580!) F. CE HTIFICATION - I hereby certify that I am the registered owner (or his agent) at the aircraft described above; that the aircraft is registered with the Federal Aviation Administration in accordance with We 49 of the United States Code 441 or mg. and applicable Federal Aviation Regulations; and that the aircraft has been inspected and is safe for the ?ight described. DATE NAME AND TITLE (Print or type) SIGNATURE A. Operating Limitations and Markings in Compliance With 14 CF Ft Section 91.9, G. Statement of Conformity. FAA Form 8130-9 (Attach when required) AS Appaicanie H. Foreign Airworthiness Certi?cation for Import Aircraft 8. Current Operating Limitations Attached (Attach when required) 3 A . I. rth' I5 0. Data. Drawings, Photographs. etc. (Attach when required) PreVIous AIrwo Iness em cate ssued In Accordance With If 14 CFFI Section 2 I, [3301. 1 CAR (Originaiaitached) 5 0. Current Weight and Balance information Available in Aircraft 5' Major Repair and Alteration FAA 337 (Att [7 'ed) . J. Current Airworthiness Certi?cate Issued in Accordance With . . orm ac an requrr 14 CPR Section 9, I. ICI I [ck-X (Copyattached) This inspection Recorded Aircraft Records K. Light-Sport Aircraft Statement of Compliance. FAA Form 8130-15 (Attach when required) FAA Form 8130?6 (04-2011) All Previous Editions Superseded Etectronic Format - PDF Page 2 of 2 UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION - FEDERAL AVIATION ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE A EXPERIMENTAL RESEARCH AND DEVELOPMENT MANU- NAME WA A A FACTURER ADDRESS [fo??L?Cx?V/ FLIGHT FROM TO N- SIPR SERIAL NO. 1425 AEROSPACE MODEL GIV DATE OF ISSUANCE 24 JUN 2018 EXPIRY 24 JUN 2019 LIMITATIONS DATEDL 24 W913 ARE PART OF THIS CERTIFICATE (SIGNATURE FAA REPRESENTATIVE DESIGNATION OR OFFICE NO. 05:75 DART-200064EA Any an? reproduotI6n or/f?isuse 0W certi?cate may be punishable by a ?ne not exceeding $1,000 or impriso ent not exceeding 3 years, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE TITLE 14. CODE OF FEDERAL REGULATIONS (CFR). FAA Form 8130-7 (0412011) Previous Edition 07/04 May be Used until Depleted SEE REVERSE SIDE 0052-00-693-4000 This airworthiness certi?cate is issued under the authority of Public Law 104-6, 49 United States Code . (USC) 44704 and Title 14 Code of Federal Regulations (CFR). The airworthiness certi?cate authorizes the manufacturer named on the reverse side to conduct production ?ght tests. and only production ?ight tests, of aircraft registered in his name. No person may conduct production ?ight tests under this certi?cate: (1) Carrying persons or property for compensation or hire: and/or (2) Carrying persons not essential to the purpose of the ?ight. This airworthiness certificate authorizes the ?ight speci?ed on the reverse side for the purpose shown in Block A. This ainlvorthiness certi?cate certi?es that as of the date of issuance, the aircraft to which issued has been inspected and found to meet the requirements of the applicable CFR. The aircraft does not meet the requirements of the applicable comprehensive and detailed ainlvorthiness code as provided by Annex 8 to the Convention On International Civil Aviation. No person may operate the aircraft described on the reverse side: (1) except in accordance with the appiicable CFR and in accordance with conditions and limitations which may be prescribed by the FAA as part of this certi?cate; (2) over any foreign country without the special permission of that country. Unless sooner surrendered, suspended, or revoked, this certi?cate is effective for the duration and under the conditions prescribed in 14 CFR, Part 21, Section 21.181 or 21.217. Received by: Greensboro FSDO, EA39 JUL 02 2018 Cy U.S. Department of Transportation Greensboro, NC 27409 Federal Aviation Administration 1301 Terminal Service Road Operating Limitations for N51PR Aerospace G-IV 1425 Issued 24 Jun 2018 FAA Order 8130.2] Appendix 1) This aircraft does not meet the airworthiness standards of Annex 8 to the Convention on International Civil Aviation. Operations in airspace outside of the United States will require the permission of the applicable foreign authority. That permission must be carried aboard the aircraft together with this U.S. airworthiness certificate and, upon request, be made available to an FAA inspector or the applicable foreign authority in the country of operation. Operations may be further restricted by the applicable foreign authority. This may include not allowing use of an airport. requiring specific routing, and restricting ?ight over specific areas. The operator must comply with any additional limitation prescribed by the applicable foreign authority when operating in its airspace. (1) 2) These operating limitations do not provide any relief from any applicable law or regulation. This aircraft must be operated per applicable regulations and the additional limitations prescribed herein. Note that a clearance from air traf?c control (ATC) is not authorization for a pilot to deviate from any rule, regulation, operating limitation. or minimum altitude. or to conduct unsafe operation of the aircraft. If ATC issues a clearance that would cause a pilot to deviate from a rule, regulation, or operating limitation, or in the pilot's opinion. would place the aircraft in jeopardy, it is the pilot's responsibility to request an amended clearance. These operating limitations are a part of FAA Form 8130-7 and are to be carried in the aircraft at all times and to be available to the pilot in command of the aircraft. (2) 1 Page 3) This special airworthiness certificate is not in effect during public aircraft operations (PAO). Concurrent public/civil operations are not permitted; the aircraft cannot be operated as a civil aircraft and as a public aircraft at the same time. No weapons or special military mission systems may be added to the aircraft. This airworthiness certi?cate is not in effect during flights related to providing military services (that is, air combat maneuvering, air-to-air gunnery, target towing, electronic countermeasures simulation, cruise missile simulation, and air refueling). These activities are inherently military, not civil activities. The FAA makes the distinction between the authorized ?ights for experimental purposes. and FAQ. Before operating this aircraft under this special airworthiness certi?cate following a FAQ, the aircraft must be returned to the condition and configuration at the time of inspection for the issuance of this airworthiness certi?cate. The operator must have written procedures for returning the aircraft to the civil con?guration. This action must be documented in the maintenance records. The maintenance records and entries must clearly differentiate between a civil experimental flight per this certificate and any other flights. (3) 4) Application to amend this certificate must be made to the local Flight Standards District Office (FSDO) or Manufacturing Inspection District Office (MIDO). (4) 5) Not Applicable 6) Not Applicable 7) Not Applicable 8) The pilot in command must hold? An appropriate type rating (if one has been established); or An experimental aircraft authorization, by make and model. on their pilot certificate; or A temporary letter of authorization (LOA) issued by an FAA Flight Standards Operations Inspector. (8) 9) Not Applicable 10) Additional required members must hold the appropriate airman certi?cate. (10) 11) When filing a flight plan. the experimental nature of this aircraft must be listed in the remarks section. (11) 12) Not Applicable 13) This aircraft must not be used for towing, including. but not limited to glider towing, banner towing. target towing. or towing electronic receivers or emitters. This aircraft must not be used for intentional parachutejumping. (13) 2 Page 14) If aircraft, engine, or propeller operating limitations are exceeded outside of planned test conditions, an appropriate entry will be made in the maintenance records. (14) 15) No person may operate this aircraft unless it is maintained per an inspection program meeting the scope and content described in The operator must select and identify in the aircraft maintenance records one of the following programs for the inspection of the aircraft: For type-certificated aircraft. a current inspection program recommended by the manufacturer: or For former-military aircraft, an inspection program recommended by the manufacturer or North Atlantic Treaty Organization (NATO) military service; or An FAA-approved inspection program. Note: To extend an inspection interval, the owner/operator must submit a request for that extension with supporting documentation and data to the local F500 and obtain concurrence from that FSDO. Inspections must be recorded in the aircraft maintenance records showing the following, or a similarly worded, statement: certify that this aircraft has been inspected on [insert date] per [identify applicable inspection program] and found to be in a condition for safe operation." (15) 16) Not Applicable 17) Not Applicable 18) Not Applicable 19) Only FAA-certi?cated repair stations. FAA-certificated mechanics with appropriate ratings, or a manufacturer as authorized by 43.3 may perform inspections required by these operating limitations. (19) 20) The aircraft may not be operated unless the replacement for life-limited articles specified in the applicable technical publications pertaining to the aircraft and its articles are complied with in one of the following manners: Type-Certificated Products: Replacement of life?limited parts required by 91.409(e) applies to experimental aircraft when the required replacement times are specified in the US. aircraft specifications or type certificate data sheets. Non-Type- Certificated Products: All articles installed in non?type-certificated products operated under an ain~orthiness certificate issued for an experimental purpose. in which the manufacturer has specified limits. must include in their program an equivalent level of safety for those articles. These limits must be evaluated for their current operating environment and addressed in the approved inspection program. All articles installed in non-type-certi?cated products in which the manufacturer has speci?ed limits, must include in their program an equivalent level of safety for those articles. The article must be inspected to ensure the equivalent level of safety still renders the product in a serviceable condition for safe operation. (20) 21) For aircraft originally incorporating fatigue life recording systems, the owner/operator must maintain and use the system as prescribed by the aircraft manufacturer and comply with the manufacturer's fatigue life limits. (21) 3 Page 22) Not Applicable 23) Not Applicable 24) Not Applicable 25) Not Applicable 26) When changing between experimental operating purposes, the operator must determine that the aircraft is in a condition for safe operation and appropriate for the purpose intended. A record entry will be made by an appropriately rated person to document that finding in the maintenance records. (26) 27) Not Applicable 28) Not Applicable 29) Not Applicable 30) Not Applicable 31) Not Applicable 32) Not Applicable 33) Not Applicable 34) Not Applicable 35) Not Applicable 36) Not Applicable 37) Not Applicable 38) Not Applicable 39) Not Applicable 40) Enhanced Flight Vision System (EFVS) operations for the purpose of research and development and/or showing compliance with regulations are not authorized if any component associated with the instrument approach procedure being flown. or any component of the approach lighting system associated with the instrument approach, is inoperative. (40) 4 Page 41) Not applicable 42) Not Applicable 43) Not Applicable 44) Not Applicable 45) Not Applicable 46) Not Applicable 47) Kinds of operations authorized: Day VFR flight operations are authorized. (47) 48) Night flight operations are authorized if the instruments specified in 91.205(c) are installed. operational. and maintained per the applicable requirements of part 91. (48) 49) Instrument flight operations are authorized if the instruments speci?ed in 91.205(d) are installed. operational, compliant with the performance requirements of, and maintained per the applicable regulations. All maintenance or inspection of this equipment must be recorded in the aircraft maintenance records and include the following items: date, work performed, and name and certificate number of person returning aircraft to service. (49) 50) Instrument flight operations are authorized if the instruments specified in 91.205(d) are installed, operational, compliant with the performance requirements of, and maintained per the applicable regulations. The pilot in command must have a method to comply with the 91.319(c) prohibition from operating over densely populated areas or in congested airways. All maintenance or inspection of this equipment must be recorded in the aircraft maintenance records and include the following items: date, work performed, and name and certificate number of person returning aircraft to service. (50) 51) Not Applicable 52) Not Applicable 5 Page 53) All flights must be conducted within the geographical area described as follows. 1100 Nautical mile radius from Greenville, South Carolina (KGYH). Flights for maintenance. as de?ned in 1.1, of the aircraft are permitted outside the defined area. (53) 54) Not Applicable 55) Flight over a densely populated area or in a congested airway is authorized per 91.319(c) only for the purpose of takeoff and landing. The area on the surface described by the term "only for the purpose of takeoff and landing" is the traffic pattern. For the purpose of this limitation, the term "only for the purpose of takeoff and landing" does not allow multiple traffic patterns for operations such as training or maintenance checks. This does not restrict a go around/ rejected landing for safety reasons. When avoiding populated areas, aircraft speed and weight must be considered. The information in FAA Order 8900.1. Flight Standards Information Management System (FSIMS). regarding set-back distances from spectator areas for aviation events such as air shows or air races may assist in determining a suitable space to fly the aircraft. (55) 56) Not Applicable 57) Operations in RVSM-designated airspace may be allowed under 91.180(b) for climbing/descending through RVSM flight levels without intermediate level-off to or from ?ight levels above RVSM airspace. Refer to part 91 and the Aeronautical Information Manual. (57) 58) Not Applicable 59) Not Applicable 60) Not Applicable 61) No person may be carried in this aircraft during flight unless that person is essential to the purpose of the ?ight. (61) (2 2/1 Jerry Hugpps/ DART 200064EA 6 Page 71" SPECHAL T0 WHQM i7" MAY (CONCERN: ii eeuify ihui i have read and understand the Limitations which are a part (if the Airworthiness Ce?ii?ieu?ie PM Form 8130= 7 issued .5 22:1 25:3 This Aimei?ihiuess is issued for make MSW aim/93p 9 Model Gift/'8? 9 Serial Number /280 9 and Number IU 51/9,: 2?2- Jmu? 201? DATE DATE: 6-23 -2018 TT: 4455.6 N51 PR SIN 1425 I certify I have inspected this air a for the certi?cate requested and issued a orthiness Ce' (FAA For 8130-7) this Jerry ghes 0 DAR 2000 -EA DAR-T GEOGRAPHIC EXPANSION REQUEST Date of Expansion Rguest: 6-11-2018 mom DAR-T Name: Jeny Hughes DAR-T Designation Number: DART-200064EA DAR-T Core Certi?cate Number: IA-1822184 DAR-T Telephone Number: 336-312?1 1 12 Proposed Activity Location Information: Name of Facility: Stevens Aviation Facility Address: 600 Delaware Street, Greenville, SC 29605 Facility Telephone Number: 864?678-6257 Facility POC for FAA Oversight: Columbia SC FSDO (803-822-1064) Proposed Activity Details: Proposed Start Date: 6?15-2018 and 7-15-2018 Estimated time required to complete activity: 30 Days function(s) requested to be authorized: Inspection for Special Airworthiness Certi?cate (Function Code -28) A detailed description of the activity requested. If it involves multiple activities, this must be explained: Inspection of NSIPR 1425 for the purpose of possible issuance of Special Airworthiness Certi?cate in Research and development Certi?cation Aetivi A licant Information Not the DAR- Name of Applicant: Ed Spirko (601-397-0829) Applicant Address: 3420 Ocean ION Highland Beach FL 33487 \lk Date: BY ELECTRONIC MAIL Attn: Mr. Jerry Hughes, DAR-F Experimental Research and Development Program Letter N51 1425 1) Project Description: a. N51PR is being used to determine compatibitity and operational functionality of the following systems: i. Tracer Radar ii. Hdi EOIIR Camera Viasat Sat-com b. STC Program Number ST00464MC-T has been initiated with the FAA MCO. This experimental ?ight test program will be accomplished in accordance with Aery document SYSTEM FLIGHT TEST rev IR or latest revision; and TEST PLANIREPORT, rev IR or latest revision. 2) Number of aircraft required: 3. N51 PR is the only aircraft required for this project. 3) Duration: a. A 1 year Experimental RD certi?cate is requested. 4) Number of ?ights and or hours: 3. Estimate of 1200 hours b. Estimate of 100 ?ights 0. Estimate does not include positioning time to and from flight test location. Cont. on next page 44174 Airport Rd, Suite 300, California. MD 20619 m?yairtec.com 301-373-2101 Telephone 301-373-2154 Facsimile . - g" a Ear ?l 5) Area of operations and airports required: 3. Aircraft base for initial Experimental RD ?ight tests will be KGYH Greenville, SC. b. Geographic area of Experimental RD ?ight test to check compatibility and operational functionality is described as having a Western boundary of Wichita, Kansas to allow for RVSM altitude monitoring; a Southern Boundary of ZODNM south of Key West, Florida to allow for aerial mapping and of uninhabited atolls; a Eastern boundary of ZOONM off of the Atlantic coastline to allow for aerial mapping of the waters off of the coast; and a Northern boundary of Maryland to allow for repositioning and routine maintenance at our Caiifornia, Maryland facility. c. Reference illustration showing Geographic Areas of Operation; to be identi?ed by user waypoints. 6) Person to contact during Experimental RD Flight Test period: 3. Steve Walton. swalton@aemaviation.com. +1-757-709-0077 Sincerely, Ed Spirko 44174 Airport Rd. Suite 300, California. MD 20619 301-373-2101 Telephone 301-373-2154 Facsimile US. DEPARTMENT OF TRANSPORTATION can APPROVED OMB No. 21mm EXP DATE: 113112021 APPLICATION FOR TYPE CERTIFICATE, PRODUCTION CERTIFICATE, OR SUPPLEMENTAL TYPE CERTIFICATE LNameomwlieam 3. AIRTEC. INC. mm . Waterman Amen I Wartime: Type Carti?caleD med Type mm? Em Amended Supplemental Type Certi?cate ?Wen? 4. Address City State 0. Code 44174 AIRPORT RD, SUITE 300 California MD. 20619 . 5. TYPE CERTIFICATE (Complete item 53 below) a. Wmm, and 8. PRODUCTION CERTIFICATE (Ownplete items Sa-c below. Submit with this icon, in manual form, one copy of quality control data or Merges literate cam-lg new pmducfs. as remitted by applicable FAR. a Fem address (if different above) b. Applicatim is for RC. No. New production certifu?ate Additions to production Certi?cate {Give P. c. No.) No. c. Applicant isholderofora ?cemeewderaTypaCe?i?wte ore Smplememal Type CerJti??mte (Attach evidence of?oensing agreement and give certi?cate number) 7. SUPPLEHENTAL TYPE cermacme (Complete items 734mm Single STC a. Make and model designation of product to be modi?ed b. Desaiptim 0f mdi?ca?m Installation of special mission equipment into Serial Number 1425. Refer to document number1749?ED-1000 Project certi?cation plan submitted with this application for complete description of modi?cation. Will data be available for sale or release to other persons? at Will parts he menuiaclured for sale? (Ref. FAR 21.303} Yes No Yes N0 8. CERTIFICATION - I certify that the above statements aratrue. Title Date ?g/??ff/Ila/X FAA Form SI IO-IZ 4) SUPERSEDES PREVIOUS EDITION DEPARTMENT OF THE NAVY NAVAL AIR svsraas comma mm A HOFFEIT BUILDING 47123 BUSE ROAD. awe 2272 RIVER. mama 2011704547 ?mama 13000 Ser 05 March 2018 MEMORANDUM FOR: U.S Department of Transportation Federal Aviation Administration Attention: Derek Morgan Manager, Military Certi?cation Of?ce (ACE-100M) 8200 East 34';h Street Building 1000, Suite 1005 Wichita, Kansas 67226 From: Director, Naval Air Systems Command, Airworthiness Of?ce, (AIR 4. Building 460, Room 227, 22244 Cedar Point Road, Patuxent River, Maryland 20670-1163 To: Mr. Morgan Subj: SPONSORSHIP NOTIFICATION FOR FAA MCO SUPPORT FOR THE UNITED STATES NAVY GIVSP WITH TRACER RADAR, VSTAR A KIT, 15? WESCAM FLIR and VIASAT- 1. In accordance with the current Interagency Federal Reimbursable Agreement between the Federal Aviation Administration (FAA) and the United States Armed Forces for support of military commercial derivative aircraft signed Dec 28, 2017, the United States Navy (USN) requests the FAA Military Certi?cation Of?ce (MCO) provide certi?cation services for the changes planned for the GIVSP aircraft, serial number 1425 (N5 The requested services include supplemental type design change certi?cate services for this aircraft as de?ned below: Tracer Radar outer mold line modifications Tracer Radar interior modi?cations (including workstations, equipment racks, etc.) Viasat outer mold line modi?cations ?1th interior modi?cations VStar' A Kit( 13 external antenrms) ARC-182 Radio pilots Station PRC 117 Radio workstation 15? Wescam FLIR outer mold line modi?cations Wescam LIR interior modi?cations (including workstations, equipment racks, etc.) Auxiliary electrical power solution use the existing aircraft Auxiliary Power Unit (APU) Ventral Snakes outer mold line modi?cations Tracer Steering interface Cg mm mm Ach: 4455.6 Date: 6/24/2018 HM: 4455.6 3 SIN: 1425 Am: 1743 Mode!: APU: 4749.0 AIRFRAME INSPECTIONS APRIL 2018 6.2) Complied with 12-rnonths CMP Task Code 23 7004 Cockpit Voice Recorder Operational Check. 6.3) Complied with 24-months CMP Task Code 240108 Standby Hydraulic Generator System Test. 6.4) Complied with 24-months CMP Task Code 240129 External Battery Switch on Warning Operational Test. 6.5) Complied with 12-months CMP Task Code 241060 Emergency Lighting Power System Operational Test. 6.6) Complied with 12-months CMP Task Code 240250 Emergency Securaplane No. 1 (Self-Test) Operational Test. 6.7) Complied with 12-months CMP Task Code 240251 Emergency Securaplane No. 2 (Self-Test) Operational Test. 6.8) Complied with 48-months CMP Task Code 240266 Emergency Securaplane Battery Heater No. 2 - Discard. 6.9) Complied with 500-hourS/12-months CMP Task Code 250063 Protective Breathing Equipment PBE #1 Detail Inspection. CMP 250060 No. 1 BPE E28180-20-0001 SIN BEF3-0324. 6.10) Complied with 12-months CMP Task Code 251036 F1ash1ight(s) Operational Test. 6.11) Complied with 24-months CMP Task Code 251118 Crew Seat Restraint Detail Inspection. 6.12) Complied with 24?months CMP Task Code 251125 Crew Seat Inertia Reels Operational Test. 6.13) Complied with 24-months CMP Task Code 252556 Passenger Seat Inertia Reels - Operational Test. 6.14) Complied with 24-months CMP Task Code 252557 Passenger Seat Restraints - Detailed Inspection. 6.15) Complied with 12-months CMP Task Code 256101 ELT Operational Test. (FAR 91.207) 6.16) Complied with 24-rnonths CMP Task Code 256204 Life Vest(s) Restore. Crew CMP: 256240, 256241, 256242. Pax CMP: 256211, 256212, 256213, 256214, 256215, 256216, 256217, 256218, 256219, 256220, 256221, 256222, 256223, 256224 6.17) Complied with 36-months CMP Task Code 256261 Life Raft #1 Restore. 6.18) Complied with 36-months CMP Task Code 256262 Life Ra? #2 4 Restore. 6.19) Complied with 12-months CMP Task Code 256312 First Aid Kit Detail Inspection. 6.20) Complied with 12-months CMP Task Code 256313 First Air Kit Discard. 6.21) Complied with 24?months CMP Task Code 262153 Fire Pull Handle (Fuel Hydraulic Shutoff) Le? Operational Test. 6.22) Complied with 24-months CMP Task Code 262154 Fire Pull Handle (Fuel I Hydraulic Shutoff) Right - Operational Test. 6.23) Complied with 12-months CMP Task Code 262631 Detail Inspection Portable Halon Fire Extinguisher (Right Cockpit). CMP 262621, 262601. 6.24) Complied with 12-months CMP Task Code 262632, Detail Inspection Portable Halon Fire Extinguisher (Forward Cabin). CMP 262622, 262602, Extinguisher C354TS A-94386145. 6.25) Complied with 12-months CMP Task Code 262633 Detail Inspection Portable Halon Fire Extinguisher (Aft Cabin). CMP 262623, 262603, Extinguisher C354TS B10808009. 6.26) Complied with 12-months CMP Task Coed 262720 Trash Receptacle Enclosure (Aft Galley) - Detailed Inspection. 6.28) Complied with 12-months CMP Task Code 262722 Trash Receptacle Enclosure Lavatory) - Detailed Inspection. 6.29) Complied with 12-months CMP Task Code 262724 Trash Receptacle Fire Extinguisher Nozzles (Aft Lav) - Detailed Insp. 6.30) Complied with 12-months CMP Task Code 262726 Trash Receptacle Fire Extinguisher Nozzles (Aft Galley) - Detailed Insp. 6.31) Complied with 24-months CMP Task Code 270101 Stall Barrier Angle of Attack System - Operational Test. 6.32) Complied with 48-months CMP Task Code 270221 Stall Barrier Dump Valve - Operational Test. 6.33) Complied with 24-months CMP Task Code 271046 Aileron Control and Trim Cables in Main Wheel Wells and Wing Rear Beam - Detailed Inspection. 6.34) Complied with 24-months CMP Task Code 272026 Rudder Control and Trim Cables in Main Wheel Well - Detailed Inspection 6.35) Complied with 24-Months CMP Task 273038 Elevator Control and elevator Trim Cables in Main Wheel Wells. 6.36) Complied with 48-months CMP Task Code 275013 Emergency Flap System - Operational Test. 6.37) Complied with 12-months CMP Task Code 276013 Spoiler Hinges (LH Inboard Middle Outboard) Lubrication. 6.38) Complied with lZ-months CMP Task Code 276014 Spoiler Hinges (RH Inboard Middle Outboard) Lubrication. 6.39) Complied with 24?months CMP Task Code 276088 Speed Brake Cable Assemblies in Main Wheel Well Wing Rear Beam - Detailed Inspection. 6.40) Complied with 12?months/4500?hours CMP Task Code 277012 Throttle Lever Gust Lock Protection - Functional Test. 6.41) Complied with 24-months CMP Task Code 282084 Engine/APU Fuel Feed Line Witness Port (Left) -Detailed Inspection. 6.42) Complied with 24-months CMP Task Code 282085 Engine/APU Fuel Feed Line Witness Port (Right) -Detailed Inspection. 6.43) Complied with 24-months CMP Task Code 291020 Flight Powered Shutoff System - Operational Check. 6.44) Complied with 24-months CMP Task Code 313011 Flight Data Recorder - Functional Test. 6.45) Complied with 72-months CMP Task Code 313019 FDR Underwater Locator Beacon - Battery Discard. (DK120) 6.46) Complied with 12-months CMP Task Code 316006 Electronic Display System Automatic Recon?guration Mode - Operational Test. (SPZ-8400) 6.47) Complied with 12-months CMP Task Code 316007 Electronic Display System Manual Recon?guration Mode Operational Test. 6.48) Complied with 12-months CMP Task Code 316009 Symbol Generator Switching - Operational Test. 6.49) Complied with 4-months CMP Task Code 320004 Main Landing Gear and Systems (left) Lubrication. 6.50) Complied with 4-months CMP Task Code 320005 Main Landing Gear and Systems (right) Lubrication. I?ll!? R2 November 27, 2017 Page 1 of 6 m: N51PR ACIT: 4455.6 Date: 6/24/2018 HM: 4455.6 SIN: 1425 ACTL: 1743 Model: (34v APU: 4749.0 AIRFRAME INSPECTIONS APRIL 2018 (cont.) 6.51) Complied with 4-months CMP Task Code 320006 Nose Landing Gear and Systems Lubrication. 6.52) Complied with 12-months/500-hours CMP Task Code 320008 Nose and Main Landing Gear and Landing Gear Doors - Zonal Inspection. 6.53) Complied with 24-months CMP Task Code 320009 Landing Gear (left main) Corrosion Inhibiting Compound Reapplication. 6.54) Complied with 24-months CMP Task Code 320010 Landing Gear (right main) Corrosion Inhibiting Compound Reapplication 6.55) Complied with 24-months CMP Task Code 320034 Nose Landing Gear Corrosion Inhibiting Compound Reapplication. 6.56) Complied with 12-months CMP Task Code 322042 Detail Inspection Nose Gear Axle Assy. 324009, 324010, 322036) 6.57) Complied with 24-months CMP Task Code 322433 Nose Landing Gear Spring Rod Assembly Lubrication. 6.58) Complied with 24~months CMP Task Code 322434 Main Landing Gear Bungee (left) Lubrication. 6.59) Complied with 24-months CMP Task Code 322435 Main Landing Gear Bungee (right) Lubrication. 6.60) Complied with 24-months CMP Task Code 326001 Landing Gear Aural Warning System - Operational Test. 6.61) Complied with 12-months CMP Task Code 335047 Emergency Securaplane Battery No. - BITE Battery Level Test. 6.62) Complied with 12-months CMP Task Code 335048 Emergency Securaplane Battery No. 2 - BITE Battery Level Test. 6.63) Complied with CMP Task Code 340100 Reduced Vertical Separation Minimum (RVSM) Monitoring Policy. 6.64) Complied with lZ-months CMP Task Code 341027 Transceiver, #1 Radio 6.65) Complied with IZ-months CMP Task Code 341028 Transceiver, #2 Radio 6.66) Complied with 30?day CMP Task Code 343064 Very High Frequency Omni Range - Instrument Flight Rules Check. 6.67) Complied with 24-months CMP Task Codes 344051 and 344005 No. 1 Cooling Fan Filter - Inspection Clean. Removed #1 - HG1075AE04 - 0082944. Inspected/cleaned cooling fan ?lter. Installed #1 IRU. No defects noted. 6.68) Complied with 24-months CMP Task Codes 344052 and 344006 No. 2 Cooling Fan Filter - Inspection Clean. Removed #2 - HG1075AE04 - 00072938. Inspected/cleaned cooling fan ?lter. Installed #2 IRU. No defects noted. 6.69) Complied with 24~months CMP Task Codes 344055 and 344010 IRU No. 3 Cooling Fan Filter - Inspection Clean. Removed #3 HG1075AE04 - 746. Inspected/cleaned cooling fan ?lter. Installed #3 IRU. No defects noted. 6.70) Complied with 12-month CMP Task Code 344095 Inertial Reference Unit No. 1 Securaplane Battery (BITE Level Test) Operational Test. 6.71) Complied with lZ-month CMP Task Code 344096 Inertial Reference Unit No. 2 Securaplane Battery (BITE Level Test) Operational Test. 6.74) Complied with 12-months CMP Task Code 353052 Portable Oxygen Bottle/Mask - Detailed Inspection. 6.75) Complied with l-months CMP Task Code 497007 APU Hour meter Reading 4749 APU hours. ECU Hobbs reading 487l-hours: there is placard to subtract 122 hours. Corrected HM reading 4749-hours. 6.76) Complied with 24-months CMP Task Code 520306 Main Entrance and Baggage Door Seal High Flow Pressure Regulator - Functional Test. 6.77) Complied with 72-months CMP Task Code 521002 Main Entrance Door Cable - Tension Check. 6.78) Complied with 12-months CMP Task Code 521003 Main Entrance Door - Lubrication. 6.79) Complied with 72-months CMP Task Code 521007 Main Entrance Door Internal - Detailed Inspection. 6.80) Complied with 24-months CMP Task Code 521011 Main and Baggage Door In?atable Seals - Detailed Inspection. 6.81) Complied with 24-months CMP Task Code 521016 Cabin Door and Emergency Exits (view from ground) Zonal Inspection. 6.82) Complied with 36-months CMP Task Code 521024 Main Entrance Door Hinge Pins - Detailed Inspection. 6.83) Complied with 24-months CMP Task Code 521050 Door Seal Regulator and System - Inspection. 6.84) Complied with 12-months CMP Task Code 521080 In?atable Door Seal - Purging Procedure. 6.85) Complied with 12-months CMP Task Code 523004 Baggage Door Lubrication. 6.86) Complied with 24?months CMP Task Code 527005 Main Entrance Door Warning System - Operational Test. 6.87) Complied with 24-months CMP Task Code 527008 Baggage Door Warning System - Operational Test. 6.88) Complied with 24-months CMP Task Code 532039 Baggage Compartment below Floor FS 539 - FS 596 Internal - Zonal Inspection. 6.89) Complied with 24-months CMP Task Code 532066 APU Enclosure FS 605 - FS 635 Internal - Zonal Inspection. 6.90) Complied with 24?months CMP Task Code 532071 External Lower Fuselage FS-4 thru FS-596, (viewed from ground) - Zonal Inspection. 6.91) Complied with 24-months CMP Task Code 532073 External Upper Fuselage 44 - FS 596 (viewed from ground) - Zonal Inspection. 6.92) Complied with 24-months CMP Task Code 532075 Aft Fuselage and Empennage FS 596 - FS 864 External (viewed from ground) - Zonal Inspection. 6.93) Complied with 24-months CMP Task Code 532903 Main Entrance Door Actuator Attach Fitting (borescope) - Inspection. 6.94) Complied with 24?months CMP Task Code 533010 Static Ports (Reduced Vertical Separation Minimums) - Inspection. 6.95) Complied with lZ-months/SOO-hours CMP Task Code 534021 Nose Gear Wheel Well FS 44 - FS 119 - Zonal Inspection. 6.96) Complied with 12-hours/500-hours CMP Task Code 534022 Main Gear Wheel Wells FS 452 - FS 496 - Zonal Inspection. 6.97) Complied with 24-months CMP Task Code 535013 Aft Cabin below Floor FS 498 - FS 539 Internal - Zonal Inspection. R2 November 27, 2017 Page 2 of 6 KQ Nit: N51PR ACTT: 44555 Date: 5/24/2018 HM: 4455.5 SIN: 1425 ACTL: 1743 Model: APU: 4749.0 AIRFRAME INSPECTIONS APRIL 2018 (cont) 6.98) Complied with 24-months CMP Task Code 535014 Aft Fuselage above Floor 596 - FS 812 Internal - Zonal Inspection. 6.99) Complied with 24-months CMP Task Code 541027 Pylon Internal (left) - Zonal Inspection. 6.100) Complied with 24-months CMP Task Code 541028 Pylon Internal (right) - Zonal Inspection. 6.101) Complied with 24~months CMP Task Code 541029 Pylon External View from Ground (left) - Zonal Inspection. 6.102) Complied with 24-rnonths CMP Task Code 541030 Pylon External View from Ground (right) - Zonal Inspection. 6.103) Complied with 24-months CMP Task Code 570003 Wing Lower Surface (left) - Zonal Inspection. 6.104) Complied with 24-months CMP Task Code 570004 Wing Lower Surface (right) Zonal Inspection. 6.105) Complied with 24-rnonths CMP Task Code 571045 Wing Rear Beam (left) - Zonal Inspection. (575015) 6.106) Complied with 24-Inonths CMP Task Code 571046 Wing Rear Beam (right) - Zonal Inspection. (575016) 6.107) Complied with 72?months CMP Task Code 573013 Winglet Attach Hardware Inspection. 6.108) Complied with 72-months CMP Task Code 573014 Winglet Attach Hardware (right) - Inspection. 6.109) Complied with 24-months CMP Task Code 573015 Winglet Blade (view from ground, left) - Zonal Inspection. 6.110) Complied with 24-months CMP Task Code 573016 Winglet Blade (view from ground, right) Zonal Inspection. 6.111) Complied with 24-months CMP Task Code 574007 Wing Leading Edge External BL 35.80 - RES 433 Inboard of Nav Light (Left) Zonal Inspection. 6.112) Complied with 24-months CMP Task Code 574008 Wing Leading Edge External BL 35.80 - RBS 433 Inboard of Nav Light (Right) Zonal Inspection. 6.113) Complied with 24-months CMP Task Code 575015 Wing Lower Cove Panel and Flap Well Drain Holes (left) Enhanced Zonal Inspection. 6.114) Complied with 24-months CMP 575016 Wing Lower Cove Panel and Flap Well Drain Holes (right) - Enhanced Zonal Inspection. 6.115) Complied with 24?months CMP Task Code 575105 Lower Wing Trailing Edge - Zonal Inspection. 6.116) Complied with 24-months CMP Task Code 575106 Lower Wing Trailing Edge (right) - Zonal Inspection. 6.119) Complied with 24-months CMP Task Code 710007 Powerplant Nacelle External (view from ground, left) - Zonal Inspection. 6.120) Complied with 24-months CMP Task Code 710008 Powerplant Nacelle External (view from ground, right) - Zonal Inspection. 6.121) Complied with 24-months CMP Task Code 711005 Powerplant Nose Cowls Internal (view from ground, le?) Zonal Inspection. 6.122) Complied with 24-months CMP Task Code 711006 Powerplant Nose Cowls Internal (view from ground, right) Zonal Inspection. 6.123) Complied with 72-months CMP Task Code 783007 Hot Short to Ground Circuit (left) - Functional Test. 6.124) Complied with 72-months CMP Task Code 783008 Hot Short to Ground Circuit (right) Functional Test. 6.125) Complied with 24-months CMP Task Code 783033 Thrust Reverser Unlock (left) - Operational Test. 6.126) Complied with 24-months CMP Task Code 783034 Thrust Reverser Unlock (right) - Operational Test. 6.127) Complied with 96-months CMP Task Code 571025 Fuel Tank Internal (left) - Detailed Inspection. 6.128) Complied with 96-months CMP Task Code 571026 Fuel Tank Internal (right) - Detailed Inspection. 6.129) Complied with 48-months CMP Task Code 571027 Wing Tank Internal Inboard 3 Panels Each Wing - Detailed Inspection. 6.130) Complied with CMP Task Code 280018 Fuel Tank - Leak Check. 6.131) Complied with CMP Task Code 280019 Fuel Tank (right) - Leak Check. AIRFRAME INSPECTIONS DECEMBER 2018 7.2) Complied with 5,000-hours CMP Task Code 212033 Ram Air Check Valve - Detailed Inspection. 7.3) Complied with SOO-hours CMP Task Code 212200 Display Unit Fan Filters Inspection. CMP 316021, 316022, 316023, 316024, 316025, 316026) 7.4) Complied with 120-months/2500-hours CMP Task Code 213046 Pressure Relay Switch - Screen Inspection Filter Discard. 7.5) Complied with 2,500-hours CMP Task Code 213078 Safety Valve Filter - Detailed Inspection. 7.6) Complied with 1,000-hours CMP Task Code 217027 Ozone Converter (left) - Functional Test. CMP 217025) 7.7) Complied with 1,000-hours CMP Task Code 217028 Ozone Converter (right) - Functional Test. CMP 217026) 7.8) Complied with 500-hours CMP Task Code 217075 Water Separator Bag (left) - Inspection. 7.9) Complied with SOD-hours CMP Task Code 217076 Water Separator Bag (right) - Inspection. 7.10) Complied with lZ-months CMP Task Code 23 7004 Cockpit Voice Recorder System - Operational Test. 7.12) Complied with 2,500-hours CMP Task Code 242007 Left Engine Alternator Bearing - Discard. CMP 242005, 242009, 242015) 7.13) Complied with 2,500-hours CMP Task Code 242008 Right Engine Alternator Bearing - Discard. CMP 242006, 242010, 242016) SA-OSOS R2 November 27, 2017 Page 3 of 6 ?g N4: N51PR Ac": 4455.6 Date: 6/24/2018 HM: 4455.6 3: SIN: 1425 ACTL: 1743 Model: G-IV APU: 4749.0 AIRFRAME INSPECTIONS DECEMBER 2018 (cont) 7.14) Comply with SOD-hours CMP Task Code 243137 Ni-Cad Battery No. 1 (Capacity Deep Cycle) - Functional Test. 7.15) Comply with SOD-hours CMP Task Code 243138 Ni-Cad Battery No. 2 (Capacity Deep Cycle) Functional Test. 7.16) Complied with 1,000-hours CMP Task Code 254001 Lavatory Compartment above Floor - Inspection. 7.17) Complied with CMP Task Code 272036 Rudder Torque Tube Bearing - Lubrication. 7.18) Complied with CMP Task Code 272038 Rudder Pedals - Lubrication. 7.19) Complied with CMP Task Code 275019 Wing Flap (Left) - Lubrication. 7.20) Complied with 24-months/500-hours CMP Task Code 275020 Wing Flap (Right) - Lubrication. 7.21) Complied with 24-months/500-hours CMP Task Code 275023 Wing Flap Traveling Nut (left) - Lubrication 7.22) Complied with CMP Task Code 275024 Wing Flap Traveling Nut (right) - Lubrication 7.23) Complied with CMP 276065 Aircraft Con?guration Takeoff Warning Functional Test. 7.24) Complied with CMP 291055 Hydraulic System Acoustical Filter (left) - Discard. 7.25) Complied with CMP 291056 Hydraulic System Acoustical Filter (right) - Discard. 7.26) Complied with 500-hours CMP Task Code 316097 Aural Warning System (Audio Output) - Operational Test. 7.27) Comply with SOD-hours CMP Task Code 324206 Hydro Mechanical Analog Brake Wear (HMAB) - Detailed Inspection. 7.28) Complied with 24-month/500-hours CMP Task Code 334062 Navigation Position Lights Lens - Detailed Inspection. 7.29) Complied with 24-month CMP Task Code 342038 Compass Swing No. 2. 7.30) Complied with SOD-hours CMP Task Code 361056 APU Air Check Valve - Detailed Inspection. 7.31) Complied with 96-months CMP Task Code 531000 Thrust Strut Fitting - Detailed Inspection. 7.32) Complied with 96-months CMP Task Code 531010 Forward Engine Mounts (right) detail inspection. 7.33) Complied with 96-month CMP Task Code 531012 Aft Engine Mounts (right) detail inspection. 7.34) Comply with 500-hour CMP Task Code 531046 Main Gear Wheel Wells FS 452 - FS 496 Lower Wing Cove Panel Drain Holes - Enhanced Zonal Inspection. 7.35) Comply with 500-hours CMP Task Code 531047 Main Gear Wheel Wells FS 452 - FS 496 Wiring Harness - Enhanced Zonal Inspection. 7.36) Complied with 5,000-hours CMP Task Code 539051 Pressure Bulkhead Composite Panels - General Visual Inspection. 7.37) Complied with 5,000-hour CMP Task Code 539053 Aft Pressure Bulkhead Beam Bulkhead Support - General Visual Inspection. 7.38) Complied with 5,000?hours CMP Task Code 554007 Rudder External Inspection. 7.39) Complied with 96-months CMP Task Code 572007 Wing Wedge Internal and External Surface (left) - Detailed Inspection. 7.40) Complied with 96-months CMP Task Code 572008 Wing Wedge Internal and External Surface (right) - Detailed Inspection. 7.41) Complied with 96?months CMP Task Code 575017 Aileron Area Drain Holes (left) - Enhanced Zonal Inspection. 7.42) Complied with 96?months CMP Task Code 575018 Aileron Area Drain Holes (right) - Enhanced Zonal Inspection. 7.43) Complied with LOGO-hours CMP Task Code 710005 Engine Drain System - General Visual Inspection. 7.44) Complied with 1,000-hours CMP Task Code 711007 Powerplant Nacelle Doors Internal (left) - Zonal Inspection. 7.45) Complied with 1,000?hours CMP Task Code 711008 Powerplant Nacelle Doors Internal (right) - Zonal Inspection. 7.46) Complied with 1,000-hours CMP Task Code 712091 Thrust Reverser Exhaust Internal (left) - Zonal Inspection. 7.47) Complied with 1,000?hours CMP Task Code 712092 Thrust Reverser Exhaust Internal (right) - Zonal Inspection. 7.48) Complied with 1,000-hours CMP Task Code 722019 Fan Blades (Visual Portion) - Detailed Inspection. 7.49) Complied with 1,000-hours CMP Task Code 723003 Low-pressure Compressor Case Lining - Detailed Inspection. 7.50) Complied with 1,000-hours CMP Task Code 727110 Low-pressure Turbine Bearing Support Spoke Fairing - General Visual Inspection. 7.51) Complied with CMP Task Codes 731011 Low-Pressure Fuel Filter (left) - Discard. QA03198) 7.52) Complied with 1,000-hour CMP Task Code 731053 Ejector Pump Filter (EPA Can) (left) - Inspection. 7.53) Complied with 1,000-hours CMP Task Code 762005 Rear Guide Disconnect Cable (left) - Detailed Inspection. 7.54) Complied with CMP Task Code 801009 Engine Starter Splines (left) Lubrication. 801007) 7.55) Complied with CMP Task Code 801010 Engine Starter Splines (right) Lubrication. 801008) 7.61) Complied with 72-month CMP Task Code 262171 Baggage Compartment Smoke Evaluation Valve Operational Check. AIRWORTHINESS DIRECTIVES AND SERVICE BULLETINS 7.24) Complied with IV ASC 463B Hydraulic Power Hydraulic Acoustic Filter Installation. (Left) 7.25) Complied with IV ASC 463B Hydraulic Power Hydraulic Acoustic Filter Installation. (Right) 7.56) CMP 982381 CB 238A Repaired Main Landing Gear Side Brace Actuator Fittings for Continued Airworthiness. Reviewed aircraft records and found that Repair SE0732102 has not been accomplished. Additionally it was noted that Customer Bulletin 238 Service Reply Card was submitted for accomplishment on 2/Dec/2016 at ACTT: 4205.7 and landings: 1647. No additional action required for CB 238A. Completed Service Reply Card for CB 238A and submitted to SA-OSOS R2 November 27, 2017 Page 4 of 6 ?g Nit: N51PR Acrr: 44555 Date: 5/24/2013 HM: 4455.5 SIN: 1425 ACT L: 1743 Model: APU: 4749.0 AIRWORTHINESS DIRECTIVES AND SERVICE BULLETINS tcont.) 7.57) CMP Item Number 992501 left engine: reviewed aircraft records and found item previously complied with by Dallas Airmotive on Work Order# RPR20639 Dated April 1 2011during Mid-Life and 10-year calendar Inspections. Inspected Low- Pressure Fuel Tubes and found to be in compliance IAW AD 05-03-06 by tube installed on left engine IAW Rolls?Royce Tay-73-1592. No further action required. 7.58) Complied with 1,000-hour recurring CMP 994002 AD 74-08-09 R3 Lavatory Paper and Linen Waste Receptacle Enclosure Access Door and Disposal Door InSpection. AD 74-08-09 R3 next due at 545 5-ACTT. 7.59) Complied with CMP 994042 AD 2017-18-12 Aerospace IAW AD 2017-18-12 Aerospace. AD 2017-18-12 does not apply by equipment not installed. No additional actions required. 7.60) CMP 994053 AD 2017-26-05 Aerospace Corporation Amendment 39-19136. AD 2017-26-05 not applicable due to aircraft serial number. MAINTENANCE EVENTS PARTS REMOVED OR REPLACED 2.1) Removed APU Model GTCP36-100 PIN 3800062-9-1 with 4250.0 APU hours. Installed original APU Model GTCP36-100 3800062-9-1 P-848 IAW G-IV AMM 49-10-00. CMP 490001 APU Removal/install. 2.5) Replaced fuel quantity indication coax cable. Terminated at both ends IAW 28-41-00 Fuel Quantity Wiring Diagram. 2.7) Removed expired Forward Galley portable fire extinguisher PIN C3 52, X-691221. Installed new portable ?re extinguisher C352, E68636660. Work performed GIV-MSG3. CMP 262602 Portable Halon Fire Extinguisher (Forward Cabin) - Removal/Installation). 3.2) Removed and reinstalled main ship batteries 023515-000, 090520012633C (Aft), 023515-000, 09052001263 3D (Fwd). Ref this work order squawks 7.14 and 7.15 for Ship Batteries Deep Cycle procedures. 3.3) Removed Artex C406-2 ELT 453-5000 Rev 00263 for modi?cation. Received and installed Radio Masters modi?ed C406-2 Artcx ELT 453-5000 Rev 00263. Complied with operational check with no defects noted. Work accomplished IAW the Artex Manual. 24 Bit Long Message (Beacon CCOD6 Country=3 66 USA) 3.4) Removed DU-880 Display Unit 4053000-901 97052590. Installed a Inc., 1501 Aviation Blvd., Lincoln, CA repaired DU-880 Display Unit 4053000-901 99023285. Unit repaired under work order number RC26512 dated 02/March/2018, Certi?cate No. CRS 2GDR216B. Complied with operational check with no defects noted. 6.8) Complied with 48-months CMP Task Code 240266 Emergency Securaplane Battery Heater No. 2 Discard. 6.16) Received and installed original crew life vest PIN 63600-505 L1290004, L1290005 and L1290006. Life Vest, Crew overhauled by HRD Aero Systems, Inc. under work order number L63158 dated 11/May/2018, Certi?cate No. YN2R325L. Received and installed 14 original passenger life vest 63600-105 L1184179, L1287350, L1287351, L1287352, L1287354, L1287355, L12873S6, L1287357, L1287358, L1287359, L1287361, 1.1287362, L1287364 and L2123524. Passenger life vests overhauled by HRD Aero Systems, Inc. under?work order number L63157 dated 11fMay/201 8, Certi?cate No. YN2R325L. 6.17) Removed #1 life ra? 12UL-00262 and shipped to Shoreline Marine, Inc. dba Safetech SMER451X, Dallas TX 75220. Received original life raft 1218FAUL-3JO-1-100 and installed. Ra? overhauled under Form Tracking Number AD445 77 dated 13/Mar/2018, Certi?cate No. SMER451X. The following information recorded for life raft FAA 8130 Form: cylinder hydro date: 3/2018, cylinder mfg. date: 9/2014, ELT 5621, ELT battery exp. date: 12/2022, ELT HEX ID: A666492605DB6A5, ra? inspection date: 3/2018, next due date: 3/2021. 6.18) Removed #2 life ra? 1218FAUL-3JO-1-100 12UL-00263 and shipped to Shoreline Marine, Inc. dba Safetech SMER451X, Dallas TX 75220. Received original life raft 1218FAUL-3J0-1-100 12UL-00263 and installed. Ra? overhauled under Form Tracking Number AD44571 dated 13fMar/201 8, Certi?cate No. SMER451X. The following information recorded for life raft FAA 8130 Form: cylinder hydro date: 3/2018, cylinder mfg. date: 9/2014, ELT 5622, ELT battery exp. date: 12/2022, ELT HEX ID: A666492605DB6A9, raft inspection date: 3/2018, next due date: 3/2021. 6.20) Removed outdated First Aid Kit RE1013-107 MX212. Installed new First Aid Kit RE1013-107 FASAN048 with a manufacture date of April/201 8. 6.45) Installed a new FDR ULB AT113868 with an expiration date of 01fMay/2025. Work accomplished IAW GIV Maintenance Manual Chapter 31-05-00. 6.82) Installed two new main entrance door hinge pins 159BM10108-1 IAW the G-IV CMP Chapter 52-10-00. 7.4) Installed new pressure relay switch ?lter 139495 -2 IAW Chapter 21-02-06 GIV-MSG3 Maintenance Manual. 7.6) Removed left ozone converter 1159SCAC401-1 6498. Received and installed inspected/tested ozone converter 1159SCAC401-1 SN 6498. Converter was inspected/tested under work order number 115976361 dated 29/March/18, Certi?cate No. E72R725N. Work was accomplished IAW CMP 21-00-00. 7.7) Removed right ozone converter 1159SCAC401-1 6675. Received and installed inspected/tested ozone converter 1159SCAC401-1 6675. Converter was inspected/tested under work order number 115976336 dated 29/Mar/18 Certi?cate No. E72R725N. Work was accomplished IAW the G-IV CMP 21-00?00. 7.8) Installed new water separator coalescer bag (left) 83237-20 IAW G-IV MSG3 AMM Chapter 21-00-00. 7.9) Installed new water separator coalescer bag (right) 83237-20 IAW G-IV MSG3 AMM Chapter 21-00-00. SA-OSOS R2 November 27, 2017 Page 5 of 6 (KC: mi: N51PR Acrr: 44555 Date: 5/24/2013 HM: 4455.5 SIN: 1425 ACT L: 1743 Model: G-IV APU: 4749.0 7.12) Removed left engine alternator 1159SCA373-105 (28B421-2C) 592. Installed a Consolidated Aircraft Supply Co. Inc., Ronkonkoma, NY 11779 overhauled generator 28B421-2C SIN 1212. Unit was overhauled under work order number 34843 dated 27/June/2017, Certi?cate No. GI1R167K. Work accomplished IAWG-IV AMM Chapter 24-01-01. New bearing PIN 1547770-5 installed, new spline adapter 1595443-1 installed. 7.13) Removed right engine alternator 1159SCA373-105 30-A0218. Installed a Falcon Crest Accessories, Inc., Huston, TX 77061 overhauled alternator 28B421-2-C 713. Unit overhauled under work order number 81393 dated l4/Feb/2018, Certi?cate No. GP2R854K. Work accomplished IAW G-IV AMM Chapter 24-01-01. New bearing 1547770-5 installed, new spline adapter PIN 159544-1 installed. MAINTENANCE PARTS REMOVED OR REPLACED (cont) 7.24) Installed new left hydraulic acoustic ?lter 1159H47440-1 PMS 2026 LAW with ASC 463 instructions on left engine. Complied with CMP 291049, CMP 291055 and CMP 974635 for ASC 4633 (Part 2) 7.25) Installed new right hydraulic acoustic ?lter 1159H47440-1 PMS 2268 IAW with ASC 463 instructions on right engine. Complied with CMP 291050, CMP 291056 and CMP 974636 for ASC 463B (Part 2) 7.51) Installed new low-pressure fuel ?lter using new gasket DU2310A (left) IAW the GIV MSG3 AMM Chapter 73-00-00. 17.1) Complied with Conformity Inspection and signed Form FAA 8130-9 for STC ST0046MC-T, June 24, 2018, refer to Deviation List attached to 8130?9. Placed Experimental Placards on exterior of main entrance door and inside of cabin at G-IV INSPECTION FINDINGS 13.1) Installed new fuel cap lanyard M8273 80-1 on left wing fuel caps IAW best shop practices. 13.11) Installed new nut plate on right lower pylon panel IAW G-IV SRM Chapter 51-70-00. 13.12) Applied sealant to left wing wedge inboard riv-nut IAW SRM 51?22-00. 13.13) Installed 2 new grease ?ttings on nose landing gear IAW G-IV Manual Chapter 32?08-00. 13.16) Accomplished repair to left winglet hole #3 IAW Service Letter Document No.: GSL405732001 dated 9/08/2016 Revision A. ATA: 57-32-00. Reworked hole to: 3L - .9020 Per GSL405732001-1. See FAA 337 Form dated 21/June/2018. 13.17) Removed left and right winglet attach bushings inspected, cleaned and re-installed IAW GIV Maintenance Manual Chapter 57-30-00. 13.18) Discovered small dent at UH wing inboard TE Box panel: Contacted Tech ops with ?ndings and sent pics of damaged area. Due to dimension of area they recommended cold working of area. Dent was removed by cold working method with no oil canning present. Primed and Painted area. Work performed MSG-3 GIV M.M. Ch. 51-77-12. 13.19) Removed serviceable left hand down and lock switch for continued use on G-IV N4ISC. Installed new down and lock switch assembly 920070 NSN. Work was accomplished IAW the IV MSG 3 AMM 32-01-00. Complied with operational check with no faults noted. New replacement switch was ordered under work order number Item 1.3 13.20) Removed cracked Right engine thrust reverse lower bucket inboard seal retainer. Located, drilled and installed a new retainer, channel, and 2ea gussets IAW MSG3 GIV SRM 51-42-00. 13.21) Replaced fuel damaged fuel access screws as required. AVIONICS MAINTENANCE EVENTS 3.2) Removed and reinstalled main ship batteries PIN 023515-000, 090520012633C (Aft), 023515-000, 090520012633D (Fwd). Work accomplished IAW the GIV Maintenance Manual Chapter 24. I Certify That This Aircraft Has Been Inspected In Accordance With An Inspection Program Required By FAR 91 3. The Maintenance Identi?ed In This Work Order Package Has Been Inspected and the Item(s) Are Approved For Return to Service. Pertinent Details Are On File At This Agency Under Work Order No: YH-WO-95 69. SIGNED For STEVENS AVIA TION, INC. GREENVILLE, SC 29605, CRS VIBR368K SA-OSOS R2 November 27, 2017 Page 6 of 6 AiRTi/Eci BY ELECTRONIC MAIL FAA Inspector David Hintz 1301 South Terminal Service Road Greensboro, NC 27409 Mr Hintz, We wish to place one of our aircraft; N51PR, G-IV, SIN 1425 into Experimental Research and Development. The purpose is to verify compatibility and operational functionality of Tracer Radar, Viasat Sat-Com, and MX-15 Hdi externally mounted to the aircraft. The RD Program is requested for 1 year. An application for STC has been made and STC Project Number ST00464MC-T has been assigned. The experimental ?ight tests will be accomplished as outlined in the FAA accepted Project Speci?c Certi?cation Plan Aery Document as revised. The installation of all components will be accomplished llA/W FAA Acceptable Practices and Techniques. At the and of the Experimental RD period we plan to return the aircraft to Standard Category when the STC is issued. We have consulted with Mr. Jerry Hughes, DAR-T and requested his assistance with this effort. It is our request that this certi?cation activity be delegated to Mr. Hughes. Mr. Hughes has an existing Geographic Expansion in place for work on this project and has provided support in establishing a baseline conformity for the airCraft. This expansion may need to be extended if this does not con?ict with your of?ce. Please find the. following attachments for your review: 1) Experimental RD Program Letter 2) 3 View drawings of the aircraft 3) FAA Form 8130-6 4) FAA Form 8130-9 5) FAA Form 3373 documenting aircraft modi?cations 6) Notarized letter authorizing Airtec to act as agent for service If you have any questions. please do not hesitate to contact me. Sincerely. Ed Sci: 0 44174 Airport Rd, Suite 300, California. MD 20819 301-373-2101 Telephone 301-373-2154 Facsimile Federal Aviation Administration a MAJOR REPAIR AND ALTERATION 3:35:33? (Airframe, Powerplant, Propeller, or Appliance) OMB No. 2120-0020 Electronic Tracking Number Exp: 5/3112018 For FAA use My? such violation. (49 U. S. ?46301(a)) INSTRUCTIONS: Print or type all entries. see Title 14 CFR ?43. 9. Part 43 Appendix and AC 43. 9- 1 (er subsequent revision thereon for instructions and disposition of this form. This report' IS required by law (49 U. S. ?44701). Failure to report can result' In a Civil penalty for each Nationality and Registration Mark: N51PR Sen?al No.2 1425 1. Aircraft Make: Aerospace Model: G-IV Series: 2- Owner AC4 425 LLC Name (As shown'on registration certi?cate) City: Highland Beach Zip: 33487-4703 Address (As shown an registration certi?cate) Address. 3420 8. Ocean BLVD #10 State: FL Country: U.S.A. 3. For FAA Use Only 4. Type -. 5. Unit identi?cation Repair Alteration Unit Make Model Serial Number )3 AIRFRAME (As described in item 1 above) El POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agench Name and Address B. Kind of Agency Name Stevens Aviation Inc. El U.S. Certi?cated Mechanic DJ Manufacturer Address 600 Delaware St. El Foreign Certi?cated Mechanic 0. Certi?cate NO- City Gr eenville State Certi?cated Repair Station VIBR368K i Country.__ USA El Certi?cated Maintenance Organization D. I certify that the repai iandior alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U. 3. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel Signature/Date of Authorized Individual per 14 CFR Part 43 21IJune/2018 Scott Hansel App. 7. Approval for Return to Service Administrator of the Federal Aviation Administration and Is Pursuant to the authority given persons speci?ed below, the unit identi?ed in item 5 was inspected in the manner prescribed by the APPROVED REJECTED FAA Standards . . . Person Approved by Canadian Inspector Manufacturer Maintenance Organization Department of Transport BY Other (Specify) FAA Designee Repair Station inspection Authorization Certi?cate or SignatureiDate of Authorized individual Designation No. 21 - unel2018 Mike Churchwell VIBR368K . FAA Form 337 (10-06) NOTICE Weight and balance or operating limitation changes shall be" entered.? In the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airwonfhiness requirements. 8. Description of Work Accomplished I . (if mere space is' required, attach additional sheets. identify with aircraft nationality and registration mark and. date work completed N51PR 21lJu'rie/2018 Nationality and Registration Mark I I I Date Accomplished repair to" left winglet hale #3 Letter Document No.: GSL405732001 dated 9/08/2016 Revision A ATA: 57-32- 00. Reworked hole to: .9020 Per GSL405732001- 1. . Aircraft log entry recording this Major Repair was completed. . Aircraft was reweighed at this time. - Aircraft Secured For Flight. I END Additionai Sheets Are Attached FAA Form 337 (10-06) Gm SERVICE LETTER CQ Title: Winglet Attachment Fitting Bore Repair SERVICE NQT Document No; GSL405732001 APPROVALS NQT REV we INITIAL A PREPARED BY: Robe" We're" . NEAL ?rewwmpec SERVICE 59" 1 ?We 7' 7 luv/A - Di?? STRESS. 7 NM GROUPHEAD: ?an . TECHNICAL APPROVAL: NM TECHNICAL APPROVAL: MIA PROJECT ENGINEER: Mina . Aleu- Van Eaten. 4.41/4? MANAGER: ?Wig: REV LTR PREPARED BY: SERVICE DOCUMENTS: ST RUCT URESISYSTEMS: STRESS: GROUP HEAD: TECHNICAL APPROVAL: APPROVAL: PROJECT ENGINEER: USE DGCUMENT This document is provided to 08449 for information only. Buyer agrees that price paid authorizes installer or buyer to modify aircraft Accepts no responsibility for use of information on referenced aircraft. Document shall not be used forany other purpose or reproduced without written consent of Aerospace Corporation. wasmn SERVICE LETTER Gulfsu?eam Aerospace Corporation Document No.: GSL405732001 500 Road Savannah, Georgia 31408 Release Date: 9/08/2016 1-912?965-3000 Revision Status: A ATA: 57-32-00 GH-B, GHI, G-IV, GIV MSG-3, 6300, G400, 0350, G450 Classi?cation: Major EIMinor El Methods, Techniques and Practices Winglet Attachment Fitting Bore Repair 2015 Gul?umAaospaceCmpu-a?m. Depanman ofCommerce. WHO. REV A Page 1 of13 I ll GENERAL SERVICE LETTER REVISION HISTORY REVISION REVISION DATE DESCRIPTION OF CHANGES - 6/17/2016 Initial Release 1 Updates statement of Compliance and Engineering Data A TBD Removes rework identi?cation step on the 2 Winglet Attachment Fitting. (Para. 2.M., GSL405732001 Rev. -) 68144057320? REV A Page 2 of 13 GulfstIeamm A GENERAL ave-Auras COMPANY SERVICE LETTER ENGINEERING DATA: CONCURRENT REQUIREMENTS: ASSOCIATED DOCUNIENTS: PUBLICATIONS DATA: EFFECTIVITY: This repair to the 1159WM30700 and 1159WM40700 Winglet Attachment Fitting is applicable to the following aircraft serial numbers. This Senice Letter provides the repair instructions for removing darmge from the Winglet Attachment Fitting Bores and creates oversize repair sleeves for the Winglet Attachment common to the 1159WM40700 and 1159WM30700 61l59B) Winglet Fitting. The following Engineering Data substantiates this Service Letter and is considered proprietary data: 0 SGER-854-?Structurat Substantiation for 6500405 73200! Winglet Attach Repair? I GSDD405732001 ?Winglet Attachment ittz'ng Bore Repair? None. This Service Letter accomplishes a Major Repair. The Engineering Data for this Service Letter has been shown to comply with the applicable and is FAA Approved. This Service Letter may only be used with a Service Engineering disposition. Service Letters are classi?ed as a Manufacturer?s Service Document. No serial number speci?c FAA Form 8100-9 is required upon completion of the repair per this Service Letter (Ref AC 20-176A). It is the responsibility of the maintainer to ensure that safe maintenance practices, as de?ned in the Aircraft Maintenance Manual (AMI) and by the FAA, are complied with. 611-8, 6111 Aircraft Maintenance Manual 1M) 0 20?80-00 Test Inspection Methods GII-B GIV G300 G400. G350 G450 Corrosion Prevention Control Manual 0 20-53-00 "Corrosion Inspection and Detection G-IV, 61V 6300, 6400, 6350, 6450 Nondestructive Testing Procedures Manual - 01-00-10 "Instructions-for Liquid Penetrant 0 06-00-00 ?Eddy Current" Gil-B GW 61"! M863. 6300 6400. 6350 6450 Stluctmalkw' Manual I 13m I 0 51-07-10 Coatings? 0 51-14-00 ?Aeroohmamic smoothness Requirements" I 51-2l-00 ?Granical Treatment ofMateriaIs" The data in this Service Letter will be published in a future revision of the 611-8, 6111, (LIV, 61V 6300, 6400, 6350, and 6450 Structural Repair Manual (SRM). MODEL PART NUMBER EFFECTIVITY GB 1 159WM30700 1-258 (excluding 249, 252), 775 With ASC-300 Incorporated GlIi 159WM30700 249, 252, 300-498, 875 DOCUMENT NO. 681105732001 REVA PageBoflS QWEEIB SERVICE LETTER GIV-X ?saws/140700 43%?Eg?3: WEIGHTS AND BALANCE IMPACT: None. EFFECT ON SPARES: None. WARRANTY: None. SPECIAL EQUIPMENT I TOOLS REQUIRED: None. BACKGROUND: The holes on the Winglet Attachment Fitting have been reported to become damaged. has developed appropriate repair, ?brication, and installation instructions for an oversize repair sleeve that is applicable to the GIL-B, G111, GIV, GIV M853, G300, G400, G350, and G450 aircraft. INSTRUCTIONS: 1. Applicability A. This procedure removes damage ?om the holes in the Winglet Attachment Fitting by oversizing the holes and installing repair sleeves. Refer to FIGURE 20i for hole locations. 1W CAUTION: THE USE OF ALODINE (FINISH #213) IS NOT PERMITTED AT ANY A. LOCATION WHEN ACCOMPLISHING THIS REPAIR. Gain access to the damaged area. L) Ifthe damaged area has been previously repaired using a repair sleeve and the repair sleeve exhibits corrosion (or other discrepancy), rennve the repair sleeve and inspect the [1013 I :l ?arr Roamthe dame, . oorizntal bore ole: -. the Sleeve Installation tln'oughthe 1159WM40700 or ll59WM30700 nglet Attachment Fitting and mating structure to the minimum diamter necessary to remove all corrosion. The maximum hole diameter as not to exceed 1.0015 inch. Ream the damaged'vertical bores (holes #1 l-#16) in the -3 Sleeve Installation through the or Winglet Attachment Fitting and mating wing plank structure to themininunndiameter necessarytorennve allcon'osion isrlot to exceed 0 9390 inch. If damage remains after reaming to the maximum hole diameter contact Gulfsneam Technical ?Operations. Remove all the nicks, scratches, burrs and sharp edges from the bare sur?aces ofthe reworked parts. Ensure the surface ?nish of the reamed hole is 125 RMS or smoother. Perform an open hole HFEC NDT inspection of the reamed bore holes to ensure a damage . condition. For aircraft. refer to NDT manual Chapter 06-00400, para. 70 (57-34-100, ?nglet Installation?Eddy Current Inspection For aircra?, refer to AMM 20-80-00. After NDT inspection, solvent wipe the retained bore hole stack up per SRM 51-41-00. Allow to airdry. Apply Finish #3012 (Epoxy primer) per SRM 51-07-10. DOGJMENTNO. GSL405732001 REV A Page 4 of 13 A CEMEML COHPANY SERVICE LETTER I. Measure the reamed bore hole diameter to four (4) decimal places at three equally rotated locations around the circumference of the hole to ensure the hole is round. I. Make the repair parts. as required. Refer to Table 201 for the repair parts. TABLE 201: Repair Materials ITEM DESCRIPTION QUANTITY MATERIAL INBOARD SLEEVE AS NEEDED CRES BAR PER AMS 5629, CONDITION H1000. FOR USE ON HORIZONTAL BORE LOCATIONS (-1 SLEEVE INSTL) ONLY. SEE FIGURE 204 FOR PART DIMENSIONS. 11595341403413 /-25/-29 SLEEVE WITH A DIAMETER THE SAME AS, LARGER THAN, THE REAMED HOLE. REFER TO TABLE 202. MACHINE THE DIAMETER OF THE RESPECTIVE 11598341403 SLEEVE SUCH THAT ITS FINAL AS AN ALTERIQVZ, IT IS ACCEPTABLE TO PROCURE A 21 DIAMETER IS 00030-00060 LESS THAN THE FINAL DIAMETER OF THE REAMIED HOLE. OUTBOARD SLEEVE AS NEEDED CRES BAR PER AMS 5629, CONDITION H1000. FOR USE ON HORIZONTAL BORE LOCATIONS (-1 SLEEVE INSTL) ONLY. SEE FIGURE 205 FOR PART DIMENSIONS. ASANAL 11595341403-33 41/45/49 SLEEVE WITH A DIAMETER THE SAME AS, LARGER THAN. THE REAMED HOLE. REFER TO TABLE 202. MACHINE THE DIAMETER OF THE RESPECTIVE 115951341403 SLEEVE SUCH THAT ITS FINAL DIAMETER IS 0. 0030-00060 LESS THAN THE FINAL DIAMETER OF THE REAMED HOLE. LOWER SLEEVE AS NEEDED CRES BAR PER AMS 5629, CONDITION H1000. FOR USE ON VERTICAL BORE LOCATIONS (-3 SLEEVE INSTL) ONLY. SEE FIGURE 204 FOR PART DIMENSIONS. AS AN ALTERNATIVE, IT IS ACCEPTABLE TO PROCURE A SLEEVE WITH A DIAMETER THE SAME AS, OR LARGER THAN. THE REAMED HOLE. REFER TO TABLE 203. MACHINE THE DIAMETER OF THE RESPECTIVE 11598341403 SLEEVE SUCH THAT ITS FINAL DIAMETER IS 00030-00060 LESS THAN THE FINAL DIAMETER OFTHEREAMEDHOLE. UPPER SLEEVE CRES BAR PER AMS 5629, CONDITION H1000. FOR USE ON VERTICAL BORE LOCATIONS (-3 SLEEVE INSTL) ONLY. SEE FIGURE 205 FOR PART DIMENSIONS. AS AN ALTERNATIVE, IS ACCEPTABLE TO PROCURE A 11593841403-311-351-39 SLEEVE WITH A DIAMETER THE SAME AS, OR LARGER THAN. THE REAMED HOLE. REFER TO TABLE 203. MACHINE THE DIAMETER OF THE RESPECTIVE 11598341403 SLEEVE SUCH THAT ITS FINAL DIAMETER IS 00030-00060 LESS THAN THE FINAL DIAMETEROFTHEREAMEDHOLL DOCUMENT NO. 681440573 2001 REVA PageSoflS GWHI SERVICE LETTER TABLE 202: Alternative Repair Sleeves for Procurement at the Horizontal Bore Locations (-1 Sleeve EQUIVALENT SLEEVE PIN SLEEVE LENGTH (INJ SLEEVE ON.) 11151334831143.333531153?) 1-44 mac-.8740 1-44 9017-9027 ?44 9330-9340 1-44 saw-.9652 1-44 sass-.9965 TABLE 203: Alternative Repair Sleeves for Procurement at the Vertical Bore Locations (-3 Sleeve Inst!) EQUIVALENT SLEEVE PIN SLEEVE LENGTH SLEEVE DIAMETER aN.) 1159534140341 (LOWER) . 1159334140341 (UPPER) 1'30 3730-3740 1159534140345 (LOWER) 11595341403455 (UPPER) 13? 9017-9027 11593134140349 (LOWER) 11595341403-39 (UPPER) 1-30 9330-9340 K. Finish the repair sleeves by passivatiOn per AMS 2700. L. Fluorescent Penetrant inspect the repair sleeves to ensure there are no defects on the surface. Use Type I, Method A, Level 3 sensitivity. Developers shall be Form A or D. Cleaners shall be Class 2. More sensitive procedures may be used. For aircralt, refer to NDT manual Chapter 01- 00-10 and ASTM 1417. For Gl [598 aircraft, refer to AMM 20-80-00 and ASTM E1417. M. Assemble the repair sleeves. Winglet Attachment Fitting, and the wing plank/winglet. N. Install repair sleeves at the reworked hole locations with Type VI Corrosion Inhibiting Compound (CIC). Refer to Corrosion Prevention Control Manual, Chapter 20-53-00. 0. Install l65?( screws (preferred) or screws (alternative) at the reworked bore location with Type VI Corrosion Inhibiting Compound (CIC). See Table 204 to determine screw grip length NOTE: Only CRES screws shall be installed through CRES repair sleeves. (INSTRUCTIONS CONTINUED ON THE NEXT PAGE) DOCUMENTNO. REV A Page 6 of 13 wastneamt A GENERAL DYIIAMICB SERVICE LETTER TABLE 204: CRES Attach Screw Grip Length. HOLE 0 GRIP LENGTH HOLE 9 GRIP LENGTH EFFECTIVITY 1-999 1.999 1 41 1000-3999 9 43 1000-3999 4001-SUBQ 4001-st 1-999 1.999 42 1000-3999 10 41 1000-3999 4001-51130 4001-st 1-999 65 1-999 43 1000-3999 11 1000-3999 4001-5111302 5?5 4001-3111312 W99 58 1-999 42 1000-3999 12 1000.3999 4001-3111312 5? 4001.513) 1-999 51 1-999 40 1000-3999 13 10003999 4001-st 5? 4001.st 1-999 65 1-999 42 1000-3999 14 1000-3999 4001-SUBQ 67 40mm 1-999 58 1-999 43 1000-3999 1 5 1000,3999 4001-st 60 4001 1-999 51 1-999 43 1000-3999 15 1000.3999 4001.3an 52 4001-5030 The end of the screw is to be installed 0000-0060 inch recessed from the end of the repair sleeve. Refer to Figure 206. NOTE: It is acceptable to substitute the next grip length (longer or shorter) to meet this requirement. . Aerodynamic seal the repair sleeves and screws as given in SRM 51-14-00. Each reworked hole location must be documented in aircraft records as follows: A . ?7 OZ 0 @93- REWORKED PER 681405732001" .3 7i 96139929 Rewomzoaons DIAMETER . P69 0:0 L005 732.cot-l HOLE LOCATIONNO. Examples: 6L-l.0000 Reworked per No. 6 on LH side, hole diameter reworked to 1.0000 inches) 1111-03390 Reworked per GSL405732001-3 (Hole No. 11 on RH side, hole diameter reworked to 0.9390 inches) EDIE: Ifa hole location was not reworked from its original speci?cations or con?guration, no additional documentation is required. Restore the aircraft to an airworthy condition. DOCUMENT NO. REVA Page'lofls GW SERVICE LETTER 115911140701 (REF) ON 115911130701 (REF) ON SEE FIGURE 202 FOR THE ?1 SLEEVE INSTALLATION FOR HORIZONTAL BORE LOCATIONS (HOLES shag) INSTALLED THROUGH THE EN HOLE EF AND WINGLET FITTING (REF) . #5 (REF) HOLE #2 (REF) HOLE #10 (REF) HOLE #1 (REF) HOLE g9 (REF) HOLE #5 (REF) (as? HOLE #12 REF :y 1159111.!40700 (REF) ON 1159WMSO700 (REF) 0N wedges v/ 0 4? HOLE :11 (REF) HOLE #15 (REF) HOLE #15 (REF) HOLE (REF) FWD SEE FIOORE 203 FOR THE ?3 SLEEVE INSTALLATION FOR BORE LOCATIONS (HOLES ((11-416) INSTALLED THROUGH WINGLET ATTACHMENT FITUNG THE PUNK AND WGLET (LEFT SIDE SHOWN. RIGHT SIDE OPPOSITE) (REF) FIGURE 201 DOCUMENT NO. 681105732001 REV A Page 8 of 13 MET 57A am SERVICE LETTER 15.00 HOLEIH ,1 1 ?m -- . -.--.. -.. a LlHOLEJB J?hl. ?.375 1159m3Wm (REF) 0N Gum/B (REF) SLEEVE INSTALLATION . HORIZONTAL BORE LOCATIONS. (VIEW LOOKING OUTBOARD, NORMAL T0 LH mom. AI WINGLET ATIACH FIGURE 202 DOCUMENTNO. REV A Pug: 9 of 13 SERVICE LETTER (REF) ON nsswumoo (REF) ON HOLE i15\ HOLE -3 SLEEVE INSTALLATION VERTICAL BORE LOCATIONS (VIEW LOOKING DOWN. NORMAL T0 U-i UPPER WING PLANK, AT WINCLET ATTACH FITTING) (WENG PLANK STRUCTURE REMOVED FOR CLARITY) FIGURE 203 DOCUMENTNO. GSIAOSTSZODI REV A Page 10 of 13 01??th SERVICE LETTER ?4 v.43 1394- 1.23? 1.227 DIA 010 [Es-Zoos DIA 1 1 CONICAL SURFACE 005 015 2 PL 39 '094 A . . 59* 0111 . 1 .575 DIA DIAMETER TO BE 0.131313114311513 LESS THAN THE FINAL DIAMETER OF THE REAMEU HOLE DIA 2719?3799 1 90' .535 DIA F2, TAP 1112544 DEIEJ PD 2554?2891:: @1005 DIA -005 50$ 1.114 (PART ~11 11190111313 SLEEVE 1.80 (PART ~15 LOWER SLEEVE TO OMET NOTED COUNTERBORE SLEEVE 131-1 -1 SLEEVE WSTALLATIDN, HOLES #14101 LOWER s: EEVE (USFD ON -3 SLEEVE HOLES i1111?11161 .005 -.020 (9314* 1.237 1.227 DIA (REF) FIGURE 204 DOCUMENTNO. GSIAOST32001 REV A Page 11 0113 SERVICE LETTER A GENERAL DVNAHICS [2?le 1.227 .005 DIA CONICAL SURFACE E: .094 Egg; .523 DIA I 375mgr?It?? \s 1y firf? i 1/ 7 ?5 DIAMETER TO BE omsoumoao .545 DIA 0 L. H.005 \q ?71040?050 LESS THAN THE FINAL DIAMETER CHEMICAL SURFACE x; OF THE REAMED HOLE A .5012: 1.44 SLEEVE LSD ?17 UPPER SLEEVE I: TO NOTED 5? OUTBOARD SLEEVE (USED ON ?1 SLEEVE HOLES UPDER SLEEVE ON ?3 SLEEVE LNSTALLATIOH, DLES .005 ?.020 7E 1275 227 Dik (REF) 1 a" DETAIL FIGURE 205 DOCUMENTNO. REV A Page 12 of 13 WW SERVICE LETTER ATTACH SCREW (REF) REPAIR SLEEVE - A WINGLET (REF) - WING PLANK (REF) FIGURE 206 Fred Karst Director, Service Engineering DOCUMENT N0. REV A Page I3 of 13 . Work Order Detail A GENERAL DYNAMICS COMPANY Repair Station: SE 500 Rd. Savannah, Georgia 31407 Work Order: CS547993 Title: STEVENS AVIATION, INC. Department: IS TO - W0 (GAC) Customer: STEVENS AVIATION, INC. Contact Name: RICK SCREEN StatuS: Open Address: BILLING ADDRESS Account Code: C8449 P-O- #1 Squawk: 1.1 P.O. BOX 310 Target Date: 3/19/2018 Invoice Created: 3/15/2018 Date Closed: Posted: Aircraft: GIV 1425 Reg: P4-NMD Company: STEVENS AVIATION Acct. Code: C8449 P.O. GYH-P018-01537 Status: NON Contact: RICK SCREEN Phone: 912.663.9466 Mobile: Email: VisNetic 2720700 Opened By: J. Inscho Warranty: NO Airframe GIV MSG3 Part GIV MSG3 Serial 1425 Winglet bore scratch . Discrepancy? Please see Winglet bore hole with scratch inside it. Status: Completed Resolution: Engineering Disposition: I) It is acceptable to repair the LH RH Winglet discrepant bores in accordance with Service Letter GSL405732001 Rev. "Winglet Attachment Fitting Bore - Repair". . 2) Service Letters (GSL) are classi?ed as a Manufacturer's Service Document and are governed by Advisory Circulars 20-176A and AC 120-77. Completing a repair per a Service Letter is similar to completing a repair per the Structural Repair Manual No serial number speci?c FAA Form 8100-9 is required and will not be provided in support of a GSL repair. The Engineering (Source) Data for this Service Letter has been shown to comply with the applicable FAR's and is FAA Approved. Engineering source data is retained by as proprietary data. Sent by Mark Wilson 3/16/18 Signed of 3/16/2018 By: WILSON, DOLPHUS-309040 Completed: 3/16/2018 By: WILSON, DOLPHUS-309040 GAC_WorkOrderDetail.rpt v2.3 Printed: 3/16/2018 Ref: 209 Page 1 of 2 Work Order Detail GENERAL DYNAMICS COMPANY Repalr Station: SE 500 Rd. Savannah, Georgia 31407 Work Order: CSS47993 Title: STEVENS AVIATION, INC. Department: IS TO - W0 (GAC) Step: Description' Engineering Disposition: 1) It' 1s acceptable to repair the LH RH Winglet discrepant bores' 1n accordance with Service Letter GSL405732001 Rev. "Winglet Attachment Fitting Bore? Repair". 2) Service Letters (GSL) are classi?ed as a Manufacturer' 5 Service Document and are governed by Advisory Circulars 20- 176A and AC 120-77. Completing a repair per a Service Letter is similar to completing a repair per the Structural Repair Manual No serial number speci?c FAA Form 8100-9 is required and will not be provided in support of a GSL repair. The Engineering (Source) Data for this Service Letter has been shown to comply with the applicable FAR's and is FAA Approved. Engineering source data is retained by as proprietary data. Status: Completed Comments/notes: Signed of 3/16/2018 By: TITUS, SHAW-319956 Completed: 3/16/2018 By: TITUS, SHAW-319956 End of Report ted: GAC_WorkOrderDeta11.rpt v2.3 Page 2 of 2 mm Ra? 209 Form Approved OMB. No. 2120-0018 FOR INSTRUCTIONS - Print or type. Do not write in shaded areas; these are for FAA em AIRWORTHINESS CERTIFICATE II and VI oerl as appIchale 1. REGISTRATION MARK AIRCRAFT 811le (Make!) 3. AIRCRAFT Leone. DESIGNATION 4. CODING t: 2 N425GA Aerospace G-IV 2000 5. AIRCRAFT SERIAL NO. 6. ENGINE PIN-1E {Make} 7. ENGINENODEL DESIGNATION 1425 Rolls:Royce Tay Mk 611-8 3. NUMBER OF ENGINES 9. PROPEILER 1o. PROPELLERLIODEL DESIGNATION 11. Two NIA APPLICATION IS HEREBY MADE FOR: {Checkappfcahfe Gems) A 1 STNIDARD mam (Mm $189007 I IUTIUTY I IACROBATIC ITRANSPORT IGUDER BALLOON 3 CERTIFICATE (Check Eems) 2 LUIITED 1 5 PROVISIDNN. 2 1 AGRICULTURE AND PEST CONTROL 2 AERIAL SURVEYING 3 AERIALADVERTISBIG 3 RESTRICTE) operafonfs} 4 FOREST maze mnsena'onj 5 PATROLIJNG WEATHER CONTROL robe Dondueted) 7 CARRIAGE OF CARGO 0 OTHER (5mm 1 RESBIRCH AND DEVEOPIJENT AMATEUR BUILT 3 emamoN 4 BCPERIIJENTAL (Mare 012212501115) 4 RACING 5 CREW TRAINING 3 to be conducted) 0 FAR 1 SPECIAL FUGHTPERI-lrf?nafmfe 2 EVACUATE FRDNAREAOE INPENDING DANGER 5 operab'on to becanduded, than 3 OPERATION IN EXCESS OF LMJUM CERTIFICATED TAKE-OFF WEIGHT DompfeteSee?on Wort/Ila: 4 DELIVERING 0R BIPDRT 5 FUGHTTESTING . on reverse ?115) 6 CUSTOMER DEMONSTRATION FLIGHTS I 3 I MULTIPLE CERTIFICATE Opexafun'and 'Standard'or Wiasappl?mh'a) A REGISTERED an Weofafrua?regmmn) LFDEALER. CHECK HERE 11.03.15 AEROSPACE CORPORATION ADDRESS PO BOX 2206 THIS D-06 SAVANNAH GA 31402-2206 3. AIRCRAFT CERTIFICATION BASIS {Check appfwae blocks and compfeie Earns as in?ated? AIRCRAFT 0R TYPE CERTIFICATE DATA SHEET {Gire No DIRECTIVES {Cheek 1135' compred 1-511: and gm 2 No.) fefestAD No.) A12EA, REV 22 THROUGH SUMMARY 2001-10 AIRCRAFT LISTING page numberrs? SUPPLEMENTAL TYPE CERTIFICATE of each STC hmrporaieo) fg? SEE ATTACHED c. MRCRAFTOPERATIONANDIMINTETWICE RECORDS 3 CHECK IFRECIORDS INCORPLIMICE TOTALAIRFRME HOURS (ENerhaurs rarms'nceeucemse 5' VITH 3 issued onenened} 9.2 0.0 D. CERTIFICATION - I hereby that I am the regIstered Gamer (or his agent) of the aircraft desmbed above, that is registerd With the Federal Aviation Administration in accordance with Section 501 of the Federal Aviation Act of 1958, and applizzble Federal Aviation Regulations. and that the aircraft has been inspected and is and eligible for the ain-mrthiness certi?wte requested. DATE OFAPPUCATTON SIGNATURE 5L7 22 MAY 20 131 STANLEY G. GODEK. JR. 0c - A. THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND BY (Camp'ete This seefan 01131? FAR 21.183111) apples) FAR PART121 OR 127 CERTIFICATEHOLDER {Gale CERTIFICATED MECHANIC {Give CERTIFICATED REPAIR STATION (63:8 We 2 691135322 No.) 3 CemfmieNo.) 6 ND.) 2 .9. 8 2 '5 ofme) 3 5 5 DATE TITLE SIGNATURE {Check NJ. amicable blocks miemsA we; THE CERT FICATE REQUESTED A. I rm Theme antral! aesmbed as Seam or VII meets requemaes Ia 4 ANENDUENT CR or- CURRENT NEGG GATE 2 3. Mspemonioraspeaakgmpem?ur?ermw FAA INSPECTCR FAR DEGGNEE u. ul waseonduded by CERWTE HOLDERUNDER 12512121, 1271:1135 FAR 145 ?d Gamer OFFICE ease ss j] SIGNATURE 5/26/01 4 1?1 1 Bi?. BARF 7195395?? FAA Form 8130-6 (6-86} EDITION (COMPUTER GENERATED) A. MANUFACTURER VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT TEST NAME ADDRESS ?3 3 5 3, PRODUCTION BASIS {Check app?cable item) PRODUCTION CERTIFICATE {Give production oer??mle number) ?g TYPE CERTIFICATE ONLY APPROVED PRODUCTION INSPECTION SYSTEM 0. GIVE OUANTIIYOF CERTIFICATES REQUIRED NEEDS DATE OFAPPLICATION NANEANDnneranormel SIGNATURE A. OF AIRCRAFT REGISTERED OWNER ADDRESS BUILDER (Make) MODEL SERIAL NUMBER REGISTRAIION MARK 8. DESCRIPTION OF FLIGHT CUSTOMER DEMONSTRATION FLIGHTS I FROM TO VIA DEPARTURE DATE DURATION C. CREW REQUIRED TO OPERATE THEAIRCRAFT AND ITS EQUIPMENT IPILOT ICC-PILOT INAVIGATOR 1 0mm (SW) D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS: E, THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION [Use a?aahment?'necessam F. CERTIFICATION - I hereby certify that I am the registered owner (or his agent) of the airora? described above, that the airera?. is registered with the Federal Aviation Administration in accordance with Section 501 of the Federal Aviation Act of 1958. and the applicable Federal Aviation Regulations, and that the aircraft has been inspected and is air-worthy for the ?ight described. DATE NAME (Printortype) SIGNATURE A. G. - a} 91.9 asapp?cabie . H. e. (Mummers? .. 2: c. I. O. CurreatWeightand 31mm FAR 2mmFAR 21.191 WW - @Pa/ UNITED STATES LIP AMERICA DEPARTMENT OF TRANSPORTATION - FEDERAL AVIATION ADMINISTRATION . SPECIAL AIRWORTHINESS CERTIFICATE AI PURPOSE RESEARCH AND DEVELOPMENI MANU- NAME FACTUFIEFI ADDRESS FROM NIA FLIGHT To MA 4235A SERIAL NO. BUILDER UuIIsteam Aerospace L0. MODEL U-l DATE OF ISSUANCE ?3129?? EXPIRY ?0147101 OPERATING LIMITATIONS DATED ARE A PART OF THIS CERTIFICATE SIGNATURE OF FM am A VE DESIGNATI FFICE NO. Bill P. McDo?Elina Z: Any alteration. reproduction or misuse of this certlficate may be punishable by a-Iine not exceeding $1.000 or imprisonment no: exceeding 3 years. or both? THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. FAA FORM 8130?7 (10/82) SEE REVERSE SIDE This airworthiness certi?cate is issued (Rider the authority of the Federal Aviation Act of 1958 and the Federal Aviation Regulations (FAR). This airworthiness certificate authorizes the manufacturer named on the reverse side to conduct production flight tests. and only production flight tests. of aircraft registered in his name. No person may conduct production flight tests under this certificate: (1) Carrying persons or piropertry for compensation or hire: andfor (2) Carrying persons not essential to the purpose of Iig t. This airworthiness certificate authorizes the flight specified on the reverse side for the purpose shown in Block A. This airworthiness certificate certifies that. as of the date of issuance. the aircraft to which issued has been inspected and found to meet the requirements of the applicable aircraft does not meet the reqUirements of the applicable comprehensive and detailed airtvorthiness code as provided by Annex 8 to the Convention On International Civil Aviation. No person may operate the aircraft described on the reverse side? (1) except in accordance with the applicable FAR and in accordance with conditions and limitations which may be prescribed by theAdministratoras part of this certificate: (2) over any foreign country without the special permission of that country. Unless sooner su rrendered. suspended. or revoked. this airworthiness certi?cate is effective for the duration and under the conditions prescribed in FAR Part 21. Section 21.181 or 21217. UNI TED STATES OF AMERICA - DEPARTMENT OF AVIATION ADMINISTRATION I STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND 2 MANUFACTURER AND MODEL 3 AIRCRAFT SERIAL 4 REGISTRATION MARKS NUMBER . - . MEGA Gl?fstream G-IV 14-25 g/?Itransport 5 AUTHORITY AND BASIS FOR ESSUANCE 1 Thssaurworthmess IS Issued pursuant to the FederaIAvratIon Act of aIrcraft to Web Issued has been Inspected and found to conIorm to the operatlon. and has been shown to meet the requtremenls of the apphca provrded by Annex 8 to the Conventlon on InternatIonaI Cm] Awat i ExceptronS' None Ines that.as ot the dale obssuonce. the mIIcate therefor. to be In common for safe omprehenswe and detaIted aInvonhInes?codeas . except as noted hereIn 6 TERMS AND CONDITIONS Unress sooner surren spended. revoked. or a terhIInaIIon date Is otherwIse estabIIshed by the IhIs aIrwothIness cemhoa effectrve as long as the maInterIance. preventatwe maIntenance. and alterations are performed In accordance 1.43. and 91 of the FederalAVIatI'on Regulatrons. as appropnate. and thealrcraft Is regIstered Inthe UnIted States DATE OF ISSUAN FAA REPRESENTATIVE DESIGNATION NUMBER 9/ 00 Lewis c. Watkins 22., Mm commune Meratron. reproduchon. byafmenotexceedmg SI H000 years or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS FAA Form 3100-2 (8.82, r: us. GOVERNMENT PRINTING OFFICE: 1991 - seems UNITED STATES OF AMERICA DEPARTMENT OF AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE I NATIONALITY AND 2 MANUFACTURER AND MODEL 3 AIRCRAFT SERIAL 4 ?iQAreconY REGISTRATION MARKS NUMBER NZIZSGA G-IV 1425 Transport 1 5 AUTHORITY AND BASIS FOR ISSUANCE TnIs aInvonhInesscerIIfIcaIeIs Issued pursuant lo the Federal AwaIIonAcI oI I9583nd thal. 3501 me dale oI me aIrcraft Io Issued has been Inspected and Iound to conform Io Ihe tyne therefor. to be In condmon for safe operanon. and has been shown to meal Ihe requ-remems 01 me appIIcabIe comprehenswe and aIn-zonmness code as prowded by Annex 8 to the ConvenIIon on InternalIonal Cm! Awaken except as no:ed harem Excepnons None 5 TERMS AND CONDITIONS Unless sooner surrendered suspended. revoked? or a Ierhunahon dale Is omen-use estabhshed by me AdrmnIsIranr. IhIs aIrwonhmess Is e?ecIIve as Iong as the mamlenance. preventam'e mamtenance, and alteralrons are performed In accordancewuh PansZI ?manual of [he as appropnale andthe reglsjeredll'llhe Umled States, DATE OF ISSUANCE FAA REPRESENTATIVE DESIGNATION NUMBER . . . I- . 9/27/00 Lens C. Watkms "an: L- 575;, In, 0DARF100127CE Any allerauon. reproducnon. or mIsuse oI IhIs may be pumshabIe bya {me not exceedmg I .000. or Imnnsonmenr not exceedmg 3 years, or both THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS FAA Form 31 00-2 6.82, II- u.s. GOVERNMENT PRINTING OFFICE: 1991 - ssezza 009V OPERATING LIMITATIONS ?Research and Development? Make: Aerospace Corp. Model: G-IV Serial Number: 1425 Registration Number: N425GA Issuance Date: 05/29/01 Expiration Date: 06/29/01 (1) No person may operate this aircraft unless the FAA Form 8130-7, Special Airworthiness Certi?cate is displayed at the cabin or cockpit entrance so that it is visible to passengers or crew. (2) No person may operate this aircraft for other than the purpose(s) of Research and Development to accomplish the ?ight operation outlined in Aerospace Corp. Program Letter, dated May 22, 2001, describing compliance with FAR and made available to the pilot-in- command of the aircraft. Additionally, this aircraft shall be operated in accordance with applicable air traffic and general operating rules of FAR Part 91, and all additional limitations herein prescribed under-the provisions of FAR (3) All ?ights of this aircraft shall be conducted within the geographic area described as follows: Within the US. main land boundaries, from KDAL, Dallas, TX. (4) This aircraft shall not be operated unless it is maintained in accordance with the appropriate manufacturer?s recommendations. The owner/operator shall select, establish, identify, and use an inspection program as set forth in FAR and This inspection program shall be recorded in the aircraft maintenance records. (5) The pilot-in-command of this aircraft must, as applicable, hold an appropriate category/class rating. If required for the type of aircraft to be ?own the pilot in command must also hold either an appropriate type rating or Letter of Authorization issued by a FAA Flight Standards District Operations Inspector. (6) This aircraft may be operated under Instrument Flight Rules (IFR), and must be properly equipped for instrument ?ight in accordance with 91.205. (7) No person may operate this aircraft for carrying persons or property for compensation or hire. (8) No person may he carried aboard this aircraft during ?ight unless that person is essential to the purpose of the ?ight. (9) The pilot in command this aircraft shall advise each person carried of the experimental nature of this aircraft, and explain that it does not meet the certi?cation requirements of a standard certi?cated aircraft. (10) This aircraft shall contain the placards, markings, etc., (or other operating instructions developed for an STC modi?cation) as required by FAR 91.9. (11)Tl1is aircraft is prohibited from aerobatic ?ight; an intentional maneuver involving an abrupt change in the aircraft?s attitude, an abnormal attitude, or abnormal acceleration not necessary for normal ?ight. Page 1 of 3 EXPERIIVIENTAL OPERATING LIMITATIONS (cont?d) (12) The cognizant FSDO must be noti?ed, and its response received in writing, prior to ?ying this aircraft after incorporation Of a major change as defined by 21.93. (13) This aircraft shall not be operated for glider towing or parachute jumping operations. (14)No person shall operate this aircraft unless within the preceding 12 calendar months it has had a condition inspection performed in accordance with the scope and detail of Appendix to Part 43, or other FAA approved programs, and found to be in a condition for safe Operation. This inspection shall be recorded in the aircraft maintenance records. (15) Only FAA-certi?cated mechanics with appropriate ratings as authorized by FAR 43.3 may perform insPections required by these operating limitations. (16) Inspections shall be recorded in the aircraft maintenance records showing the following or a similarly worded statement: certify that this aircraft has been inspected on (insert date) in accordance with the scope and detail of FAR Part 43, Appendix D, or other FAA approved programs and found to be in a condition for safe operation.? The entry will include the aircraft total time?in service, the name, signature, and certi?cate number and type of certi?cate held by the person performing the inspection. (17)If aircraft, engine, or propeller limitations are exceeded, an appr0priate entry will be made in the aircraft records. (18) This aircraft shall not be operated unless it is maintained in accordance with the requirements of part 43, Maintenance, Preventative Maintenance, Rebuilding, and Alteration. (19) This aircraft must display the word EXPERIMENTAL in accordance with 45.23 (20)The pilot in command of this aircraft shall notify the air traf?c control tower of the experimental nature of this aircraft when Operating into or out of airports with operating air traf?c control towers. The pilot in command shall plan routing that will avoid densely pOpulated areas and congested airways when operating VFR. (21) This aircraft does not meet the requirements of the applicable, comprehensive, and detailed airworthiness code as provided by Annex 8 of the International Convention of Civil Aviation (ICAO). The owner/Operator of this aircraft must obtain written permission from another country?s Civil Airworthiness Authority (CAA) prior to Operating this aircraft on or above that country. That written permission must be carried aboard the aircraft together with the U.S. airworthiness certi?cate, and upon request, be made available tO an FAA inspector or the CAA in the country of Operation. (22)Aircraft instruments and equipment installed and used under 91.205 must be inspected and maintained in accordance with the requirements Of parts 43 and 91. Any maintenance or inspection of this equipment must be recorded in the aircraft records. Page 2 of 3 EXPERIMENTAL OPERATING LIMITATIONS (cont?d) (23)App1ication must be made to the FAA certi?cating o?ice for any revision to these operating limitations. (24)App1ication must be made to the geographically responsible FSDO for any revision to these operating limitations. MW 51 Date Page 3 of 3 A GENERAL DYNAMICS COMPANY FAA CSR-VJ1R560K 7350 Cedar Springs Rd. Dallas, 7X 75235 22 May 2001 Bill P. McDonald DARF71053QSW Mr. McDonald, Aerospace Corporation, located at Love Field in Dallas, Texas is hereby submitting a request for issuance of a Special Airworthiness Certi?cate, Experimental - Research and Development for aircraft model G-IV, serial number 1425, registration number N425GA. This request is required in order to complete a ?ight test on the project listed below: Executive Cabin Interior, SIN 1425: STC Project No. GACD 01-07 DAS Certi?cation of the STC Project referenced above requires ?ight-testing to verify the in-?ight safety and operation of the systems installed. This ?ight test will not present a hazard to public safety. This aircraft is in compliance with CFR Title 14, Chapter 1, Sub-chapter C, Part 36 - Noise Standards, Amendments 36-] through 36-12. We estimate a total of one (1) test ?ight to be conducted under FAR All ?ight tests will originate and terminate at Love Field (KDAL), Dallas, TX. In the event that we are required to conduct additional ?ights, we will notify you with an explanation of the purpose of the ?ight. If you have any questions, please do not hesitate to contact me at (214) 902-7724. Respectfully, Stanley G. Godek, Jr. Quality Control Analyst GAC Dallas, TX MAY-23-91 16 32 ID: PAGE 2?sh: at; to 01W mperformDAR funcnons. . W9 - France! Nnuiam?fs): 01 7?9 4. =9an 72.52:; dx?? 1% . .mwt. hm/ym?T?w?o ?a/?zcem {71:1 Estimwd ?merequired [:2chme inc function?): A?ivi issuiwdulndm "nc'nz 255/1510! . . I [f 14431551.. 9/ Zwi?z '74! t. Bi}! Manama WNW mumidm??ed imam As arm]: ofthe: Speci?c to this 0150:: within seven [my Maw Din-1 .MmungW-m-? Date: {[737 2/2 -.- PAGE MAY-ZB-QI 18:32 ID- - 4 AGER 0 SW. This is in mints: a?ho?z?axinn-lopaform DAR functions. The functions main 61955 - - Project '1 0! 4- I?km 72.24654? ?f?remt. .. 74? ?a/?zam 5-11"; 57? Eslimawd gamma [tritium-1h: {misting}: 4/64: Ac?vily is schedtded no bdgia 0:11: 1 Location whim: rumsmn?bemfmned: Z7 Applinm's?mm: Tcth?f-Z) 9?33" 7724/ $17474!? it? M'a ?ak-u 9/ Zd/? '74? 7522? Dag/Li/c/ The above-idmti?ed DAR is authorized to perronn 15: Wind Marianna}. All qudrcd As areal}: ofthc speci?c and must bcsuhmiucd to this of?ce within sum days nfnomplishmeqt. 421/ 2 [may Ww:%w%w 5 .Manugcr.sw-MIDo-42 Daze: Form Approved OMB. NO. 2120-0018 APPLICATION FOR INSTRUCTIONS - Print or type. Do not write in shaded areas; these are for FAA use 0 I . Submit ori inaI ml to an authorized FAA 55m AIRWO RTHIN ESS spaoeni: required, Ugo an attichment. For special m'mn CERTIFICATE II and VI oerl as appIchaIe 1. REGISTRATION MARK 2. AIRCRAFT WINE Intake} 3. AIRCRAPTMODEL DESIGNATION 4. YR MFR FAA N425GA Aerospace 2qu 5. AIRCRAFT SERIAL N0. 6. ENGINE NAME (Make) 7. ENGINE MODEL DESIGNATION 1425 Rolls-Royce Tay Mk 611-8 5Ll5?0/ a IB. NUMBER OF ENGINES 9. PROPELLER NAME (Make) 10. PROPELLER MODEL DESIGNATION 11. AIRCRAFT '3 Two IA IIMPORT APPUCAIION IS HEREBY MADE FOR: (Check apptimbte items) A 1 STANDARD AIRWORTHINESS CERTIFICATE {Inwcate category) I I NORMAL I I UTILITY I I ACROBAIIC I I TRANSPORT I I GLIDER I I BALLOON a SPECIAL AIRWORTHINESS CERTIFICATE (Check appropriate items) 2 LIMITED 1 CLASSI 5 PROVISIONAL 2 CLASS a 1 AGRICULTURE AND PEST CONTROL 2 AERIAL SURVEYING 3 AERIAL ADVERTISING g. 3 RESTRICTED (Indicate operationfs} 4 FOREST {If-Wife conservation) 5 PATROLLING 6 WEATHER CONTROL 5 to be conducted) 7 CARRIAGE OF CARGO 0 OTHER (Specify) 1 RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION 4 MERIMENTAl-tlndicate opemtionts) 4 RACING 5 CREWTRAINING MKTSURVEY to be conducted) 0 TO SHOW COMPLIANCE WITH FAR =5 1 FERRY FLIGHT FOR REPAIRS. ALTERATION S. MAINTENANCE OR STORAGE SPECIAL FLIGHT PERMIT {Indicate 2 EVACUATE FROM AREA OF IMPENDING DANGER 5 Operation to be conducted, then 3 OPERATION IN EXCESS OF MAXIMUM CERTIFICATE) WEIGHT complete Section Vior VII as 4 DELIVERING OR EXPORT I 5 I I PRODUCTION FLIGHTTESIING applicable on reverse side) 6 CUSTOMER DEMONSTRATION FLIGHTS I 5 I MULTIPLE AIRWORTHINESS CERTIFICATE 'Restricted Operation' and 'sendard'ar 'Linrited', as apprebre) A, REGISTERED OWNER {As shown on certrI?iwte otaircratiregistratr'an) IF DEALER, CHECK HERE NAME AEROSPACE CORPORATION ADDRESS PO BOX 2206 M18 D-06 SAVANNAH GA 31402-2206 5, AIRCRAFT CERTIFICATION BASIS {Check applicable blocks and complete Hams as indicated) AWOME DATA (Give No Am {Checkifall AD's compliedTrriTh?and give 2 and Revision No.) IatestAD No.) A12EA, REV 22 THROEH SUMMARY 2001-10 3 AIRCRAFT LISTING {Give page numbeds? SUPPLEMENTAL TYPE CERTIFICATE {List number of each 870 incorporated) r: SEE ATTACHED C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS i 5 CHECK IF RECORDS IN COMPLIANCE TOTAL AIRFRAME HOURS EXPERIMENTAL ONLY (Enterhours ?own since team a WITH FAR 91.417 3 issued arrenewed) 18.0 3.3 D. CERTIFICATION - I hereby certify that lam the registered owner (or his agent) of the aircraft described above, that is regis- erd with the Federal Aviation Administration In accordance with Section 501 of the Federal Aviation Act of 1958, and applicable Federal Aviation Regulations, and that the aircraft has been inspected and is airworthy and eligible for the airworthiness certi?cate requested. A DATE OFAPPLICATION NAMEAND TITLE (Printortype) SIGNATURE I 04 JUNE 2001 STANLEY G. GODEK. JR. 0C ANALYST (5 A, THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY (Complete this section onty if FAR 21.183fd) applies) FAR PART 121 OR 127 CERTIFICATE HOLDER (Give CERTIFICATED MECHANIC {Give CERTIFICATED R-EEIIR STATION (Give Ce 2 Certi?cate No.) 3 Certi?cate NO.) No.) a AIRCRAFTMANUFACW name arm) 2 2 5 2' DATE TTILE SIGNATURE {Check ALL appIicable blocks in HemsA and a; .: A. I?ndthatthe aircratt described InSec?ootorVit meets Iet~ 3 we. e. . CERTIFICATE Inspection Tor especial EAADESIGNEE Ct i. - :3 "as ?me? by . :3 Hom?i?tt??R? I - WI w? I FAR 145 DATE DISTRICTOFFICE . ?55: giro: PAAINSPEOTORS . 0/4/01 a . i ?If. FAA 8130-6 (6-86) SUPESEDES PREVIOUS EDITION A. MANUFACTURER VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHTTEST NAME ADDRESS 5 3, PRODUCTION BASIS {Check item} PRODUCTION CERTIFICATE {Gitepmduc?on certi?catenumbea TYPE CERTIFICATE ONLY APPROVE) PRODUCTION INSPECTION SYSTEM CIVEOUANTITYOFCERTIFICATES REQUIRED FOR OPERATING NEEDS DATE OFAPPLICATION NAMEANDTITLE SIGNATURE A. DESCRIPTION OF AIRCRAFT REGISTERED OWNER ADDRESS BUILDER (Make) MODEL SERIAL NUMBER REGISTRATION MARK 8. DESCRIPTION OF FLIGHT CUSTOMER DEMONSTRATION FLIGHTS (Check FROM TO VIA DEPARTURE DATE DURATION C. CREW REQUIRED TO OPERATETHEAIRCRAFTAND EQUIPMENT IPILOT ICC-PILOT INAVIOATOR I D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS: E, THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION {Use attachment ffnecessary) -l hereby certify that I am the registered owner (or his agent) of the aircratt described above. that the aircraft is registered with the Federal Aviation Administration in accordance with Section 501 of the Federal Aviation Act of 1958, and the applimble Federal Aviation Regulations, and that the aircraft has been inspected and is airworthy for the ?ight Map: Remand Amt-am. FAA Fomt 337(Attach when ranked) .3. inspecfcn Recorded In A'Emt Records FAR described. DATE NAME ANDTTILE {Pnhtortype} SIGNATURE A. BNEISOORS and Madmgs comm with FAR G. Statementot Coniomtky, FAA Fonn8130v9wtach when recurred; :3 2 91.9 asepp??mbte H. Fetesgn Certi?cationbrtuponmalt Egg a. I. PrevsoDsAnwommess Certi?cate IssuedmAccordanOeth . Information AvaibblehAircra? PAR 214919,; (OtigfnalAtfachedl Current Ceru?cate issued In Accordance wan 3.183(3) CAR {Copy attached} 04%? UN STATES OF DEPARTMENT OF AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE NATIONALITY ANQ 2. MANUFACTURER AND MODEL 3 SERIAL 4. CATEGORY MARKS Aerospace Corp. N425GA G-IV 1425 Transport 5. AUTHORITY AND BASIS FOFI ISSUANCE This airworthiness certi?cate is issued pursuant to the Federal Aviation Act of 1958 and cert-ties that. as at thedate of issuance. the aircraft to which issued has been inspected and found to conform to the type certificate therefor. to be in condition for safe operation. and ha: been shown to meet the requirements of the applIcable comprehenswe and detaIIed code as prowded by Annex to the Convention on International Civil Aviation. except as noted herein. Exceptions: None 6. TERMS AND CONDITIONS Unless sooner surrendered. suspended. revoked. or a termination date is otherwise established by the Administrator. this airworthmess certificate is effective as long as the maintenance. preventative maintenance. and alterations are performed in accordance With Part521 . 43. anth of the Federal AviationRegulatIons. as appropriate. and theaircraft IS registered In theUnited States. A DATE OF ISSUANCE FAA REPRESENTATIVE DESIGNATION NUMBER Bill P. McDonald E. wk Anyalleratton. reproduction. or misuse of thiscertilIcate may be punishable by a fine not exceeding $1,000. or ImprIsonment not exceeding3 years. or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. FAA Form 8100-2 (8-82) 4: US. UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION - FEDERAL AVIATION ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE A EXPERIMENTAI PURPOSE SHOW COMPLIANCE TO THE REGULATIONS MANU- NAME FACTURER ADDRESS FROM FLIGHT TO 4256A .7 SERIAL NO. 14-43 BUILDER Gultstea?n CO. MODEL DATE OF ISSUANCE IV 03/51/01 EXPIRY OPERATING DATED 05/31/94 ARE A PART OF THIS CERTIFICATE SIGNATURE OFF RESENT DESIGNATION OR OFFICE NO. Wnald a impr' ment not exceeding 3 years. or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN A ORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. . FAA FORM 8130-? (10/82) I .SEE REVERSE SIDE reproduction or misuse of this certi?cate may be punishable by a ?ne not exceeding $1,000 or This airworthiness certi?cate is issued under the authority of the Federal Aviation Act of 1958 and the Federal Avnation Regulations (FAR). This airworthiness certificate authorizes the manufacturer named on the reverse side to conduct production flight tests. and only production flight tests. of aircraft registered in his name. No person may conduct production flight tests under this certificate: Carrying person's or property for compensation or hire: and/or (2) Carrying persons not essential to the purpose of the light. This airworthiness certificate authorizes the ?ight specmed on the reverse side for the purpose shown in Block A. This airworthiness Certificate certifies that. as of the date of issuance. the aircraft to which issued has been inspected and found to meet the requirements of the applicable FAR. The aircraft does not meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention On International Civnl Aviation. No person may operate the aircraft described on the reverse Side: (1) except in accordance with the applicable FAR and in accordance with conditions and limitations which may be preseribed by the Administrator as part of this certificate: (2) over any foreign country without the speCial permission of that country. Unless sooner surrendered. suspended. or revoked. this airworthiness certificate is effective for the duration and under the conditions prescribed in FAR Part 21. Section 21.181 or 21.21? ATTACHIVIENT 1. FAA FORM 8130-6 SUBMITTED 04 JUNE 2001, SIN 1425: INSTALLED THE FOLLOWING FAA APPROVED SUPPLEMENTAL TYPE CERTIFICATE SYSTEMS ON MODEL G-IV, SIN 1425, REGISTRATION NO. N425 GA. STC NUMBER SYSTEM TITLE SA2622NM SA2809SO SA283930 SA3850NM SA4286NIVI-D SA4291NM-D ST00248AT STOIO77CH-D ST01078CH-D ST09583 SC ST09667SC ST09789SC-D PRECISE FLIGHT PULSELITE CONTROL GLOBAL WULFSBURG AIRBORNE FLIGHT INFORMATION SYSTEM HONEYWELL LASERTRAK NAVIGATOR ROSEN Iv MONORAIL SUNVISOR SYSTEM STANDBY HORIZON INDICATOR WITH EMERGENCY ILS (BF GOODRICH 5) PROVISIONS FOR HEAD UP DISPLAY, HUD-2020 HONEYWELL GEC MARCONI SATCOM ANTENNA INSTL (HONEYWELL) AFT COMPARTMENT TOWBAR AFT COMPARTMENT STORAGE BOX INSTALLATION INSTALLATION OF ARTEX 406 EMERGENCY LO CATOR TRANSMITTER TCAS 2000 (HONEYWELL) CO CKPIT AREA MODIFICATIONS ROSEMONT ICE DETECTOR INSTALLATION CABIN INTERIOR THE FOLLOWING FAA APPROVED SUPPLEMENTAL TYPE CERTIFICATES ARE INCORPORATED IN CABIN INTERIOR SUPPLEMENTAL TYPE CERTIFICATE STC NUMBER SYSTEM TITLE SA2657SO SA3655NM-D SA3 ST00817LA-D ST02182AT-D ST02185AT-D ST0958 1 SC CLASS BAGGAGE COMPARTMENT LAVATORY SERVICE PANEL, AFT RS JUMPSEAT INSTL, FWD RADIO RACK INSTALLATION OF NORDAM AC OUSTICAL LINER OXYGEN SYSTEM EMERGENCY POWER SYSTEM INTERIOR EMERGENCY LIGHTS MSA WINDOW SHADES INSTALLATION (1) (2) (3) (4) (5) (6) (7) (3) (9) EXPERIMENTAL OPERATING LIMITATIONS ?Show Compliance to the Regulations? Make: Aerospace Corp. Model: G-IV Serial Number: 1425 Registration Number: N425GA Issuance Date: 05/31/01 Expiration Date: 06/30/01 No person may operate this aircraft unless the FAA Form 8130-7, Special Airworthiness Certi?cate is displayed at the cabin or cockpit entrance so that it is visible to passengers or crew. No person may operate this aircraft for other than the purpose(s) of Show Compliance to the Regulations to accomplish the ?ight operation outlined in Aerospace Corp. Program Letter, dated May 25, 2001, describing compliance with FAR and made available to the pilot-in-command of the aircraft. Additionally, this aircraft shall be operated in accordance with applicable air traf?c and general operating rules of FAR Part 91, and all additional limitations herein prescribed under the provisions of FAR All ?ights of this aircraft shall be conducted within the geographic area described as follows: Within the US. main land boundaries, from KDAL, Dallas, TX. This aircraft shall not be operated unless it is maintained in accordance with the appropriate manufacturer?s recommendations. The owner/operator shall select, establish, identify, and use an inspection program as set forth in FAR and This insPection program shall be recorded in the aircraft maintenance records. The pilot?in?command of this aircraft must, as applicable, hold an appropriate category/class rating. If required for the type of aircraft to be ?own the pilot in command must also hold either an appropriate type rating or Letter of Authorization issued by a FAA Flight Standards District Operations Inspector. This aircraft may be operated under Instrument Flight Rules (IFR), and must be properly equipped for instrument ?ight in accordance with 91.205. No person may operate this aircraft for carrying persons or property for compensation or hire. No person may be carried aboard this aircraft during ?ight unless that person is essential to the purpose of the ?ight. The pilot in command this aircraft shall advise each person carried of the experimental nature of this aircraft, and explain that it does not meet the certi?cation requirements of a standard certi?cated aircraft. (10) This aircraft shall contain the placards, markings, etc., (or other operating instructions developed for an STC modi?cation) as required by FAR 91.9. (11)This aircraft is prohibited from aerobatic ?ight; an intentional maneuver involving an abrupt change in the aircraft?s attitude, an abnormal attitude, or abnormal acceleration not necessary for normal ?ight. Page 1 of 3 EXPERIMENTAL OPERATING (cont?d) (12) The cognizant FSDO must be noti?ed, and its response received in writing, prior to ?ying this aircraft after incorporation of a major change as de?ned by 21.93. (13) This aircraft shall not be operated for glider towing or parachute jumping operations. (14)No person shall Operate this aircraft unless within the preceding 12 calendar months it has had a condition inspection performed in accordance with the scope and detail of Appendix to Part 43, or other FAA approved programs, and found to be in a condition for safe operation. This inspection shall be recorded in the aircraft maintenance records. (15) Only FAA-certi?cated mechanics with appropriate ratings as authorized by FAR 43.3 may perform inspections required by these operating limitations. (16) Inspections shall be recorded in the aircraft maintenance records showing the following or a similarly worded statement: certify that this aircraft has been inspected on (insert date) in accordance with the scope and detail of FAR Part 43, Appendix D, or other FAA approved programs and found to be in a condition for safe operation.? The entry will include the aircraft total time-in service, the name, signature, and certi?cate number and type of certi?cate held by the person performing the inspection. (17) If aircraft, engine, or propeller limitations are exceeded, an appropriate entry will be made in the aircraft records. (18) This aircraft shall not be operated unless it is maintained in accordance with the requirements of part 43, Maintenance, Preventative Maintenance, Rebuilding, and Alteration. (19) This aircraft must disPlay the word EXPERIMENTAL in accordance with 45.23 (20) The pilot in command of this aircraft shall notify the air traf?c control tower of the experimental nature of this aircraft when operating into or out of airports with operating air traf?c control towers. The pilot in command shall plan routing that will avoid densely populated areas and congested airways when Operating VFR. (21)This aircraft does not meet the requirements of the applicable, comprehensive, and detailed airworthiness code as provided by Annex 8 of the International Convention of Civil Aviation (ICAO). The owner/operator of this aircraft must obtain written permission from another country?s Civil Airworthiness Authority (CAA) prior to operating this aircraft on or above that country. That written permission must be carried aboard the aircraft together with the US. airworthiness certi?cate, and upon request, be made available to an FAA inSpector or the CAA in the country of operation. (22)Aircraft instruments and equipment installed and used under 91.205 must be inspected and maintained in accordance with the requirements of parts 43 and 91. Any maintenance or inspection of this equipment must be recorded in the aircraft records. Page 2 of 3 EXPERINIENTAL OPERATING LIIVIITATIONS (cont?d) (23)App1ication must be made to the FAA certi?cating of?ce for any revision to these operating limitations. (24) Application must be made to the geographically responsible FSDO for any revision to these operating limitations. (E Bill P. McDonald, DAS-710555-SW Date Page 3 of 3 NC: . ICE Weight and balance limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible With all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished Aircraft Model: G-IV Aircraft Serial N0.: 1425 Aircraft Registration No: N425GA Dated: 01 June 2001 Reference: Aerospace Corporation Job Order No. 0024623. Instructions for Continued Airworthiness (cont): Aft Compartment Towbar and or Crew Ladder Artex 406 Emergency Locator Transmitter Aft Compartment Equipment Storage Box Installation Artex 406 BLT Maintenance Instructions Cockpit Area Modifications Rosemont Ice Detector 871FA322 Honeywell TCAS-2000 Provisions for Honeywell GEC Marconi Cabin Interior Aft Lavatory External Service Panel Installation Cockpit Observer Seat Installation - light Industries 4 Flight Component Maintenance Manual Installation of Nordam Acoustic Liner Nordam Acoustic Liner Maintenance Requirements Passenger/ Crew Oxygen System Interior Emergency Power Interior Emergency Lights MSA Window Shades Installation MSA Window Shades Functional Test Class Baggage Compartment equipment listing. Cabin Interior STC ST09789SC-D for data approval. [BI/Additional Sheets are attached. (if more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed). Aircraft Time Since New: 18.0 Aircraft Landings Since New: 11 Item 8: Page 2 of 5 GC42004A003 GC42904A002 $041129 04 C-6455 GC42801A065 GC42801A090 25-10-04 GC42212A001 0-7499 GC42212A001 GC41453A003 GC41486A002 GC42216A001 (30422163001 none required E. Installed a new Aircraft Weight and Balance Report Document GC428WR1425, Rev and updated the F. All Cabin Interior Materials meet the requirements of FAR Part 25 through amendment Appendix F. Reference G. The following Systems and Alterations were installed per the Supplemental Type Certi?cates shown. The Flight Manual Supplements referenced have been added to the Aircraft Records. Nb 1 ICE Weight ?and balance limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible With all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required. attach additional sheets. Identify with aircraft nationality and registration mark and date work completed). Aircraft Model: Aircraft Time Since New: 18.0 Aircraft Serial No.: 1425 Aircraft Landings Since New: 11 Aircraft Registration No: N425GA Dated: 01 June 2001 Item 8: Page 3 of 5 Reference: Aerospace Corporation Job Order No. 0024623. Supplemental Type Certificates (cont) STC NUMBER SYSTEM TITLE DATA LIST REV AFMS 1. ST00248AT Satcom Antenna Instl (Honeywell) SC44103807 None Required Reference Deviation Index List - Satcom Radome Antenna Instl. (Racal) Document No. GC41 103 6006, Rev D. Reference Form FAA 8110?3 dated 23 May 2001 for structural data approval. 2. SA2622NM Pulselight Installation Model 1150B IR - 8056 A None Required Reference Deviation Index List Precise Flight Pulselite Control Document GC411886038, Rev A. Reference Forms FAA 8110-3 dated 30 May 2001 for structural data approval and 29 May 2001 for systems and equipment data approval. - 3. SA2809SO Global-Wulfsburg Airborne Flight SC41306801 SC41306M01 Information System Reference Deviation Index List Global Wulfsburg AFIS Document GC413066046, Rev Reference Forms FAA 8110-3 dated 23 May 2001 for structural data approval and 29 May 2001 for systems and equipment data approval. 4. SA2839SO Honeywell Lasertrak Navigator SC41113831 SC41113M02 Reference Deviation Index List Lasertrak Document GC411136030, Rev Reference Form FAA 81 10-3 dated 29 May 2001 for systems and equipment data approval. 5. SA3850NM Rosen Cockpit Sunvisor System RG-IV-OODL A None Required 6. Standby Attitude Indicator with Emergency ILS (BF Goodrich ILllOll448 A Reference Deviation Data List?Standby Attitude Indicator Document GC413316030, Rev A. Reference Form FAA 8110?3 dated 29 May 2001 for systems and equipment data approval. 7. Aft Compartment Towbar and/or Ladder None Required 8. ST01078CH-D Aft Compartment Storage Box Installation None Required Reference Deviation Index List - Aft Compartment Storage Box Installation: Document GC426086005, Rev A. Reference Form FAA 8110-3 dated 30 May 2001 for structural data approval. 53/ Additional Sheets are attached. Nb . ICE Weight and balance limitation changes shall be entered In the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. identify with aircraft nationality and registration mark and date work completed). Aircraft Model: G-IV Aircraft Time Since New: 18.0 Aircraft Serial No.: 1425 Aircraft Landings Since New: 11 Aircraft Registration No: N425GA Dated: 01 June 2001 Item 8: Page 4 of 5 Reference: Aerospace Corporation Job Order No. 0024623. Supplemental Tvpe Certi?cates (cont) STC NUMBER SYSTEM I TITLE DATA LIST REV AF MS 9. ST01080CH-D Artex 406 E.L.T. Installation GAC-AFMS-99020 Reference Deviation Index List Artex 406 ELT: Document GC414236044, Rev B. Reference Forms FAA 8110-3 dated 30 May 2001 for structural data approval and 29 May 2001 for systems and equipment data approval. 10. ST09583SC Cockpit Area Modi?cations GC420008103 GC42004M001 Reference Deviation Data List Cockpit Area Modi?cations, Mechanical: Document GC420006089, Rev A. Reference Form FAA 81 10?3 dated 30 May 2001 for structural data approval. Reference Deviation Data List Cockpit Area Modi?cations, Electrical: Document GC410006010, Rev Reference Form FAA 8110-3 dated 29 May 2001 for systems and equipment data approval. 11. ST09667SC Rosemont Ice Detector GC420008099 GC41446M001 Reference Deviation Index List Ice Detector Installation: Document GC414466009, Rev A. Reference Forms FAA 8110-3 dated 30 May 2001 for structural data approval and 29 May 2001 for systems and equipment data approval. 12. Installation of Honeywell TCAS-2000 SC411298006 SC41129M007 Installed TCAS-2000, Change 7 in accordance with Note 7 of Index List SC411298006, as follows: Removed and Replaced No. 1 ATC Transponder - PIN: 622?9210-004, SIN: 4BMX Off, PIN: 622-9210-006, SIN: 4BMX On. Removed and Replaced No. 2 ATC Transponder - PIN: 622-9210-004, SIN: 4G9U Off, PIN: 622?9210-006, SIN: 4G9U On. Installed Software Mod: NIC to Honeywell TCAS-2000 Computer PIN: 7517900-55004, SIN: 00073 641, in accordance with L3 Communications (Honeywell) Service Bulletin 7517900-34?6006. 13. Provisions, Honeywell I GEC Marconi HUD-2020 IL11011473 None Required Reference Deviation Index List Honeywell GEC Marconi HUD-2020 Heads Up DiSplay: Document GC441356005, Rev Reference Form FAA 8110-3 dated 23 May 200] for structural data approval. Reference Deviation Index List? Heads Up Display: Document GC441356015, Rev Reference Form FAA 8110-3 dated 29 May 2001 for systems and equipment data approval. H. Incorporated the following Major Changes in accordance with Aerospace ASC (Aircraft Service Changes) listed below: ASC 10 Hi-Intensity Anti-Collision Light Instl ASC 94 Ground Spoiler Fault Detection Functional Test - Modification lg Additional Sheets are attached. 4 Nb . ICE Weight ?and balance limitation?changes shall be entered in the appropriate aircraft record. An alteration must be compatible With all previous alterations to assure continued conformity with the applicable ainlvorthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed). Aircraft Model: G-IV Aircraft Time Since New: 18.0 Aircraft Serial No.: 1425 Aircraft Landings Since New: 11 Aircraft Registration No: N425GA Dated: 01 June 2001 Item 8: Page 5 of 5 Reference: Aerospace Corporation Job Order No. 0024623. Incorporated Maior Changes (cont): ASC 367A PT 1 Installation Forward Aft Wing Fuselage Pairings I. The following additional Aircraft Flight Manual Supplements have been supplied for the aircraft records: ASC 102 Cat II ASC 320 Max Gross Landing Weight GIV 93-04 ASC 349 - FMZ-2000 FMS GIV-2000-03 ASC 351 Max Fuel Gross Landing Weight GIV 94-03 ASC 380 RVSM GIV-97-02 EPR GIV-9S-05 The above installed equipment must be operational unless listed on the aircraft Master Minimum Equipment List for disposition. END El Additional Sheets are attached. 3511mm {$121185 (America g?Eepm-tmrni of ?lrunsportntion - g?rhrral C?A?intion (?Abutmisiration ?npplemenial (@1ng Cleriificaie 5 Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 .972}; ?r/x/r?ca/F (3-1/er (fr/(fa) r/"razyp (k ?o We (?uff/x1 14/ Ma?/??Im/hy/Moz/acl (in a?dco/z?7z2w? Mare/4r rz-J 4/10 (climax/[Maw rayz/(hwm/MJ n/ggzr/ 2:5? a/M? ?r?rafu/?wk/fcw . ?13.7(ha/ gar/(7 V'I?vz?r .- A 1 ZEA AerOSpace Corporation t/Z?w?v/Z- G-IV ?drny/zhxz (/7y/m Installation of an executive cabin interior in accordance with Index List GC420008245, Rev. dated 6/01/2001 or later FAA approved revision. FAA approved Flight Manual Supplement GC41468MOIO, Rev. None, dated or later FAA approved revision is requiredrzzar/ The compatibility of this design change with previously approved modi?cations must be determined by the installer. Descriptive data pertaining to this design change are considered inadequate for duplication on other aircraft. This approval is limited to the installation made in G-IV SIN 1425 only. .7174}; r/(z/rz. Me {Jr/4(5) 09/5}! (/Iz?cf recto/?ra?c? (6 k/wa/hcz/(b/b (-3 /y M2 (pf/[fa wr/n-w? gar/(3 .-April 1 3, 2001 MBJr/ozzcn ll I16 1, 2001 gin/(2 (z/IM/IK/fr(Signature) David K. Neese DAS Administrator DAS-710555-SW Title) Any a] ceranon of this cer::f:ca:e J's panzshabie by a ?ne of ac: exceed;ng $1,000, cr not exceeding 3 years. or both. PM Form 8110-2110-68! Page 1 of 2 ?1'an certificate may be transferred in accordance with FAR 2L47. Form Approved OMB. NO. 21200018 .1 I APPLICATION FOR INSTRUCTIONS - Print or type. Do not write in shaded areas; these are for FM use 0 . Submit ori in to a mi ed enta . fadd' I up; AIRWO RTHIN ESS spacenil: required, 039 Szpeazmlgahtigznits gzglete 9:23:35 m?m CERTIFICATE REGISTRATION MARK 2. AIRCRAFT NAME (Make) 3. AIRCRAFTMODEL DESIGNATION 4. FAA come I: N425GA Gulfst?ream Aerospace 2000 2917/5. 5. AIRCRAFT SERIAL No. 6. ENGINE NAT-IE (Make) 7. ENGINE MODEL DESIGNATION a, . 1425 Rolls-Royce Tay Mk 611?8 {115 0 0. NUMBER OF ENGINES 9. PROPELLER NAME (Make) 10. PROPELLER MODEL DESIGNATION 11. AIRCRAFT IS ICOee'rrtappbcable) Two IIMPORT APPLICATION Is HEREBY MADE FOR: {Check app?cabfe items) A 1 STANDARD NRWORWCATE (Jamie Paragon/l I NORMAL I I UTILITY ITACROBATIC I I GLIDER I BALLOON 3 SPECIAL AIRWORTHINESS CERTIFICATE (Check appropriate items) 2 LIMITED 1 CLASSI I3, 5 PROVISIONAL 2 CLASS II 1 AGRICULTUREAND PEST CONTROL 2 AERIAL SURVEYING 3 AERIAL ADVERTISING 3 RESTRICTED (IndI?cate operationfs) 4 FOREST {V?d?fe conservation) 5 PATROLLING 6 WEATHER CONTROL 3 to be conducted) 1 CARRIAGE OF CARGO 0 OTHER (Spam) 1 RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITTON 4 EXPERIMENTAL (Inmate operationrsl 4 RACING 5 CREW TRAINING MKTSURVEY to be conducted) 0 TO SHOW COMPLIANCE WITH FAR 1 FERRY FLIGHTFOR REPAIRS. ALTERATIONS. MAINTENANCE OR STORAGE SPECIAL FLIGHT PERMIT {indicate 2 EVACUATEFROMAREAOFIMPENDING DANGER 5 operation to be concluded then 3 OPERATION IN EXCESS OF MAXIMUM CERTTFICATED WEIGHT campers Section Woerlas 4 DELIVERING OR EXPORT I 5 I PRODUCTION FUGHTTESTING .appt?cabte on reverse side) 6 CUSTOMER DEMONSTRATTON FLIGHTS I a I MULTIPLE AIRWORTHINESS CERTIFICATE - Rest?cted Opera?on'and 'Standard' or 'Limr'ted', as appt?cable) A. REGISTERED OWNER (As shown on certi?cate afarcratiregistration} IF DEALER, CHECK HERE NAME AEROSPACE CORPORATION ADDRESS PO BOX 2206 MIS SAVANNAH GA 31402-2206 5. AIRCRAFT CERTIFICATION BASIS (Check applicable blocks and complete items as indicated) AIRCRAFT SPECIFICATION No AIRWORTHINESS DIRECTIVES compIedmIIz and give 2 and REVISION No.) IatestAD No.) A12EA, REV 22 THROUGH SUMMARY 2001-10 a AIRCRAFT LISTING {Give page numbeds? SUPPLEMENTAL TYPE CERTIFICATE (List number of each STC SEE ATTACHED c. AIRCRAFT OPERATION AND MAINTENANCE RECORDS CHECKIF RECORDS IN COMPLIANCE TOTAL AIRFRAME HOURS EXPERIMENTAL ONLY (Enterhours ?own sincelastcer??mre a? WITH FAR 91.417 3 issued orrenewed] 16.6 7.4 D. CERTIFICATION - I hereby certIfy that I am the registered owner (or me agent) of the aircraft desmbed above. that Is regis 'erd the Federal Aviation Administration in accordance with Section 501 of the Federal Aviation Act of 1958. and applicable Federal Aviation Regulations. and that the aircraft has been inspected and is airworthy and eligible for the airworthiness certi?cate requested. A DATE OF APPLICATION NAMEAND (Printortype) SIGNATURE g/ i 2 II 31 MAY 2001 STANLEY G. GODEK. JR. QC ANALYST A. THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY (Complete this section onfy If FAR 21.183fd} applies} 4/ FAR PART 121 DR 127 CERTIFICATE HOLDER (Gil/e CERTIFICATED MECHANIC {Give CERTIFICATED REPAIR STATION {Give Certi?cate 2 Cem??cate NO.) 3 Certi?cate No.) 6 No.) tumme name af?rm) 2 DATE TITLE SIGNATURE (Check ALI. applicable blocks m?ems A GOOD) THE CERTIFICATE REQUESTED A. Ifmd that the aIrcraItdesaIbecI a: Section torVit meets mum Tor 4 AMENDMENTOR NODEICATION OFGURRENTAIRWORTHINESS CERTEICATE 5 B. Inspectlon Iota speaaI ?ight penal under Sect?nn VII FAA EISPECTOR FAA DESIGNEE :7 was conducted by UNDER PARES I IFAR m, 127m 135 I 13 us 5 8 DATE DISTRICTOFFICE 4' We FAA INSPECTORS SIGNAIINTE 5/341? I MCDONALD 91387105558?? FAA Form 8130-6 (e05) SUPESEOES PREVIOUS EDITION (COMPUTER GEHERATED) A. MANUFACTURER VII. SPECIAL FLIGHT PERMIT PURPOSES OTHERTHAN PRODUCTION FLIGHT TEST NAME ADDRESS 3 B. PRODUCTION BASIS {Check item) PRODUCTION CERTIFICATE {Give production oertf?mts number] TIPE CERTIFICATE ONLY APPROVED PRODUCTION INSPECTION SYSTEM c. GIVE OUANTIIY 0F CERTIFICATES REQUIRED FOR OPERATING NEEDS DATE OFAPPLICAIION NAME AND TITLE {PnhtortyPeI SIGNATURE A. DESCRIPTION REGISTERED OWNER ADDRESS BUILDER {Make} MODEL SERIAL NUMBER REGISTRATION MARK 3. DESCRIPTION OF FLIGHT CUSTOMER DEMONSTRATION FLIGHTS (Checkifappticabfe) FROI. TO VIA DEPARTURE DATE DURATION c. CREW REOUIREDTO OPERATETHE AIRCRAFIAND ITS EQUIPMENT I PILOT I COPILOT NAVIGATOR OTHER (Spent?) D. THEAIRCRAFT DOES NOT MEETTHE APPLICABLEAIRWORTHIN ESS REQUIREMENTS AS FOLLOWS: E, THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION (Use attachmentifnecessary) F. CERTIFICATION - I hereby certify that I am the registered owner (or his agent) of the aircraft described above. that the airaaft is registered with the Federal Aviation Administration in accordance with Section 501 of the Federal Aviation Act of 1958, and the applicable Federal Aviation Regulations. and that the aircraft has been inspected and is airworthy for the ?ight desc?bed. DATE NAME SIGNATURE Madangsmoomkawew?h FAR s. wern recanted) 2 91.9 as H. e. (Mahatma) 935 C. Dm Dramas. Photosm, etc I'm wiIeI mowed) I. Pm Aiwo?hmess Certi?cate Issued mAcoorOanCe mm 2 D. BNmoeMTomAvaGMemA?xm PAR (On'ginaJA?ached) 5 requiem a. CamacaIeSsueGRAmIdancem F. Inspection Rewded in A'maRReoords FAR 21.19101} {Copy attached) UNITED STATES OF A DEPARTMENT OF TRANSPORTATION - PEDE AL ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE 5 A IAL PURPOSE SHOW COMPLIANCE '10 11-11:, MANU- NAME FACTURER ADDRESS FROM FLIGHT To A 4256A SERIAL mg?? BUILDER Gultsteam Aerospace LO. MODEL DATE OF ISSUANCE l/Ul EXPIRY UUIJUIU1 OPERATING LIMITATIONS DATED 05/51/01 ARE A PART OF THIS CERTIFICATE SIGNATURE OF FAA REPRESENT DE I Tl FICE NO. Bill P. Any .alteration. reproduction or misuse of this certi?cate may be punishable by a fine not exceeding $1,000 or Imprisonment not exceedIng 3 years. or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. FAA FORM 3130-7 (10l82) . SEE REVERSE SIDE A This airworthiness certificate is issue under the authority of the Federal Aviation Act of 1958 and the Federal Aviation Regulations FAB). This airworthiness certificate authorizes the manufacturer named on the reverse srde to conduct production flight tests. and only production flight tests. of aircraft registered in his name. No person may conduct production flight tests under this certificate: (1) Carrying persons or property for compensation or hire: and/or (2) Carrying persons not essential to the purpose of the flight. This airworthiness certificate authorizes the flight specified on the reverse side for the purpose shown in Block A. This airworthiness certificate certifies that. as of the date of issuance. the aircratt to which Issued i has been inspected and found to meet the reqUirements of the applicable FAR. The aircraft does not meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention On International Civil Awation. No person may operate the aircraft described on the reverseSIde: 1) except in accordance with the applicable FAR and in accordance with conditions and limitations which may be prescribed by the Administrator as part of this certificate: (2) over any foreign country without the speCial permissmn of that country. Unless sooner surrendered. suspended. or revoked. this airworthiness certificate is effective for the duration and under the conditions prescribed in FAR Part 21. Section 21 181 or 21.217 UNITED STATES OF AlfiEngA DEPARTMENT OF TRANSPORTATION - FEDERAL AVIATION ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE I EXPERIMENTAL RESEARCH AND DEVELOPMENT MANU- NAME . FACTUFIER ADDRESS FROM FLIGHT TO I A 4256A . A SERIAL NO. 1425 BUILDER Gulf?earrwe?me Co. MODEL G-IV DATE OF ISSUANCEW 05/29/01 EXPIRY 06/29/01 OPERATING LIMITATIONS DATED 05/29/01 ARE A PART OF SIGNATURE OF REPRESENTAT DESIGNATION OR OFFICE B.McDonaldm DARF710539SW Any eratIon reproduction or misuse of this certificate may be punishable by a fine not exceeding 000 or risonment not exceeding 3 years or both THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS FM FORM 3130-7 (10/32) SEE REVERSE SIDE This airworthiness certificate IS i3$ued under the authority of the Federal AViation Act of 1958 and the Federal Aviation Regulations (FAQ). This airworthiness certi?cate authorizes the manufacturer named on the reverse srde to conduct production flight tests. and only production flight tests. of aircraft registered in his name. No person may conduct production flight tests under this certificate: (1) Carrying personsdor property for compensation or hire: and/or (2) Carrying persons not essential to the purpose of the flight. This airworthiness certificate authorizes the flight spemfied on the reverse Side for the purpose shown in Block A. This airworthiness certificate certifies that. as of the date of issuance. the aircraft to which issued has been inspected and found to meet the requirements of the applicable FAR. The aircraft does not meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention On International CiVil Aviation. No person may operate the aircraft described on the reverse side: (1) except in accordancewith the applicable FAR and in accordance with conditions and limitations which may be prescribed by the Administrator as part of this certificate: (2) over any foreign country without the Special permission of that country. Unless sooner surrendered. suspended. or revoked. this airworthiness certificate is effective for the duration and under the conditions prescribed in FAR Part 21. Section 21.181 or 21 .217. (1) (2) (3) (4) (5) (6) (7) (3) (9) EXPERIMENTAL OPERATING LIMITATIONS ?Show Compliance to the Regulations? Make: Aerospace Corp. Model: G-IV Serial Number: 1425 Registration Number: N425GA Issuance Date: 05/31/01 Expiration Date: 06/30/01 No person may operate this aircraft unless the FAA Form 8130-7, Special Airworthiness Certi?cate is disPIayed at the cabin or cockpit entrance so that it is visible to passengers or crew. No person may operate this aircraft for other than the purpose(s) of Show Compliance to the Regglations to accomplish the ?ight operation outlined in Aerospace Corp. Program Letter, dated May 25, 2001, describing compliance with FAR and made available to the pilot-in?command of the aircraft. Additionally, this aircraft shall be operated in accordance with applicable air traf?c and general operating rules of FAR Part 91, and all additional limitations herein prescribed under the provisions of FAR All ?ights of this aircraft shall be conducted within the geographic area described as follows: Within the US. main land boundaries, from KDAL, Dallas, TX. This aircraft shall not be operated unless it is maintained in accordance with the appropriate manufacturer?s recommendations. The owner/Operator shall select, establish, identify, and use an inspection program as set forth in FAR and This inspection program shall be recorded in the aircraft maintenance records. The pilot-in?command of this aircraft must, as applicable, hold an appropriate category/class rating. If required'for the type of aircraft to be ?own the pilot in command must also hold either an appropriate type rating or Letter of Authorization issued by a FAA Flight Standards District Operations Inspector. This aircraft may be operated under Instrument Flight Rules (IFR), and must be properly equipped for instrument ?ight in accordance with 91.205. 0 person may operate this aircraft for carrying persons or property for compensation or hire. No person may be carried aboard this aircraft during ?ight unless that person is essential to the purpose of the ?ight. The pilot in command this aircraft shall advise each person carried of the experimental nature of this aircraft, and explain that it does not meet the certi?cation requirements of a standard certi?cated aircraft. (10) This aircraft shall contain the placards, markings, etc., (or other operating instructions developed for an STC modi?cation) as required by FAR 91.9. (11)This aircraft is prohibited ?om aerobatic ?ight; an intentional maneuver involving an abrupt change in the aircraft?s attitude, an abnormal attitude, or abnormal acceleration not necessary for normal ?ight. Page 1 of 3 EXPERIMENTAL OPERATING LIMITATIONS (cont?d) (12)The cognizant FSDO must be noti?ed, and its reSponse received in writing, prior to ?ying this aircraft after incorporation of a major change as de?ned by 21.93. (13) This aircraft shall not be operated for glider towing or parachute jumping Operations. (14)No person shall operate this aircraft unless within the preceding 12 calendar months it has had a condition inspection performed in accordance with the sc0pe and detail of Appendix to Part 43, or other FAA approved programs, and found to be in a condition for safe operation. This inspection shall be recorded in the aircraft maintenance records. (15) Only FAA-certi?cated mechanics with appropriate ratings as authorized by FAR 43.3 may perform inspections required by these operating limitations. (16) Inspections shall be recorded in the aircraft maintenance records showing the following or a similarly worded statement: certify that this aircraft has been inspected on (insert date) in accordance with the scope and detail of FAR Part 43, Appendix D, or other FAA approved programs and found to be in a condition for safe operation.? The entry will include the aircraft total time-in service, the name, signature, and certi?cate number and type of certi?cate held by the person performing the inspection. (17)If aircraft, engine, or propeller limitations are exceeded, an appropriate entry will be made in the aircraft records. (18) This aircraft shall not be operated unless it is maintained in accordance with the requirements of part 43, Maintenance, Preventative Maintenance, Rebuilding, and Alteration. (19) This aircraft must display the word EXPERIMENTAL in accordance with 45.23 (20) The pilot in command of this aircraft shall notify the air traf?c control tower of the experimental nature of this aircraft when operating into or out of airports with operating air traf?c control towers. The pilot in command shall plan routing that will avoid densely populated areas and congested airways when operating VFR. (21) This aircraft does not meet the requirements of the applicable, comprehensive, and detailed airworthiness code as provided by Annex 8 of the International Convention of Civil Aviation (ICAO). The owner/operator of this aircraft must obtain written permission from another country?s Civil Airworthiness Authority (CAA) prior to operating this aircraft on or above that country. That written permission must be carried aboard the aircraft together with the US. airworthiness certificate, and upon request, be made available to an FAA inspector or the CAA in the country of operation. (22) Aircraft instruments and equipment installed and used under 91.205 must be inspected and maintained in accordance with the requirements of parts 43 and 91. Any maintenance or inspection of this equipment must be recorded in the aircraft records. Page 2 of 3 EXPERIIVIENTAL OPERATING LEVIITATIONS (cont?d) (23) Application must be made to the FAA certi?cating of?ce for any revision to these operating limitations. (24) Application must be made to the geographically responsible FSDO for any revision to these operating limitations. Bill P. McDonald, DAS-710555-SW Date Page 3 of 3 ATTACHIVIENT 12 FAA FORM 8130-6 SUBMITTED 31 MAY 2001, SIN 1425: INSTALLED THE-FOLLOWING FAA APPROVED SUPPLEMENTAL TYPE CERTIFICATE SYSTEMS ON MODEL G-IV, SIN 1425, REGISTRATION NO. N425GA. STC NUMBER SYSTEM TITLE SA2622NM SA2809SO SA283980 SA3 850NM ST00248AT STO 1077CH-D STOI 078CH-D ST09583SC ST09667SC PENDING PRECISE FLIGHT PULSELITE CONTROL GLOBAL WULFSBURG AIRBORNE FLIGHT INFORMATION SYSTEM HONEYWELL LASERTRAK NAVIGATOR ROSEN IV MONORAIL SUNVISOR SYSTEM STANDBY HORIZON INDICATOR WITH EMERGENCY ILS (BF GO ODRICH ADI-33 5) PROVISIONS FOR HEAD UP DISPLAY, HUD-2020 HONEYWELL GEC MARCONI SATCOM ANTENNA INSTL (HONEYWELL) AFT COMPARTMENT TOWBAR AFT COMPARTMENT STORAGE BOX INSTALLATION INSTALLATION OF ARTEX 406 EMERGENCY LO CATOR TRANSMITTER TCAS 2000 (HONEYWELL) CO CKPIT AREA MODIFICATIONS ROSEMONT ICE DETECTOR INSTALLATION CABIN INTERIOR THE FOLLOWING FAA APPROVED SUPPLENIENTAL TYPE CERTIFICATES ARE INCORPORATED IN THE CABIN INTERIOR SUPPLEMENTAL TYPE CERTIFICATE (PENDING). STC NUMBER SYSTEM TITLE SA2657SO SA3 ST008 17LA-D ST02185AT-D ST0958 1 SC CLASS BAGGAGE COMPARTMENT LAVATORY SERVICE PANEL, AFT RS INSTL, FWD RADIO RACK INSTALLATION OF NORDAM ACOUSTICAL LINER OXYGEN SYSTEM EMERGENCY POWER SYSTEM INTERIOR EMERGENCY LIGHTS MSA WINDOW SHADES INSTALLATION (1) (2) (3) (4) (5) (6) (7) (8) (9) EXPERIIVIENTAL OPERATING LIIVIITATIONS ?Research and Development? Make: Aerospace Corp. Model: G-IV Serial Number: 1425 Registration Number: N425GA Issuance Date: 05/29/01 Expiration Date: 06/29/01 No person may Operate this aircraft unless the FAA Form 8130-7, Special Airworthiness Certi?cate is displayed at the cabin or cockpit entrance so that it is visible to passengers or crew. No person may Operate this aircraft for other than the purpose(s) of Research and Development to accomplish the ?ight operation outlined in Aerospace Corp. Program Letter, dated May 22, 2001, describing compliance with FAR and made available to the pilot-in- command of the aircraft. Additionally, this aircraft shall be operated in accordance with applicable air traf?c and general operating rules of FAR Part 91, and all additional limitations herein prescribed under the provisions of FAR All ?ights of this aircraft shall be conducted within the geographic area described as follows: Within the US. mainland boundaries, from KDAL, Dallas, TX. This aircraft shall not be operated unless it is maintained in accordance with the appropriate manufacturer?s recommendations. The owner/operator shall select, establish, identify, and use an inspection program as set forth in FAR and This inspection program shall be recorded in the aircraft maintenance records. The pilot-in-command of this aircraft must, as applicable, hold an appropriate category/class rating. If required for the type of aircraft to be ?own the pilot in command must also hold either an appropriate type rating or Letter of Authorization issued by a FAA Flight Standards District Operations Inspector. This aircraft may be operated under Instrument Flight Rules (IFR), and must be properly equipped for instrument ?ight in accordance with 91.205. No person may operate this aircraft for carrying persons or property for compensation or hire. No person may be carried aboard this aircraft during ?ight unless that person is essential to the purpose of the ?ight. The pilot in command this aircraft shall advise each person carried of the experimental nature of this aircraft, and explain that it does not meet the certification requirements of a standard certi?cated aircraft. (10) This aircraft shall contain the placards, markings, etc., (or other Operating instructions developed for an STC modi?cation) as required by FAR 91.9. (11) This aircraft is prohibited from aerobatic ?ight; an intentional maneuver involving an abrupt change in the aircraft?s attitude, an abnormal attitude, or abnormal acceleration not necessary for normal ?ight. Page 1 of 3 EXPERIIVIENTAL OPERATING LIIVIITATIONS (cont?d) (12) The cognizant FSDO must be noti?ed, and its response received in writing, prior to ?ying this aircraft after incorporation of a major change as de?ned by 21.93. (13) This aircraft shall not be operated for glider towing or parachute jumping operations. (14)No person shall operate this aircraft unless within the preceding 12 calendar months it has had a condition inspection performed in accordance with the scope and detail of Appendix to Part 43, or other FAA approved programs, and found to be in a condition for safe Operation. This inspection shall be recorded in the aircraft maintenance records. (15) Only FAA-certi?cated mechanics with appropriate ratings as authorized by FAR 43.3 may perform inspections required by these Operating limitations. (16) Inspections shall be recorded in the aircraft maintenance records showing the following or a similarly worded statement: certify that this aircraft has been inspected on (insert date) in accordance with the scope and detail of FAR Part 43, Appendix D, or other FAA approved programs and found to be in a condition for safe operation.? The entry will include the aircraft total time-in service, the name, signature, and certi?cate number and type of certi?cate held by the person performing the insPection. (17)If aircraft, engine, or propeller limitations are exceeded, an appropriate entry will be made in the aircraft records. (18) This aircraft shall not be Operated unless it is maintained in accordance with the requirements of part 43, Maintenance, Preventative Maintenance, Rebuilding, and Alteration. (19) This aircraft must display the word EXPERIMENTAL in accordance with 45 (20)The pilot in command of this aircraft shall notify the air traf?c control tower of the experimental nature of this aircraft when operating into or out of airports with Operating air traf?c control towers. The pilot in command shall plan routing that will avoid densely populated areas and congested airways when operating VFR. (21)This aircraft does not meet the requirements of the applicable, comprehensive, and detailed airworthiness code as provided by Annex 8 of the International Convention of Civil Aviation (ICAO). The owner/Operator of this aircraft must obtain written permission from another country?s Civil Airworthiness Authority (CAA) prior to operating this aircraft on or above that country. That written permission must be carried aboard the aircraft together with the U.S. airworthiness certi?cate, and upon request, be made available to an FAA inspector or the CAA in the country of operation. (22) Aircraft instruments and equipment installed and used under 91.205 must be inspected and maintained in accordance with the requirements of parts 43 and 91. Any maintenance or inspection of this equipment must be recorded in the aircraft records. Page 2 of 3 EXPERINIENTAL OPERATING LIMITATIONS (cont?d) (23)App1ication must be made to the FAA certi?cating of?ce for any revision to these operating limitations. (24) Application must be made to the geographically responsible FSDO for any revision to these Operating limitations. Eggnog Bill P. McDonald, Page 3 of 3 A GENERAL DYNAMICS COMPANY FAA CSR-VJ1R560K 7350 Cedar Springs Rd. Dallas, TX 75235 25 May 2001 Bill P. McDonald Mr. McDonald, Aerospace Corporation, located at Love Field in Dallas, Texas is hereby submitting a request for issuance of a Special Airworthiness Certi?cate, Experimental - Show Compliance for aircra? model G-TV, serial number 1425, registration number N425GA. This request is required in order to complete ?ight tests on the project listed below: Executive Cabin Interior, SIN 1425: STC Project No. GACD 01-07 DAS Certi?cation of the STC Project referenced above requires ?ight-testing to verify the safety and operation of the systems installed. The ?ight-testing will not present a hazard to public safety. This aircraft is in compliance with CFR Title 14, Chapter 1, Sub-chapter C, Part 36 Noise Standards, Amendments 36-1 through 36-12. We estimate a total of two (2) test ?ights to be conducted under FAR All ?ight tests will originate and terminate at Love Field (KDAL), Dallas, TX. Test Flight No.1 Show Compliance. (Systems check ?ight) Test Flight No.2 Flight to clear any discrepancies. In the event that we are required to conduct additional ?ights, we will notify you with an explanation of the purpose of the ?ight. If you have any questions, please do not hesitate to contact me at (214) 902-7724. Respectfully, Stanley G. Godek, Jr. Quality Control Analyst GAC Dallas, TX Form Approved a MAJOR REPAIR AND ALTERATION OMB No_ 21200020 USD rim . oiTraiigiw?tri?on (Airframe, Powerplant, Prepelier, or Appliance) For FAA Use Only ?Federal Aviation Of?ce Identi?cation Administration Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each violation (Section 901 of Federal Aviation Act of 1958). Make Model G-IV 1. Aircraft Serial No Nationality and Registration Mark 1425 N4ZSGA Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) 2. Owner AEROSPACE CORPORATION PO BOX 2206 MS D-os SAVANNAH GA 31402-2206 3. For FAA Use Only 4. Unit Identi?cation 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) POWERPLANT PROPELLER Type APPLIANCE Manufacturer . 6. Conformity Statement A. Agency?s Name and Address B. Kind of Agency C. Certi?cate No. u.s. Certi?cated Mechanic CRS VJ1R560K Aerospace Corporation Foreign Certi?cated Mechanic Airframe Class 2, 3, 4. 7350 Cedar Springs Certi?ed Repair Station Radio Class 1, 2, 3. Dallas, Tx 75235 Manufacturer Limited Instrument D. I certify that the repair and/or alteration made to the unit(s) identi?ed in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the US. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date Signature of Authorized Individual 01 June 2001 Chris Lee! Sr. Airworthiness InSpector 7. Approval for Return To Service Pursuant to the authority given persons speci?ed below, the unit identi?ed in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is REJECTED FAA F't- Standards Manufacturer Inspection Authorization Other (Speci?x) Inspector BY FAA Designee Repair Station Person Approved by Transport Canada Ainrvorthiness Group Date of Approval or Rejection Certi?cate or Signature of Authorized Individual Designation No. - 01 June 2001 FAA CRS VJ1R560K Chris Lee 1 Sr. Airworthiness Inspector L4 FAA Form 337 (12-88) (Computer Generated) NO I ICE Weight and balance limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable ainivorthiness requirements. ?9 .1 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed). Aircraft Model: G-IV Aircraft Time Since New: 18.0 Aircraft Serial 0.: 1425 Aircraft Landings Since New: 11 Aircraft Registration No: N425GA Dated: 01 June 2001 Item 8: Page 1 of 5 Reference: Aer05pace Corporation Job Order No. 0024623. A. Installed a Custom Cabin Interior per Master Index List Document GC414910074, Rev and Aerospace Corporation STC NO. per GC420008245, Rev A - Index List: Installation, Cabin Interior. The following STC's are incorporated in the Cabin Interior STC STC NUIVIBER SYSTEM TITLE DATA LIST REV AFMS JSA2657SO Class Baggage Compartment SC42504M02 Lavatory Service Panel IL11011111 Not Required Jumpseat Instl, Radio Rack 1111011122 Not Required ST00817LA-D Installation of Nordam Acoustical Liner GC428268004 Not Required Oxygen System GC414538001 GC41453M004 ST02184AT-D Emergency Power System GC411898001 GC41189M001 Interior Emergency Lights GC414868002 Not Required MSA Window Shades Installation GC420008096 Not Required Instructions for Continued Airworthiness for G-IV: GC42801A065, Rev and Aircraft Flight Manual Supplement: and the Completion Center Wiring Diagram Manual have been provided for the aircraft records. B. Installed Custom Avionics and Electrical Modi?cations per Aerospace Corporation Data List Miscellaneous Electrical Modi?cations: GC414680076, Rev Reference Form FAA 8110-3 dated 29 May 2001 for systems equipment data approval. C. Installed Custom Avionics and Electrical Modi?cations per Aerospace Corporation Data List Avionics/Electrical, Mechanical: A. Reference Form FAA 8110?3 dated 30 May 2001 for structural data approval. i D. The following Instructions for Continued Airworthiness as required by FAR 25.1529 and Appendix have been . provided to the owner operator. MODIFICATION ICA NUMBER Satcom Antenna Instl (Honeywell) none required Precise Pulselite 8056 Global Wulfsberg Airborne Flight Information System CE41306A001 LaserTrak Navigator none required Rosen Monorail Sunvisor System ROW-400 Standby Attitude Indicator (BF Goodrich Additional Sheets are attached. FAA . Form QAQA a MAJOR REPAIR AND ALTERATION OMB No 2130002" SW05 [564 (Airframe, Powerplant, Propeller, or Appliance) For FMU?bmgy Zn?i Federal Aviation Of?ce identi?cation Administration eg? 3.0251 DOV g" 0 INSTRUCTIONS: Print or type all entriesAppendix B, and AC 43. 9- 1 (or subsequent Vl I reof) for instructions and disposition of this form. This report is required by law (49 U. S. C. 1421). Failure to report can result In a civil penalty rim?) 'exoeeda?l?.? 000 for each violation (Section 901 of Federal Aviation Act of 1958). Make Model G-IV 1. Aircraft Serial No Nationality and Registration Mark 1425 N425GA Name (As shown on registration certificate) Address (As shown on registration certi?cate) 2. Owner AEROSPACE CORPORATION PO BOX 2206 M15 D-06 SAVANNAH GA 31402-2206 3. For FAA Use Only 4. Unit Identi?cation 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in item 1 above) POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certi?cate No. US. Certi?cated Mechanic CRS VJ1R560K Aerospace Corporation . Foreign Certi?cated Mechanic Airframe Class 2, 3, 4. . 7350 Cedar Springs Certi?ed Repair Station Radio Class 1, 2, 3. Dallas, Tx 75235 Manufacturer Limited Instrument D. I certify that the repair and/or alteration made to the unit(s) identi?ed in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the US. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date Signature of Authorized Individual 01 June 2001 Chris Lee 1 Sr. Airworthiness Inspector a; 7. Approval for Return To Service Pursuant to the authority given persons speci?ed below. the unit identi?ed in item 4 was inspected in the manner prescribed by the Administrator of'the Federal Aviation Administration and is IZIAPPROVED L?l REJECTED FAA F't- Standards Manufacturer Inspection Authorization Other (Specify) Inspector BY FAA nee Re air Station Person by 85.9 Transport Canada Ainrvorthiness Group Date of Approval or Rejection Certi?cate or Signature of Authorized Individual Designation No. 01 June 2001 FAA CRS VJ1R560K Chris Lee I Sr. Airworthiness Inspector L4, FAA Form 337 (12-88) (Computer Generated) NOTICE Weight and balance limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed). Aircraft Model: G-IV Aircraft Time Since New: 18.0 Aircraft Serial No.: 1425 Aircraft Landings Since New: 11 Aircraft Registration No: N425GA Dated: 01 June 2001 Item 8: Page 1 of 5 Reference: Aerospace Corporation Job Order No. 0024623. A. Installed a Custom Cabin Interior per Master Index List Document GC414910074, Rev and Aerospace Corporation STC NO. ST09789SC-D per GC420008245, Rev A - Index List: Installation, Cabin Interior. The following STC's are incorporated in the Cabin Interior STC ST097893C-D: STC NUMBER SYSTEM TITLE DATA LIST AFMS SA2657SO Class Baggage Compartment SC42504801 SC42504M02 SA3655NM-I) Lavatory Service Panel Not Required SA3660NM-D umpseat Inst], Radio Rack Not Required ST00817LA-D Installation of Nordam Acoustical Liner GC428268004 Not Required ST02182AT-D Oxygen System GC414538001 GC41453M004 ST02184AT-D Emergency Power System GC411898001 GC41189M001 ST02185AT-D Interior Emergency Lights GC414868002 Not Required ST09581SC MSA Window Shades Installation GC420008096 Not Required Instructions for Continued Airworthiness for GC42801A065, Rev and Aircraft Flight Manual Supplement: GC41468M010, Rev and the Completion Center Wiring Diagram Manual have been provided for the aircraft records. B. Installed Custom Avionics and Electrical Modifications per Aerospace Corporation Data List Miscellaneous Electrical IVIOdifications: GC414680076, Rev Reference Form FAA 8110-3 dated 29 May 2001 for systems equipment data approval. C. Installed Custom Avionics and Electrical Modi?cations per Aerospace Corporation Data List - Avionics/Electrical, Mechanical: GC420000266, Rev A. Reference Form FAA 8110-3 dated 30 May 2001 for structural data approval. D. The following Instructions for Continued Airworthiness as required by FAR 25.1529 and Appendix have been provided to the owner operator. MODIFICATION ICA NUMBER Satcom Antenna Inst] (Honeywell) none required Precise Pulselite 8056 Global Wulfsberg Airborne Flight Information System CB41306A001 LaserTrak Navigator none required Rosen Monorail Sunvisor System RGIV-400 Standby Attitude Indicator (B Goodrich 5) C63 01 Additional Sheets are attached. NOTICE Weight and balance limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed). Aircraft Model: Aircraft Serial No.: 1425 Aircraft Registration No: N425GA Dated: 01 June 2001 Reference: Aerospace Corporation Job Order No. 0024623. Instructio?ns for Continued Airworthiness (cont): Aft Compartment Towbar and or Crew Ladder Artex 406 Emergency Lo cator Transmitter Aft Compartment Equipment Storage Box Installation Artex 406 MHZ ELT Maintenance Instructions Cockpit Area Modi?cations Rosemont Ice Detector 871FA322 Honeywell TCAS-2000 Provisions for Honeywell GEC Marconi HUD-2020 Cabin Interior . Aft Lavatory External Service Panel Installation Cockpit Observer Seat Installation - light Industries 4 Flight Component Maintenance Manual Installation of Nordam Acoustic Liner Nordam Acoustic Liner Maintenance Requirements Passenger/ Crew Oxygen System Interior Emergency Power Interior Emergency Lights MSA Window Shades Installation MSA Window Shades Functional Test Class B?Baggage Compartment Aircraft Time Since New: 18.0 Aircraft Landings Since New: 11 Item 8: Page 2 of 5 GAC-ICA-99009 90 1 9 GAC-MIVIS-99 021 GC42004A0 03 GC42904A0 02 SC41 129A004 C-645 5 GC42801A065 GC42801A088 GC42801A090 25?10-04 GC42212A001 GC42212A001 GC41453A003 GC41 189A001 GC41486A002 GC42216A001 GC422163001 none required E. Installed a new Aircraft Weight and Balance Report Document GC428WR1425, Rev and updated the equipment listing. F. All Cabin Interior Materials meet the requirements of FAR Part 25 through amendment 51, Appendix F. Reference Cabin Interior STC ST09789SC-D for data approval. G. The following Systems and Alterations were installed per the Supplemental Type Certi?cates shown. The Flight Manual Supplements referenced have been added to the Aircraft Records. IZ/Additional Sheets are attached. NOTICE Weight and balance limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable ainivorthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed). Aircraft Model: G-IV Aircraft Time Since New: 18.0 Aircraft Serial No.: 1425 Aircraft Landings Since New: 11 Aircraft Registration No: N425GA Dated: 01 June 2001 Item 8: Page 3 of 5 Reference: Aerospace Corporation Job Order No. 0024623. Supplemental Type Certificates (cont) STC NUMBER SYSTEM TITLE DATA LIST REV AFMS 1. ST00248AT Satcom Antenna Inst] (Honeywell) SC44103807 None Required Reference Deviation Index List - Satcom Radome Antenna Instl. (Racal) Document No. GC411036006, Rev D. Reference Form FAA 8110-3 dated 23 May 2001 for structural data approval. 2. SA2622NM Pulselight Installation Model 1150B 1R - 8056 A None Required Reference Deviation Index List Precise Flight Pulselite Control Document GC41 1 88603 8, Rev A. Reference Forms FAA 8110-3 dated 30 May 2001 for structural data approval and 29 May 2001 for systems and equipment data approval. 3. SA2809SO Global-Wulfsburg Airborne Flight SC41306801 SC41306M01 Information System . Reference Deviation Index List Global Wulfsburg AFIS Document GC413066046, Rev Reference Forms FAA 8110-3 dated 23 May 2001 for structural data approval and 29 May 2001 for systems and equipment data approval. SA2839SO Honeywell Lasertrak Navigator SC41113831 SC41113M02 Reference Deviation Index List Lasertrak Document GC411136030, Rev Reference Form FAA 8110-3 dated 29 May 2001 for systems and equipment data approval. 5. SA3850NM Rosen Cockpit Sunvisor System RG-IV-00DL A None Required 6. SA4286NM-D Standby Attitude Indicator with Emergency ILS (BF Goodrich 114110114418 A C-6300 Reference Deviation Data List?Standby Attitude Indicator Document GC41331603 0, Rev A. Reference Form FAA 8110-3 dated 29 May 2001 for systems and equipment data approval. 7. ST0107 7 Aft Compartment Towbar and/or Ladder None Required 8. ST01078CH-D Aft Compartment Storage Box Installation None Required Reference Deviation Index List Aft Compartment Storage Box Installation: Document GC426086005, Rev A. Reference Form FAA 8110-3 dated 30 May 2001 for structural data approval. [Er/Additional Sheets are attached. NOTICE Weight and balance limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed). Aircraft Model: G-IV Aircraft Time Since New: 18.0 Aircraft Serial No.: 1425 Aircraft Landings Since New: 11 Aircraft Registration No: N425GA Dated: 01 June 2001 Item 8: Page 4 of 5 Reference: Aerospace Corporation Job Order No. 0024623. Supplemental Type Certi?cates cont.) STC NUNIBER I SYSTEM TITLE DATA LIST REV AFMS 9. . Artex 406 E.L.T. Installation Reference Deviation Index List Artex 406 BLT: Document GC414236044, Rev B. Reference Forms FAA 8110-3 dated 30 May 2001 for structural data approval and 29 May 2001 for systems and equipment data approval. 10. Cockpit Area Modi?cations GC420008103 GC42004M001 Reference Deviation Data List Cockpit Area Modi?cations, Mechanical: Document GC420006089, Rev A. Reference Form FAA 8110-3 dated 30 May 2001 for structural data approval. Reference Deviation Data List Cockpit Area Modi?cations, Electrical: Document GC410006010, Rev Reference Form FAA 8110-3 dated 29 May 2001 for systems and equipment data approval. 11. ST09667SC Rosemont Ice Detector GC420008099 GC41446M001 Reference Deviation Index List Ice Detector Installation: Document GC414466009, Rev A. Reference Forms FAA 8110-3 dated 30 May 2001 for structural data approval and 29 May 2001 for systems and equipment data approval. 12. Installation of Honeywell TCAS-2000 SC411298006 SC41129M007 Installed TCAS-2000, Change 7 in accordance with Note 7 of Index List SC411298006, as follows: Removed and Replaced No. 1 ATC Transponder PIN: 622-9210?004, SIN: 4BMX Off, PIN: 622-9210-006, SIN: 4BMX On. Removed and Replaced No; 2 ATC Transponder - PIN: 622-9210-004, SIN: 4G9U Off, PIN: 622-9210-006, SIN: 4G9U On. Installed Software Mod: to Honeywell Computer - PIN: 7517900-55004, SIN: 00073 641, in accordance with L3 Communications (Honeywell) Service Bulletin 7517900-34?6006. 13. SA4291NM-D Provisions, Honeywell/GEC Marconi HUD-2020 11.11011473 None Required Reference Deviation Index List Honeywell GEC Marconi HUD-2020 Heads Up Display: Document GC44135 6005, Rev Reference Form FAA 8110?3 dated 23 May 2001 for structural data approval. Reference Deviation Index List - Heads Up Display: Document GC441356015, Rev Reference Form FAA 8110-3 dated 29 May 2001 for systems and equipment data approval. H. Incorporated the following Major Changes in accordance with Aerospace ASC (Aircraft Service Changes) listed below: ASC 10 Hi?Intensity Anti?Collision Light Instl ASC 94 Ground Spoiler Fault Detection Functional Test - Modi?cation 12/ Additional Sheets are attached. NOTICE Weight and balance limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations?to assure continued conformity with the applicable airworthiness requirements. 8. Descriptidn of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed). Aircraft Model: G-IV Aircraft Time Since New: 18.0 Aircraft Serial No.: 1425 Aircraft Landings Since New: 11 Aircraft Registration No: N425GA Dated: 01 June 2001 Item 8: Page 5 of 5 Reference: Aerospace Corporation Job Order No. 0024623. Incorporated Maior Changes (cont): ASC 367A PT 1 Installation Forward Aft Wing Fuselage Pairings I. The following additional Aircraft Flight Manual Supplements have been supplied for the aircraft records: ASC 102 Cat ASC 320 Max Gross Landing Weight GIV 93-04 ASC 349 FMS ASC 351 Max Fuel Gross Landing Weight GIV 94-03 ASC 380 RVSM EPR 1N The above installed equipment must be operational unless listed on the aircraft Master Minimum Equipment List for disposition. END El Additional Sheets are attached. :?Hn?u?n ?_izxics (9f Citrus-rim of - Heberal C'A?izttirm ,ZAhminisira?on ogupplemenial (@ng Cler?ficaie (5/23 6/4 ST09789SC-D 97?" Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 (k #52 .{r/fza ?1/044.ch (07% ?bzzi?zz/akwg [gm/0,1. ?mg/.5 hf? ?5 (1/5/10 ?a?wm/J??orh??n .?gy/I??l/fr/M . g?t?z?a/n .- A 1 213A did/If}: AerOSpace Corporation J?nr?/s (3-1V .(Zr-ijm Installation of an executive cabin interior in accordance with Index List GC420008245, Rev. A, dated 6/01/2001 or later FAA approved revision. FAA approved Flight Manual Supplement GC41468MOIO, Rev. None, dated 6/Olr?200l or later FAA approved revision is required. The compatibility of this design change with previously approved modifications must be determined by the installer. Descriptive data pertaining to this design change are considered inadequate for duplication on other aircraft- This approval is limited to the installation made in 1425 only. crr/??ca/r erymr/?y a?z/y (wide/(Z (-3 [Pl-Jr?) (?z/cf Jz/rrcwa?/aof dad/Iw/m4wf 4/4/10. (-3 gig/[21 ?a?rrz/Z :Zwi/I/zkw. gar/e .-April 13, 2001 erz/n -- June 1, 2001 fade/M?/Z: 21/ a?rcf?c/ma a I #197 (Signamre) David K. Neese DAS Administrator Tide) Any alteration cf :his is punishabie by a fine of not exceeding $1,000. or zmprisomnen: exceeding 3 years. or both. FM Silo-Ell?-GE! Page 1 of 2 This certificace may be crans:e:'reci accerc?ance with FAR 2i.47. ??niq 'mm or Elmira Kaspartmant or transportatwn??zdere! aviation Edministren?on @2ng Certi?catt SA2657SO - Aerospace Corporation 13.0- Box 2205 Savannah. GA 31A02 md 00,. 44-59,, 3, 25 - 95$ Federal Aviation ?Ml: 6-3; 0 . 0 67 - 24232,. Installation of a Class Baggage Compartment per Aerospace Drawing 8042 50Q801, Revision G, Dated March 26, 1991, or later approved FAA revision. This approval Should not be extended to other aircraft of previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modificatiOns'will produce no adverse effect upon the airworthiness of that airplane. For.Airplane Serial Numbers 1000 through 1155, FAA approved Airplane Flight Manual Supplement (AFMS) Number SC 42 SOQMOI, dated November 21, 1989, and for Airplane Serial Numbers 1156 and Subsequent' FAA approved AFMS Namber SC 42 SOAMOZ, dated April 4, 1991,.are a r?m??wo?y? awe?. do/m Wz??warmid c3 91% July?l9, 1989 me November 21, 1989 ?ammaxs April 2, 1991 Manager, Certification 0 ice . (Tilt!) narration of {In} is punishable lg}: a?nc of no! 17,000, or no! acceding 3 or bath. Thl': may 6: in accordanc: with FAR A GENERAL DYNAMICS May/4, 2001 Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 Subject: STC Authorization Attn: Danielle Chipps Aerospace, Savannah, Georgia (the STC Certi?cate Holder) authorizes AerosPace Dallas, Texas, to use the following Supplemental Type SA2657SO ST00248AT SA2809SO SA2839SO ST02182AT-D ST02184AT-D ST02185AT-D for installation in a model 1425 aircraft. Additional authorizations may be obtained by submitting a request to the DAS Administrator, specifying the applicable aircra? serial number(s) intended for this installation. . Should you have any questions, please do not hesitate to contact the undersigned. Sincerely, - Mm. 7 5 Carmen L. Djulvezan STC Analyst Aerospace Corporation. R0. Box 2206, Savannah, Georgia 31402-2206, Telephone: 912-965-3000 of Transportation1 Eniation gdministration ?01,ng (erti?tatz, J2Z3xm~943ug1au1a?e- Aerospace Corporation 4150 Donald Douglas Drive Long Beach, California 90808 W?ddcha 2W w?ry?-r?aw ?40: "Wand/MW 25* #169, Federal Avi a ti on Egguu??ama (For certification basis see T.C. Data Sheet AIZEA) A12EA ?454?: M: G-IV Installation of Lavatory Service Panel, AFT RH Side in accordance approved Aerospace Corporation Index List IL11011111, Revision dated July 22, 1987, or later approved revision. This approval should not be extended to other aircraft of this model on which_other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will produce no adverse effect upon the airworthiness of that airplane. This determination should include consideration of significant changes in'weight distribution such as an increase in the fixed disposable weight in the fuselage. Jun 8 4 1 987 @a?wmkduaa/I Sep tembe 8 1987 {SI-gnaw?) DAS Facility Director DAS3NH Aly afltrah'on oflfu} arh?calc f: punz'shaH: b} a?nc qf'no! Exceeding 11,000, or imprisonment no! txcadr?ng 3ycar5, or 6011:. Th": (lili?foft may?bc harufartd r'n ?ardent: FAR foleD?leO??a) 05/21/2001 08:29 FAX 5626276168 DAS @002 A GENERAL DYNAMICS COMPANY May 21, 2001 Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 Subject STC Authorization Attn: Stanley Godek By receipt of this letter, you are hereby authorized by Aerospace Corp, Long Beach to use STC SA3660NM-D, SA3655NM-D, SA4291NM-D, and ST00817LA-D for the modi?cation of aircraft, SN 1425 only. I trust this letter will provide you with the necessary information. However, should you require further clarification, please contact the undersigned at (562) 627?5 030. Sincerely, Marco A. Morejon, DAS Administrator, DAS-100271-NM Long Beach CC. Doug Prentiss Randy wood' Aerospace Corporation. 4150 Donate? Douglas Drive, Long Beach, California 90808.TeiephonE' 562-420-1818 Far~ 562-627-5090 pf jig?Enigma S?minisu?arion ?61:ng @uu?tatz SASGSONM-D 3.5 5 1, M, Aerospace Corporation 4150 Donald Douglas Drive Long Beach, California 90808 92? 5 5. (For certi?cation basis see TC Data Sheet A12EA for Model Aircraft) A12EA Vainstaiiation of a Cockpit Jumpseat (Custom Productsi1875- 35 in accg?ldc?hce aper Aerospace Corporation Index List lL 11011122, Revision dated February 9, 1988 or later approved revision. FAA Approved oxygen system STC SA147380 or 5T00812AT: must be lstalled for use the occupant of this cockpit seat. This installation should not be incorporaied in any aircraft unless It is determined that the lnterreiation?ship between this Wary (in: ?agww: November 4, 1987 mew- ?cag/M: February19,1988 4 (Lemma: October 10, 1996 .g?g?JMJ-n .Pgm 0314:}! More (Sigmund DAS Coordinator. DASSNM (Till!) 11:37 akaalr'orz nfUlir a-rh?cd: 13 pum'xlxabl: by a?m afno? 31,000, or I'nyOanmw-i! ml (ml-c151; Samar, or both. - TM: aro?mk ray 5: in.? 05/21/2001 08:29 FAX 5626276168 DAS @002 A GENERAL DVNAIVIICS COMPANY May 21, 2001 Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 Subject STC Authorization Attn: Stanley Godek By receipt of this letter, you are hereby authorized by AerOSpace Corp, Long Beach to use STC SA3660NM-D, SA4286NM-D, and ST00817LA-D for the modification of aircraft, SN 1425 only. I trust this letter will provide you with the necessary information. However, should you require further clari?cation, please Contact the undersigned at (562) 627-5030. Sincerely, Marco A. Morejon, DAS Administrator, DAS-100271-NM Long Beach CC. Doug Prentiss Randy wood Aerospace Corporation. 4150 Donal-3' Douglas Drive, Long Beach, California 90808. Telephone 562-620-1815, Fax' 562-62?-5090 . ?nk: or Errata; of ?thranaportahon ?-jii?drr9t ?otation ?QEgpz-O?mi?cate I 8T00817LA-D gumgzo Aerospace Corporation 4150 Donald Booglas Drive Long Beach, California 90808 AQMWMAW Jo,? ,1 25 . Fecjeral AViatiOn . (For certification basis see TC Data Sheet for Model Aircraft) a? . 4 4/34. .5 5- . f} . installation of Nordam Acoustic Liner in accordance with approved orporat on index List 60128288004, Revision dated November 29. 1999 or later approved revision. :l'his installation should not be incorporated in any aircraft unless it is Wig/:8 in erretationship between this change and any previously approved con?guration will not introduce any adverse effect upon the airworthiness of the aircraft. i If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. . - 57%. m- a. m- 26. 1999 - DEC-ember 1, 1999 I (M;'rt Marco A. DAS Coordinator, DASBNM \k Tl'lfr} no! acceding 3 or both. 11:9: nth-ration Bf?n': (digital: l-J pum?u?iobi?c a_?nc qfnoi 31,000, at I?m?rfjo I Tin} urn-?tnlr Ina] b: candor": {0&5 FAR 21-!7. nu los- ?10-Jun-05: 05/21/2001 08:29 FAX 5626276168 DAS @002 A GENERAL DVNAMICS COMPANY May 21, 2001 Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 Subject STC Authorization Attn: Stanley Godek By receipt of this letter, you are hereby authorized by Aerospace Corp, Long Beach to use STC SA3655NM-D, SA4286NM-D, SA4291NM-D, and ST00817LA-D for the modi?cation of G-IV aircraft, 1425 only. I trust this letter will provide you with the necessary information. However, should you require further clari?cation, please contact the undersigned at (562) 627-5030. Sincerely, 549/. Marco A. Morejon, DAS Administrator, Long Beach CC. Doug Prentiss Randy wood Aelospace Corporation. 4150 Donald Douglas Drive, Long Beach, California 90808. Telephone' 562-420-1818, Fax- 562-627-5099 ??nitr? Starts at ma of transportation aviation ?dminiattgtiun Emit Qtrti?tatt A . 3/29? We, Aerospace Corporation PO. Box 2206 Savannah, GA 31402 WM 14,, WW 25 y? Federal ?Al/iation Wm?. A12EA . MInstallation of 21 Passenger stem, in accordance with Aerospace Co oration Index List 4538001, Rev. B, ted ctober 07, 2000, or later FAA approved rewsion. approved Airplane Flight Manual Supplement, GC41 453M004, dated October 27, 2000, or later FAA approved revision is required. The follow on oxygen plumbing installations for this STC must be compatible with an oxygen equipment layout drawing approved as a deviation for the Speci?c interior layout of each aircraft. The installation of this to be ?mctionally ground and ?ight tested per the test plans listed in GC41 453A003, Instructions for Continued Airworthiness. Compatibility of this design change with previously approved modi?cations must' be determined-by the installer. If the holder agrees to permit another person?to use this certi?cate to alter the product, the holder shall give the other person written evidence of that permission- ?rma??mA/a?xdl Wed e'd M/(cr- effi?go August 22, 2000 f/xu? Middle/I/S gees/mm.- October 20, 2000 October 27, 2000 .g/Me I ferry?outwelr (Signature) AS Administrator, 1 l3 I-CE (Title) An} alteration aftlu's certi?cate is punishable by a'?ne of not exceeding 31,000, or imprisonment not exceeding 3 years, or both. This certi?cate may be transferred in accordance with FAR 2!.47. FM Fom 81 10?2 (10?68) 5 SDIJIPIAEEY May 4, 2001 AemSpace Corporation 7440 Aviation Place Dallas, TX 75235 Subject: STC Authorization Attn: Danielle Chipps Aerospace, Savannah, Georgia (the STC Certi?cate Holder) authorizes AerOSpace Dallas, Texas, to use the following Supplemental Type Certificate(s): SA2657SO ST00248AT SA2809SO SA2839SO ST02185AT-D STOI545AT-D for installation in a model 1425 aircraft. Additional authorizations may be obtained by submitting a request to the DAS Administrator, specifying the applicable aircraft serial number(s) intended for this installatiOn. Should you have any questions, please do not hesitate to contact the undersigned. Sincerely, Carmen L. Djulvezan STC Analyst Gu?skeam Aersspace Carnation. 9.0. Box 2206. Savannah, Georgia 31402-2206. Telephone: 912-965-3000 Sm uranium of Enumeration. frat-m! aeration administration "1!:ng (intimate ST02184AT-D Aerospace Corporation PO. Box 2206 Savannah, GA 31402 5- 2 25. . 25 952$, Federal Aviation Wm AREA Wg?zy?ug ?510,70.- lnstallation of an Emergency Power System, in accordance with 611 stream Aerospace Eorporation Index List GC41 189800], Rev. D, dated September 20, 2000, or later FAA approved revision. FAA approved Airplane light Manual Supplement, 6011 189M001, dated September 22, 2000, or later FAA approved revision is required. Compatibility of this design change with previously approved modi?cations must be determined by the installer. If the holder agrees to permit another person to use this certi?cate to alter the product, the holder shall give the other person written evidence of that permission. Mfg/1% ?$422437 (51 (Ilvgo - .m m? August 21, 2000 Iceman/.- meg/Mm; September 22, 2000 .1). ya?M/?Trm inc/or? Q/jm gee/?xlr/ J8 {Signalma} Administrator, DAS-SI I 13 Title) . An} alteration offal-r certi?cate is punishable Q), a?ne qf not exceeding 31,000, or imprisonment not exceeding 3 years, or both. This certi?cate ma} be tramferred in accordance with FAR 21-47. rout BI l0-2 - - May 4, 2001 Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 Subject: STC Authorization Attn: Danielle Chipps Aerospace, Savannah, Georgia (the STC Certi?cate Holder) authorizes Aerospace Dallas, Texas, to use the following Supplemental Type SA2657SO ST00248AT SA2809SO SA2839SO ST02182AT-D ST02184AT-D ST01545AT-D for installation in a model 1425 aircraft. Additional authorizations may be obtained by submitting a request to the DAS Administrator, specifying the applicable aircraft serial number(s) intended for this installation. Should you have any questions, please do not hesitate to contact the undersigned. Sincerely, 7 79107.?, {40% Carmen L. Djulvezan STC Analyst Gait st: 933'. As ospace Ceres. '22 ion {-10.832206 Satcnnah. Georgias 31402- 202 6. Tefephone:912-965-3000 ?Bnimi is at Emma of ?'jkd?ral ?otation ??ministm?on ??11?,ng Enti?tatr - Aerospace Corporation P.O- Box 2206 Savannah, GA 31402 25 ems Federal Aviation Wm?. WM?tg?ow: AIZBA ArgoInstallation of Interior Emer ency Li ts, in accordance with Aerospace Corporation Index List (301] 4868002, Rev. dated eptember 20, 2000, or later FAA approved remsron. ?qu/?gmw/MJ Compatibility of this design change with previously approved modi?cations must be determined by the installer- If the holder agrees to permit another person to use this certi?cate to alter the product, the holder shall give the other person written evidence of that permission. 9.60%? WW ?0721. fia??Wi?a??m? August 16, 2000 September 21, 2000 .?ya?'mmwr/ x14? JC Boutwell (Signature) Administrator, - - (Tin?) Aryr alteration qfthit certi?cate is punts/table Efy a?ne ofnol exceeding SLOW, or imprisonment not exceeding 3 years, or both. .leir certi?cate may be transferred in accordance with: FAR 21.47. tom Bl 10-2 (Io-ca) GE. JCS May 4, 2001 Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 Subject: STC Authorization Attn: Danielle Chipps Aerospace, Savannah, Georgia (the STC Certi?cate Holder) authorizes Aerospace Dallas, Texas, to use the following Supplemental Type SA2657SO ST00248AT SA2809SO SA2839SO ST02184AT-D ST02185AT-D for installation in a model G-IV, SN 1425 aircraft. Additional authorizations may be obtained by submitting a request to the DAS Administrator, specifying the applicable aircraft serial number(s) intended for this installation. Should you have any questions, please do not hesitate to contact the undersigned. Sincerely, ?7 *Qrz Carmen Djulvezan STC Analyst Gut? us: earn Ae: snore tton. RC. Box 2206. Savannah. Georgia 31402-2206. Telephone: 912-9615- 3000 llnileh 07f America nf - pilE'ehcral Cathialinn ?uppleme?tal (@ng Gerti?catie . _1 ST095818C AerosPace Comoration 7440 Aviation Place Dallas, TX 75235 11-1/1- 111' r/1111/1- 111 11 /1-r 1111711/11-111' ?11/ [11-1111 17711111111111/1'1 /111-/ .1 7131/11/11? 11- 4111/1/11. A 1 ZEA ?2/6111; Aerospace Corporation 6-1159; 0415913; _Z1~jrr1/1/1111 11 5/191)? {/1111113- Installation of MSA Accordia Window Shades in accordance with Index List number GC420008096, Rev- dated 1 110200 01 laten FAA app1oved 1ex ision. ?111/ {61111111.}.- Compatibility ofthis design change with previously approved modi?cations must be determined by the installer. lithe holder agrees to permit another person to use this certi?cate to alter the product, the holder shall give the other person written evidence of that permission. J11/1/11-r/111/ 1 11/11 11/11/ 131? 11/ /1/11 11/. 111 1/1/1111/1f .5111-11111/111-1/ 1'1'1 1-/11/11' 11 /11'11111111/1111 1/ 1/1 1-) 11/11/ 41/11/ /1 1/1/11- '41-111/11-11, .1 51/11/1- November 7, 998 04.1999 5/11/1- 1111111111/1/ November 20. 2000 1/171/11-11 . . A23. S. Frances Cox Manager?, Special CertificatiOn Of?ce SOuthwest Region (Til/1') any cinnamon 0! this certificate is punishable by a fine of no: exceeding $1.690. c: not exceeding 5 years. a: 11:41:. -I FAA Fan-1 rage accordance 11::31 21.61?. 2001?46 U.S. DEPARTMENT OF TRANSPORTATION DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS 29 May, 2001 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL NO. TYPE (Airplane, Radio, Helicopter, NAME OF APPLICANT Aerospace Aerospace G-IV Airplane Love Field, Dallas, TX LIST OF DATA IDENTIFICATION TITLE GAC DOCUMENT AEROSPACE DATA LIST GC414680076 D.L. Miscellaneous Electrical Modi?cations Rev. I Dated 5/23/01 END OF DATA SI: 1. This approval covers electrical systems and equipment design aspects only. 2- Approval of this data does not constitute installation approval. 3. This approval valid for SIN 1425 only. PURPOSE OF DATA . Support of installation and/or modi?cation of miscellaneous electrical/electronic systems accomplished during completion of aircraft 1425. APPLICABLE REQUIREMENTS (List speci?c sections) FAR FAR 25.1351 FAR 25.1381 FAR FAR 25.1353(a) FAR 25.1431 FAR 25.1309(a) FAR - FAR 25.1322 . FAR 25.1359(d) CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered None have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. I (XX) Therefore Recommend approval ofthese data Approve these data OF DESIGNATED ENGINEERING REPRESENTWEIS) DESIGNATION NUMBERS) DERY-710088-SW Systems Equipment -r . ?7 CHARLES E. ETHERIDGE . PAR 25 FAA Form 81 10-3 (1 -70) SUPERSEDES PREVIOUS EDITION (COMPUTER GENERATED) File: us. oiwa?mem 05 TRAFSPORTATION Dale FEDERAL AVIATEON WTRATION STATEMENT OF COMPUANCE THE FEDERAL ATION REGULATIONS May 30, 2001 AIRCRAFT 0R AIRCRAFT COMPONENT IDENTIFICATION m??E NOBEL no. TYPE (Airplane. Radio, Helimprer. NAME OFAPPUCANT Aerospace Corp. Airplane Dallas, Texas LIST OF DATA . Whore ME 60420000266 DATA LIST MECHANICAL . Rev A STC Dtd.5/29/01 md NOTE: I. The above data details avionics/electrical custon?zation items incorporated in SIN 1425 2- This 81 l0?3 approves the Design and Structural aspects of 1the above data only. Systems Equipment [Electrical] evaluation is required for this installation. The aircra? must be returned to service in accordance with all applicable FARs. me or DATA To show compliance with FARs for modi?cations to Gul?stream G-IV Serial Number 1425 only. REGUIREAENTS (List :paci?c nanom) FAR 25.301, .303, .305, .307, .601, .603, .605(a), .609 CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Pm 183 ofthe Fedetal Regulations, date listed ebovc and on attached sheets numbexed . have been examined in accordance with established pmcedurw and found to comply with applicable requirements of the Federal Aviation Regulations. IWa-cfore Recommend approval of these data Approve these data . OF DEBBNATED DESEGNATFON NWBERLS) CLASSIFICATIOMIS) BERT-7 10242-SW Structures, stems Bqui 1" #67 l?-ny it. 3? 9mg George B. Sparling PE . Management FAA Form 31104 (AEC Comm Gmrala-d 1292} A8 39Vcl 11439141st 838VSSL-LT8 1883/88/98 arm :5an arm of ?UEansportation ?j?zdzrai aviation administration ?@ng (Enti?tatz . . . Aerospace Corporation P- O. Box 2206 Savannah, Georgia 31402 Am, . 25 Federal Aviation 220W: am - M: M, Installation of a vertical fin mounted RACAL Avionics Ltd- Satellite Communication (SATCOM) Radome and Antenna in accordance with Aerospace Corporation Drawing List SC44 103807, "Index List SATCOM Antenna Installation", Revision A, dated May 24, 1993, or later FAA approved revision. This STC is for structural provisions only and does not include evaluation of the operation of the SATCOM System. This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will produce no adverse effect upon the airworthiness of that airplane- Wig/?e owzufn?? ?w/(ao 9/Ma February 9 19 9 3 (Az? June 2 I 19 93 @oger . Andesg's?z} Manager, Atlanta ircraft Certification Office Title) An} alteration of [his certi?cate is punisha?le by ?ne of not exceeding $1,000, or imprisonment not exceeding Byears, or bot/1- This certi?cate ma}- be lramferred in aecordanre FAR 21.47. FM Fan-I 8l10?2{10?68) AG: NE :5 May 4, 2001 Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 Subject: STC Authorization Attn: Danielle Chipps AemSpace, Savannah, Georgia (the STC Certi?cate Holder) authorizes AerOSpace Dallas, Texas, to use the following Supplemental Type SA2657SO ST00248AT SA2809SO SA2839SO ST02184AT-D STO2185AT-D ST01545AT-D for installation in a model G-IV, 1425 aircraft. Additional authorizations may be obtained by submitting a request to the DAS Administrator, specifying the applicable aircraft serial number(s) intended for this installation. Should you have any questions, please do not hesitate to contact the undersigned- Sincerely, {diam jg/jrt?izet Carmen L- Djulvezan j? STC Analyst DAS-511131-CE Aerospace craa aticn. $3.0 Box 2205 Saxannah. Georgi: z: 3 1-102- 2206. T=lephone2 912- 965 6000 File: US. DEPARTMENT OF TRANSPORTATION Date FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVI ATION REGULATIONS May 23, 2001 0R AIRCRAFT COMPOWENTIFICATION MAKE MODEL no. TYPE (Airplane, Radio. Helicopter, NAME OF APPLICANT G-IV 9W Aerospace Corp. Airplane Dallas, Texas . LIST OF DATA TITLE GC41103 6006 INDEX LIST SATCOM RADOME ANTENNA INSTL. (RACAL) Rev STC Dtd.4/ 12/01 ernd NOTE: 1. The above data details the deviations to an existing installation as incorporated in 1425- 2. The deviations do not impact the structural integrity of the previously approved installation. 3. This 8110-3 approves the Design and Structural aspects of the above data only. The aircraft must be retumed to service in accordance with all applicable FARs. PURPOSE OF DATA . I To show compliance with FARs for modi?catioas to G-IV Serial Number 1425 only. APPLICABLE REQUIREMENTS (List speci?c: sections) FAR 25.301, .303, .305, .307 per note 2 above. FAR 25.601, .603, -605(a), . 609, .611, .1301(a) by data review. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and Iimitatiozrs of appointment under Part 183 of the Federal Aviation Regula?ons, data listed above and on attached sheets numbered have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. I OM Therefore El Recommend approval of these data Approve them- data OF DESIGNATED ENGINEERING Structures, 7 . 1354/41 fk/?/I/Ifza . System &Bq?1Pmta George B. Sparling PE Management FAA Form 8110-3 (AEC Computer Generated 12/92) 'd E96 HIS H79 Zl? 33V WV6l=l IOOZ 1%??de Wit of (imam?Emma 311121111111 Miriam-11111111 $11,131: Mame/x SAZ622NM I earl/We, airmen/tot Precise Flight, Inc. 63120 Powell Butte Rd. Bend, OR 97701 car/2' 4:41 afar a 1% We d?/??wi/y/a?aa?zci ?12% 1% @2211?;an Wcaw'ia'arw Klara/?red ?agged/?rearm meg/d Mia: ?WU/{mid ragamma? #94214 @W?amr?% ga/f?/?v?caidM/t' *see attached FAA Approved Model List (AML) M: No. list of approved airplane models and applicable airworthiness regulations Earp/52112214 (Ty??eQZwQ/a gig/gag.- Installation of Precise Flight, Inc Pulselite Control Unit 1n the Land1n0fl?ax1 Recognition Visual Control Light system, in accordance with the appropriate Precis Flight Manual as listed on FAA AMI. No. SA2622NM dated September 1, 1999, or later FAA approved revision. NOTE: This Pulselite system is considered Optional equipment and the aircraft may be diSpatched with the system turned off. In case of malfunction, an alternate means of deactivating the system by pulling the circuit breaker has been evaluated as an alternate con?guration and is considered acceptable for dispatch 5&uratiww ma?gaxza?Z?co/M: Approval of this change 1n type design applies to the above model aircraft only This approval should not be extended to other aircraft of this model on which other previously approved modi?cations are incorporated unless it is determined by the installer that the relationship between this change and any ofthose other previously approved modi?cations, including changes 1n type design, will introduce no adverse effect upon the airworthiness of that aircraft. A copy of ?ns certificate, and FAA approved AML No- SA2622NM, dated September 1, 1999, or later FAA approved revision, must be maintained as part ofthe permanent records for the modified aircraft. If the holder agrees to permit another person to use this certi?cate to alter the product, the holder shall give the other person written evidence of that permission- 1/0752}! cert; ataxia mag/(? a/dz?a MM 63 fairly-4r (Ira ?at (2412/ Jw?re/aa?ma/ Jw/wna?a/ ravaged or a [dimmiw/a 53 0512/1505}; 4% Ma?zmi?ula/ Jazz/e/a/Jy??a??mxa ?Wtraimm 9m q/qyz/abaiio/z: AprilZO, 1984 gate/val?wd' July 13, 1984 gafamd' July 22, 1987; March 31, 1988; 1 August 24, 1992; May 20, 1993 September 13, 1999; April 21, 2000 1 1' - If .95? yawn? a/M? Manager,- 4? XIL 1.14:1 Egg/'2 l\ (Sightilure) I Acting Manager- Seattle Aircraft Certification Of?ce (Title) Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years. or both. This certificate may be transferred in accordance with FAR 21.47_ FAA Form 3110-2110-1381 A luiqo rhlunl 1m; 113113041 066 HUD -:pn?ass mom, mc. Scott Philiben Vice President Engineering Precise Flight Inc. . 63120 Powell Butte Rd- Bend, OR 91(01 November 29, 2000 Aerospace Dallas TX Starting on November 29. 2000, Aerospace is authorized to use STC SA2622NM Pulselite Model 11503. Si/ntjerely, My @fott Philiben - ice President of Engineering Fax to 214-902-7796 HM. $110 l'uwc" Bum: Hold 54 382 3634 8005157 3353 Bend. Dream 9770! l?MAil ?05 File: Dag. 4 STATEMENT OF COMPLIANCE THE FEDERAL ATION REGULATIONS May 30, 2001 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION moat. NO. TYPE ?0151mm. Radio. Helicopter, NAME OF G-IV m) Aerospace Corp. Airplane Dallas, Texas USTOFDAIA manor: rm: 6011188603 8 DEVIATION DATA LIST PRECISE FLIGHT PULSELITE CONTROL Rev A STC Dtd.5/22/01 end NOTE: 1. The above data details the deviations to an existing installation as incorporated in SIN 1425. 2. The deviations do not impact the structural integrity of the previously approved installation. 3. This 81 10-3 approves the Design and Structural aspects of the above data only. Systems Equipment [Electrical] evaluation is required for this installation. The aircraft must be returned to service in accordance with all applicable FARs. ammo: OF DATA To show compliance with FARs lior modi?cations to G-IV Serial Number 1425 only. REWNTS :pect?c sectional FAR 25.301, .303, .305, .307 per note 2 above. FAR 25.601, .603, .605(a), . 609, .611, .1301(a) by data review. Under authority vested by direction ofthe Administrator and in with conditions and limitations under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered have been examined in accordance with established procedmcs and found to comply with applicable requirements of the Federal Aviation Regulations. Therefore approval ofthese data Approve these data - SIGNATURE OF oesmrao ancmasamo Humming) M7 sanctum, [5341/57 yK/?/Ahf?b Systemsd?quunpment, George B. Sparling PE Management PM Form 81104! (AEC Generated 12192) SE 1N3 838b?6ir?18 ?1391: 2001-41 US. DEPARTMENT OF TRANSPORTATION DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS 29 May, 2001 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL NO. TYPE (Airplane, Radio, Helicopter, NAME OF APPLICANT em) Aerospace Aerospace Auplane . Love Field, Dallas, TX LIST OF DATA IDENTIFICATION TITLE GAC DOCUMENT AEROSPACE DATA LIST 1886038 D.I.L- Precise Flight Pulselite Control Rev. A, Dated 5/22/01 END OF DATA NOTE 1. This approval covers electrical systems and equipment design aspects only. 2. Approval of this data does not constitute installation approval. 3. This approval valid for SIN 1425 only. PURPOSE OF DATA Support of installation of Pulselite control system using STC SA2622NM with deviations. APPLICABLE REQUIREMENTS (List Specific sections) FAR 25.1301 FAR 25.1351 (3) FAR 25.138305) FAR 25.1307 (0) FAR 25.1353 (3) FAR 25.1309 FAR 25.1357 FAR 25.1322 FAR CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered None have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. Recommend approval of these data I Therefore Approve these data SIGNATURES) OF DESIGNATQENGINERING DESIGNATION Systems Equipment CHARLES E. ETHERIDGE _7 - FAR 25 FAA Form 81 10-3 (ll-70) SUPERSEDFS PREVIOUS EDITION (COMPUTER GENERATED) of Eransporigrio ?jidtrat?gbignon gdminisrrarion (?ng (intimate SA2809SO xylem-M4, Aerospace CorporatiOn 0. Box 2206 Savannah, GA 31402 Wm?. A IZEA M: WM on gdf?'gxaw' Installation of a Global-Wulfsberg Airborne Flight Information System (AFI per Aerospace Corporation Index List 306801, Rev. Pg dated July 24, 1990, or later FAA approved revision. This approval should not be extended to other aircraft of this model on which other previously approved modi?cations are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modi?cations will produce no adverse eHed upon the airworthiness of that airplane. FAA Approved Airplane Flight Manual Supplement, dated August 3, 1990, or later FAA Approved revision, is a required pan of the STC. .o/J 495.0 yam/.- 5/24. Imma: May2,1996 {Signature} Associate Manager,ACE?l 16A Atlanta Aircraft Certi?cationO?rlce (Trrl'rf (A. An} alrnolran qfh?lu punishabl} by a of nor cxrna?mg H000 or nor 0" 1? (n rhj?luh mo} In crtardonu WI If}! FAR 2f IM m- 38: 0 A 553353;?. May 4, 2001 AerOSpace Corporation 7440 Aviation Place Dallas, TX 75235 Subject: STC Authorization Attn: Danielle Chipps AerOSpace, Savannah, Georgia (the STC Certi?cate Holder) authorizes AeIOSpace Dallas, Texas, to use the following Supplemental Type SA2657SO ST00248AT SA2809SO SA2839SO ST02182AT-D for installation in a model G-IV, 1425 aircraft. Additional authorizations may be obtained by submitting a request to the DAS Administrator, Specifying the applicable aircraft serial number(s) intended for this installation. Should you have any questions, please do not hesitate to contact the undersigned. Sincerely, 7V9 . [Zigm a-L?iaez :1 Carmen L. Djulvezan 7 STC Analyst DAS-511131-CE Enlistment Aerospace Corp-:2: tic-1?. R0. 50:: 2266. Savannah. Georgia 31402-2206. Telephone: 912-965-3000 I File: us. DEPARTMENT or TRANSPORTATION Dale I FEDERAL AVIATION ADMINISTRATION. STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS May 23, 2001 AIRCRAFT 0R AIRCRAFT COMPONENT MAKE MODEL NO. TYPE airplane, Radio. Helicopter. NAME OF APPLICANT G-IV m) . Aerospace Corp. Airplane Dallas, Texas LIST OF DATA IDENTIFICATION ms 60413 066046 DEVIATION INDEX LIST AHS Rev - STC Dtd.4/22/01 . ..- end NOTE: 1. The above data details the deviatiOns to an existing installation as incorporated in SIN 1425. 2. The deviations do not impact the structural integrity of the previously approved installation. 3. This 8110-3 approves the Design and Structural aspects of the above data only. Systems Equipment [Electrical] evaluation is required for this installation. The PURPOSE DATA aircraft must be returned to service in accordance with all applicable PARS. To show compliance with PARS for modi?cations to Serial. Number 1425 only. APPUCABLE sections) FAR 25.301, .303, .305, .307 per note 2 above. . FAR 25.6013 .603, .605(a), . 609, .611, .1301(a) by data review- CERTIFICATION - Under mrthority vested by direction of the Administrator and in accordance with conditions and limitations of under Part 183 of the Federal Aviation Regulations, data listed above and an attached sheets nmnbered have been caramined in accordance ?With established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. I 9?43 Therefore I: Remand approval of these data Approve these data SIGNATURES) 0F DESIGNATED ENGINEERING DESIGNATION NUMBERGS) CIASSIFICATIOMS) 0242- SW - Structures, F444 System ?Wm? George B. Sparling PE I Management PM Form 8110-3 (AEC Computer Generated 1292) 6 'd HIE 1?99 316 . 03V WVOUI 2001-43 us. DEPARTMENT OF TRANSPORTATION DATE . FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS 29 May, 2001 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL NO. TYPE (Airplane, Radio, Helicopter, NAME OF APPLICANT em) Aerospace Aerospace G-IV Airplane I Love Field, Dallas, TX LIST OF DATA IDENTIFICATION TITLE GAC DOCUMENT AEROSPACE DATA GC413066046 D.I.L. - GLOBAL WULFSBERG AFIS Rev. Dated 4/22/01 END NOTE 1. This approval for electrical systems and equipment design aspects only. 2. Approval of this data does not constitute installation approval. 3. This approval valid for SIN 1425 only. PURPOSE OF DATA Support of installation ofGlobal-Wulfsberg AFIS using STC SA2809SO with deviations. APPLICABLE REQUIREMENTS (List speci?c sections) FAR I FAR 25.1322 FAR 25.1359(d) FAR 25.1307(c) FAR 25.1353(a) FAR 25.1431(c) FAR FAR authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered None have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. I (XE) Therefore Recommend approval of these data Approve these data 0F DESIGNATED ENGINEERING DESIGNATION CLASSIFICATIONS) Systems Equipment CHARLES E. ETHERIDGE FAR 25 FAA Form 81 10-3 (11-70) SUPERSEDES PREVIOUS EDITION (COMPUTER GENERATED) of transportation ?j?rdzral sanitation Edministration @ng Gian?ratr 9933950 6 - - . ?14in Aerospace Corporation- P- O. Box 2206 Savannah- GA 31402 25 ?J?a Federal Aviation Wm g? (92 ?gg 5 45,4, .. AIZEA M.- G-IV . . 6' . - Modi?cation to allow dISplay of course donation information from a Honeywell Laser Track Inertial Navigation System on the Honeywell or Electronic Display System, per Index List SC 4 1 l383 1. Revision B. dated March 29, 199 l, or later FAA approved revision.. . This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will produce no adverse effect upon the airworthiness of that aircraft. FAA?approved Airplane Flight Mahual Supplement 13MOZ, dated September 26- 199l, or later FAA Approved revision, is a required part of this STC. ?W??oMa do Janina?! ?-vz/or (/69 March 23. l990 f/h? Eja??j/mm. September 26, {990 July 3, W91, August ll, 1995 David P. Westh' (513mm: Associate Manager, I6A Atlanta Aircra? Certi?cation Of?ce (Title) alteration qflizfs certi?cate is [21? ?(?4535 31,000, 0? ?5?de 31?0": 0? both. This czrr?cate ma} be transferred in. acmra'anct with FAR 2117. (Mica: 8H0?2llO?60} A 353525133. Dalmpmazszs May 4, 2001 Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 Subject; STC Authorization Attn: Danielle Chipps Aerospace, Savannah, Georgia (the STC Certi?cate Holder) authorizes Aerospace Dallas, Texas, to use the following Supplemental Type SA2657SO ST00248AT SA2809SO SA2839SO STOZ 1 ST02 1 85AT-D ST01545AT-D for installation in a model 1425 aircraft. Additional authorizations may be obtained by submitting a request to the DAS Administrator, specifying the applicable aircraft serial number(s) intended for this installation. Should you have any questions, please-do not hesitate to contact the undersigned. Sincerely, .. .7 7? . 4/4711. ?air? Carmen L. Djulvezan STC Analyst Gu?skear?u Aemspaca Coroeratien. P10. Sex 2208. Savannah. Georgia 31482-2266. Telephone: 912-965-3000 2001-40 US. DEPARTMENT OF TRANSPORTATION DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS 29 May, 2001 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL NO. TYPE (Airplane, Radio, Helicoptel; NAME OF APPLICANT em) . AerosPace Aerospace G-IV Airplane Love Field, Dallas, TX LIST OF DATA IDENTIFICATION TITLE GAC DOCUMENT AEROSPACE DATA LIST GC411 136030 D.I.L. Rev. Dated 4/22/01 END OF DATA NOTE 1. This approval covers electrical systems and equipment design aspects only. 2. Approval of this data does not constitute installation approval. 3. This approval valid for SN 1425 only. PURPOSE OF DATA Support of installation of LASERTRAK Navigation System using STC SA283980 with deviations. APPLICABLE REQUIREM ENTS (List speci?c SECTIONS) FAR FAR 25.1307(c) FAR FAR 25.1335 FAR 251351 FAR 25.1353(a) FAR 25.1359(d) FAR 25.1381 FAR 25.1431 FAR 25.132901) FAR CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered None have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. Recommend approval of these data I W) Therefore Approve these data ENGINEERING REPRESENTATIVES) DESIGNATION NUMBERS) CLASSIFICATIONS) Systems Equipment CHARLES E. ETHERIDGE PAR 25 FAA Form 8] 10?3 (1 1-70) SUPERSEDES PREVIOUS EDITION (COMPUTER GENERATED) of ?Emmportntion?j ml Emotion ??minisrmtion ?Uliypa Eerti?tatz 3385mm :ZbeaMy?mz?AMua?lb Roaen Product Development Inc. Lay/fair. filmy/5r wtv?w?2n (Zn/(hr: 25 ,9/Ida Aiviation ?fa?z?'oruk . @mf??hh/f?n?r: Al 213A Aerospace M.- C4 i - Cockpit Sun Visor installation in accordance with pproyed Rosen Drawing List Number OODL, dated September 12,1986, or later pproved revisions. - The approval of this change in type design applies basically to the above aircraft model only. This approval should not be extended to other aircraft of this model on which previously-approved modifications are incorporated, unless it is determined that the interrelationship between this change and any other previously approved modifications will introduce no adverse effect upon the airworthiness of that aircraft- A copy of thi_s Certificate and FAA?approved Drawing gist Number OODL shall be maintained as part of the permanent records of the nodvi?ed ai craft. Ir/?gdr mrta/a-aIKAuA/t 5/1475??sz 0,01 m6): J: [m izazmJm??a?anna?znana?aeznu ?ay/,A/Azaazm: March 1'3, 1987 @Jamaaual: 'June 18, 1987 ?amgmags - y?V?Nv Assistant Manager, Seattle Aircraft clutch-nu 9/1513 ruh?fual?c puny-51min? qfno! $1,000, or no! (Inuit-n! 31:01.? or bar/t. Tin-J (?nri?lolr ma} 5: haru?nzd' ortuxJonrt xvi-t]: FAR [an? hl ., - Rosen Product; LLC 1020 Owen Loop South Eugene, OR 97402 Phone: (541) 342-3802 November 29, 2000 - Aerospace Corp Dallas? z. To whom it may concern, This letter 18 to be considered permission to use for installations of Rosen Part Number RGIV 300-1, Sunvisor Monorail system for the GIVhaunt. . 'u[Zr/?h enmehouse Customer Service Supr. Rosen Products LLC ?In; tl? i 3. aw .t .312?. - airing ski/?UNLIMITEDYISION iinicrd S. . of ?rm-ire iBEpgrn'nznr of 1213:1an UI?lIintlli ?jl?rd?rIIl ?niation Sl?minisrrerion ?6]:ng @rrti?ratr ?aw?wgo Gulistream Aerospace Corporation 4150 Donald Douglas Drive Long Beach, California 90808 Wm (For certification basis see TC Data Sheet A12EA for Model Aircraft) [44. M: le jw Installation of a BF Goodrich ADI-335 standby. attitude indicator in accordao ce gmhew apr roved configurations defined on Aerospace Corporation Index List lL 11011448, Revision dated November 27, 1995 or later approved revision. Approved Aerospace Corporation Airplane Flight Manual Supplements required for the various approved configurations are listed on the approved Aerospace Corporation Index List. This installation should not be incorporated in any aircraft unless it is determined that the interrelationship between this change and any previously approved configuration will not introduce any adverse effect upon the airworthiness of the aircraft ?5414-1 d?/?dd igu- Ma dad/W1? will 27 a3 -7- 3?me .8424..an september 29,1995 .?z?oymms December 18, 1995 .?yAk/Zn/ ac. [auras/MA- 449/. 4 1,4 QED .- (Signatuuj DAS Coordinator, DASBNM r'TIllr} .4 diltranon a 7-H: rati?rat: 2'5 unlit-molt 51' a itnc I) .110! ?'xradin 37,009- In no! c'erO'HW .3 ran}, int/'1. 1 - - in: :car 5: urrunirmrr .?ruf: 5?31? Foo- 8 I (IO-68) 05/21/2001 08:29 FAX 56262?6168 DAS @002 A GENERAL DYNAMICS COMPANY May 21, 2001 Aerospace Corporation 7440 Aviation Place Dallas, TX 75235 Subject STC Authorization Attn: Stanley Godek By receipt of this letter, you are hereby authorized by Aerospace Corp, Long Beach to use STC SA366ONM-D, SA4286NM-D, SA4291NM-D: and ST00817LA-D for the modi?cation of aircraft, SW 1425 only. I trust this letter will provide you with the necessary information. However, should you require further clari?cation, please contact the undersigned at (5 62) 627-5030. Sincerely, Marco A. Morejon, DAS Administrator, DAS-100271 -NM Long Beach CC. Doug Prentiss Randy wood Aerospace Corporation, 4150 Donald Douglas Drive, Long Beach, California 90808. TeiephonE' 562-420-1816, Far 562-627-5090 2001?39 us- DEPARTMENT OF TRANSPORTATION DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS 29 May, 2001 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL NO. TYPE (Airplane, Radio, Helicopten NAME OF APPLICANT etc-J Aerospace Aerospace G-IV Auplane Love Field, Dallas, TX LIST OF DATA IDENTIFICATION TITLE GAC DOCUMENT AEROSPACE DATA LIST 60113316030 D.D.L- Standby Attitude Indicator (ADI-335) Rev. A, Dated 5/22/01 END OF DATA 1. This approval covers electrical systems and equipment design aspects only. 2- Approval of this data does not constitute installation approval. 3. This approval valid for SIN 1425 only. PURPOSE OF DATA Support of installation of ADI-335 Standby Horizon using STC SA4286NM-D with deviations. APPLICABLE REQUIREMENTS (List speci?c sections) FAR FAR 25.1331 FAR 25.1359(d) FAR 25.1303(b4) FAR 25.135l(a) FAR 25.1381 FAR 25.1307(c) FAR 25.1353(a) FAR 25.143l(c) FAR FAR CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered None have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. 1 Therefore Recommend approval of these data Approve these data SIGNATURES) OF REPRESENTATIVES) DESIGNATION NUMBERS) CLASSIFICATIONS) . Systems Equipment - CHARLES E. ETHERIDGE FAR 25 FAA Form 81 10?3 {1 1?70) SUPERSEDES PREVIOUS EDITION (COMPUTER g?nitrh gluing. of ?rparimni of UransPUIta?on -- ?eberal CRhialinn cam?ministration ?npplemenial @gpe alertifieai'e STDIO77CH-D JZle Aerospace Corporation W6365 Discovery Drive Appleton, WI 54914-9190 car/?gs 05:5 03?2" (/5547: 1/ {/6105} [fr-0? 60/ ?115/60sz7!an 0599/! a) 0105/; 65': 25 57/7/59 Federal Aviation ?ayagcfz'cwn See Type Certi?cate Data Sheet Al ZEA for complete certi?cation basis. 1'00?! 970%ch - 9? rail/1' far/c -?l/z?kn?r .- ZEA . V/?mg, Aerospace Corporation G-IV ?225579'0/1'5w- 5744/20 gulf/n (555/975.- Installation ofa one or two Piece Tow Bar andfor Crew Ladder (Con?gurations -09,-109, -l 15, -l l9,-l2l,-123,-125 and- 127) the aircra? aft compartment in accordance with Aerospace Corporation Drawing List GAC-MDL-99008, Rev. E, dated December 13, 2000, or later FAA Approved revision. 'gc'w?'lziw? l. Compatibility of this design change with previously approved modi?cations must be determined by the installer. 2. If the holder agrees to permit another person to use this certi?cate to alter the product, the holder shall give the other person written evidence of that permission- .923 ctr/5' (ca/c avid/(Z5- 052155- (005212" (I: .05: fez-sz?z/ (17/0/51sz Jaye/105% {er/J! r/aJZ' (.1 attic/(9134' cMz/gaf?aftfr/ 05$ 56?: (ha/ra/c/ $5 521:0 c/rgo/e?auaam- July 20, l999 92m: July 5 2000 .6220.- July 26, I999 . ?290 amen?rz- February 23, 2000, January 16, 2001 0/ 1% - 7:1 I UV (Signature) Emery P. tse DAS Coordinator, FAA DASZCH Aerospace Corporation Appleton, Wisconsin (Tide) Any aJCeraczon of this cerei?cace is punishable by a fine of not exceeding $1,000. or imprisonment not exceeding 3 years. or both. FAA Form 8110-2l10?68) PAGE 1 of 2 PAGES This certificate may be transferred in accordance with FAR 21.67. MQY. 4.2881 GULi-bthS-lm FUN 9287357139 AEROSPACE May 4, 2001 Mr. David Neese AerOSpace 7440 Aviation Place Dallas, TX 75235 Dear David: Aerospace, Appleton, Wisconsin (the STC Certi?cate Holder) authorizes AerosPace Dallas, Texas use of Supplemental Type Certi?cates for the following aircra? model and serial numbers: G-IV serial number 1422 l. STC No. ST01077CHFD, Aircraft Tow Bar and Ladder Installation 2. STC No. Compartment Storage Box Installation 3. STC No. STOIOSOCH-D, ART BX 406 BLT Installation G-IV serial number 1425 1. STC No. isrm (mono, Aircraft Tow Bar and Ladder Installation 2. STC No. Aft Compartment Storage Box Installation 3. STC No. ARTEX 406 MHZ BLT Installation This authorization is effective for the model and serial number aircra? listed. Additional authorizations may be obtained by submitting a request to the undersigned, Specifying the applicable aircraft serial number(s) intended for the installation- If you have any questions regarding this authorization, I can be reached at 920-735-7114. Sincerely, tat-It? brand tax transmittat memo 7671 l?oiplgox Dew new; CH I PS mm?t NJ e735; Ca. 3PM Phone {5 ?yogi?? ?02? 71323- Fax!? Discovery Drive. Appleton. Wisconsin 54915. [elephune' 920-735-7000. com . ?nniiah 513125 of :Amzrig: . ?epartmerd of -- general Afr-tir?on Wena?m .agupplenrenial (agree MW srororscn-D WW Wk Aerospace Corporation W6365 Discovery Drive Appleton, WI 54914-9190 90.2944/pr ?g Wait! 25 z7/Z? Federal Aviation See Type Certi?cate Data Sheet AIZEA for complete certi?cation basis. . WgaWJy?t?. A ZEA Gulfsn?eam Aerospace Corporation 159A and G-IV 931% 9a?? go?zya- Installation of a Aft Compartment Mounted Storage Box per Aerospace Corporation Drawing List Rev. A, dated July 22, 1999, or later FAA Approved revision. 1. Compatibility of this design change with previously approved modi?cations must be determined by the installer. 2.1ftbe holder agrees to permit another person to use this certi?cate to alter the product, the holder shall give the other person written evidence of that permission. We: WM arm/mm We as; aw;- a, waa/JM/wm a? gram/- Mme/m: 2.66 - . jam @244 July 6, 1999 @422 ray/AmsJuly 26,1999 MW Mn 47/119 .2644;me- . Kgnamre) Emery P. iltse DAS Coordinator, FAA DASZCH Gulfsneam Aerospace Corporation Appleton, Wisconsin (me) Any alzerarion of this cerzifieare is punishable by a fine of not exceeding $1,000, or imprisonzem: not: exceeding 3 years. or both. PM PM alln-Ztlc-G?l PAGE 1 of 1 PAGES This certi?cate my be transferred in accordance with FAR 21-47. mgr. 4.2mm 5319:?: mu 92217357139 2 F2) 0? RU - AEROSPACE CORPORATION May 4, 2001 Mr. David Neese Aerospace 7 440 Aviation Place Dallas, 75235 Dear David: Aerospace, Appleton, Wisconsin (the STC Certi?cate Holder) authorizes AerOSPaee Dallas, Texas use of Supplemental Type Certi?cates fer the following AerosPace aircraft model and serial numbers: serial number 1422 1. STC No. ST Aircra? Tow Bar and Ladder Installation 2. STC No. Aft Compartment Storage Box Installation 3. STC No. STOIOSOCH-D, ARTEX 406 MHZ BLT Installation G-IV sen'al number 1425 I l. STC No. ST01077CH-D, Aircraft Tow Bar and Ladder Installation 2. STC No. STOIO7SCH-D, Aft Compartment Storage Box Installation 3. ST No. ARTEX 406 MHZ ELT Installation This authorization is effective for the model and serial number aircraft listed. Additional authorizations maybe obtained by submitting a request to the undersigned, specifying the applicable aircra? serial number(s) intended for the installation. If you have any questions regarding this authorization, I can be reached at 920-735-7114. Sincerely, - ip) Wiltse - . DAS oordinator, oaszcn at-lt?" brand fax transmittal memo 7671 Isolmgos 1 a ?71f Rho/3:5; Ca. _v . pl. Phone f! . 7523. FBXE Discovery Drive. Appleton. Wisconean 54915, retephuno: 920-735-7000 File: DBRT-71 1/05 6 us. DEPARTMENT or mmspoanmon Dab FEDERAL mum ADMINISTRATION Id?y30,2001 AIRCRAFT 0R AIRCRA-FT COMPONENT IDENTIFICATION MAKE MODEL NO. TYPE airplane, Radio. Haifa-0pm, OF APPUCANT G-IV 9?4} Aerospace Corp. Airplane Danae, Texas LIST OF DATA mm?hon TITLE GC426086005 DEVIATION INDEX LIST - AFT COMPARTMENT STORAGE BOX INSTL. Rev A STC Dtd. 5/24/01 NOTE: 1. The above data details the deviations to an existing installaiion as incorporated in SIN I425. 2. The deviations do not impact the structural integrity of the previously approved installation. 3. This 8110-3 approves the Design and Structural aspects of the above data only. The aircraft must be returned to service in?acoordance with all applicable FARs. To Show compliance with FARs for modi?cations to Serial Number 1425 only. {11m :pccz?c sections) FAR 25.301, .303, .305, .307 per note 2 above. FAR 25.601, .603, .605(a), 609, .611, .1301(a) by data review. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Pan 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered have been examined in accordance With established procedures and found to comply with applimblc requirements ofthc Federal Aviation Regulations. I (W Therefore Reomnmem? approval of these data Approve these data sromrunsrs) OF DESIGNATED ENGINEERING Repnesew?-WEE) nmenrs) DERT-710242-SW Structures, . Fag mega/?4; 8? Equ?Pm?m" George B. Sparling PE . Management Form 8110-3 (AEC Cmnputur summed 12192) 89 39th! ?13913 g?niirb 5 .c5 of glmrita ?Bepartment of r51ramspunriatinn -- glfeheral fibiation c??Ahministraiion ?upplemertial @ng- (?er?ficaie Mfg/d 7/551 60'1" 12/44 (after/4' Aerospace Corporation W6365 Discovery Drive Appleton, WI 34914?9190 arr/f 12;} (y/Ir (fail/fez: [13/7/ (4-1 weer/fet/?/ean areal; //fe c/?o?fl 25 (3/016: Federal Aviation See Type Certi?cate Data Sheet AIZEA for complete certi?cation basis. maf? .7?7/16 -- A EZEA Aerospace Corporation G-IV @Jag'a/x'c/b 0 .gm ?Ff/rmfc- Installation of an ARTEX 406 Emergency Locator Transmitter in accordance with Aerospace Corporation Master Drawing List 8, Rev. E, dated June 16, 2000, or later FAA Approved revision. ,(thHZ/z/(b/o} Iz/zz/ alirllZ'I-C'Il-J I. Compatibility of this design change with previously approved modi?cations must be determined by the installer. 2. FAA Approved Airplane Flight Manual Supplement, Report No. GAC-AFMS-99020, Rev. dated September 3, I999, FAA approved December 9, 1999 or later FAA Approved revision is required for the ARTEX ELT System. . 3. FAA Approved Maintenance Manual Supplement, Report No. GAC-MMS-99021, Rev. A, dated December 17, 1999, FAA approved December 28, 1999 or later FAA Approved revision is required for the ARTEX ELT System. 4. If the holder agrees to permit another person to use this certi?cate to alter the product, the holder shall give the other person written evidence of that permission. (1111/ JI/?/I?r/fry (?z/rz (1.7.621 (I) 55:11:} or swag/ae/zr/?l reac/rt/cr (z [cranking/(Ev; (3 c/[ErzcziJc e/yie .J?gt?n (rug/ra/(ba. Ezra/e August 16, I999 E?Zk/e ?at/e December 9, 1999 gel, (mire/u?r? July ll, 2000 $7 (/?rcfr?w? ef?/fe ?6 (Signature) Emery P. iltse DAS Coordinator, FAA DASZCH Aerospace Corporation Appleton, Wisconsin Title) Any alteration of this certificate is punishable by a tine of not exceeding $1,000. or imprisonment: not exceeding 3 years. or both. FAA Pom ano-zuo-ss: PAGE 1 of 2 PAGES This certificate may be crans?erred in accordance with FAR 21.47. my. 4.2881 5:319:11 Gnu?smear: on: 9227357139 Hose: 0 1/1 AEROSPACE CORPORATION May 4, 2001 Mr. David Neese Aerospace . 7 440 Aviation Place Dallas, TX 75235 Dear David: . Aerospace, Appleton, Wisconsin (the STC Certi?cate Holder) authorizes AerosPaee Dallas, Texas use of Supplemental Type Certi?cates for'the following Gulfsneam AeIOSpace aircraft model and serial numbers: G-IV serial number 1422 l. STC No. Aircraft Tow Bar and Ladder Installation 2. STC No. Compartment Storage Box Installation 3. STC N0. ARTEX 406 MHZ ELT Installation G-IV serial number 1425 1. ST No. 077CH-D, Aircraft Tow Bar and Ladder Installation 2. STC No. Aft Compartment Storage Box Installation 3. ST No. ARTBX 406 MHZ BLT Installation This authorization is effective for the model and serial number aircraft listed. Additional authorizations may be obtained by submitting a request to the undersigned, Specifying the applicable serial number(s) intended for the installatiOn. If you have any questions regarding this authorization, I can be reached at 920-735-7114. Sincerely, . rat?It? brand fax transmittal memo 7671 irolpwus I DAN IDLUL- CH PS mm If; {i L731: Ca. apt. Phunl if 202?- 71323- Fax?! Discovery Drive. Appleton. Wisconsin 54915. telephon01920-735-7000, tum-Lguliatreamalrcraheom File: us. DEPARTMENT or TRANSPORTATION Dale FEDERAL AVIATION AIRCETFT on AIRCRAFT COMPONENT IDENTIFICATION nwos MODEL NO. TYPE (Airplane, Radio, Helicopter, APPLICANT Gum . Gulfetream Aerospace Corp- Airplane Dallng OF DATA DENTIFICATDN mu?: GC414236044 DEVIATION INDEX LIST ARTEX 406 MHZ BLT Rev STC -- end -- NOTE: .1. The above data details the deviations to an existing installation as incorporated in SIN 1425. 2. Thedevia?ons do not impact the structural integrity of the previously approved installation. 3. This 8110?3 approves the Design and Structural aspects of the above data only. Systems Equipment [Electrical] evaluation is required for this installation. The aircraft must be returned to service in accordance with all applicable FARS. PURPOSE OF DATA To show compliance with PARS for modi?cations to G-IV Serial Number 1425 only. WE REWNTS (Us! speci?c sections) FAR 25 .301, .303, .305, .307 per note 2 above. FAR 25.601, .603, .605(a), . 609, .611 .l301(a) by data review. CERTIFICATION - Under authority vested by direction ofthc Adminislmtor and in accordance with conditions and limitations of appoinmnt under Part 183 of the Federal Aviation Regulations. date listed above and an attached sheets numbered have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. I ?mentors Recommend approval of these data Approve these data or oe'smre? oesremnou MMBERQL BERT-71 0242-SW Structures, Systems Equipment, #4 George B. Sparling PB - Management FAA Form 8110-3 (AEC Computer Generated 12192} 92 .LNB . 2001?42 U.s. DEPARTMENT OF TRANSPORTATION . DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS 29 May, 2001 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE I MODEL NO. TYPE (Airplane, Radio, Helicopter, NAME OF APPLICANT . Aerospace AemSpace G-IV Alrplane Love Field, Dallas, TX LIST OF DATA IDENTIFICATION TITLE GAC DOCUMENT AEROSPACE DATA LIST GC414236044 406 MHZ BLT Rev. B, Dated 5/26/01 END OF DATA NOTE 1. This approval covers electrical systems and equipment design aspects only. 2. Approval of this data does not constitute installation approval. 3. This approval valid for SIN 1425 only. PURPOSE OF DATA Support of installation of ARTEX 406 MHZ ELT using ST STOIOSOCH-D with deviations. APPLICABLE REQUIREM ENTS (Us: speci?c sections) FAR 25.1301 FAR 25.1353(a) FAR 25.1307(c) FAR FAR 25.1309(a) FAR 25.1 359((1) FAR 25.1322 FAR CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered None have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. I Recommend approval of these data I (We Therefore Approve these data SIGNATIQRELS) OF DESIGNATED ENGINJERING REPREENTATIVEIS) DESIGNATION NUMBERIS) CLASSIFICATIONS) Systems Equipment CHARLES E. ETHERIDGE PAR 25 FAA Form 81 10-3 (11?70) supeaseos PREVIOUS some? (COMPUTER CENERATED) Emit-2b c- ?5 (9f ramrricn