UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE NAUONAUTYAND 2 MA UFACT NRCRAFTSERML 4 CATEGORY REGISTRATION MARKS BEE EORP. NSOSJ 13?200 333935 NORMAL 5 AUTHORITYAND BASIS FOR ISSUANCE v? I 7 I. A This airworthiness certi?cate is Issued pursuant to 49 U.S.C. 44704 and certi?es that. as oithe date 9! issuance; the aircraft to which issued has been inspected and louno to conform to the type certi?cate thereIOr, to be in condition iorsate OperatiOn; and has been shown to meet the requirements of the applicable comprehensive and detailed ainvorthiness?codeas provided by Annex 8 to the Convention on International Civil Aviatitin, eircept as noted herein. Exceptions: r. None 6 TERMSANDCONDITIONS '7 \e 3 i :7 . Unless sooner surrendered, suspended, revoked/or, a termination date is otherwise the airworthiness certi?cate is effective as long as the mainlenance?preventative maintenance, and alterations are performed in'aocordance with Parts 21. 43. and 91 ot the Federal Aviation Regu_lations.las appropriatefand the aircraft is registered in the United States. DATE OF ISSUANCE FAA REPRESENTATIVE I DESIGNATION NUMBER Jeffrey W?Sx?tl'rns I 'x r? Any alterationl reproduction, or misuse of this certi?cate may be punishable by a ?gnot exceedind $10110 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 8100-2 (04-11) Supersedes Previous EditioReiSSued 01/28/2016 . DEPARTMENT OF AVIATION ADMINISTRATION "3431-11: 1 STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND 2 MANUFACTURER AND MODEL 3 AIRCRAFT SEFIT 4 REGISTRATION MARKS NUMBER Aw Beech Aircraft Cor N6 50 (R P- . I AUTHORITY AND BASIS FOR ISSUANCE prowded by Annex 810 the Convenhon on Imem NONE 6 TERMS AND CONDITIONS Unless sooner surr airworthiness cemflc pended. revoked or a leri?mnatlon ?date I5 otherwlse by Ihe e?echve as Iong as The maInIenance, prevemalwe maInIenance. and a IeratIons are accordance wuh Pa I43.nn0910itheFeder on Regulations. as approprtaleand The reglstered IntheU SIaIes A DATE OF IW DESIGNATION NUMBE 1 (V 5.1 A. WARD . Any alteranon. reproduction. CT rmsuse of this ceruhcate may be punrshabffy a ?ne not exceeding $1.000. or imprisonment no: years. on both THIS CERTIFICATE MUST BE DISPLAYED IN THE RCRAFT IN ACCORDANCE WITH APPLICABLE AVIATION REGULATIONS. FAA Form (3.52) U3. GOVERNMENT PRINTING OFFICE: 1991 - - Federal Aviation Administration Albuquerque Flight Standards District Of?ce 1601 Randolph Rd. SE Albuquerque, NM 87106 Subject: Replacement Airworthiness Certi?cate I am requesting a replacement airworthiness certi?cate for the following aircraft: Make: @756; tic, u?L?lc?T Model: ZOO Number: 3?3 ?a A Serial Number: - Reason for replacement: laer A) 0 AJQ (Leif/Ago Name: Dr $u+t?i12j?ut+drf Title: Ad t/xr?olk) C) (Zr-1:49 (Q Signature: @Vb Phone Number: 5734? @b 1&5 8 Address: 2-1 01 \C?tolts. fix??2'0 DVIL Ath b3 1'10 Fm? Electronic Tracking Number (d MAJOR REPAIR AND ALTERATION 0MB 21200020 2i28l2011 (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 Serial No. USA N6507B 88-498 1. Aircraft . Make Mode! Series Beechcraft King Air 200 Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) . . Add 5020 Meridian Ave 2' United States Customs Sewice fess . City Oklahoma City State Oklahoma Of?ce of Patrol Zip 73119 Country USA 3. For FAA Use Only 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model Serial Number (As described in item 1 above) El POWERPLANT PROPELLER Type El APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Name Sierra Nevada Corporation IMS us. Certi?cated Mechanic [Manufacturer Address 18635 Jarkey Drive [3 Foreign Certi?cated Mechanic 0- Certi?cate City Hagerstown State Maryland Certi?cated Re - . . pair Station J8UR891 Zip 21742 Country USA Certi?cated Maintenance Organization D. 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. Extended range fuel Signature/Date of Authoriz ed lndivid gigigcra Part 43 Michael powers 21 March 2013 7. Approval tghetu'r?n 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 IE APPROVED El REJECTED FAA Standards . . . Person Approved by Canadian Inspector Manufacturer Maintenance Organization Department of Transport BY OtheriSpecify) FAA Designee Repair Station inspection Authorization 2. Certi?cate or SignatureIDate of Authorized Individual 6 Designation No. J8UR891Y Robert W. Strong a v. 21 March 2013 FAA Form 337 (IO-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. ldentify with aircraft nationality and registration mark and date work completed.) USA N6507I3 21 March 2013 Nationality and Registration Mark Date Acft BB-498 12609.9 TC: 9394 HOBBS: 2604.8 COMPLETED THE FOLLOWING REMOVALS: 1. Removed ?ve mission antennas on the lower fuselage, One FS 120.00, Two each FS 212.00 and FS 222.00. A closeout plate was installed FS 120.00 location IAW SNC Drawing 01895304, Revision A. The remaining locations were modi?ed by Item 3 LETC VHF Array noted below. COMPLETED THE FOLLOWING MODIFICATIONS: 1. Installed 01891304-1 Adapter Plate and MX-15HDI Sensor FS 266.00 IAW SNC Drawing 01891303, Revision 8, Feed-thru Installation IAW SNC Drawing 01891301, Revision B. Reference FAA Form 8110-3, dated 20 March 2013, signed by Abbie Wathen The Adapter Plate is mounted to the three existing ANIAAS-36 ?ttings previously installed per STC SA1811CE. 2. Installed LETC UHF Antenna Array (Eight Antennas) on lower fuselage at the following locations: FS 130.37- L, FS 144.37- L, FS 148.50 R, FS 153.50 R, FS 419.35 and FS 471.35 IAW SNC Drawing 01895301, Revision C, Deviation 2. 3. Installed LETC VHF Antenna Array (Five Antennas) on lower fuselage at the following locations: FS 175.87- R, FS 205.87 8 R, FS 216.00 8 IAW SNC Drawing 01895302, Revision C. 4. Installed LETC Pressure Bulkhead Pass-Thru FS 347.57, approx 3.50 above the ?oor IAW SNC Drawing 01895306, Revision B, Deviation 1. 5. Re-Iocated both Transponder Antennas on lower fuselage from F8 222.00 FS 310.00 to F8 323.00 FS 295.5 respectively IAW SNC Drawing 01892301, Revision A. 6. Relocated the lower VHF COMM Antenna from F8 149.00 to FS 89.5 IAW SNC Drawing 01892302, Revision B. Installed Cockpit Monitor Provisions on Co?pilots Side Glare Shield and Lower Instrument Panel IAW SNC Drawing 01891601, Revision A. 8. Modified the Center Console IAW SNC Drawing 01891602, Revision B. 9. Installed LH and RH Cabin Swing-Out Monitors FS 196.00 IAW SNC Drawing 01892001, Revision A, Deviation 3. 10. Installed an 8-Way GPS Splitter in RH Cabin FS 291.00 IAW SNC Drawing 01892023, Revision C. 11. Installed LETC Rack LH Cabin FS 165.60 IAW SNC Drawing 01892029, Revision B, LETC Rack Components IAW SNC Drawing 01892028, Revision F. 12. Installed Special Mission Equipment, Aft Cargo Area FS 326.75 IAW SNC Drawing 01892030, Revision C. 13. Installed Audio Control Panel and Video Recorder LH Cabin Sidewall between FS 217.00 and 241.00 IAW SNC Drawing 01892101, Revision E, Deviation 2. The Audio Control Panel was an existing unit relocated from RH sidewall FS 193.00. 14. Installed Cabin lWorkstation Interface Panels on LH RH cabin sidewalls between FS 190.00 and 215.00 IAW SNC Drawing 01892701 Revision E, Deviation 3. 15. Installed LETC Beamformer Unit under the ?oor FS 201.00 IAW SNC Drawing 01895303, Revision C. 16. Installed LETC Interface Panel Assembly LH cabin FS 182.75 IAW SNC Drawing 01895305, Revision A. 17. Installed GPS Antenna, 867-1575-39 on an existing external doubler at FS 288.00 IAW SNC Drawing 01892601 Revision A, Deviation 1. 18. Installed Mission Power Provisions IAW SNC Drawing #5 01891502, Revision B, 01891503, Revision B1. Wiring Provisions IAW SNC Drawing 01891302, Revision A. and Special Mission Equipment Wiring Provisions IAW WGS Systems Drawing #5 800-0022- 0000, Revision F1, 800-0023-0000,Revision D, 800-0024-0000 Revision B, 800-0025-0000, Revision F1, and 800-0026-0000, Rev. C. For additional data concerning the above Installations, Reference the following Documentation; FAA Form 8110-3, dated 20 March 2013, signed by.Abbie Wathen, DERT-830893-NM. FAA Form 8110-3, dated 12 March 2013, signed by Nelson White, DERT-750279-SW. Additional Sheets Are Attached FAA Form 337 (IO-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.) USA 21 March 2013 Nationality and Registration Mark Date Instructions for Continued Airworthiness (ICA) to be completed as follows: Items 1 thru 6 and 17 listed above are contained in SNC Document 01890005. Revision B. Items 7 thru 16 and 18 to be completed as follows; For all Structural- A Visual (10X magnification as required) Inspection should be completed of all locations to include; condition of fasteners. loose and missing fasteners. signs of corrosion. cracks. distorting or buckling. and any other damage or anomalies. For all Special Mission Wiring- Inspect condition of canon plugs for security. and missing hardware. check condition of wiring for security. signs of chaf?ng. cracking. or broken wires and any other damage or anomalies. These Inspections to be completed initially at 200 hours and then every 400 hours thereafter. they will also be aligned with the existing Aircraft Maintenance Inspection Program as outlined in the Hawker Beechcraft Maintenance Manual 101-590010-19. Chapter 5. Removal I Installation Instruction for FLIR Remove the external Fairing, disconnect the harnesses to the sensor. Support the sensor to prevent damage. remove the cotter pins and 5l16-24 fasteners (5 places), tower and remove the sensor. Cap and stow the harnesses and install the original Aircraft closeout panel. Complete an airframe log book entry and revise aircraft weight and balance records. Installation of the can be accomplished by reversing the above procedures. Torque 5l16-24 fasteners (5 Places) to 100-140 in. and install cotter keys. Reference FAA Form 337. dated 21 March 2013. Removal Installation Instruction for LETC Mission Rack Disconnect harnesses to the Rack components at the IFP Panel aft of the Rack. remove the four 5/16-24 seat track fitting fasteners and remove the rack. Install the IFP cover. Complete an airframe log book entry and revise aircraft weight and balance records. Installation of the Rack can be accomplished by reversing the above procedures, Torque the four seat track ?tting 5i16-24 fasteners to 100 in lbs. Reference FAA Form 337. dated 21 March 2013. Airplane Flight Manual Supplement (AFMS), SNC Document 01890010. Revision A. dated 21 March 2013. was inserted into Pilot's Operating Handbook. Reference FAA Form 8110-3. dated, 21 March 2013. signed by Dave Roland. DERT-955096-NE. An Aircraft Weight and Balance was performed subsequent to these Modifications and the Aircraft Records revised to re?ect these Changes. An Electrical Load check was performed with all Mission Equipment on. Electrical load did not exceed the 90% limit. checks were performed and new equipment did not affect existing systems. Pertinent details are on ?le CRS J8UR891Y under SNC Work Order 5178. END Additional Sheets Are Attached FAA Form 337 (10-06) DEPARTMENT or TRANSPORTATION Date FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS 03/12/13 AIRCRAFT 0R AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL NO. TYPE (Airplane, Radio, Helicopter, etc.) NAME OF APPLICANT Hawker Beechcraft Corp 200 Airplane Sierra Nevada Corporation Hagerstown, Maryland LIST OF DATA IDENTIFICATION TITLE Drawings: 01890000-BB498 Master Drawing List for the Mongoose King Air 200 BB498 Rev. A, Date: 03/12/13 -- End This approval is for the electrical drawings and electrical reports contained in the above mentioned MDL TCDS: A24CE NOTE: 0 This approval is for enginerring design data only and is not an installation approval. It indicates the data listed above demonstrates compliance only with the regulations speci?ed by paragraph and subparagraph listed below as ?Applicable Requirements?. This form does not constitute FAA approval of all the engineering design data necessary for substantiation of compliance to necessary requirements for the entire alteration/repair. The above data is approved for the electrical/ electronic and avionics design aspects only. System should be veri?ed to Operate properly and not adversely affect other aircraft systems. This approval does not address the structural aspects of installation, nor does it address continued airworthiness or operation instuctions. This approval is not for major power distribution. PURPOSE OF DATA To support the Electrical Engineering Design Modi?cations for aircraft SN BB-498 only. This 8 10-3 is in support of FAA Form 337. APPLICABLE REQUIREMENTS (List speci?c sections) 14 CFR 23.1301, 23.1309 14 CFR 23.1357 14 CFR 23.1351 14 CFR 23.1365,14 CPR 23.1431 Per the original certi?cation basis of the model Beechcraft 200 per TCDS A24CE, the above regulations include all amendments 23-] through 23-] l. 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 0 have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. I (I) Therefore I Recommend approval ofthese data, (x I Approve these data OF DESIGNATED ENGINEERING DESIGNATION NUMBERIS) Nelson White BERT-750279-SW Systems and Equipment ?z/Z (Avionics Electrical) FAA Form 8110-3 (11-70) SUPERSEDES PREVIOUS EDITION (COMPUTER GENERATE D) NPW13016 GPO 901-613 DEPARTMENT OF TRANSPORTATION DATE FEDERAL AVIATION ADMINISTRATION March 20' 2013 STATEMENT OF COMPLIANCE WITH FEDERAL AVIATION REGULATIONS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL NO. TYPE (Airplane, radio NAME OF APPLICANT Hawker Beechcraft 200 Helicopter. etc.) AirPlane Sierra Nevada Corporation LIST OF DATA IDENTIFICATION TITLE Drawing 01890000-38498A Rev. A 03/12/13 Master Drawing List for the Mongoose King Air 200 SIN 88498 End of Date Notes: - 1. This approval is for engineering design data only and is not an installation approval. It indicates the data listed above demonstrates compliance only with the regulations speci?ed by paragraph and subparagraph listed below as uApplicable Requirements". (Compliance with additional regulations not listed here may be required.) This form does constitute FAA Approval of the engineering design data necessary for substantiation of compliance to necessary structural requirements for this alteration. 2. The agency approving the modi?ed aircraft to service is responsible to insure that the installation conforms to the data listed. 3. This approval is for static strength only. This does not include approval for 23.571. 4. This approval is for structural aspects only. PURPOSE OF DATE In support of a major alteration for Hawker Beechcraft model 200 serial number 88498 only. APPLICABLE REQUIREMENTS (LIST OF SPECIFIC SECTIONS) 14 CFR Part 23.301 23.303; 23.561 23.601; 23.609 23.611 23.623 Certi?cation Basis at amendment 23?11 per Type Certi?cate Data Sheet A24CE. CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointments der Part 183 of the Federal Aviation Regulations, data listed above and on Attached sheets numbered IA: have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. Recommended approval of these data I (we) Therefore {2 Approve these data SIGNATUREIS) OF DESIGNATED ENGINEER DESIGNATION CLASSIFICATIONS) REPRESENTATIVE Abbie Wathen DERT-B30893-NM Structures FAA Form 8110-3 (11-70 SUPERSEDES PREVIOUS EDITION) Macintosh mongoose 3 20 13.doc AIRPLANE FLIGHT MANUAL SUPPLEMENT for HAWKER BEECHCRAFT MODEL 200 AIRPLANE when modi?ed to incorporate the WESCAM FORWARD LOOKING INFRARED (FLIR) am. Document Number 01890010 Rev A This supplement must be attached to the Pilots Operating Handbook and FAA . Approved Airplane Flight Manual when the airplane is modi?ed in accordance with FAA Form 337 dated 2] March 2013 for the installation of the Wescam Forward Looking Infrared The information in this document supplements or supersedes the basic Pilots Operating Handbook and FAA Approved Airplane Flight Manual only where covered in the items contained herein. For limitations, procedures and performance not contained in this supplement, consult the basic Pilots Operating Handbook and Airplane Flight Manual. This Aircraft Flight Manual Supplement is FAA Approved by appropriately authorized Designated Engineering Representative, David Roland, as authorized by the New York Aircra? Certi?cation Office. FAA Form 8] 10-3 is attached directly behind this cover page. WARNING: This document contains technical data that is subject to the lntemational Traf?c in Arms Regulations or the Export Administration Regulations (EAR). Expon ofthis technical data to foreign persons or foreign entities inside or outside of the United States requires prior written authorization by the U. S. Department of State or the US. Depanment of Commerce. Violations of these expon regulations are subject to severe criminal penalties. FAA Approved Date: March 21, 20l3 MFG IDENT CODE 4HVG5 SIERRA snow CORPORATION IN TEG RATED ?55113 18635 Jarkey Drive Hagerstown', MD 21742 Airplane Flight Manual Supplement for King Air 200 Doc No: 01890010 Rev A U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION I. DATE March 21. 2013 STATEMENT Of COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT IDENTIFICATION 2. MAKE i Sr MODEL NO. 4. TYPE (Alrcre?. Engine, Propeller. etc.) 5. NAME OF APPLICANT Hawker Beechcraft 200 Aircraft Sierra Nevada Corporation Hagerstown, MD 21743 LIST OF DATA ts 7 TITLE SNC Doc No: 01890010 Rev A. Of Data Airplane Flight Manual Supplement for Hawker Beechcrafl Model 200 Airplane when modi?ed to incoporate the Wescarn Forward Looking Infrared (FLIR). End Of Data The approval of this Airplane Flight Manual Supplement is valid ior Hawker Beechcraft Model 200. SIN 38-498 only. 8. PURPOSE OF DATA Supper! at a Major Alteration 9 APPLICABLE 175 (List specific sections) 14 CFR Part 23: 23.1581 (6) IOriginaI], 23.1535 (3) [Amdt 23-71. 9an I83. time Hated above under! attached sheets numbered with applicable requirement: of the Aimerthiness Standards listed. Recommend approval of these data I (We) Thereiore Approve those data 10. CERTIFICATION - Under authority vealed by direction ot the Adminlauetm end In accordance with conditions and limitations 01 appointment under l4 CFR have been examined In accordance with umbiiahed procedure: and room Io comply 11. OF DESIC NAIED ENGINEERING 12. DESIGNATION mussels; 13. CLASSIFICATIONS) WM Flight Test Pilot Part 23125 \?Jr FAA Form 8110-3 tonne) SUPERSEDES PREVIOUS EDITION FAA Approved: March 2013 ELECTRONIC FORMAT I) . . . . Doc No: 01890010 Airplane Flight Manual Supplement for ng Alr 200 Rev A REVISIONS Issue Pages Description Approved By Date A 1-7 Initial Release See Page 2 March 2013 FAA Approved: March 21, 2013 Doc No: 0l890010 Airplane Flight Manual Supplement for King Air 200 Rev A LIST OF EFFECTIVE PAGES PAGES ISSUE DATE Title A 3/2 I /2013 2-7 A 3/21/2013 gm?- I. FAA Approv?d-z. march 1, 2013 . . . Doc NO: 01890010 5 Airplane Flight Manual Supplement for ng 200 Rev A TABLE OF CONTENTS Section/Title 1.0 GENERAL .. 6 2.0 .. 6 2.1 OPERATIONAL LIMITATIONS .. 6 2.2 SYSTEM LIMITATIONS .. .. 6 3.0 EMERGENCY PROCEDURES .. 7 3.1 LOSS OF GENERATOR .. 7 4.0 NORMAL PROCEDURES .. 7 5.0 PERFORMANCE .. 7 6.0 WEIGHT BALANCE .. 7 7.0 SYSTEM DESCRIPTION .. 7 8.0 HANDLING, SERVICE MAINTENANCE .. 7 9.0 SUPPLEMENTAL PACK .. 7 10.0 SAFETY INFORMATION .. 7 5. FAA Approved: March 21, 2013 . . Doc No: 01890010 Airplane light Manual Supplement for King Air 200 Rev A 1.0 GENERAL This Supplement contains information needed to operate Hawker Beechcraft B200 Model airplanes when equipped with the Installation of the Wescam MX?lSl?lDi Forward Looking Infrared (FLIR) to the lower aft fuselage. 2.0 LIMITATIONS 2.1 OPERATIONAL LIMITATIONS l. The Wescam FLIR must be stowed during Take-off and Landing. 2. SNC Document 01890007, Rev A, or later appropriate revision, Cockpit Operating Instructions must be available to the ?ight crew when operating this system. Flight into known icing conditions prohibited. 4. Minimum Crew Requirement: ln-flight use of the Wescam FLIR System during operational missions requires a quali?ed (systems operator) crewmember in addition to the pilot. 2.2 SYSTEM LIMITATIONS 1. The Laser is approved as a Class IV laser product as defined by the US Code of Federal Regulations 1040.10 and 1040.1 1 of Title 21. 2. Laser operation is not FAA approved for civil operations. The laser feature is electrically disabled. 3. Laser feature is not FAA approved for civil operations. The laser is electrically disabled. 4. The FAA has not assessed the hazards associated with the laser feature. The laser manufacturer has stated that the laser feature can cause damage at distances of less than 1,214 feet. The FAA has not validated the manufacturer?s statement. 5. A placard must be installed near the laser control that states: Laser Operation is not FAA Approved. 6. FAA Type certification of laser system equipped aircraft, including the speci?cation of limitations, does not constitute Operational approval. Operation approval must be coordinated with the FAA in accordance with Advisory Circular 701, Outdoor Laser Operations, or other means of approval as speci?ed by the FAA, by a foreign civil airworthiness authority, or other organization that has the authority to assume operational responsibility of the use of the laser system. FAA Approved: March 21,2013 . . . Doc No: 01890010 Airplane Flight Manual Supplement for ng Air 200 Rev A 3.0 EMERGENCY PROCEDURES 3.1 LOSS OF GENERATOR I. In the event of a loss of an engine driven generator, mission power will be removed automatically as indicated by the MISSION POWER annunciator located in the center pedestal no longer being illuminated. Manually turn off the MISSION POWER annunciator to prevent mission equipment from coming back on until normal engine generator operation is re-established. 2. The Wescam FLIR system may be disconnected by the following; a. Depress the MISSION POWER Annunciator Switch. 4.0 NORMAL PROCEDURES . Both generators must be online and the GEN. GEN 2 (LEFT RIGHT) BUS AVAIL indicators must be illuminated. The MISSION POWER annunciator switch, located in the center cockpit pedestal, must be depressed with lit in green for power to be available to all mission equipment (except Mission Cockpit Monitor). 5.0 PERFORMANCE Climb Performance is decreased 50 feet/minute relative to the basic airplane. All other performance remains unchanged. 6.0 WEIGHT BALANCE No change to basic Pilots Operating Guide or basic Airplane Flight Manual. 7.0 SYSTEM DESCRIPTION The Wescam FLIR System modi?cation consists of the installation ofa FLIR Turret onto the lower aft fuselage, the installation of the receiving and processing equipment into the rear fuselage, and cables to connect and provide power to the system and system video cables. This installations is protected by (2) Circuit Breakers POWER and located on the Co-pilots RH sidewall circuit breaker panel. 8.0 HANDLING, SERVICE MAINTENANCE No change to Pilots Operating Handbook or basic Airplane Flight Manual. 9.0 SUPPLEMENTAL PACK No change to Pilots Operating Handbook or basic Airplane Flight Manual. 10.0 SAFETY INFORMATION No change to Pilots Operating Handbook or basic Airplane Flight Manual. 7 FAA Approved: March 2] 2013 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (ICA) for the MONGOOSE KING AIR 200 for EXTERNAL INSTALLATIONS AND USELAGE PENETRATIONS Document Number Rev PROPRIETARY STATEMENT: lnl?onnation contained herein represents Proprietary Intellectual Property of Sierra Nevada Corporation and shall not be duplicated, used, or disclosed in whole or in part by arty means. person. or organization for any purpOSes without express written permission. Neither receipt nor possession ofthis data, from any source, constitutes such permission Infringement data rights may result in criminal and/or civil liability. WARNING: This document contains technical data that is subject to the International Traf?c in Anus Regulations (ITAR) or the Export Administration Regulations (EAR). Export of this technical data to foreign persons or foreign entities inside or outside of the United States requires prior written authorization by the U. S. Department oI?Stnte or the US. Department OI'Commerce. Violations ol?these export regulations are subject to severe criminal penalties. DESTRUCTION NOTICE: Destroy by any method that will prevent disclosure of contents or reconstruction of this decument in accordance with the National Industrial Security Operating Manual August 14, 2012 SII NEVADA MFG IDENT CODE CORPORATION INTEGRATED MISSION SYSTEMS 18635 Jarkcy Drive Hagerstown, MD 21742 Instructions for Continued Airworthiness 01890005 Rev REVISIONS Issues Descriptions Date Author Engineering Con?guration 'Jason Mertz Abbie Wathen Brenda Barkdoll A Initial Release 12/2/201 jaw? AW Jim [a Emma [a Corrected page numbers Jason Mertz Abbie Wathen ?or Brenda Barkdoll in Effective Pages; Add inspection intervals for 8/14/2012 01892601 GPS Antenna; add s/n speci?c inspection intervals MM ii Use or disclosure of data contained on this sheet is subject to the restrictions on the title page. . . . . 1 005 ContmuedAlrworthmess 0 890 Rev LIST OF EFFECTIVE PAGES PAGES ISSUE DATE Title A 12/2/20] 1 1? A 12/2/2011 1 8 A 12/2/20] 1 Title 8/14/2012 ii?v 8/14/2012 1 9 8/14/2012 i-ii Use or disclosure ofdata contained on this sheet is subject to the restrictions on the title page. Instructions for ContinuedAirworthiness 01890005 Rev TABLE OF CONTENTS Section/Title - Page 1.0 INTRODUCTION ..1 1.1 SCOPE .. 1 1.2 PURPOSE ..1 1.3 APPLICABILITY ..1 1.4 DISTRIBUTION ..1 1.5 REVISIONS ..1 1.6 REFERENCES AND APPLICABLE DOCUMENTS ..2 1.7 EFFECTIVITY ..2 1.7.1 200 Aircraft ..2 2.0 GENERAL INFORMATION ..3 2.1 DESCRIPTION ..3 2.2 LOCATION OF ACCESS PANELS ..3 2.3 PLACARDS AND MARKINGS ..3 2.4 SERVICING EQUIPMENT ..4 2.5 SPECIAL TOOLS ..4 2.6 SERVICING INFORMATION ..4 2.7 FASTENER INFORMATION ..4 3.0 MAINTENANCE PROGRAM ..5 3.1 MAINTENANCE MANUAL ..5 3.2 INSPECTION DEFINITIONS ..5 3 .2.1 General Visual Inspection (G VI) .. 5 3.2.2 Detailed Visual Inspection (D VI) ..5 3.2.3 Wiring Inspection ..6 3.2.4 Intervals ..6 4.0 AIRWORTHINESS LIMITATIONS ..7 4.1 MANDATORY REPLACEMENT TIMES ..7 4.2 AIRWORTHINESS LIMITATION ITEMS ..7 4.3 INSPECTION PROCESS ..8 4.4 APPROVAL ..9 iV Use or disclosure of data contained on this sheet is subject to the restrictions on the title page. Instructions for Continued Airworthiness 01813330; LIST OF FIGURES Figu re/Title Page FIGURE 1: LOWER FUSELAGE ..3 LIST OF TABLES - Table/Title Page TABLE 1: REPORT ACRONYMS ..2 TABLE 2: TORQUE VALUES ..5 TABLE 3: STRUCTURE AND FASTENERS FOCUS AREAS ..6 TABLE 4: WIRING INSPECTION FOCUS AREAS. ..7 TABLE 5: MAINTENANCE ACTIONS ..8 TABLE 6: AIRWORTHINESS LIMITATION ITEMS ..8 I Use or disclosure of data contained on this Sheet is subject to the restrictions on the title page. 01890005 I Instructions for Continued Airworthiness Rev 1.0 INTRODUCTION These of Continued-Airworthiness (ICA) are for the Hawker Beechcraft King Air 200 Model aircraft with installation of and LETC antenna arrays. 1.1 SCOPE This document contains the Instructions for Continued Airworthiness in accordance with 14 CFR 23.1529 and 14 CFR 23 Appendix for the LETC UHF Array, LETC VHF Array, VHF Comm and TransponderAntenna Relocations, and the Pressure Bulkhead Disconnects for the MX- The instructions for Continued Airworthiness described in this document are to be incorporated by the operator into the aircraft?s scheduled maintenance program. 1.2 PURPOSE These instructions supplement the Instructions for Continued Airworthiness as provided by the Hawker Beechcraft?Company for the aircraft. These instructions must be included in the aircraft Operator?s approved maintenance program. 1.3 APPLICABILITY These instructions for Continued Airworthiness are applicable to Beechcraft King Air 200 model aircraft, 88482, 88493, BB498. 1.4 DISTRIBUTION An electronic copy of this document in format and all revisions are provided to the owner/operator of the aircraft, to the FAA as an attachment to Form 337, and the original is maintained by Sierra Nevada Corporation. 1.5 REVISIONS Revisions to this report will be issued as complete documents. All pages will re?ect the latest revision level. Changed material will be indicated by change bars in the left margin. Deleted material will be indicated by a change bar adjacent to a blank space. Revisions will be distributed to the owner/operator of the aircraft as described above. Revisions to referenced vendor documents which affect airworthiness instructions will be forwarded to the Operator along with a revision to this document that updates the reference information in accordance with the Distribution statement above. 1 Use or disclosure ofdata contained on this sheet is subject to the restrictions on the title page. Instructions for Continued Airworthiness 1.6 REFERENCES AND APPLICABLE DOCUMENTS A. B. C. P7 .2971 ZEFFH 1.7 EFFECTIVITY 1.7.1 200 Aircraft King Air 200 Series Maintenance Manual, latest revision, 101-590010-19 01890005 Rev King Air Series Structural Inspection and Repair Manual, latest revision, 101-590097-13 FAA AC 4313-] B: Acceptable Methods, Techniques and Practices Aircraft Inspection and Repair FAA AC 43.13-lB: Acceptable Methods, Techniques and Practices Aircraft Alterations Title 14 CFR Part 23 Airworthiness Standards; Normal, Utility, Acrobatic, and Commuter Category Airplanes 01890002 Mongoose 200 Antenna Arrangement 01891301 Feedthru Installation DIN 01891303 Installation DIN 01892301 Transponder Antenna Relocations 01892302 VHF Comm Antenna Relocation 01895301 LETC UHF Array Installation 01895302 LETC VHF Array Installation . 01895306 LETC, Pressure Bulkhead Pass-through 01892601 GPS Antenna Installation 83-482, 88-493, 88498 Table 1: Report Acronyms Acronym Term CFR Code of Federal Regulations DVI Detailed Visual Inspection Electo-Optical Infra Red EWIS Electrical Wiring Interconnect Systems FAA Federal Aviation Administration GVI General Visual Inspection HFEC High Frequency Eddy Current ICA Instructions for Continued Airworthiness LETC Lavv Enforcement Technical Collection STC Supplemental Type Certificate UHF Ultra High Frequency VHF Very High Frequency Use or disclosure ofdata contained on this sheet is subject to the restrictions on the title page. 2 01890005 Instructions for Continued Airworthiness Rev 2.0 GENERAL INFORMATION 2.1 DESCRIPTION . This installation provides locates an Sensor in the lower fuselage pressure box previously installed by STC SAIBI ICE and installs two (2) LETC Antenna Arrays on the lower fuselage skin. Installation of the LETC Arrays required the relocation of several existing antennas, all current antenna locations are de?ned in 01890002 Antenna Arrangement. 6f: am: an: or- 2 me: wanna; 025953?; E?ru?iF?l-I? Kathi?: [(1?th Wil?ummn autumnal) atmwr I'm-Hm RAHEIALIMTIZRP- t?EFGwmali an; '35" com?mat-o sham: treatment IFEF meow" . 1. PM ?Emma? 01.9 ml Ins 0mm? iiuzl? Ml?" per ENSTIAGI Ef?. FIATTENNA ?lm-yuanth? Ell Ea 5 cm water-w 2.3V . "tr oummv [57; um: cmmow I 51:, a 01581111!) I. mur- cumin] ANTENNA um: mm at: I I 913mm: on our: ?Demo! 55; u: 513561011 c; mam-.1: nus-nu tn- 0mm? Ew' [Mr Fl? 5 INTIVAF I aerommn um (HEP-111) Figure 1: Lower Fuselage 2.2 LOCATION OF ACCESS PANELS The VHF Comm Antenna is installed on the forward lower access panel, which is utilized for access to pulleys and control cables under the pedestal. This antenna will need to be removed ?rst in order to remove this access panel. 2.3 PLACARDS AND MARKIN GS No new maintenance instructional placards have been added by this modi?cation. 3 Use or disclosure ot'data contained on this sheet is subject to the restrictions on the title page. 01890005 Instructions for Contmued Airworthiness Rev 2.4 SERVICING EQUIPMENT No special tools or equipment are required for the servicing procedures in this document. 2.5 SPECIAL TOOLS No special tools are needed. 2.6 SERVICING INFORMATION There is no special service information pertaining to this ICA. 2.7 FASTENER INFORMATION Fastener speci?cations and any allowable substitutions are indicated on the fabrication and installation drawings listed. The following torque values apply to all installations unless speci?cally noted in the installation instructions. Table 2: Torque Values Fastener Size Torque Value 10-32 30-35 inch pounds 1/4-28 65-l 00 inch pounds 5/ 16-24 130-200 inch pounds 4 Use or disclosure of?data contained on this sheet is subject to the restrictions on the title page. 01890005 Instructions for Continued Airworthiness Rev 3.0 MAINTENANCE PROGRAM 3.1 Maintenance Manual This modi?cation has been evaluated and determined not to require any additional supplements to the Maintenance Manual. Suf?cient inspection and maintenance instructions are contained herein and noted as required. 3.2 Inspection De?nitions 3.2.1 - General Visual Inspection (GVI) A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise speci?ed. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked. 3.2.2 Detailed Visual Inspection (DVI) An intensive examination ofa speci?c item, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required. Particular attention should be paid to the items listed in Table 3. Table 3: Structure and Fasteners Focus Areas Subject Criteria Fasteners Condition Loose or missing Holes Elongation Structure Evidence of corrosion Cracks, distortion or buckling 3.2.3 High Frequency Eddy Current (HFEC) Eddy current inspection to determine structural integrity of uncovered structure. Refer to SNC 01210124 for inspection procedures. I 5 Use or disclosure of data contained on this sheet is subject to the restrictions on the title page. 01890005 Instructions for Continued Airworthiness Rev 3.2.4 Wiring Inspection A GVI Inspection of the modi?cation wiring paying particular attention to the items listed in Table 5. Table 4: Wiring Inspection Focus Areas. Subject. Criteria Wire bundles evidence of cuts, abrasions, heat, ?uids or dirt and debris damage to conduit or sleeving Clamping proper installation damage to clamp or wire clamp cushion separation Connectors loose Back shells worn seals proper build-up proper strain relief drip loops where appropriate Terminations lugs tight and clean Grounds Splices secure evidence of corrosion Pigtail braid evidence of cuts, abrasion or pinching remove braid and inspect wire - if evidence is found 3.2.5 Intervals When intervals are provided in terms of ?ight hours, ?ight cycles and calendar months actions are due at whichever threshold is reached ?rst. intervals expressed in ?ight hours can be addressed within a window of $20 hours. Thus a 200 hour inspection may be performed between 180 and 220 hours. 6 Use or disclosure ofdata contained on this sheet is subject to the restrictions on the title page. 01890005 Instructions for Continued Airworthiness Rev 4.0 AIRWORTHINESS LIMITATIONS 4.1 MANDATORY REPLACEMENT TIMES The following table 5 presents a frequency summary and extent of the inspections necessary to provide for the continued airworthiness of the lnstallation on Beechcraft 200 Model Aircraft certi?ed to the requirements of 14 CFR 23.571 Amdt. 23-34. All installations listed herein require inspection cycle of 200 hours or 6 calendar months. These inspections can be performed at the time of scheduled regular inspection phases ofthe aircraft. Table 5: Maintenance Actions Description of Structure Action Interval FLIR Turret Installation 200 or 6 calendar mos. Adapter Plate GVI 200 or 6 calendar mos. 4.2 AIRWORTHINESS LIMITATION ITEMS The Airworthiness Limitations section is FAA approved and speci?es maintenance required under 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. Airworthiness Limitation Inspections per CFR 23 Appendix are listed below. inspection intervals for these items are provided in Table 6. Table 6: Airworthiness Limitation Items Intervals Item Action Threshold Repeat Feedthru (see note 2) HFEC 16,361 cycles 8,180 cycles Transponder Antenna Relocations I HFEC 1,101 cycles 550 cycles VHF Comm Antenna Relocation DVI Note 1 LETC, UHF Array Note 1 LETC, VHF Array Note 1 LETC, Aft Pressure Bulkhead, HFEC 12,483 cycles 12,483 cycles Pass-through GPS Antenna DVI Note 1 Note 1: No special limitation use maintenance manual inspection intervals. - Note 2: BB-482 should be inspected at 4,000 and 2,000 cycles respectively. 7 Use or disclosure of data contained on this sheet is subject to the restrictions on the title page. Instructions for Continued Airworthiness 4.3 INSPECTION PROCESS 01890005 Rev Task No Description Inspection interval 0189-001 01891301 feedthru Installation The connector holes and fastener holes to be inspected using eddy current inSpection techniques. The detectable crack length for eddy current inspection is 0.05?. The threshold crack length for each location indicates that a crack should be detectable at the threshold inspection. For the connector holes, the inSpector should look for cracks on the surfaces of the doubler and skin around the hole. For the fastener holes, the inspector should look for cracks on the surfaces of the doubler and skin around the fastener holes. Initial: 16,361 ?ights Repeat: 8,180 flights 0l 89-002 01892301 Transponder Antenna Relocations The connector holes and fastener holes to be inspected using eddy current inspection techniques. The detectable crack length for eddy current inspection is 0.05?. The threshold crack length for each location indicates that a crack should be detectable at the threshold inspection. For the connector holes, the inspector should look for cracks on the surfaces of the doublers and skin around the hole. For the fastener holes, the inspector should look for cracks on the surfaces of the doubler and skin around the fastener holes. Initial 1,101 flights Repeat 550 ?ights 0189-003 01892302 VHF Comm Antenna Relocation The connector hole and fastener holes to be inspected. For the connector hole, the inspector should look for cracks on the surfaces ofthe doubler and skin around the hole. For the fastener holes, the inSpector should look for cracks on the Surfaces of the doubler and skin around the fastener holes. For Access Panel fastener holes the inspector should look for cracks on the surface of the aircraft skin around the fastener holes. See Maintenance Manual chapter 05-00-00-001 01897004 01895301 LETC, UHF Array Installation The connector holes and fastener holes to be inspected. For the connector holes, the inspector should look for cracks on the surfaces of the doubler and skin around the hole. For the fastener holes, the inspector should look for cracks on the surfaces of the doubler and skin around the fastener holes. See Maintenance Manual chapter 05-00-00-001 0189-005 01895302 LETC, VHF Array Installation The connector holes and fastener holes to be inspected. For the connector holes, the inspector should look for cracks on the surfaces ofthe doubler and skin around the hole. For the fastener holes, the inspector should look for cracks on the surfaces of the doubler and skin around the fastener holes. See Maintenance Manual chapter 05-00-00-001 8 Use or disclosure ol?data contained on this sheet is subject to the restrictions on the title page. Instructions for Continued Airworthiness 01890005 Rev Task No Description Inspection Interval 0189-006 01895306 LETC, Pressure Bulkhead Pass-Through The connector holes and fastener holes to be inspected using eddy current inspection techniques. The detectable crack length for eddy current inspection is 0.05?. The threshold crack length for each location indicates that a crack should be detectable at the threshold inspection. For the connector holes, the inspector should look for cracks on the surfaces of the doubler and bulkhead around the hole. For the fastener holes, the inspector should look for cracks on the surfaces of the doubler and bulkhead around the fastener holes. Initial: 12,483 ?ights Repeat: 12,483 ?ights 0189-007 01892601 GPS Antenna Installation The connector holes and fastener holes to be inspected. For the connector holes, the inspector should look for cracks on the surfaces of the doubler and skin around the hole. For the fastener holes, the inspector should look for cracks on the surfaces of the doubler and skin around the fastener holes. See Maintenance Manual chapter 05-00-00-001 4.4 APPROVAL The inspection and airworthiness limitations specified in this section have been determined by FAA-Designee in accordance with 14 CFR 23.573 of the Federal Aviation Regulations and approved via Form 81 10-3. This section Specifies maintenance required under 14 CFR 43.16 and 91.403 ofthe Federal Aviation Regulations unless an alternate program has been FAA approved. 9 Use or disclosure ol'data contained on this sheet is subject to the restrictions on the title page. (2 US Department of Transponation Federal Aviation Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form Approved OMB No. 2120-0020 2/28/2011 Electronic Tracking Number For FAA Use Only 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 Serial No. USA N6507B 88-498 1' Aircraft Make Model Series BEECH 200 King Air Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) Address 8020 Meridian Ave 2' owner United States Customs Service Oklahoma CitV OK Zip 73119-5105 Country USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No: NRFRAME {As described in item 1 above) POWERPLANT Ci Ci PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Name 7 U. S. Certificated Mechanic Manufacturer Address 8092 Hangar Road Foreign Certi?cated Mechanic C. Certi?cate No. CW San Angelo State TX Certificated Repair Station Zip 76904 Country USA Certificated Maintenance Organization 4osRss7B D. certiiy 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. App. Extended range fuel per 14 CFR Part 43 Cl Signature/Date of Authorized Individual CE 4?10? 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 BY Administrator of the Federal Aviation Administration and is Approved Rejected . . . . Pe sons A roved Canadian Manufacturer Maintenance Organization Bazaadmm?pof Transit)? Other (Specify) FAA Designee Repair Station inspection Authorization Certi?cate or Designation No. 4DSR637B Signature/Date of Authorized Individual F. (Es-(Qikbwn CK 337 (10-06) NOTICE Weight and balance or operating limitation changes shall be entered in the 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.) NBSOTB Q?s?(tan Nationality and Registration Mark ACTT: 12,189.93 feed through below outflow valves, FS 347.75. END Date During other maintenance. found unapproved alteration in aft pressure bulkhead in the form of a 1.375 inch A. Repaired in accordance with Georgian Aerospace drawing 356-720M024 Rev. IR. Reference attached 8110-3 from Alan B. Georgian BERT-230242-CE Structures dated 18 July 2011 approving this data. . The Weight and Balance change was deemed negligible per AC43.13-1B, Chapter 10, paragraph 10-2 (0). Additional Sheets Are Attached FAA Form 337 (10-06) DBAG-104 US. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE AIRWORTHINESS STANDARDS 18 July 2011 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Alr'cra?, Engine, Propeller. etc.) 5. NAME OF APPLICANT Hawker Beechcraft 200 Airplane Defense Support Services, LLC Corporation CRS 4DSR637B LIST or DATA 6. IDENTIFICATION 7. TITLE DRAWINGS: REV 35G-720M024 IR Repair, RH Aft Pressure Bulkhead Web, F.S. 347.75 REPORTS: 356R720M024 IR Structural Analysis of Drawing 35G-720M024 NOTES: . 1. The structural aspects only of the above listed data are approved herein, only those regulations listed below in "Applicable Requirements? are approved. 2. For Certification Basis, refer to TC Data Sheet Number A24CE. 3. The approval is only for the engineering design data and is not installation approval. 8. PURPOSE OF DATA In support of the Major Repair listed for the Beechcraft Model 200, SN: 88-498, N6507B. . .9. APPLICABLE REQUIREMENTS (List speci?c sections) Title 14 CFR Part .303, .307(a), .601, .603, .605(a), .609, .611, I 10. 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 none have been examined In accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed Recommend approval of these data. - I {We} Therefore: Approve these data. 11. OF DESIGNATED ENGINEERING 12. DESIGNATION 13. CLASSIFICATIONS) Alan B. Georgian Leg/5% DERT-230242-CE Structures FAA 8110-3 (03/10) EDITION Computer Generated Copy I Form Approved Electronic Tracking Number OMB No. 2120-0020 US Department MAJOR REPAIR AND ALTERATION mm :fgranslmatilon (Airframe, Powerplant, Propeller, or Appliance) are va on 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 Serial No. USA 1' Aircraft Make Model Series BEECH 200 King Air Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) Address 5070 Meridian Ave 2' owner United States Customs Service Oklahoma CitV 0K Zip 73119?5105 Country USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No. (As described in Item 1 above) - POWERPLANT El PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address 8. Kind of Agency Name Defenge Support Services U. S. Certificated Mechanic I Manufacturer Address 8092 Hangar Road Foreign Certi?cated Mechanic C. Certi?cate No. 'cny Saanng'?lp State TX ,7 "?Ce?r?tiric?ate'd'Repair Station ?m 33p A 76904 Country USA Certificated Maintenance Organization 4DSR637B 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 knowiedge. Extended range'fuei Signature/Date of Authorized Individual 14 CFRP rt43 Per a [j App. 7. Approval for Return to Service ?Pursuant to the authority given persons specified below, the unit identi?edin item 5 was inspected in the manner prescribed by the Adrriinistrator of the Federal Aviation Administration and is [3 Approved Rejected IFAA Flt. Standards - . . Persons Appmved by Canadian Inspector Manufacturer Maintenance Organization Department of Transpon BY I . Other (Speciijr) FAA Designee Repair Station Inspection Authorization Certi?cate or Signature/Date of Authorized Individual Desi nation No. . 9 QCWAQ 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 aim/orthiness 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.) N6507B Co's?Cl: Nationality and Registration Mark Date 1. Installed the following antennas and equipment: A. Installed an Iridium Antenna (Sensor Systems PIN 867-1575?109) on the upper FS 2180 in accordance with Georgian Aerospace drawing Rev. IR (4 pages). Reference 8110-3 from Alan B. Georgian Structures dated 18 July 2011 approving this data. B. Removed the Trimble GPS antenna 16248-20 and installed a Garmin GA35 GPS antenna PIN 013?00235-00 on the upper FS 203 in accordance with Georgian Aerospace drawing 356-316F358 Rev. IR (3 pages). Reference 8110-3 from Alan B. Georgian dated 18 July 2011 approving this data. C. Installed a Sensor Systems WX antenna PIN 867-1575-650 on the upper FS 220 in accordance with Georgian AerOSpace drawing 356-323F019 Rev. IR (4 pages). Reference 8110-3 from Alan B. Georgian CE Structures dated 18 July 2011 approving this data. D. Installed a Inertia Switch PIN 3LO-882I10 in the aft compartment at FS 367 in accordance with Georgian Aerospace drawing 356-347F122 Rev. IR (3 pages). Reference 8110-3 from Alan B. Georgian BERT-230242- CE Structures dated 18 July 2011 approving this data. E. Installed a Transmit Antenna PIN N000-1553 on the RH upper FS 319 in accordance with Georgian Aerospace drawing Rev. IR and Receive Antenna N000-1552 on the LH upper FS 327 in accordance with Georgian Aerospace drawing Rev. A. Reference 8110-3 from Alan B. Georgian DERT-230242-CE Structures dated 18 July 2011 approving this data. F. Installed avionic cable feed-throughs in the aft pressure bulkhead FS 348 in accordance with Georgian Aerospace drawing Rev IR. Reference 8110-3 from Alan B. Georgian Structures dated 18 July 2011 approving this data. 2. The Weight and Balance was updated for these installations. 3. A logbook entry was made to reflect these installations. END OF ENTRIES Additional Sheets Are Attached FAA Form 3371(10-06) DBAG-103 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE AIRWORTHINESS STANDARDS July 13, 201 1 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE - 3. MODEL NO. 4. TYPE Englne, Propeller, etc.) 5. NAME OF APPLICANT Hawker Beechcraft 200 Airplane Defense Support Services Corporation San Angelo, TX 76904 LIST DATA 6. IDENTIFICATION 7. TITLE DRAWINGS: REV 35G-257F 133 IR Feed Thrus, F.S. 348 35G-316F358 IR RH GA35 GPS Antenna, FS 203 356-323F019 IR RH 867-1575-650 WX Antenna, PS. 220 35G-347F113 IR RH CP-3 TX AntennaAntenna, F6. 327 35G-347F122 IR System Inertia Switch, PS. 367 356-347F134 IR RH 867?1575-109 Iridium Antenna, FS 180 REPORTS: 35GR257F 133 IR Structural Analysis of Drawing 35G-257F133 356R316F358 IR Structural Analysis of Drawing 35GR323F019 IR Structural Analysis of Drawing 350-323F019 35GR347F113 IR Structural Analysis of Drawing 13 356R347F114 IR Structural Analysis of Drawing 35G-347F114 35GR347F 122 IR Structural Analysis of Drawing 35G-347F122 35GR347F 134 IR Structural Analysis of Drawing 35G-347F134 NOTES: 1. The structural aspects only of the above listed data are approved herein, only those regulations listed below in "Applicable Requirements?are approved. 2. For Certification Basis, refer to TC Data Sheet Number A24CE. 3. The approval is only for the engineering design data and is not installation approval. 4 Drawings 35G-347F113 and 356-347F114 Rev A, along with associated reports was previously approved on 03 March 2009. Drawings 356-323F019 and 356? 347F122 with reports was previously approved on 10 September 2010. 356? 257F133, with report approved on 13 April 2011. 3. PURPOSE OF DATA In support Of the major alterations listed for the Beechcraft Model 200, SN: BB-498, N65OTB. 9. APPLICABLE REQUIREMENTS (List specific sections) Title 14 CFR Part 23.301 .303, .307(a), .337, .561, .601, .603, .605(a), .609, .611, 10. CERTIFICATION - Under authority vested by direction of the Administratorand in accordance with conditions and limitations of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered none have been examined in accordance with established prDCedures and found to comply with applicable requirements of the Airworthiness Standards listed Recommend approval of these data. I We) Therefore: Approve these data. 11. SIGNATUREIS) OF DESIGNATED ENGINEERING REPRESENTATIVEIS) 12. DESIGNATION 13. CLASSIFICATIONIS) Alan B. Georgian DERT-230242-CE Structures FAA Form 8110-3 (03/10) EDITION computer Generated Copy "c 1 Approved Electronic Tracking Number OMB No. 2120-0020 use MAJOR REPAIR AND ALTERATION 2?23?20? apartment For FAA Use Only otTranspona?on (Airframe, Powerplant, Propeller, or Appliance) 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 Serial No. USA N6507B 88?498 1' Aircraft Make Model Series BEECH 200 King Air Name (As shown on registration certificate) Address (As shown on registration certi?cate) Address 5070 Meridian Ave 2? owner United States Customs Service CW Oklahoma CitL QK Zip 73119-5105 Country USA 3. For FAA Use On_ly 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No. AIRFRAME (As described in Item 1 above) - POWERPLANT El PROPELLER Type APPUANCE Manufacturer - 6. Conformity Statement .A. Agency's Name and Address B. Kind of Agency Name Defgnge' Suppan Services U. S. Certificated Mechanic I Manufacturer ?Address 8092 Hanqar Road Foreign Certi?cated Mechanic C. Certi?cate No. 'City "S?aii?i'?inij?io setng Certificated Repair Station ~ultra 7690.4 Country USA . 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 furnished herein is true and correct to the best of my knowledge. "Ex-Ended rrange fue Signature/Date of Authorized Individual .esrii?ECFRPaW Caerth ?App.B 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 El Approved Rejected . . . A d' I rn??eilg?rstandards Manufacturer Maintenance Organization Dzss?e?pg?fansiorfna ?an BY . I I Other (Specify) FAA Designee Repair Station Inspection Authorization Certi?cate or Signature/Dale ofAuthorized Individual . Des'gnat'on 4.33 . om ca, Rah el? ?35- 1 4DSR637B 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.) N6507B 4; ??le ~10? Nationality and Registration Mark Date ACTT: 12,1899 1. installed an Avidyne EX500 Multi-Function Display in accordance with Supplemental Type Certificate SA00161BO. 2. The Weight and Balance was updated for this installation. 3. A logbook entry was made to reflect this install. 4. Maintenance should refer to the Avidyne AVMFD-083 ICA release 4 dated 11/17/08 or later revision for Instructions for Continued Airworthiness. 5. Installed FAA Approved FMS dated February 8, 2005 and must be available to the pilot while this unit is installed under STC SAOO161BO. END OF FIRST ENTRY 1. installed an Avidyne Multi-Link Broadcast (MLB 700) PIN 700-00159-001 Receiver and antenna in accordance with Installation Manual 600-00174-000, AC43.13-ZB and DER's 8110-3. 2. Installed a Sensor Systems WX antenna PIN 867?1575-650 on the upper FS 220 in accordance with Georgian Aerospace drawing 356-323F019 (4 pages). Reference 8110-3 from Alan B. Georgian Structures dated 18 July 2011 approving this data. 3. The MLB Receiver was installed onto an existing shelf in the aft compartment at PS 358 using techniques and practices given in Advisory Circular AC43.13-2B: Chap. 1 PARA 111. Chap. 2 PARA 201 b, c, e, g, PARA 202 ALL, PARA 205, PARA 207 b, c, cl, e, f& PARA 208 PARA 209 PARA 210 d. 4. Control and indication ofthe MLB 700 is through the Avidyne EX500 Multi-Function display noted above. 5. The Weight and Balance was updated for this installation an a logbook entry was made. 6. Maintenance should refer to the Avidyne Instructions .for Continued Airworthiness, document AVSSG-OOB Rev. 4 or later revision for continued airworthiness. END OF ENTRIES Additional Sheets Are Attached FAA Form 337 (10-06) DRAG-103 US. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE AIRWORTHINESS STANDARDS July 18' 2011 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircra?, Engine. Propeller, etc.) 5. NAME OF APPLICANT Hawker Beechcraft 200 Airplane Defense Support Services Corporation San Angelo, TX 76904 LIST OF DATA 6. IDENTIFICATION . 7. TITLE DRAWINGS: REV .356-257F133 IR Instl, Feed Thrus, F8. 348 IR - Instl, RH GA35 GPS Antenna, FS 203 IR Instl, RH 367-1575-650 WX Antenna, ES. 220 13 IR Instl, RH CP-3 TX Antenna, PS. 319 A Instl, LH CP-3 RX Antenna, F.S. 327 358-347F122 IR System Inertia Switch, PS. 367 IR Instl, RH 867-1575-109 Iridium Antenna, FS 180 REPORTS: 35GR257F133 IR Structural Analysis of Drawing 35G-257F 133 35GR316F358 IR Structural Analysis of Drawing 35G-316F358 35GR323F019 IR Structural Analysis of Drawing 356-323FO19 356R347F113 IR Structural Analysis Of Drawing 13 14 IR Structural Analysis Of Drawing 14 35GR347F122 IR Structural Analysis Of Drawing 35G-347F 122 35GR347-F134 IR Structural Analysis of Drawing 35G-347F134 NOTES: 1. The structural aspects only of the above listed data are approved herein. only those regulations listed below in "Applicable Requirements" are approved. 2. For Certification Basis, refer to TC Data Sheet Number A24CE. 3. The approval Is only for the engineering design data and is not installation approval. 4 Drawings 356-347F113 and 35G-347F114 Rev A, along with associated reports was previously approved on 03 March 2009. Drawings 35G-323F019 and 35G- 347F122 with reports was previously approved on 10 September 2010. 356- 257F133, with report approved on 13 April 2011. 8. PURPOSE OF DATA In support Of the major alterations listed for the Beechcraft Model 200, SN: BB-498, N65OYB. 9. APPLICABLE REQUIREMENTS (List speci?c sections) Title 14 CFR Part .303, .307(a), .337, .561, .601, .603, .605(a), .609, .611, 10. 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 none have been examined in accordance with established procedures and found to comply with applicable requirements Of the Standards listed Recommend approval of these data. I We} Therefore: 8 Approve these data. It. SIGNATURES) OF DESIGNATED ENGINEERING 12. DESIGNATION 13. CLASSIFICATIONIS) Alan B. Georgian DERT-230242-CE Structures FAA Form 811 0-3 (03/10) sueeasso?sems?ous EDITION Computer Generated Copy ?lin?tnh ?tting 09f cAmerica ?epartment of Wransporta?on - g?'eheral Canadian Abminietra?nn ?npplemntal (Tlng Gerti?caie WW SAOOIGIBO Wat/?0 Avidyne'Corporation 55_>Old BedfordRpad Lincoln, Massachusetts 01773 ?ew/WW; fem E?m/m .MMea .- See attached FAA Approved Model List (Alva), Document No. AVMFC-076, Rev (D), dated February 08, 2005, or" later FAA approved revisions for the list of approved airplane?models and applicable regulations. ?eece/<- 951% 9/%/30 9% $941499: Installation of Avidyne Corporation FlightMax 700-00007-( Multi-Function Display in accordance vvith Avidyne Corporation'Ma'ster Document List, Document No. AVMFD-OSS, Revision 09, dated Februzny 4, 2005, or later AA-approved revisions. l. The lightMax EXSOO Mum-Function Display integrates with separately approved system installations. Adherence to the limitations in the appropriate Aircraft Flight Manual Supplements for those systems is mandatory. 2. Instructions for Continued Airworthiness (ICA), Avidyne Corporation Document Revision 05, datedOctober 15, 2004 or later FAA accepted revision shall be made available to the operator at the tithe or installation. i I 3. Compatibility of this design 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. yW?eem?W/Mm. gm .- September 10, 2002 . ?ne @449 MW .- February 6, 2003 @m February 3, 2005 ?y We? 95% age/mamm- I (Signature) I Robert G. Mann Manager Boston Aircraft Certi?cation Office (Title) Any alteration of this certificate is punishable by a fine of not exceeding 51.000. or imprisonment not exceeding 3 years, or both. FAA Form Page 1 of 1 This certificate may be transferred in accordance with FAR 21.47 Received '2 1 (Flair; agg?vz?oozo Tracking Number US De MAJOR REPAIR AND ALTERATION mm? mu 0 partment . or so ny (Airframe, Powerplant, Propeller, or Appliawgfsoosw?ai 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 Serial No. USA N6507B 88-498 1- A?rc'a? Make Model Series BEECH 200 King Air Name (As shown on registration certificate) Address (As shown on registration certi?cate) 2 I Address 5020 Meridian Ave wner United States Customs Service CW Qi?ahoma CitL 0K Zip 73119-5105 Country USA 3. For FAA Use Only ?The data identi?ed herein complies with applicable nirworthi ss requirements and by a person authorized in 43.7." APR 2 5 approved for the above described aircraft, subject to conformity inspection District Office Date Signature of inspector 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No. AIRFRAME (AS described in Item 7 above) POWERPLANT Ci PROPELLER Type Ci APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Name Defense support Services U. S. Certificated Mechanic I Manufacturer Address OOQE??gtlgar Road Foreign Certi?cated Mechanic C. Certi?cate No. Qty San Angelo State TX Certificated Repair Station Zip 75904 Country USA Certificated Maintenance Organization 4DSR637B D. I certify that the repair andr'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. Extended range fuel Signature/Date of Authorized Individual per 14 CFR Part 43 MaegaQ $34-th App. 8 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 8 Approved Rejected 81 I . . . Persons Approved Canadian Inspector an ar Manufacmrer Ma'ntenance Organ'zat'on Department of Transisort BY I Other (Specify) FAA Designee Repair Station Inspection Authorization Certi?cate or Signature/Date of Authorized Individual Designation No. . . k. camifo?IAQS a 2 i? SCCQ 'xxV?Ile 4DS R6378 FAA Form 837 (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 ain/vorthiness 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.) Nationality and Registration Mark Date 1. Removed a Trimble Approach Plus GPS and installed a Garmin 400W GPS in accordance with STC SAO1933LA-D. 2. This 337 is to also update the Approved Flight Manual Supplement for a Garmin 400W GPS-WAAS Navigation System. 3. The Limitations Section remains unchanged from the original that was Approved on 7/31/2009 by David G. ODA STC Unit Administrator, Garmin International, lnc. ODA-240087-CE. a 9.. km 4. This FMS is for N6507B, SIN 88-498 and is to be carried in the airplane 'at all times the Garmin 400W series unit is installed in accordance with STC 8A01933LA-D. 5. The Weight and Balance was updated for this installation. 6. A logbook entry was made to reflect this installation. 7. Maintenance should refer to the Garmin 400W Series ICA document 190-00356-65 Rev. dated 7/30/09 for continued airworthiness. . - 8. Installed FAA Approved FMS dated?q?lg?le? and must be available to the pilot while this unit installed under STC SA01933LA-D. END Additional Sheets Are Attached FAA Form 337 (10-06) (2 US Department of Transportation Federal Aviation Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Prepeller, or Appliance) Form Approved OMB No. 2120-0020 2128201 1 Electronic Tracking Number For 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. ?44701). Failure to report can result in a civil penalty for each Nationality and Registration Mark Serial No. N6507B 88-498 1. Aircraft Make Model Series Beechcraft 200 King Air Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) US Customs Service Address 5020 Meridian Ave 2' owner Of?ce of Patro City Oklahoma Slate 0k Zip 73119-5105 Country USA 3. For FAA Use Only i'iio data identified herein complies with the applicable airworthiness requirements and is approved for the abovu described aircraft. subject to co spection by a person authorized 14 FR Pa i0 .43] District Office ate Signature of FAA lnspe tor 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No. AIRFRAME (As described in item 1 above) POWERPLANT El PROPELLER Face quick donning 02 APPLIANCE Mmask - MF20-001 anufacturer Intertechnique L1 6. Conformity Statement W0 "11? A. Agency's Name and AddLess B. Kind of Agency Name Address 2701 Kirtland Dr. SE, 291 KAFB City Zip 37117 Country State U. S. Certi?cated Mechanic I Manufacturer Foreign Certificated Mechanic C. Certi?cate No. Certificated Repair Station Certificated Maintenance Organization 3329649 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. Extended range fuel Signaturel per 14 CFR Part 43 App. El Auth 5, Individual ri?e e/?rf 7. Approval for Return to Service Approved 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 Rejected FAA Flt. Standards urer inspector a act BY Maintenance Organization Persons Approved by Canadian Department of Transport FAA Designee Repair Station inspection Authorization Other (Specify) Certificate or Designation No. 3364923 IA SignaturelD te 0 thorized Individual nge?? a/m/ 2.9/1 vv 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 ainivorthiness requirements. 8. of Work Accomplished (if more space is required, attach additional sheets. identify with aircraft nationality and registration mark and date work completed.) N6507B 3/16/2011 Nationality and Registration Mark Date King Air 200 EROS Full Faced O2 mask Installation. 1. Disconnected external power and the main battery from the aircraft. Installed warning tags. 2. Removed the plastic escutcheons on the cockpit side trim panels that house the existing PIN Z808 crew oxygen quick-disconnect valves. Ensured the oxygen push-pull control knobs located on the aft section of the cockpit headliner were in the off position and the oxygen bottle supply valve was closed. Disconnected and removed the 2808 valves and ?ttings. Transferred the elbow and plug ?ttings and installed the FAA-PMA PIN 802040-03 valves manufactured by Zodiac Avox Systems, using care not to use grease. oil. or any lubricants on any oxygen component or ?tting. 3. Removed the cockpit headliner assembly. 4. Using the stowage cup as a template, traced the outline onto the 2024T3 sheetmetal to create the backing doublets. The sheetmetal size in the materials list is enough for both doublers. Once rough cut, trimmed and deburred the doubler edges to ?nal shape. 5. Positioned each stowage cup over its corresponding doubler and marked the 4 mounting holes. Removed the stowage cups and drilled the doublers using a 21 bit in the 4 locations. 6. Referring to AC 43.13-2A as a guide, developed a rivet attachment ?eld-pattern while maintaining proper rivet spacing and edge distance. Marked the doublers in the locations desired and drilled using a 30 bit. 7. Positioned a nut plate on each doubler on each of the four mounting holes drilled in step 5. Drilled for the nut plate attachment rivets using a 40 drill bit and countersank the holes. Deburred all holes and primed the doubler using Zinc Phosphate. 8. Installed the 4 nut plates on each doubler using the AD3-4 rivets. 9. Positioned each doubler on the rear of the headliner panel making sure they were in the correct context. The aft corner of the doubler is approximately 3.5? from the aft edge of the headliner panel. The side corner is approximately 6? from the side edge of the headliner panel. Angled the doubler approximately 45 degrees so that once the cup was installed, the regulator valve pointed toward the side window. Measured both sides to make sure both doublers were positioned correctly. 10. Held the doublers in place and drilled through the plastic headliner with a 30 bit using light pressure. Turned the headliner over and countersank the holes just drilled. Installed the doublers using the CR3212-4-03 rivets. 11. Installed the stowage cup on the headliner using the M824694-S7 machine screws. Tightened to 25 Inch-pounds. Reinstalled the headliner. Positioned the MF20-001 masks in the cups. 12. Turned on the oxygen supply valve and the push pull control and leak checked both cockpit oxygen quick- disconnect valves. No leaks were found, installed the escutcheons and plugged in both masks and audio plugs. 13. Conducted a complete mask operational check in accordance with the EROS Series Operating and Maintenance Instructions. 14. Calculated the appropriate weight and balance changes (negligible). 15. Completed and submitted a Form 337 to local FAA FSDO. 16. Completed a logbook entry. Materials: Full face Quick donning Mask/Regulator MF20-001 2 Crew Oxygen Mask Stowage Cup MXP405-10 2 Oxygen Quick-Disconnect Valve 802040-03 2 2024T3 Aluminum Sheetmetal 15" 7" .032" 1 Countersunk Rivets M820426AD3-4 16 Countersunk Rivets CR3212-4-03 40 Floating Anchor Nuts M521059L08 8 Countersunk Machine Screws MSZ4694-ST 8 A 337 for a similar installation on aircraft N7166P was approved 8/31/2010. Additional Sheets Are Attached FAA Form 337 (10-06) INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Make: Beechcraft Model: KA-200 BB-498 Reg. N6507B Revision: Original Date: 3I1612011 This sixteen item checklist contains Instructions for Continued Airworthiness (ICA), to comply with FAA Handbook Bulletin for Airworthiness (HBAW 98-18 Dated October 7, 1998), and are applicable to the aircraft listed above when the following equipment is installed: SYSTEM: Oxygen ITEM a a CHECKLIST INFORMATION. 1 Introduction: This alteration to the above aircraft obligates the operator to include the maintenance information provided by this document in the owner/operator?s aircraft scheduled maintenance program. 2. Description: The existing crew oxygen masks are replaced with Full Face Quick Donning EROS model 02 masks. The EROS masks are The 02 outlet fittings are replaced to accommodate the new mask bayonet fittings. Stowage cups to accommodate the masks are installed into the headliner, the old mask books on the cockpit to cabin partitions are removed. 3. Control: Reference the EROS Operating and Maintenance Instructions for the Full Face Quick Donning Mask-Regulator, Series, document 4NUT0080A dated Oct. 30/02. 4 Servicing information: The EROS masks require an annual inspection/operational check, and overhaul every six years, please see item 5 below. 5 Maintenance Instructions: Taken from sections 4 and 6 of the Operating and Maintenance instructions manual, document 4N UTOOBOA dated Oct. 30/02. -A system test should be performed at periodic intervals (at least once a year) as recommended by the aircraft flight manual and EROS maintainability data. -Remove the mask-regulator from the stowage box as defined in paragraph 1.1. Hold the mask-regulator and depress the harness inflation control (red plates). ?On the pneumatic harness, check that correct position of spacers on hoses is provided by efficient sealing or position on printed marks (this is applicable to items manufactured from March 2000; for older items refer to instructions in the applicable CMM). -Position the mask-regulator onto the head per normal operation. Note The following test must be performed with the control lever in the ?100%? position. -Rotate the TO control knob counter-clockwise (in the direction of the arrow). Take a few breaths. Breathing should be free and unrestricted. Rotate the TO control knob (clockwise) back to its original position. ?Test the microphone per normal operating procedure. -Stow the unit per instructions in paragraph 2. Note Proper stowage is essential for quick and efficient donning of the mask-regulator assembly. It is strongly recommended that crew members authorized to use the unit be properly trained to this procedure. - Under normal environmental conditions and use. EROS recommends that the mask regulator is submitted, at least, to a ONE year complete system test (refer to paragraph 4) and overhauled EVERY SIX YEARS. -Overhaul of this equipment shall be performed at INTERTECHNIQUE, Plaisir FRANCE, or at an USCSAVP-118 2 JULY 01 19?95 INTERTECHNIQUE approved overhaul facility. Trouble shooting information: Reference the Hawker Beechcraft King Air 200 MM, chapter 35, for information describing probable malfunctions. Removal and replacement information: Reference the Hawker Beechcraft King Air 200 MM, chapter 35, for information describing replacement of 02 system components. The masks utilize bayonet type fittings and connectors and are installed by inserting bayonet fitting into receptacle and turning clockwise until it locks. Removal is the opposite of installation. The microphone jack simply plugs in and unplugs. Diagrams: There are no special diagrams for this alteration. Special inspection requirements: Special inspection requirements are not applicable except as noted in items 4 5 above. IO. Application of protective treatments: Protective treatments are not applicable. Data: There are no structural fasteners or special installation requirements. Standard practices from chapter 20 of the KA 200 MM apply to torques for the outlet fittings. 12. List of special tools: There are no special tools required. 13. For commuter category aircraft: Not a commuter aircraft. 14. Recommended overhaul periods: Overhaul of this equipment shall be performed EVERY SIX YEARS at INTERTECHNIQUE, Plaisir FRANCE, or at an INTERTECHNIQUE approved overhaul facility, per the manual in item 3 above. Airworthiness Limitation Section: There are no additional ain/vorthiness limitations. l6. Revision: The Instructions for Continued Airworthiness Checklist (ICA), may be revised by submitting a letter to the local FSDO with a copy of the revised FAA Form 337 and revised ICA. The FAA inspector accepts the change by signing Block 3 and including the following statement: "The attached revised/new Instructions for Continued Airworthiness (date for the above aircraft or component major alteration have been accepted by the FAA, superseding the Instructions for Continued Airworthiness (date Once the revision has been accepted, a maintenance record entry will be made, identifying the revision, Its location, date of the Form 337. Note: USCSAVP-118 2 JULY 01 2 o?e? Implementation and Record Keeping: For major alterations performed in accordance with FAA Field Approval policy, the owner/operator operating under part 91 is responsible for ensuring that the ICA is made part of the applicable section 91.409 inspection program for their aircraft. This is accomplished when a maintenance entry is made in the aircraft's maintenance record in accordance with section 43.9. This entry records the major alteration and identi?es the original ICA location Block 8 of FAA Form 337, dated 5/28/98) along with a statement that the ICA is now part of the aircraft's inspection/maintenance requirements. For major alterations performed in accordance with a ?eld approval on air carrier aircraft, the air carrier operator is responsible for ensuring that the ICA is made part of the applicable inSpection/maintenance program for their aircraft. If a procedure is not currently included in the operator's manual to incorporate ICA, this process will need to be appropriately addressed the operator submits a revision to its maintenance program to the applicable certi?cate-holding district of?ce (CHDO). For aircraft inSpected under an Approved Aircraft InSpection Program (AAIP), the Operator will submit a change to the CHDO in accordance with section 135.419 For air carrier aircraft inspected using an annual/ 100 hour inspection program, a reference to the new ICA will be made in the aircraft?s maintenancerecord in accordance with section 43.9. This entry records the major alteration and identi?es the original ICA location ICA are located/attached to Block 8 of FAA Form 337, dated 5/28/98). In addition, the operator will request a revision to the operator's Operations Speci?cations, additional maintenance requirements, which incorporates the ICA into the inspection program. USCSAVP-118 2 JULY 01 3 of 5 0 US Department 01 Transportation Federal Aviation Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form Approved OMB No. 2120-0020 2/28f2011 Electronic Tracking Number For FAA Use Only 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 Serial No. N65078 BB-498 1' A'rcraft Make Model Series Beechcraft King Air 200 Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) US Customs Service Address 5020 Meridian Ave 2- owner City Oklahoma City srre 0k Zip 73119-5105 Country USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No. AIRFRAME (AS described in item 1 above) [3 POWERPLANT El PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address 8. Kind of Agency Name Address 2701 Kirtland Dr, 291 KAFB U. S. Certi?cated Mechanic I Manufacturer Foreign Certificated Mechanic C. Certi?cate No. City Albuqueroue State NM Certi?cated Repair Station Zip 871 17 Country USA Certificated Maintenance Organization 2814345 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. Extended range fuel per 14 CFR Part 43 App. Si ureIDate of Authorized Individual or o'f/ 39? 7. Approval for Return to Service [3 Approved 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 Rejected BY FAA Flt. Standards Manuf inspector act? Maintenance Organization Persons Approved by Canadian Department of Transport FAA Designee Repair Station Inspection Authorization Other (Specify) Certi?cate or Designation No. 3364923 SignaturelD of thorized Individual l/if/Zolt FAA Form 337 (woe) 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 ainivorthiness requirements. 8. Description of Work Accomplished (if more space is required, attach additional sheets. identify with aircratt nationality and registration mark and date work completed.) N6507B 1/7/2011 Nationality and Registration Mark Date Removed floor panel and 2 ea) support beams and channels located between FS 248-273. Fabricated 2 ea) new support beams and 8 ea) angle attach brackets from aluminum extrusion p/n: AND 10137-2005, 2024-T3511, .125 thickness. Also fabricated 1 ea) new ?oor panel from aluminum clad sheet 2024-T3, .063 thickness. Cleaned, alodined and primed beams, attachment brackets and ?oor panel. Installed 11 ea) nutplates, p/n: M821059L08 on each beam. picked up existing screw holes from aircraft structure and beams onto new floor panel. Secured 2 ea) angle brackets to each end of the beams with Hi-Loks, pin: HL18PBL-8, and installed beams on aircraft between FS 248-273 with ANS-5A bolts, NAS114QDO363J washers, and NA8679A3 nuts. Applied a bead of sealant between ?oor panel, beams and aircraft structure and secured new ?oor panel with M827039-0809 screws. All work was done as per Georgian Aerospace Group, Inc. repair de?nition 356-724F003, see drawings for more details. Change in weight and balance negligible. Additional Sheets Are Attached FAA Form 337 (10-06) DBAG-O96 US. DEPARTMENT OF TRANSPORTATION DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS 13 January 201 1 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL NO. TYPE (Airplane. Radio, Helicopter, etc.) NAME OF APPLICANT Hawker Beechcraft 200 Airplane Defense Support Services Corporation San Angelo, TX 76904 LIST OF DATA IDENTIFICATION . TITLE DRAWINGS: REV 35G-724F003 IR InstI, Cabin Floor Panel, F.S. 248 - 273 REPORTS: 35GR724F003 IR Structural Analysis of. Drawing 35G-724F003 NOTES: 1. The structural aspects only of the above listed data are approved herein, only those regulations listed below In ?Applicable Requirements" are approved. 2. For Certi?cation Basis, refer to TC Data Sheet Number A24CE. 3. The approval is only for the engineering design data and is not installation approval. PURPOSE OF DATA . In support of the major alteration listed for the Hawker Beechcraft Model 200, SN: BB-498 - APPLICABLE REQUIREMENTS (List speci?c sections) Title 14 CFR Part .303, .307(a), .601, .603, .609, .611, 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 applicable requirements of the FederalAviation Regulations. Recommend approval of these data. Approve these data. OF DESIGNATED ENGINEERING DESIGNATION CLASSIFICATIONS) . Aian B. Georgian Structures FAA Form 8110-3 (11?70) SUPERSEDES PREWOIJS EDITION Computer Generated Copy I We)- Therefore F.S. 273 REF 8. EOUALLY SPACED IS ABBREVIATED BY F.S. 24-8 7. INSTALL FASTENER APPROXIMATELY AS SHOWN. MINIMUM REF EDGE DISTANCE 2 DIA AND MINIMUM SPACING 4 DIA. 6. FASTENER CODE: INSTALL M527039-08 SCREWS AND MSZOTSQLOB NUTPLATE. LA INSTALL NUTPLATE ON ITEM 03 WITH 2 EACH MSZO4-26ADS RIVETS. INSTALL: (COLLAR) PER NOTE 7. ANS (BOLT). (WASHER) AND NASS79A3 (NUT) PER NOTE 7. 01 REF M520470A04 PER NOTE 7. EXISTING FASTENER LOCATION. GENERAL LOCATION I INSTALL ORIGINAL SCREWS (M527039-08). EXISTING FASTENER (REF). 5. HEAD SEAL ANTENNA INSTALLATION WITH PR-14228 SEALANT (0R EQUIVALENT). 4. USE PR-14225 SEALANT (OR EQUIVALENT) BETWEEN FAYING SURFACES OF PRIMARY 0R SECONDARY AIRFRAME STRUCTURE AS APPLICABLE. 5. ALODINE PER AND APPLY PRIMER PER 09 ON ALL APPLICABLE PARTS. OB 2. BREAK ALL SHARP EDGES AND REMOVE ALL BURRS. 06 1. MATERIAL PROCESS AND METHODS SHALL COMPLY WITH 3 05 ?15 ANGLE 2024435? EXTRUSIUN PERTINENT FAA AC NO. 43.15 SPECIFICATIONS OR EQUIVALENT. I 04 '13 FLUDR PANEL 0.063? CLAD 4 03 10137~2005 CHANNEL EXTRUSION NOTES- - 01 -01 CABIN FLOOR PLUG INSTALL ~01 ITEM PART NUMBER NOMENCLATURE WENDOR MATERIAL - LIST OF MATERIALS THESE Emu. DATA AND THE nEmNs 01510551: IIEREII ARE THE when?, KNG NR mm PREPARED IT - BATE rm: EXCLUSIVE PROPERTY or GEORGUN AEROSPACE OONTAN MODEU 200 "at; 5? LEE .. CABIN FLOOR PANEL MREES TO HOLD CONFIDENCE TIE DATA MD mm m- a DATE - AEROSPACE a] REM THS M.BY ITS RETENTDN RD USE 1'0 Ivrmout TIE CONSENT or GEORGIAN WAGE Runs To sacs TEcchL DATA an sum 025m 10 TIE g?w 31,553 m. ?1'30 ?an same a REV wan nun Basr- um ALL mm_ {15/ I NOTED IR 1of 5 . . . 2425REFJ \E?f REF L: REF REF -01 CABIN FLOOR PANELJS. 248?273 356-724F003 IR EL 0. 00 REF (12.3) 0.125 (12.3) ?gmjaa; 4 - CBFEF SIDE STRUCTURE REF 0.063" 2024-T3 CLAD VIEW A-A UP RH OUT q} A 0.7 NOT STRUCTURES ARE SHOWN FOR CLARITY LOOKNG FWD SCALEWE L0 4 05 REF 03 REF EXISTING SIDE STRUCTURE 0.063" 2024-T3 CLAD- DWG NO. 356-724F003 REV. IR SHT. 1-0 REF s-1a.o 0.7 F.- (24.9) REF FWD STRUCTURE EXISTING AFT STRUCTURE 0.063" 2024-T3 CLAD 0.053" 2024-T3 CLAD F.S. . F.S. 248 273 REF REF VIEW B-B NOT STRUCTURES ARE SHOWN FOR CLARITY LOOKING LH INBOARD DWG NO. REV. SHT. IR 4 0.75+Ir A (24.9) 7. ITEM 03 CHANNEL DWG NO. REV. SHT. 356-724FOO3 IR 5 of 5 I 13:11:. 35GR724F003 INTRODUCTION The following report outlines the structural aspects only of the installation of cabin floor panel at Fuselage Station 248 to 273. This repair is on the Raytheon Model: 200 (King Air), SN: BB-498, as de?ned on drawing 3 Structural substantiation for the installation is per the pertinent sections of Title 14 CFR Part 23. - 23.301 Loads 23.303 Factor of Safety 23.305 Strength and Deformation 23.307 Proof of Structure 23.365 Pressurized Cabin Loads 23.601 A General, Design and Construction 23.603 Materials and workmanship 23.605 Fabrication Methods 23.609 Protection of Structure 23.611 Accessibility Provisions 23 .613 Material Strength Properties and Design Values DISCUSSION A new ?oor panel(24.5" 25.0") is fabricated from 0.063" 2024-T3 clad and installed over the previously existing camera bay ?oor opening FS 248-273. Two supporting extrusions are installed under the new ?oor panel in order to support the new panel. ALLOWABLES Original Doubler Material 2024-T3 Clad Aluminum (0.063 to 0.128 thickness) Reference 1 Table 3.2.3.0(e1) Fm 61 ksi Fcy 37 ksi megzo) 125 ksi Extruded Aluminum (:024 thickness) I Reference 1 Table 3.2.3.00.) Ftu 57 lcsi F?y 34 ksi 108 ksi Ec 11.0 103 ksi Fasteners . . AN3 Bolt (0.063 thick 2024-T3 sheet) Reference 2 Page D1.3 Pm, 2,126 Pbmn-ng 0.191" 0.063" 108 ksi 1,300 2,210 - 1,300 shear Rev I Page 1 of 4 35GR724F003 ANALYSIS The King Air 200 Series aircraft ?maintain a 6.5 psi differential and provide a nominal pressure altitude of 10,4000 ft at an airplane altitude of 35,000 ft? psi per Maintenance Manual 21-00-00 pagel. The critical load is then 6.5 psi 1.5 X133 =13.0 psi (factor of Safety per 23.303and pressurized cabin loads per 23.365 (1). - Using Appendix A, the maximum bending moment on the beam is the following. 24,3851bs in The maximum bending stress in both tension and compression are the following. 17,539 psi creams.? 7,203 psi 0' tension The margin of safety for the tray material are the following. 17,539psz' 7,208psi The maximum reaction load at each side of the beam is 3,981 lbs. This load is transfer to the fasteners attaching the beam in shear. The ultimate shear allowable for the AN 3 bolts 1,300 lbs. There are eight (8) AN3 bolts per side of the beam. 24.5 A i . 9 0.60 Lin 0'1? l? 0.25 1.45 - LEE la?zco?ol 2.02935 in? A- 3.44533 Rev IR Page 2 of 4 35GR724F003 CONCLUSION It is concluded that the ?oor panel installation shown on drawing 35G-724F003 meets the requirements of Title 14 CFR Part 23 as listed in the Introduction. REFERENCE 1) Metallic Materials and Elements for Aerospace Vehicle Structures, 1994. 2) Brubn, Analysis and Design of Flight Vehicle Structures, June, 1973. End of Report oon S. Lee December 28, 2010 Rev Page 3 of 4 35GR724F003 Agpendix A 356-7241?003 Floor Panel? BEAM LENGTH 24.5 in 7 MATERIAL PROPERTIES 1 Floor: Modulus of elasticity 10500000.0 lblin2 BemLeno?lh: 24.5 In Location 11862031n7 3 'l 1' CROSS-SECTION PROPERTIES In Floor: Moment of inertia 2.02985 in"4 0111153741 Top height 0.6 in Danac?on 0mm Bottom height 1.46 in 05353524 Area 3.44533 in2 :1 UNIFORMLY DISTRIBUTED FORCES 45355521 UNIFORMLY LOAD 1: 325.0 lblin at 0.0 over Slope 24.5 in 24385.16 SUPPORT REACTIONS SI: Simple at 0.0 in an Reaction Force 981.25 1b 359125 82: Simple at 24.5 in Reaction Force =?3981.25 lb .mus MAXIMUMDEFLECTION 0.07153741in at 12.25in 17539.39 1 1.111111? Stu 5: Tesla 17651 ?mk?mm .. MAXIMUM muse 24385.161b-in at 12.25in I 2 1155.15 MAXIMUM SHEAR FORCE 11? i 3981.251b at 0.0m -3981.251?o at 24.5in . .m 1 Avmgo Shear Stun 5mm? MAXIMUM STRESS . Tensile 17539.39 1b/in? Compressive 7207.968 1b/in2 Shear (Avg) 1155.55 lb/in2 Rev 1R Page 4 of 4 Federal Aviation . . . Form Approved as - - (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Office Identi?cation Administration INSTRUCTIONS: 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 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 BEECH 200 1. Aircraft Serial No. Nationality and Registration Mark BIB-498 Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) United States Customs Service 5020 Meridian Ave. 2. Owner Oklahoma City, OK 731 19 3. For FAA Use Only 4. Unit identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in item 1 above) POWERPLANT PROPELLER Type APPUANCE Manufacturer 6. Conformity Statement A. Agency?s Name and Address B. Kind of Agency C. Certificate No. L-3 Communications Vertex Aerospace, LLC U.S. Certi?cated Mechanic Limited Airframe 8092 Hangar Rd. Foreign Certificated Mechanic RCOR173N San Angelo, Texas 76904 Certified Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unitis) identified 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 7 Signature of Authorize Individual 0:2 0 Dec. 0 4 . Norm 7. Approval for Return To Service Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is APPROVED El REJECTED FAA F't- Standards Manufacturer Inspection Authorization Other (Spec??f) inspector FAA Designee Repair Station Person Approved by Transport Canada Airworthiness Group Signature of Authorized Individual Dorm J. Marah . Certificate or Designation No. t3 /Bc> RCOR173N Date of Approval or Rejection FAA Form 337 (12-88) 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.) Date: Reg. No. NBSOYB Serial No. 88-498 tel 90/3009 Total Time: 11062.0 1. Installed a Northrop Grumman DMRSOO SATELLITE Tracking Beacon Unit in accordance with mfg. drawing no. 250107WD dated 6/13/2002 and Engineering Order No. 03-06 dated July 2, 2003 at Station 321.0 See FAA Form 8110-3 dated 14-Nov-06 approving this data. 2. At completion of this work, all affected systems were tested for correct operation. The Aircraft Weightl . Balance and Equipment List revised. Theaircraft was pressurized to max differential to verify integrity of installation. END - I I as. DEPARTMENT OF TRANSPORTATION DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL NO TYPE (Airplane. radm. heiicoptcmic.) NAME OF APPLICANT Beech 200 AIRPLANE U.S Customs Service Oklahoma City, OK LIST OF DATA IDENTIFICATION TITLE Engineering OTdef 03-05 Satellite tracking beacon antenna doublers installation (3 pages) dated July 2, 2003 NOTES: 1. THE STRUCTURAL ASPECTS ONLY OF THE ABOVE LISTED DATA. ARE APPROVED HEREIN. THIS APPROVAL IS FOR THE STRUCTURAL ENGINEERING DESIGN DATA ONLY AND DOES NOT CONSTITUTE INSTALLATION APPROVAL OF ELECTRONIC SYSTEMS. 2. THIS APPROVAL IS VALID ONLY FOR N6507B SIN PURPOSE OF DATA TO SHOW COMPLIANCE WITH APPLICABLE FAR 23.301 2330333305 (3)2330? 23.607 and 23.61.3(0) CERTIFICATION Under authority vested by direction of the Administrator and under part 183 of the Federal Aviation Regulations 1 I 3 have been examined In accordance with established procedures and found to comply with appiicabie reqLIIrements of the Federal Aviation Reguiatiorm. Recommend Approval of these data I (WE) THEREFORE Approve these data SIGNATUREIS) OF DESIGNATED ENGINEERING DESIGNATION CLASSIFICATIONIS) REPRESENTATIVEIS) ASHOK K. VIJ DERT-605582-NM STRUCTURES FAA FORM 81 10-3 (i PREVIOUS EDITION Poem-ms Department of Transportation Federal Aviation Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification 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 bylaw (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1.000 for each such violation (Section 901 Federal Aviation Act 1958) Make Model Beech 200 1. Aircraft A I I Serial No. Nationality and Registration Mark BB-498 N6507B Name {As shown on registration certificate) Address (As shown on registration certi?cate) . 2_ Owner United StatesCustoms Service. 5020 Meridian Ave. Oklahoma City. OK 73119 3. For FAA Use Only 4. Unit Identification 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 8. Kind of Agency C. Certi?cate No. L-3 Communications Vertex Aerospace, LLC 8092 Hang ar RD San Angelo. TX 76904 US. Certi?ed Mechanic CRS N0. RCOR173N Ci Foreign Certi?ed Mechanic [2 Certi?ed Repair Station Limited Airframe Cl Manufacturer 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. A Date ?0 Deg Signature of Authorized Individual Norm Woods ?ue?.1 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 Other (Specify) BY Administrator of the Federal Aviation Administration and is APPROVED REJECTED FAA Standards Manufacturer Inspection Authorization Inspector FAA Designee Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection tel sojeooLo Certificate or Designation No. RCOR173N Signature of Authorized Individual Donn J. Maren?F?- ?t 4' Mm . FAA Form 337 (12-88) 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.) Reg. No. N6507B 88-498 Acft.TT11062.0 1. Antenna Provisions - King Air 200, Rev IR dated 12/20/05. and UHF Antenna Doublers -Beech 8200, Rev IR dated 02/09/06 installed in accordance with Threshold Engineering Co. Drawings 117-001 and 117-002. Reference attached FAA Form 8110-3, Identification Drawings 117-001 and 117-002, Designation No. DERT-710075-SW, dated May 3, 2006 approving this data. 2. Weight Balance change negligible. reference AC43.13-1B Change 1, Chapter 10 PARA End Additional Sheets Are Attached U.S.GPO: 1989-0-663-1 71 i. OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION - may Br 2006 I STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION WAKE NO. . TYPE (Airplane, Radio, Helicopter, etc.) -NAME OF APPLICANT I Airplane L3 Communications ?Raytheon 200 San Angelo, Texas OF DATA IDENTIFICATION - - TITLE Drawings ?117-001 ANTENNA PROVISIONS KING AIR 200, Rev dated 12/20/05, by Threshold Engineering CO. - NOTE: The above data is approved for structural design aspects only PURPOSE OF DATA In support Of ?eld Alteration, Raytheon (Beech) King Air 200, APPLICABLE REQUIREMENTS (List speci?c sections) FARS 25.305, 25.603, 25.605, 25.607, 25.609 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 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 (We) Therefore Approve these data SIGN DESIGNATION I ,2 I. 710075?sw Structures . ?i James A. EugeleI I IFAA Form 8110?3 (11-70) Supercedes previous edition (Computer Generated) I .7. I ru?m .wg?h . -.. i a 2.2.3.. MM A. nan .Jkrn ?rm u. hog??wm ?agUtm?qm .4 "army. in?m magzu?i?. wauNL .0 U. . t: >3u. .UCHmru G. . LY: 53.. .1blah/3M 9.55:7. {Ev I: .. h. Lu?mh a?ng hart .rum new?. Eu 0:12.903. .m .U Nein? 1 7rd?me L: hr ?NULknm 5.5.. Umn?ur. ud.%b.h6\ .Eh?z?u. ?hug5:5 u\i ~110591.?. 39.x. .ID who {gbe. .40. 5:21up. 0006. up. v.51?: ?.519 J. . I .. \Luw??mu. ?3.1 . Liar .. .v .. 2.033.505 . .aU visor. LP. . . . FL: rcu?rwu?d: Iliiu. ".3er .cOOKrcm . .. .. .15.. i . . . . Ill-l 7.11-0 1? . ll I w. H. W, Ii.? 7anheiaem?mihu "20 13mm h; 9E . itl.!f1 Ill Ll Ii? . 4.?wa . -- "295qu . 3:Vi. 1-7.111: . HE 3.6.3 .OHN 1/ . n. . 1muqmm?un?h 15m. . a! uqOmiL OH ?Wl F. LI illilel.? 11a. n?u. wmmOm 911.. 3.4m. . . a muf?n. Lu. 9641!: Iliai .19an53 1qu . - Tatmii ?Qty in 360., k0? n.9, .. 1/ A . ?vguthEuUI/x Ir! . i: ,1 .1 9.0? G/Vlj . Rik MMUI LG 30.. 191. U28. DEPARTMENT OF TRANSPORTATION I i 9 - FEDERAL AVIATION ADMINISTRATION I STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MODEL No- TYPE (Airplane, Radio, Helicopter, etc.) NAME OF APPLICANT . L3 Communications 'Raytheon 200 Airplane San Angelo, Texas OF DATA IDENTIFICATION - TITLE ?Drawings l7s002 ANTENNA DOUBLERS INSTALLATION BEECH B200, Rev. 1R dated I 2/9/06, by Threshold Engineering Co. NOTE 1: The above data is approved for structural design aspects only NOTE 2: The alteration Tesults in equivalent structural strength by inspection. PURPOSE OF DATA In support of ?eld Alteration, Raytheon (Beech) King Air 200, 88-493 APPLICABLE REQUIREMENTS (List speci?c sections) FARs 25.305, 25.307ta), 25.603, 25.605, 25.607, 25.609. . CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and. limitations of appointment under Part 183 of the Federat Aviation Regulations, data listed above and on attached sheets numbered sheet 1 have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations "El Recommend approval of these data I (We) Therefore Approve these data A SIGW ATED DESIGNATION I 'DERT-Tioors-sw r157 James A. FAA Form 8110-3 (11-70) Supercedes previous edition (Computer Generated) Egg?ti: a_ CODE -. mun-w: LL LP tam-.01.: .4.st INS TALL N43 1097.104. ALL REPLA CEO FLUSH RIVETS uus?r? .05 mm a TO r345 OF THE omen-m. you; was '09. .. STE 70 55 FLUSH 03?: - HST-1H. mg.- mus-rs 35 RUSH 5,55; - - -..- ?r DouaLEws msma .. LLEC rFx-us .0 05 ms: ??1th 4:35). 0.51.0. 7'29. A5.OUND. 3 Hum.- uoumsns mm morsc m5 cc: .rwc: mm ya. 413,39; snusgcnar: $4 70.00fix 34'5le 4- Ira/?75565? . . . dz gimp 1 I 4 - an); - - a; A 5545::- o: - . - Hrs} A "5 I .1 ?31? :3 5.42 mm: .. THC ds?Ei-Zryr?? ram: 00 I 5'5. 2' 5.2: fur:- 50 [hr-Jet .oh: 7 - 7? Luau? much z: cunt: make 9:47.: my? nun--MATERIAL ENCINEERIH 4 '1 :31" ?mum-u Aft-Tamm' Dau'rril?f??i .NJE 77hr. LA 7:0 rd - 555 COMPANY .1 ".1113: {If 7N5 I71 3mg,wagookxwe?m?aai?igrjr :55. wan/owl I .0 FAA Form 337 (12-88) Form Approved MAJOR REPAIR AND ALTERATION OMB No_ 2120,0025 US Department (Airframe, PoWerplant, Propeller, or Appliance) For FAA Use Only of Transportation Fed erai Aviation Administration Of?ce identification INSTRUCTIONS: 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 BEECH 200 1. Aircraft Serial No. Nationality and Registration Mark BB-498 N6507B Name (As shown on registration certi?cate) Address {As shown on registration certi?cate) United States Customs Service 5020 Meridian Ave. 2. Owner OKLAHOMA CITY, OK 73119 . 3. For FAA Use Only The data identified hereincomplied withtapplicable airworthiness requirements and is Approved only for. the above described aircraft subject to conformity inspection by a person authorized in FAR 43.7. JUN 1 6 200 Date6 FAA inspector? SAT Fey? 4. Unit identi?cation 5. Type Unit Make Model Seriai 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. Communications Vertex Aerospace U.S. Certi?cated Mechanic 8092 HANGAR ROAD Foreign Certi?cated Mechanic RCOR173N SAN ANGELO, TX 76904 Certi?ed Repair Station LIMITED AIRFRAME Manufacturer 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 correctto the best of my knowledge. Date Signature of Authorized individual 10 Dec . 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 l3! APPROVED El REJECTED FAA Standards Manlifacturei inspection Authorization Other (51090100 Inspector BY Repair Station Person Approved by FAA Designee Transport Canada Ainivorthiness Group Certi?cate or Designation No. Date of Approval or Rejection Signature of Authorized individual IiB/p/Bwk- at. imeqs?vQ RCOR173N 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.) 1. N6507B HOURS: have .0 DATE: @13qu INSTALLED AN COMMUNICATIONS AVIONICS SYSTEMS, INC. AWARENESS WARNING SYSTEM (TAWS) IN ACCORDANCE WITH THE OPTIONS PROVIDED BY L-3 COMMUNCIATIONS AVIONICS SYSTEMS. INC.. THIS INSTALLATION IS BASED ON THE BEECH C90 INSTALLATION CERTIFIED UNDER STC-SA01663CH-D. THE SYSTEM IS A STAND-ALONE UNIT WITH INTERFACE TO THE AUDIO SYSTEM AND INSTRUMENT PANEL WARNING ANNUNCIATOR ONLY. THE ANTENNA IS LOCATED THE TOP RIGHT HORIZONAL STABILIZER, PROCESSOR IS MOUNTED TO THE AFT AVIONICS BAY EQUIPMENT RACK. AND THE ANNUNICATOR IS LOCATED ON THE INSTRUMENT PANEL. THE INSTALLATION WAS PERFORMED IN ACCORDANCE WITH FAR SECTION 23.1301 (all) 23.1309 1 2 all 23.1357 23.1359 (all)- 23.1365 23.1431 23.1513 43.9 AC43.13-1B Chapter 11 Section 1 (all) Section 3 Paragraph 11-30. 11-31. 11-32 Sectibn 16 Paragraph 16-205, 16-206 Chapter 12 Section 2 Paragraph 12-5 AC43.13-2A Chapter 2 Paragraph 21, 22. 23 27 Chapter 3 Paragraph 38 44 The manufactures installation manual PIN 009-18651-001 (Rev. C) dated September 15. 2004. The FAA Approved Flight Manual Supplement datedJ 1 6 2mI?ust be available to the pilot during operation of this system. The Pilot?s Guide for the TAWSB100 009-18650-001 (Rev. A) dated 9/01/04 was placed into the aircraft cabin for reference during operation. - THE WEIGHT BALANCE AND LOG BOOK WERE UPDATED TO REFLECT THIS INSTALLATION. Reference dated May 18. 2006 for Instructions for Continuing Airworthiness. Additional Sheets are Attached Communications Vertek Aerospace LLC 8092 HANGAR ROAD Document No. Registration No. N-6507B SAN ANGELO, TEXAS 76904 FAA RCOR173N DATE: May 18, 2006 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FOR: MAKE: BEECH MODEL: 200 REGISTRATION NO: WITH A: L-3 Communications 8100 TAWS Introduction: This major alteration to this aircraft obligates the aircraft operator to include the following maintenance information provided by this document in the owner/operator?s Aircraft Maintenance Manual and the owner/operator?s Aircraft Scheduled Maintenance Program. Description: The Communications 8100 TAWS System consists of a Processor, including its mounting rack, one antennae, a panel mounted annunciator, associated wiring, and any related hardware. The primary function of the system is to acquire signals from the satellite transponders and provide a visual/aural alert for terrain avoidance. I Control and Operation Information: Reference the L-3 Communications 8100 TAWS Pilot?s Guide Publication No.009-18650-001, Revision A, Dated 9/1/2004), and an Approved Airplane Flight Manual Supplement for this installation. Servicing Information: The L-3 Communications 8100 TAWS system is on condition and there is no periodic, preventive, of scheduled maintenance required for continued operation of this system. Maintenance Instructions: The scheduled maintenance tasks required by this modification to be added to the aircraft owner/operator?s approved airplane maintenance program as follows: a) Perform on at least an annual bases, periodic inspection of the equipment rack, equipment mountings, associated wiring, cables, connectors, hardware, antenna and related aircraft structure for integrity, security, wear, chaf?ng, and etc.. Special attention should be given to the aircraft primary structure with regards to fatigue and stress cracking, corrosion, and etc.. Troubleshooting Information: Reference the Communications 8100 TAWS Pilot?s Guide (Publication No.009-18650-001, Revision A, Dated 9/1/2004), and the Approved Airplane Flight Manual Supplement for this installation. Removal and Replacement Information: Reference the Communications 8100 TAWS Pilot?s Guide (Publication No.009-18650-001, Revision A, Dated 9/1/2004), and an Approved Airplane Flight Manual Supplement for this installation. Should it become necessary to remove the unit(s), secure the associated cables and wiring, collar the applicable circuit breakers, placard the aircraft that the unit has been removed, revise the weight balance and the equipment list and make a logbook entry that the unit(s) have been removed, for service refer to 91.213 of Title 14 of the Code of Federal Regulations and or the airplane?s MEL. Diagrams: Not Applicable. PAGE 1 of2 L-3 Communications Vertex Aerospace LLC 8092 HANGAR ROAD Document No. Registration No. N-6507B SAN ANGELO, TEXAS 76904 FAA RCOR173N 9) 10) 11) 12) 13) 14) 15) 16) 17) 18) DATE: May 18. 2006 Special Inspection Requirements: Special inspection requirements are not applicable. Application of Protective Treatments: Application of protective treatments are not applicable. Data: Installation requirements may be found within the accepted industry practices contained within Chapters 11, 15, 16, and AC43.13-2A Chapters 1, and 13. List of Special Tools: No Special Tools required. For Commuter Category Aircraft: Not applicable, this aircraft is not a commuter category aircraft. Recommended Overhaul Periods: There are no additional-overhaul time limitations. Airworthiness Limitations Section: There are no additional airworthiness limitations. Revisions: The Instructions for Continued Airworthiness Checklist (ICA) may be revised by submitting a letter to the local FSDO with a copy of the revised FAA Form 337 and revised ICA. The FAA inspector accepts the change by signing Block 3 and including the following statement: The attached revised new Instruction for Continued Airworthiness date for the above aircraft of component major alteration has been accepted by the FAA, superseding the Instructions for Continued Airworthiness dated Once the revision has been accepted, a maintenance record entry will be made, identifying the revision, its location and date of the FAA Form 337. Assistance: Not applicable. Implementation and Record Keeping: For Part 91 Aircraft) a) For a major alteration performed in accordance with FAA Field Approval policy, the owner/ operator operating under Part 91 is responsible for the ensuring that the ICA is made part of the applicable section 0f91.409 inspection program for their aircraft. This is accomplished when a maintenance entry is made in the aircraft?s maintenance records in accordance with section 43.9. This entry records the major alteration and identifies the original ICA location (cg, Block 8 of FAA Form 33 7, dated along with a inspection maintenance requirements. (I 1 ii 2300 ACCEPTED BY- PAGE 2 of2 1 L-3 COMMUNICATIONS VERTEX AEROSPACE LLC AIRPLANE FLIGHT MANUAL SUPPLEMENT 8092 HANGAR ROAD - FOR BEECH 200 SAN ANGELO, TEXAS 76904 WITH AN AVIONICS 8100 was FAA FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR SERIAL NUMBER: I BB-498 REGISTRATION NUMBER: N65 07B This supplement must be attached to the FAA Approved Airplane Flight Manual. The information contained herein supplements or supersedes the basic Flight Manual only in these areas listed, when the aircraft is modi?ed by installation of a Communications Avionics Systems, Inc. 8l00 Terrain Awareness Warning System Installation. For limitations, procedures and performance data not contained?in this supplement consult the basic Airplane Flight Manual. ,0 [13? 1/4" FAA Approved: if . (2?9 ,75? Michael P. Garvm 5 Title: Aviation Safety Inspector Flight Standards District Off] ce 10100 Reunion Place, Suite #200 San Antonio, Texas 78216?4] l8 FAA APPROVED I. Page 1 DATE: gift; ?3 Revision IR L-3 COMMUNICATIONS VERTEX AEROSPACE LLC 8092 HANGAR RO. AD SAN ANGELO, TEXAS 76904 FAA AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECH 200 EQUIPPED WITH AN 114-3 AVIONICS 8100 TAWS N-6507B LOG 0F REVISIONS REVISION REVISED 3 .I . FAA PAGES DESCRII TIOIN OF REVISION APPROVAL HE h1hjaLllelease FAA APPROVED Page 2 Revision 1R L-3 COMMUNICATIONS VERTEX AEROSPACE LLC AIRPLANE FLIGHT MANUAL. SUPPLEMENT 8092 HANGAR ROAD . . FOR BEECH 200 EQUIPPED SAN ANGELO, TEXAS 76904 WITH AN L-3 AVIONICS 8100 TAVVS FAA LOG OF REVISIONS 2 TABLE OF CONTENTS .. 3 SECTION I - LIMITATIONS .. 4 SECTION 11 - NORMAL PROCEDURES .. 4 1. DESCRIPTION .I 4 2. SYSTEM CONTROLS .. 5 3. ANNUNCIATION EATON OPTION .. 5 4. - ANNUNCIATION - OPTION .-. .. 7 5. SYSTEM SELF TEST .. 9 ADVISORY CALLOUTS ., .. 9 7. USE OF TERRAIN AWARENESS DISPLAY .. 9 SECTION ABNORMAL PROCEDURES .. 10 1. RESPONSE to a TAws WARNING .-. .. 10 2. RESPONSE to a TAws CAUTION .. 10 SECTION IV - EMERGENCY PROCEDURES .. 10 SECTION - PERFORMANCE .. 10 FAA APPROVED) . ?ha? i Page 3 Revision IR L-3 COMMUNICATIONS VERTEX AEROSPACE LLC AIRPLANE FLIGHT MANUALSUPPLEMENT . 8092 HANGAR ROAD . I - FOR SAN ANGELO, TEXAS 76904 WITH AN L-3 AVIONICS 8100 TAWS FAA N-6507B SECTION I LIMITATIONS The L-3 Communications Avionics Systems, Inc. LANDMARKTM TAWSSIOO Terrain Awareness and Warning System Pilot?s Guide, part number 009-] 8650-001, Revision A, dated 09/01/2004, or later revision must be immediately available to the pilot when Operating the aircraft with the LANDMARKTM 00 system. The approved software for the TAWS is version 2.08. NOTE: During Self Test, the TAWSS 00 announces the operating system software level (example 2.08). There is no cockpit verification of the software listed above. Navigation must not be predicated upon the use of the Terrain Awareness Display. The Terrain Awareness Display is intended to serve as a situatiOnal awareness tool only, and may not provide the accuracy and/or fidelity on Which to solely base terrain or obstacle avoidance maneuvering decisions. Pilots are authorized to deviate from their current air traf?c control (ATC) clearance to the extent necessary to comply with a TAWS warning. SECTION II -V NORMAL PROCEDURES 1. DESCRIPTION The LANDMARKTM model TAWSSI 00 is a Class Terrain Awareness and Warning System (TAWS) . that is designed to alert the flight crew of potential controlled ?ight into terrain (CFIT). The TAWS system incorporates the ability to ?look ahead?ofthe aircraft up to 60 seconds by using GPS information coupled with a terrain and obstacle database. The primary component of this warning system is the TAWS Computer. Data is collected from an external WAAS compatible GPS receiver and heading sensor. This data is processed once per second to determine ifthe aircraft is in danger. Visual (if used with a compatible display) and aural alerts advise the pilot of the system?s status and dangerous flight Situations. The TAWS installation consists Of the TAWS Computer, remote OPS sensor, various annunciator- lights/switches, and a fuselage mounted external GPS antenna. Existing aircraft equipment provides magnetic heading and display range inputs. Terrain may be displayed on the Radar indicator or the Electronic Flight Instrument System (EFIS) depending on the aircraft con?guration. (NOTE: This installation is a standalone system meaning it'does net contain provisions for external heading input nor remote display of Terrain Data.) FAA APPROVED I 4 I Page 4 Revision IR . L-3 COMMUNICATIONS VERTEXAEROSPACE LLC 8092 HANGAR ROAD . SAN ANGELO, TEXAS 76904 FAA AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECH 200 EQUIPPED WITH AN L-3 AVIONICS 8100 TAWS N-6507B SECTION 11 - NORMAL PROCEDURES (continued) 2. SYSTEM CONTROLS I The following circuit breakers, located on the right hand circuit breaker panel, provide aircraft circuit protection. - BREAKER LABEL BUS VALUE SYSTEM 'mws 28 voc Essential 2 amp TAWS, Compum . OPS sensor The TAWS is active when electrical power is ON, the system TERR NOT AVAIL annunciator is OFF (TERR for Mid-Continent option), and the following systems are Operational: - TAWS Warning Computer 0 FreeFlight GPS Sensor 3. ANNUNCIATION - EATON OPTION The following annunciators (shown below) incorporate the terrain annunciations and control functions including the optional audio inhibit pushbuttons. All annunciation colors are as described in the Table 1 below. These annunciators are sunlight readable and some have switches incorporated. The annunciators are dimmed via the Avionics Bright/Dim Switch. Refer to the TAWS8100 Pilot?s Guide for additional annunciator information. AUDIO UP TERRAIN . TERR INH ON MUTE FAA APPROVED t. Page 5 DATE: .4 .- Revision IR COMMUNICATIONS VERTEX AEROSPACE LLC 8092 HANGAR ROAD - SAN ANGELO, TEXAS 76904 FAA FOR BEECH 200 EQUIPPED WITH AN AVIONICS SIOU-TAWS N-6507B SECTION II - NORMAL PROCEDURES (continued) AIRPLANE FLIGHT MANUAL SUPPLEMENT ANNUNCIATOR COLOR FUNCTION PULL UP RED a WARNING. The annunciator remains illuminated until the alert condition is eliminated. This annunciator illuminates anytime the TAWSSI issues This annunciator illuminates anytime the TAWSSI 00 issues a CAUTION. The annunciator remains illuminated until the alert condition is eliminated. AMBER This annunciator illuminates when the TAWSS 00 cannot calculate terrain alerts. In all cases, NO TAWSSI 00 cautions or warnings are available. Terrain information may still be displayed on the terrain display depending on the cause of the annunciation. (Refer to the TAWSSIOO Pilot?s Guide for further information.) TERRAIN AMBER Depressing this switch places the TAWSSIOO in self test. The switch illuminates while the test function is active. Self-test in ?ight is inhibited. TST WHITE This switch inhibits terrain alerting when selected. The switch is illuminated when selected to inhibit. Terrain information will still- be available on the terrain display but all aural and annunciation alerts are inhibited. TERR INH ON WHITE This switch inhibits the current alert but resets automatically when the alert condition is resolved. SOC-foot callouts cannot be inhibited with this switch. PUSH ACHON snaTCH TERRAIN AUDIO MUTE TABLE I - EATON ANNUNCIATOR OPTION FAA APPROVED Page 6 DATE: it! Revision IR I AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECH 200 WITH AN L-3 AVIONICS 8100 TAWS N-6507B COMMUNICATIONS VERTEX AEROSPACE LLC 8092 HANGAR ROAD - SAN ANGELO, TEXAS 76904 FAA SECTION 11 - NORMAL PROCEDURES (continued) 4. ANNUNCIATION MID-CONTINENT OPTION (NOTE: This Option not applicable to this installation) The Mid-Continent Instrument Company MD41--1 108 and MD41-1 1 8 Terrain Awareness Control Units (shown below) incorporate the terrain annunciations and control functions except the optional obstacle inhibit and audio inhibit pushbuttons into a single panel mounted unit. All colors areas described in the Table 2 below. The three push buttons are black legends on white switches. These switbhes are dimmed via the Avionics Bright/Dim Switch. Refer tO the TAWSS 1 00 Pilot?s Guide for additional annunciator information. lx?fg?' -- a in}? "Al 13?" Vf? t?aliUul?x FAA APPROVED Page 7 DATngf-it I L- Revision IR L3 COMMUNICATIONS VERTE 8092 HANGAR ROAD TEXAS 76904 FAA AEROSPACE LLC AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECH 200 EQUIPPED WITH AN L-3 AVIONICS 8100 TAWS N-6507B SECTION II - NORMAL PROCEDURES (continued)? ANNUNCIATOR COLOR FUNCTION PULL UP lamp RED This annunciator illuminates anytime the issues a WARNING. The annunciator remains illuminated until the alert condition is eliminated. TERR lamp AMBER This annunciator illuminates anytime the TAWSSIOO issues a The annunciator remains illuminated until the alert condition is eliminated. TERR lamp AMBER This annunciator illuminates when the TAWSSIOO cannot calculate terrain alerts. In all cases, NO cautions or warnings are available. Terrain information may still be displayed on the terrain display depending on the cause of the annunciation. (Refer tothe TAWSS 00 Pilot?s Guide for further information.) I TEST switch WHITE Depressing this switch places the 00 in selftest. Self?test in ?ight is inhibited. SNSR lamp AMBER This annunciator illuminates to indicate the presence of an invalid input. The 00 may still be capable of issuing cautions and warnings, depending on failed input. RDR TERR lamp/switch WHITE This switch when selected illuminates to indicate terrain information is displayed on the radar indicator or El-lSl as selected by the pilot. Only one display may be active at any time. When terrain is diSplayed, weather radar information is not available on the associated display. Depending on the nature of the TAWSSIOO integration, some indicators may display both a TERR and a WX pneumonic when terrain display is selected. Weather radar is not available under this condition. TERR 1N l-lB iamp/switch WHITE This switch inhibits terrain aleIting when selected. The switch is illuminated when selected to inhibit. Terrain information will still be available on the terrain display but all aural and annunciation alerts are inhibited. TABLE 2 - BUTTON OPTION FAA APPROVED a Page 8 DATE: .515 -- Revision IR [oi-3 COMMUNICATIONS VERTEX AEROSPACE LLC 8092 HANGAR ROAD SAN ANGELO, TEXAS 76904 FAA AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECH 200 EQUIPPED WITH AN L-3 AVIONICS 8100 TAWS N-6507B SECTION 11 NORMAL PROCEDURES (continued) 3. FAA APPROVED I SYSTEM SELF TEST Proper operation of the Terrain Awareness Warning System can be verified when the aircraft is on the . ground as follows: - 1. Ensure that none ofthe inhibit annunciations are illuminated, then momentarily push the switch. ix) All of the annunciations illuminate to verify their operation. 3. An aural announcement of the processor software version, database coverage area, database effective date, and the outcome of the'test are announced over the cockpit speaker or headset. 4. if you hear the following ?LandMar/r System est Passed and the TERRAIN annunciation is extinguished, the system is operational. 3. if you hear the following "LandMark System Test Failed? and the annunciation is still illuminated, the system is not operationalQ Refer to the Pilot?s Guide section on ?Respond toil/re SENSOR FAIL or TERR NOTA VAIL ADVISORY CALLOUTS Advisory Callout (MODEQ) The following advisory caliout is provided in this installation: I (occurs at 500 feet AG L) USE OF TERRAIN AWARENESS DISPLAY (NOTE: Terrain Display function is not applicable to this installation) The terrain awareness display is selected by pressing the TERR DISP (RDR TERR for Mid-Continent option) to display terrainon the EFlS/Radar (depends on display type). The display is intended to enhance situational awareness with respect to separation from terrain or obstacles. The display range set I on the display determines the display range ofthe terrain data up to and including the 320 nmi range. If you choose a display range greater than 320 nmi, terrain data is still only displayed out to 320 nmi. The TERRAIN display is not intended to be used for navigation purposes. NOTE: lfthe TAWS issues a caution or warning when the terrain display mode is not selected, the pop up mode will appear on the active display ofthe To go back to the radar mode of the active display ofthe push the TERR DISP (depends on control) switch (RDR TERR for hflid-Continent option). The radar display must not be OFF or in STBY for the auto pop?up feature to function. 1? -. -, Page 9 Revision lR i COMMUNICATIONS VERTEX AEROSPACE LLC AIRPLANE FLIGHT 8092 HANGAR ROAD I . FOR BEECH 200 EQUIPPED SAN ANGELO, TEXAS 76904 WITH AN AVIONICS 8100 TAWS FAA N-6507B SECTION ABNORMAL PROCEDURES 1. RESPONSE to a TAVVS WARNING When an aural UP PULL ERRAIN, PULL UP PULL or i CLE OBSTACLE, PULL UP PULL warning occurs, or a PULL UP light illuminates, the following procedure should be followed: 1. Level the wings,?simultaneously adding maximum power. 2. Smoothly pitch up at a rate of2 to 3 degrees per second towards an initial target pitch attitude of 15 degrees nose up. Adjust pitch attitude to ensure terrain clearance, while i?eSpectiitg stall warning. lftlaps are extended, retract ?aps to the up position. U.) 4; Continue climb at best angle of climb speed (Vx) until terrain clearance is assured. 0 Only vertical maneuvers are recommended unless Operating in VMC or the pilot determines, using all available information and instruments, that a turn, in addition to the vertical escape maneuver, is the safest course of action. 2. RESPONSE to a TAWS CAUTION When an aural RA SINK 00 LOW UTION TERRAIN CAUTION or a OBSTACLE CAUTION alert occurs or TERR annunciator illuminates: 0 Take positive corrective action until the alert ceases. Stop descending, or initiate a climb and/or turn as necessary, Based on analysis of all available instruments and information. NOTE: During operations at certain locations, warning thresholds may be exceeded due to speci?c terrain or operating procedures. During day VFR, these expected warnings may be considered as cautionary and the approach continued. SECTION IV - EMERGENCY PROCEDURES For ditching or other off-airport landings, inhibit terrain alerting by selecting the TERR INH (TERR INHB for Mid?Continent option) switch. The TERR (TERR INHB for Mid-Continent option) lamp will illuminate. SECTION - PERFORMANCE No Change. FAA APPROVED N. Page 10 fl" ?1 i' Revision IR Form Approved MAJOR REPAIR AND ALTERATION 0MB No. 2120-0020 Transportation Federal Aviation M63 ldentif 1 Administration U-SDEPWEW (Airframe, Powerplant, Propeller, or Appliance) ?59 INSTRUCTIONS: 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 such violation (Section 901 Federal Aviation Act 1958) Make Model Beechcraft KA200 1. Aircraft Serial No. Nationality and Registration Mark 834% N6507B Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) 2_ Owner us CUSTOMS SERVICE 5020 s. Meridian Ave Oklahoma City. OK 73119-5105 Of?ce of Patrol 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. L3 Com Vertex Aerosoace 2701 Kirtland Dr. SE Bldo. 291 Kirtland-Air Force Base Albuoueroue. NM 87117 U.S. Certi?cated Mechanic . R3R208 Foreign Certi?cated Mechanic 0 Certi?cated Repair Station Manufacturer Limited Airframe 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. Federai Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. - Date . Signature of Authorized Individual 05/04/05 Gus Barreda 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 APPROVED REJECTED FAA It Standards Manufacturer Inspection Authorization Other (Specrijl) Inspector BY FAA Designee Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection Certi?cate or Signature of Authorized Individual, 05/04/05 Designation No. CRS: R3R2080N Marty C'ayton FAA Form 337 (12-88) 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 confonnity with the applicable airworthiness requirements. 8. Description of Work Accomplished DATE: 05/04/05 N6507B SN: BB-498 Total Time: 10576.5 Installation of approved ?eld repair 8100-9 for cracked aft spar stiffener on aft side of rear spar at approx BL 0.00. 1. Installed repair stiffener pro?led to match existing stiffener IAW Beech ?eld repair FR-KA-01619, Rev 2. a) Made from .071 thick 2024-T3 Alclad. b) Bend radius .31 c) Installed using CR3213-5 or CR3213-6 blind rivets. 2. Maintenance instructions for continued aimorthiness: None. 3. Weight and balance change negligible. (if more space is required, attach additional sheets. with aircraft nationality and registration mark- and date work completed.) END Additional Sheets Are Attached U.S.GPO: 1989-0-663-1 71 A us. DEPARTMENT OF TRANSPORTATION FAA Project No. FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL No. TYPE (Airplane, Radio. HeIrcopIer, etc.) NAME OF APPLICANTIAUTHORIZATION NO. Raytheon Aircraft Company Raytheon 200 AIrplane SUBMITTAL LETTER NO. 940-2005-05-023 LIST OF DATA IDENTIFICATION TITLE Field Repair ?Field Repair - Crack In Stiffener. Aft Side Of Rear Spar At BL 0.00" FR-KA-O1 619, Rev 2 Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering design data. 2} This approval is valid only for model 200 aircraft, serial numbers 88-493. 88-482. 88?498 and Is issued in support of a repair of these subject aircraft. PURPOSE OF DATA In support of Field Repair Rev 2 (List speci?c sections) 14 CFR Part 23.25, 23.303. 23.601, 23.603Ia), 23.607. 23.609 23.611; 23.613. 23.615 I CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations of authorization under 14 CFR. data iisted above have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed. Recommend approval of these data I Therefore Approve these data OF AUTHORIZED NAME CLASSIFICATIONS) DATE Larry Young Structures Aprii 29. 2005 {/7351} xi 94rd? ,f y/ 2 I FAA Form 8100-9 (2-02) REVISIONS APPROVED 6 THIS REPAIR IS BASED ON INFORMATION PROVIDED BY L-3 COMMUNICATIONS AEROSPACE SAN ANGELO, TX, IN DAMAGE REPORT DATED 04/22/05 AND 4/28/05. (REF DQ KA66471 AND KA66503) - DATE 04/23/05 DESCRIPTION ADDED TWO SERIAL REV ?2 RRB GENERAL NOTES 1. WEIGHT AND BALANCE CHANGE NEGLIGIBLE. 2. ALL DIMENSIONS ARE IN INCHES UNLESS OTHERWISE SPECIFIED. 3. EMBODIMENT OF THIS FIELD REPAIR MUST BE RECORDED IN THE AIRCRAFT LOG BOOK STATING THIS FIELD REPAIR NUMBER AND REVISION. PROCEDURE 1. CAREFULLY DRILL OUT THE RIVETS WHICH ATTACH THE DAMAGED STIFFENER TO THE REAR SPAR. NOTE THAT THE RIVET TAILS WILL FALL INTO A BLIND AREA AND IT IS NOT POSSIBLE TO RETRIEVE THE RIVET TAILS AFTER DRILLING. IT IS PERMISSIBLE TO LEAVE THE RIVET TAILS LOOSE IN THIS AREA. RETAIN THE DRILLED OFF STIFFENER TO USE A TEMPLATE FOR MAKING A NEW STIFFENER. 2. MAKE A REPAIR STIFFENER, PROFILE TO MATCH EXISTING STIFFENER. MAKE FROM .071 THICK, 2024-T3 ALCLAD PER BEND RADIUS .31. 3. DRILL HOLES FOR TO MATCH EXISTING LOCATIONS. HOLES FOR 5/32 RIVETS ARE TO BE .160 .164 DIA, HOLES FOR 6/32 RIVETS ARE TO BE .192 .196 DIAMETER. MAINTAIN A MINIMUM OF 2D EDGE DISTANCE ON ALL FASTENER LOCATIONS. 4. DEBURR ALL SHARP EDGES. 5. PROTECT ALL BARE METAL WITH CHEM FILM PER MIL-06541, CLASS 1A, PRIME WITH ONE COAT OF TYPE 1, CLASS PRIMER. 6. INSTALL REPAIR STIFFENER USING CR3213-5 BLIND RIVETS TO MATCH ORIGINAL SIZES. LENGTH AS REQUIRED. APPLICABLE TO AIRCRAFT SIN 88-493, 88-482, 88-498 FIELD SERVICE NOTE THIS REPAIR DRAWING HAS BEEN PREPARED FOR A SPECIFIC REPAIR TO A SPECIFIC AIRCRAFT OR COMPONENT ON THE BASIS OF INFORMATION SUPPLIED TO RAYTHEON AIRCRAFT COMPANY BY THE PERSON RESPONSIBLE FOR ARRANGING THE REPAIR OR HIS AGENT. THE USE OF THE DRAWING ON ANY OTHER AIRCRAFT OR COMPONENT MAY LEAD TO AN UNSAFE REPAIR AND THEREFORE THE DRAWING IS NOT TO BE USED FOR ANY OTHER PURPOSE THAN FOR WHICH IT WAS ORIGINALLY SUPPLIED WITHOUT THE WRITTEN APPROVAL OF RAYTHEON AIRCRAFT COMPANY. - ?0 RAYTHEON AIRCRAFT COMPANY CHKR LEAD ENGR S. TALMAN 4123105 FIELD RE STRUCT YOUNG CRACK IN STIFFENER, PROD AFT SIDE OF REAR SPAR AT APPROX BL 0.00 SPECIALIST SIZE CAGE CODE DWGNO REV RAG APPD S. TALMAN A 70898 FR-KA-01519 2 SCALE SHEET CUSTOMER APPD NONE 1 OF 1 980-32552 Reference E03047 Revised: 0412002 DOC 00001 171 33 R1 V1 . - . . -- Form Approved MAJOR REPAIR AND ALTERATION OMB No. 212043020 aim? . (Airframe, Powerplant, Propeller, or Appliance) 2; ce en ca 0 INSTRUCTIONS: 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 such violation (Section 901 Federal Aviation Act 1958) Make Model Beech 200 1. Aircraft Serial No. Nationality and Registration Mark 88-498 N6507B Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) 2, Owner U.S. CUSTOMS SERVICE 5020 S. Meridian AVE Of?ce of Patrol Oklahoma City. OK 73119-5105 3. For FAA Use Only ?the date identitieo herein complies with the appiicable airworthiness requirements and is approve described aircraft, subject to conformi peBLu 13 11; {asceeccwm 3? 3' ESSAEE 90'380009'2 15 - LEFT FUEL now 3 ?83m; INDICATDR 0.. 3 P3 4 a rem?30 COLLINS f, BUUTSTRAP 5 F7A32wm HEIDK aevac HEADING mm momma I PE SPLICE mum: Am 9 SYSTEM PRHBE SHAWN an. we. nAr PROBE 6812201 JUN-29-98 MON 10 . A MEMORANDUM TO FILE FOLDER HAS BEEN IMAGED This aircraft record was sent to imaging without ever having been a microfiche. It went directly to imaging in its paper form. The pages on the registration side of the record are not numbered and family groupings are not identified. In the imaging system, the registration?side will be identified as a single document under the Document Type of ZRL, Converted Registration/Lien, the airworthiness side under ZAW, Converted Airworthiness, and the suspense documents are identified under 288. Documents below this memorandum have been imaged and cannot be moved, removed, or changed. . UNITED STATES A DEPARTMENT TRANSPORTATION FEDERAL AVIATION A SPECIAL AIRWORTHINESS CERTIFICATE - PURPOSE Shaw 3 I I NAME FACTUFIER ADDRESS "r FLIGHT FROM 31.BUILDER X7 MODEL-W 26% DATE OF ISSUANCE M375, Bee. 3. 1982 EV PART OF THIS CERTIFICATE SIGNA A EP IGNATION OR OFFICE NO. 1 axe-mm Any alteration, reproduction or misuse of this certificate may be punishable by a ?ne 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 8130-7 {7-79) USE: PREVIOUS EDITION SEEREVERSE SIDE This airwort certi?cate is issued under the .authority of the ral Aviation Act of 1958 and th era! Aviation Regulations (FAR). This airworthiness certificate authorizes the manufacturer named on the reverse side to con-_ duct production ?ight tests, and only production ?ight tests, of aircraft registered in his name. No person may conduct production ?ight tests under this certificate: (1) Carryingper- sons or property for compensation or hire; and/org) Carrying persons not essential to the purpose of the ?ight. This airworthiness certi?cate authorizes the ?ight speci?ed on the reverse side for the pur- pose shown in Block A. This airworthiness Certi?cate 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 air- . worthiness 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 with conditions and limitations which may be prescribed by the Administrator as part of this over any foreign country with- out the special permission of that country. Unless sooner surrendered, suspended, or revoked, this airworthiness certi?cate is effective duration and under the conditions prescribed in FAR Part 21, Section 21.181 or . DEPARTMENT OF TRANSPORTATIOLEFEDE AVIATION ADMINISTRATJO ?4 ANDARD CERTI ATE 1 NATIONALITY AND MANUFACTURER ANS MODEL 3 AIRC ERIAL 4 CATEGORY REGISTRATION MARKS NUMBER 0 I eech A5. N55073 re ft- Cez?ym BB: 98 mutual 5 AUTHORITY AND BASIS FOR ISSUANCE . . Thus anrwo?hmess certi?cate IS Issued pur?uant to the Federal AwghonAct of 1958 and cert-hes that. as at the date of Issuan'ce. the aircraft to Issued has been mspecteb'and lound to conform to the type certi?cate the._relor. to be In condmon Ior?sate operatton. and has been shown to meet the requrrements oI comprehensive and detailed atmonhmess code as prowded by Annex 8 to the Convention on International Cfvil Athahon. except as noted harem, Excepttons. A a 6 TERMS AND CONDITIONS Unless sooner surrenderedhsuspended. revoked. or a teri-mnatton date IS otherwuse by the thus IS etfectwe as long as the mamtenance. preventatwe matntenance. and alterations are performed In accordance wuth Parts21. 43.and 91 olthe Feder lAWnRegulattons. as appropnate.and the atrcratt IS registered theUntted States 16 DATE OF ISSUANCE DESIGNATION NUMBER 311.19%; 1 5mm}? 5 Any alteration. reproductton. or mtsuse of may be punrsh-abte Jy?a fme not exceeding 51 .000_or Imprisonment not exceedthga years. or both THIS CERTIFICATE MUST BE DISPLAYED IN THE FICRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS FAA Form 31 00-2 (3.82, :2 us. GOVERNMENT PRINTING OFFICE: 1991 - sea-223 4 - UNITED STATES OF AMERICA DARD Atnww?gs can DEPARTMENT OF AVIATION ADMINISTRATION 2. MANUFACTURER AN date of is race. the curcra I - -- issued; - \d found/,1 therefor, to in condition pr?safe operati - -v a" comprehensive - detailed irwd?hine -- - A Aviation, except a noted 11 'ein. Exceptions: 6. TERMS AND CON - UnIess soon surrendered, sus this airwort ?ness certificate is' performed in - ordance with aircraft is registe - in the Mainte . ce, prev?ensoh he Federal Ra is at \ey?stq . - . N23i07 corpm s. AUTHORITY AND - xx. his air - - Icate a- - iation Ac as of the - dministrator, aintenance, - - alterations are - Iqtiqijg I ions, as appropriate, and the DATE OF ISSUANCE DESIGNATION NUMBER Replacement 1 1?19?82 +1 1 Any alteration, reproduction, or misuse of this certi?cate may 5e punishable by a fine not exceeding $1,000, or im- prisonment not exceeding 3 years, or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORD- ANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. FAA Form 8100-2 (7-67) FORMERLY FAA FORM 1362 REPLACED 12-15-87 UNITED STATES OF AMERICA AVIATION AD INISTRATION I NATIONALITY AND 2. MANUFACTURER REGISTRATION MARKS N6040Y suntan GEHTIF TE AIRCRAFT SERIAL 4. CATEGORY NUMBER NORMAL 5. AUTHORITY AND BASIS FOR ISSU ?c This airworthiness certi?cate 5 "s uecl pursu date of issuance. the aircr I therefor, to be in conditio comprehensive and detaile Ia Aviation, except as noted I Exceptions: . I to hich i - ?3 Mafe'o I irworthi at.- reinTERMS AND CONDITIO Unless sooner surren ered, this airworthiness certi?cat performed in accordance aircraft is registered in the date is oth%' /established by the Administrator, tenance, preventat' maintenance. and alterations are ?we of 5-. f- and certi?es that, as of the I a 91;? conform to the type certi?cate . me - requirements of the applicable ?anention on International Civil W/?ulations, as appropriate, and the DATE OF ISSUANCE April 11, 1979 e553; as long A 143, and I of i Federal A DESIGNATION NUMBER DOA, Any alteration, reproduction, or misuse of this certi?cate may be punishable by a fine not exceeding $1,000, or ifn- prisonment not exceeding 3 years, or bath. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORD- ANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. {7-871 can anus. .aen . .. . hits-I .. 2? NOV 193% I . a Form Approved Budget Bureau NO. 04-R0058 or typ'e. Do not write in shaded areas; these DEPARTMENT Submit original only to an authorized FAA FEDERAL AVIATION ADMINISTRATION Representative. If a ditIonal space is required. use an attachment. APPLICATION FOR AIRWORTHINESS CERTIFICATE 5351:5853} ?ight Permits COmP'etesec?ions and VI or V1135 I. REGISTRATION MARK 2. AIRCRAFT NAME (make) 3. AIRCRAFT MODEL DESIGNATION 4. YR. MFG. FAA CODING N604OY Beechcraft King Air 200 1978 //571 Q2425 5. AIRCRAFT SERIAL NO. 6. ENGINE NAME (make) 7. ENGINE MODEL DESIGNATION 3, 1313?498 Pratt as Whitney PISA-41 07?? a. NTMBER OF ENGINES 9. PROPELLER NAME (make) Io. PROPELLER MODEL DESIGNATION n. Amen" .5 I 2 Hartzell I IMPORT APPLICATION IS HEREBY MADE FOR: (Cluck applicable (ft-WI) A I STANDARD AIRWORTHINESS CERT. (Indicate category I INORMAL I IUTILITY I I ITRANSPORTI IGLIDER I IBALLOON X. SPECIAL AIRWORTHINESS CERTIFICATE (Client appropriate item!) 2 LIMITED DESCRIPTION I. CLASS I CLASS ll 5 PROVISIONAL (Indicate clan) AGRICULTURE a. PEST CONTROL AERIAL SURVEYING 3 ?g??nsmc, FOREST Wild life (emanation) 5 PATROLLING . 5 WEATHER CONTROL OTHER I Spa-115' RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION RACING 5 CREW TRAINING 6 MKT. SURVEY TO snow COMPLIANCE WITH FAR FERRY FLIGHT FOR REPAIRS, ALTERATIONS, MAINTENANCE OR STORAGE EVACUATE FROM AREA OF IMPENDING DANGER OPERATION IN EXCESS OF MAX. CERTIFICATED TAKE-OFF WEIGHT DELIVERING OR EXPORT L5 I IPRODUCTION FLIGHT TESTING MULTIPLE AIRWORTHINESS CERTIFICATE (Cbeck appropriate Restrirled Operation and Standard or Limited an applicable abate) A. REGISTERED OWNER (Afr/yawn an Certi?cate of Aircraft Registration) IF DEALER, CHECK HERE I NAME ADDRESS U.S. Customs Service Washington, D.C. B. AIRCRAFT CERTIFICATION BASIS (Cbeck applicable block: and complete item: 4: indicated) AIRCRAFT SPECIFICATION OR TYPE CERTIFICATION DATA SHEET (Cur Na. AIRWORTHINESS DIRECTIVES (Cbm? rfull romp/1rd Hub and and ReI-rrian No.) ?4 later! ,1 No.) Wig. AIRCRAFT Gilt/5:13: N001) SUPPLEMENTAL TYPE CERTFICATE (List number of curb STC mrwpomml) we We C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS I CHECK IF RECORDS TOTAL AIRFRAME HOURS-W EXPERIMENTAL boar: ?an-n mm luu Irma! COMPLIANCE WITH 14 3 or remuml RESTRICTED (Indicate aperamn?) be conducted 4 )2 EXPERIMENTAL op:mnon(:} to b: cam/mud) II. CERTIFICATION REQUESTED SPECIAL FLIGHT PERMIT (Imluwlr 8 oprmnon to be conducted their complete Semen Vl or t? on m: rule) CERTIFICATION D. hereby certify that I am the owner (or his agent) of the aircraft described above; that the aircraft is registered with the Federal Aviation? Administration in accordance with Secrion 501 the Federal Aviation Act of 58. and applicable Federal Aviation Regula? tions; and thatI the aircraft has been inspeaed and is airworthy and eligible for the airwo mess certi?cate requested- DATE OF APPLICAEION NAME AND TITLE {Prmt or type) SIGNAT RE /4 Oct . 53, 1982 James . Morris Jr. Presiden A. THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY: (O?plm n5}: Tet-tic?? only applies) FAR PART l2] OR 127 CERTIFICATE HOLDER (Cue CERTIFICATED MECHANIC CERTIFICATED (Gut 2 Certi?cate No. 3 Crm?rak Na.) 6 Na.) AIRCRAFT MANUFACTURER (GM: Nam: af?rm) 5 DATE TITLE 7 SIGNATURE VERIFICATION AGENCY IV. INSPECTION (CheCk ALL applicable HOCRSI I find that the aircraft described in Section I or VII meets the requirements for: gThe certification requested, or Amendment or modification OF its current airworthiness certificate. Inspection for a special flight permit under Section VII was conducted by: FAA Inspector; certificate holder under 127, or FAR I45. DATE DISTRICT OFFICE SIGNATURE AND NO. FAA INSPECT SIGNATURE 4 I 7/ Ma? MKovm/bw. A a? 4 mm (7.70; g? FAA REPRESENTATIVE CERTIFICATION V. ((2)417! A. MANUFACTURER Va 42? NAME AD DRESS B. PRODUCTION BASIS (Cluck applicable item) PRODUCTION CERTIFICATE (Givepradurtian cer?'?cate number) . - TYPE CERTIFICATE ONLY APPROVED PRODUCTION INSPECTION SYSTEM FLIGHT TESTING VI. PRODUCTION C. GIVE QUANTITY OF CERTIFICATES REQUIRED FOR OPERATING NEEDS: DATE OF APPLICATION NAME AND TITLE (Print or {We} SIGNATURE A. DESCRIPTION OF AIRCRAFT REGISTERED OWNER ADDRESS BUILDER (Malt) MODEL . - SERIAL NUMJER - REGISTRATION MARK "?le I. .1, 3. DESCRIPTION or mom FROM TO VIA DEPARTURE DATE DURATION C. CREW REQUIRED TO OPERATE TI-IE AIRCRAFT AND ITS EQUIPMENT I [mm Ico-?mor I INAVIGATOR IOTHER (Spaifj) D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS: a: E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION (Us: attachment "a VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT TEST IF. hereby certify that I am the registered owner (or his agent) of the aircraft described above; that'the aircraft is registeredl 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 airwoth for the ?ight described. DATE NAME AND TITLE (Print or type} SIGNATURE - A._Operating Limitations and Markings in Compliance with FAR - G. Statement of Conformity, FAA Form 317 (Atta?: when required) 91-3] 0? APPUCOPIP H. Foreign Airworthiness Certi?cation for Import Aircraft (Attack 19le .3. Current Operating Limitations Attached required) . C. Data, Drawings, Photographs, etc. (Attach when required I. Previous Airworthiness Certi?cate Issued in Accordance with D. Current Weight and Balance Information'AvailohIe in Aircraft FAR MAR (Original (FAA use only) DOCUMENTATION AIRWORTHINESS E. Moior Repair and Aiteration, FAA 337 {Attach when required) J. Current Airworthine? Certi?cate Issued in Accordance with y: F. TEE Inspeclian Recorded in Aircraft Records FAR ?i q/ 3 {Cop} attached) 1 s' I GD ERNMENT PRINTING OFFICE 1980?673?026?63 "4 i FMAcnm TELLS. 1. no ?3 7-.- .. . .2 ,4 Builder: Beechcraft. Serial No.: BB-498 Model: 200 - Reg. No.: These limitations are a part of Special Airworthiness Certificate: Show compliance with regulations . 1 ,"'dated Oct. 5, 1982 ,3 issued to Flight Test ELIE systems installation i a 1. No person'may Operate this.aircraft for other than the purpose(s) of to show compliance with regulations - to accomplish the test outlined in Aviation Ind. Inc. program letter, dated Obt. 5, 1982 describing compliance with FAR 2l,l93(d) and made available to the pilot in the aircraft. Additionally, this aircraft shall be operated in accordance.with applicable air traffic and-general operating rules of FAR 91, and-all additional limitations herein prescribed under the provisions of FAR 3 no? - was". IT. A mug? - a-h er 7-4- .. ,u .. mzamaypuu.MAM a 2. All flights shall be conducted Within the geographical area described as follows: 200 nautical mile radius of St.Charles County Airport, St.Charles, Mo. 3. No operations, including takeoffs and over densely populated areas or in congested airways, except th takeoffs an 'landings authorized, 8-3 _on sci-?ve runways and airports I I ent flight in accordance 4. Unless appropriatel equipped for n"-t or with FAR 91.33, this aircr ft must be Opera . .) . . hJ-?person may be arried in the aircra duri f.ight unless that person is a required flight crewmembe and/or person(s) required 0 record flight test data that ?Eannot be practicably rec rded byja req red flight crewmember. 6. This aircraft shal contain th Jplacard ,?1istings, and instrument markings required by EAR 91.31(e) r?operatio inclu - ,none and/or Flight uaauhi Supple ?nt no 7. This aircraft is'pr?hi' te from_acrobatic.flight; that is, an intentional manuever inVolving an abrupt change in the aircraft's attitude, an abnormal attitude, or abnormal acceleration not necessary for normal flight. )4 8. If aircraft; engine__or propeller operating limitations are exceeded, an': a . i . anyh?; I: aPPrOPrlate bewmadefin the historical records. an.? 9. Any major change to this aircraft, as defined by FAR 21.93, invalidates the special airworthiness certificate issued for this aircraft. 5? 10. No person may operate this aircraft for carrying or property for l, compensation or hire?0-41 A .5 u; 143- a 11. The person operating this aircraft shall advise.each person carried of the experimental nature of this aircraft. II 9 12. The aircraft shall bear inord near each entrance to the cabin Oct. 5, 1982 MKC-MIDO Date of Issue FAA Representative Designation MET?i?v-?v-j?r- . i :35 . .tit; 13? at. .2. .. 1.51 .l r, It. 3 qr?l I . .u 1:06 .J. ! 1yul.unrl q?l??j?v?gj.?f.2.. )if; .Flvl. Ill . 211?? advromrth?nu?ahjlig. ?triumuu-11?Ililn?var I.- ?ll-ll, Itvitiull?nisiyo?ll vile-fr.- TL ~1313:, 10.. Tar..va . .. st: lu.l! .51 US c: ?cnsoortottao Feature! Avioncn . MAJOR REPAIR AND (Airframe, Powerplant, Propeller, or Appliance) - Form Approved - OMB No. 2120-3020 For FAA Use Only Office Identificia?on 5w Ci for each such violation (Section so: firs'g reoeral Aviation Act of 1955 . . Feiiure to resort can resuit in acivil penalty no 4-5 - use: Print ortype all entries. See FAR 43.9. FAR 43 Accendix 5. ant: AC 43.94 (or subsequent revision thereof) forinstruczions and disposition of this form. This resort is required bylaw (49 U.S.C.1421 sec 31 .000 Make Model . . BEECHCRAFT 200 1. Atrc.att . . . Serial No. Nationality and Mark 33?498 5-: in 1? i. .mN: 650713711; :r can aviat?? Name (As shown on registration certificate,' Acoress {As snown on regisrrati'on certificate) 2 Owner U.S. CUSTOMS SERVICE 1301 CONSTITUTION AVE 5411 OFFICE OF TACTICAL WASHINGTON DC, 20229 AIR OPERATIONS DIVISION 3. For FAA Use Only HEJJIUMEI ii?lfi .4314 .I :ijsqf't?t; r?t .1. ti." .1 if}? Jamaal a? if?? it?" $1011? mail-'wa Elli} . 37"? . *t "T?it' 4. Unit identification 5. Type .tlf l? 3sz r' r" 7 ?2 Unit itrlaita'LEU 0L . 1 f, odeloq, I Se .aI?Noi f? Reoafir Alteration iki Hi: :fix iLt i iU??Hild 'idrhh?? if . s. ?12. ?4';th .1 ?ltl?v. .i'i ?33 . af?i tit, $51311" its. HimEMU (?241" :11: T153731: Hf ,i ?stTf?t?yzw. at"; (113': EH ?1 5 "T?X?fif 3:31;. 4 mi) . 23154;; 'Wl' Huh} FEGFELLET. maria-Max V'I-s-w wt! - vu?WI?b- Type APPLIANCE . Manutacturer 5. Conformity Statement A. Agency's Name and Address a. Kind of Agencv C. Certificate No THOMAS DUFRESNE 8092 HANGAR RD. SAN ANGELO, TX 76904 1/ us. Certificates: Mechanic Foreign Certificated Mecnanic Certificated Reoair Station Manufacturer 364549516 D. I certify that the repairand/or aiteration made to the unit(s) identified in item above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date W- Authoriz- vi T. Aocroval for Return To service 4 Pursuant to the authority given persons speci?ed below. the unit identified in item 4 was inspected in the manner prescribed by the BY Administrator of the Federal Aviation Administration and is WPROVSD Ci - - . Other (Scecify) a? Manufacmrer I l/hnspection Authorization . i . . 'Person A rover? FAA Desngnee Inepair Station lcanada grasp or Rejection or Ignat esignation go 3&4; 4376 we? FAA Form 337 nz-aa) NOTXCE Weight and balance or operating iirnitation changes shall be entered in the appropriate aircraft record. An altera ticn must be comoatibie. with all previous alterations to assure continued conformity with the applicable airworthiness requirements. I 8. Description of Work Acoumpiiehec (It more space is required. attach additional sheets. identify with aircraft nationality and registration mark and date work completed. E0: 6507B HOURS 7311.8? . 8?t~33 EE.EA EIA Ina; EEDTEUD BETH-J 33$ 2501?"? T?ftf'lifl?'?it 1"11?13 JHITDAT 3314110 INA . .c 1. REMOVED RDR 1400 RADAR SYSTEM AND INSTALLED NEW RDR 2000 RADAR SYSTEM. 2. TRIS INSTALLATION IS PER THE MANUFACTURS INSTALL MANUAL NUMBER 006-00643?-0003, REV 3, FEB. 1995. 3; GUIDE FOR THE RDR 2000 PART-NUMBER 006?08755-0001 WAS PLACED INTO THE AIRCRAFT. 4. A LOG BOOK ENTRY WAS MADE, THE AIRCRAFT WEIGHT WAS CHANGED, 1 AND THE EQUIPMENT LIST UPDATED. 5. A FUNCTIONAL TEST OF THE WORK DESCRIBED IN THIS 337 WAS PERFORMED, THE OPERATION WAS SATISFACTORY, AND DID NOT ADVERSELY AFFECT THE EXISTING COMPONENTS SYSTEMS IN THE AIRCRAFT3313133133 Evit?j?ct?ld.--.-- 1.53531 J. Additional Sheets Are Attached T1 uni Adamant-arm ?3 MAJOR REFAIR AND ALTEEATION .nrenr . .. (Amtame, Pewerpiant, rcpeiier, or Accuance) Rem Awe-non . Form OMB No. 2129?2620 For FAA Use Only for eacn such violation (Section 3-2-1 Aviatfcn Ac: unu- INSTRUCTECNS: Print ortypeeii entries. See PAP. FAR dSAppendix E. encAC 433-1 (orsu'csecuent rewsnon therect} tor instructions and discoszticn of this form. This resort is required by law {49 U.S.C.1421). Feiiure to resort can res ?ci eitin acivil penalty 3. 00 Mm BEECHCRAFT ?2350 1. Aircm? 2"13! V0 ?3 Mark I - I 5411 have been made in accordance with the requirements of Part 43 of the US. Federal Aviation .3. furnished herein is true and correct to the best of my knowledge. eguiations and that the i t'crmation 2. Owner OFFICEOF TACTICAL ENFORCEMENT WASHINGTON DC, 20229 -AIR OPERATIONS DIVISION 31'} it." . I 3?325-221 I- 11? Unit ide?nti?cation' - 5. Tyne Unit Meite . 1 . - ,t 1: :53 ai?Modeig .6, 3-, SeriavNo. Repair Alteration . .. u- 3."ll AIEFEAME .- - a e? {As desc?beo' i_n (text; 1 accve} - . a 3. Jud 2.221142? .. .153: It)? . o't. 1 ,r J. FCWEFPLANT - r445" {if ?35 ?332' I .-s "Nia- . - e15 - .. FQCFE: LEE . 7 ?9 2 73-. 31? at}? ?ype" AFGUANCE . Manuracturer - S. Canton-.1th Statement A. Aqencv's Name and Address 1 E. Kind of Agencv C. Certificate No. THOMAS DUFRESNE Mechanic 8092 HANGAR RD. Foreign Certi?cated Mechanic 364549516 SAN TX 76904 Certi?cated Recair Station Manufacturer 0. I certify th tthe reeair and/oreiteration made to the unit(s) identi?ed in item dabove and described on the reverse orettechments hereto Date . f? uthorized indivi . 7. Return Service Mei-twee CE REJEUTES Pursuant to the authority given persons speci?ed beicw. the unit identi?ed in item 4 was insceoted in the manner prescribed by the Administretcr cf the Federal Avi-tfcn Administration an: is - Ctherr AA Fit. Standards A Inscecmr . nienmacdirer nspeci.on_ EY A .. . . . erson t: raved trans-'C't FAA Cesrghee [necatr Station I lcanada Aig?onmn??ss Grogg' kin-luau Q-ar-I'fy) Date of Apcrc'zei or Re;ec:ion Certificate or Designation No. 02? fr 91 FAA Form 337' ?2-38) w-w NOTECE Weight and Science cr operating itmitatfon changes shat! be entered in the appropriate aircraft reccrd. An alters must be ccmcatibie WI alterations to assure continued conformity with the applicable airworthinqss . 911:8. S. Besc?pticn cf Worx Accomplisnec (If more space required, attach additiona! Sheets. {den-git: with aircraft naticnal?tj and :egistraticn mark and date work Dr- 7?2: [91105073 FEEROARYS 9; .HOURS 30116.0 1. - T- - I REMOVED RDR ?14?00 INSTALLED NEE Rm 2000 RADAR-SYSTEM. - - - INSTAELATIOR313 PER INSTALL MANUAI. :3 DOS-0004370003, I995. GUIDE FOR THE RDR NUMBER 1 THE AIRCRAET. 43 A LOG MADE, THE AIRCRAFT WEIGHTERAS CHANGED, - LIST UPDATED. 3 ATEUNCTIONAEITEST OE THE WORK DESCRIBED IN THIS 337 WAS PERFORMED, OPERATION W139 SATISFACTORY, AND ADVERSELY - AFFECT THE EXISTING- COMPORERTS AND SYSTEMS IN THE AIRCRAFT. it 1 A - . rim A9- TM: Size 9168 .1,th i g" 2' 3T 2-9131.4333, As??f??lhi? ?Awe AW3 - - a; F806 M..- A :2 . L. DPS .JEYEI ?195:101.] 5 (mm) I. "r D?AdciticynaISheets'A're Attached A . 4.9.. . MAJOR REPAIR AND ALTERATION Form Approved OMB No. 2120-0020 US Department . . FA OlTronspo?onon - (Airframe, Powerplant, Propeller, or Appliance) Off 8 Idgt'mcaggfe Federal Aviation . Administration 3/7 INSTRUCTIONS: 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 such violation (Section 901 Federal Aviation Act of 1958). Make Model 1 AI BEECHCRAFT 200 KING AIR mm Serial No. Nationality and Registration Mark 33?498 A ?65073 Name (As shown on registration certificate) Address (As shown on registration certificate) U.S. CUSTOMS SERVICE 1301 CONSTITUTION AVE. OFFICE OF PATROL WASHINGTON D.C. 20229 3. For FAA Use Only 4. Unit identification 5. Type Unit Make Model Serial No. Repair Alteration AIHFRAME WW (AS described in itemgjLaggyeLmW XX . as as ??es as! sci?? a? \u u2?s U35 . POWERPLANT ?Ed? um? ?49" Dayle!" 2W4 5W3 um 1! - 2A1 PROPELLER DEC 8 1994 a r-I-hr\ L5 UVV Type 101 102 103 104 303 mm awz APPLIANCE Manufacturer 1w2 3W3 3W4 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. certificated Mechanic 8092 HANGAR RD Foreign Certificated Mechanic SAN ANGELO TEXAS 76q04 certificated Repair Station SW9621K Manufacturer-nv??H?mn i ?and - Hip? D. I certify that the repair and/or alteration made to the unit(s) identified 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 U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date 12/ 06/ 94 RAYMOND BRAZIEI. Signature of Authorized Individual 7. Approval for Return To Service Pursuant to the authority given persons specified below. the unit identified in item 4 was inspected in the manner prescribed by the BY Canada Airworthiness Group Administrator of the Federal Aviation Administration and is El APPROVED El REJECTED Other 8 ec'f rrgge?i?tandards Manufacturer inspection Authorization FAA Designee XX Repair Station Person Approved by Transport Date of Approval or Rejection 12/06/94 Certificate or Designation No. KARLW. BENNETT Signature of Authorized Individual baht? FAA Form 337 (12-38) . 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. 5 8. Description of Work Accomplished . (ll more space is required, attach additional sheets. identity with aircraft nationality and registration mark and date work completed.) 1165073 SIN: 33?498 HRS 6788 .4 BEECHCRAFT FACTORY INSTALLED RADOME PIN: 101-410095-9 AND INSTALLED NORTON RADOME, PIN: SIN: 273, IN ACCORDANCE WITH STC - AND. NORTON COHPANY DRAWING REVISION a WEIGHT AND BALANCE RECORDS WERE UPDATED 1'0 REFLECT THIS MODIFICATION. END Form Approved . MAJOR REPAIR AND ALTERATION 0MB "$211332?" 0 t! mam (Airframe, Powerplant, Propeller, or Appliance) . Of?ce ,der?ft'i?ca?onAdministru?m M) 1?7 66?, INSTRUCTIONS: Print ortype all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (orsubsedugnt revision thereof) for instructions and disposition of thisform. This reportis required by law (49 U.S.C. 1421 for each such violation (Section 901 Federal Aviation Act of 1958). Failure to report can result in a civil penalty not to exceed $1,000 Make Model 1 BEECHCRAFT 253 rcra Serial No. Nationality and Registration Mark BB-498 Name (As shown on registration certificate) U.S. CUSTOMS SERVICE Address (As shown on registration certificate 1391 CONSTITUTION AVE 541] z-omwr OFFICE OF TACTICAL ENFORCEMENT WASHINGTON DC, 26229 AIR OPERATIONS DIVISION - - A For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (AS described in item 1 above) ?T'Wn?ra?rw'w um w: POWERPLANT use Viv 79" Cam awe: {i ll 3 PROPELLER .e NOV 2 1994 i3? NRA '"Ti Type 3, i. 2:5. An?L??iisfi?thL {101 1102; lei roe i 903 gamn 3mm APPLIANCE t_ I, i Manufacturer hm? a?sz? m3 4 W43 3W4 3A1 mums. ewe-gel; 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. INC. 82592 HANGAR RD. SAN ANGELO, TX 769l34 U.S. Certificated Mechanic Foreign Certificated Mechanic LIMITED Certificated Repair Station AIRFRAME Manufacturer CRS SVYS 6 2 1K D. I certify that the repair and/or alteration made to the unit(s) identified 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 U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge.w Date M4997 7. Appro?al for Return a entice h/ - I - Pursuant to the authority given persons specified below. the unit iden?fied in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is PROVED El REJECTED Other 8 ecr'f m?e?f?tanda?ds Manufacturer pJiclspection Authorization y) BY Date of Approval or Rejection Certificate or Designation'No. 355/9757; m/ FAA Form 337 (12-88) . - NOTICE Weight and balance Or opera-ting limitation changes shall be entered in the appropriate aircraftrecordiAn alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness reqwrements. 2, 3, 4, 8. Description of Work Accomplished (ll more space is required, attach additional sheets. Identity with aircraft nationality and registration mark and date work completed.) NOVEMBER 15, 1994 HORNE REMOVED SYSTEN RECEIVER FROM THE TAIL SECTION OE THE AIRCRAFT AND THE CONTROL UNIT FROM THE CENTER CONSOLE. INSTALLED A TRIMBLE NAVIGATION TNL 3196 LORAN WITH GLOBAL POSITIONING SYSTEM IN ACCORDANCE WITH TRIMBLE NAVIGATION INC, DRAWING LIST REV. DATED MARCH 25, 1992, OR LATER FAA APPROVED REVISION. THIS PLACED INTO THE CENTER CONSOLE IN PLACE OF THE ONS AN APPROVED FLIGHT MANUAL SUPPLEMENT WAS PLACED INTO THE AIRCRAFT. . THE PANEL WAS LABLED NOT APPROVED FOR A LOG BOOK ENTRY AND EQUIPMENT LIST UPDATES WERE MADE. THE AIRCRAFT WAS WEIGHTED AND THE WEIGHT AND BALANCE WAS UPDATED. THE AIRCRAFT STRUCTURAL AND METAL WORK WERE ACCOMPLISHED IN ACCORDANCE WITH AC CHAPTER 1, CHAPTER 22, CHAPTER 3, PAR 42, AND AC 43.13-1A, CHAPTER 2, SECTION 8. AIRCRAFT HARDWARE USED WAS IN ACCORDANCE WITH AC CHAPTER 5, SECTION 1. THE ELECTRICAL LOAD, CIRCUIT PROTECTION AND WIRE INSTALLATION WERE ACCOMPLISHED IN ACCORDANCE CHAPTER 11,. 6, AND 7. A FUNCTIONAL TEST AFTER THE DESCRIBED IN THIS 337 WAS WAS SATISFACTORY, AND THE REMOVAL DID NOT ADVERSELY AFFECT THE EXISTING COMPONENTS AND SYSTEMS IN THE . AIRCRAFT. i Additional Sheets Are Attached ?o 6., Us Department MAJOR REPAIR AND . Form Approved OMB No. 2i20-0020 . . For FAAU olTronsportonon (Airframe, Powerplant, Propeller, or Appliance) Of?ce Identi?cations" 3' MommiesAdmlt?tlsl?ru?al?l [7 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 acivil penalty not to exceed $1.000 for each such violation (Section 901 Federal Aviation Act of 1958). Make 1 Aircraft SerialB498 Natio?falgysa?dgegistration Mark Add?is??qf NW, RM 54 OFFICE OF TACTICAL ENFORCEMENT WASHINGTON DC, 23229 n. "w 5 "WaiForFAAUseoniy i le 2W2 2W3 ac LAN famine? 12w 4 2W5 A 61994 leQA . M- - ,sAZ-isz?aggpmi a. Unit identification 5. Type rut 102 um rub 303. 5M1 3W2 Unit :i Model Serial No. Repair Alteration N1) 1W2 111*? m1 :2 auto SA AIRFHAME (As described in item 1 above) ?t'l alto ?Ti?e . 1 OZ. POWEHPLANT . "r ZH 8" a. A . 7?77; reel Pa 2, 85 3761 PROPELLER . Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address 8. Kind'of Agency 0- Ce?i??mD INC. ?8692 HANGAR RD. SAN ANGELO, TX 76904 U.S. Certificated Mechanic AIRFRAME Foreign Certificated Mechanic or Certificated Repair Station Manufacturer CRS SVY9 6 2 1K D. I certify that the repair and/or alteration made to the unit(s) identified in item 4above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date Sam .f Auth ?vi a! - 247%? Y. Approval for Retu To Service Pursuant to the authority given persons specified below. the Wenti?ed in item 4 was inspected in the manner prescribed by the - REJECTED Administrator of the Federal Aviation Administration and is Manufacturer yd?spection Authorization BY FAA Designee Repair Station Person Appmved by Transport Canada Aimorth_in_ess Group Other {Specify} Date of Approval or Rejection 527/422 Certificate or Designation No. 4 Auth divf' ual FAA Form 337l12-88 a) e55) - ?ax/W5 EV Weightand balance or operating limitation changes shall lie entered in the appropriate aifcr?ft record. An alteration must be compatible With all prewous alterations to assure continued conformity with the applicable airworthiness requirements. NOTICE -- 1 - 8. Description of Work Accomplished I (If more space is required, attach additional sheets..ldentity with aircraft nationality and registration mark and date work completed.) - .- ll -. 4-..- A - . mu?wg -- .. .. 1 .L- 7.. SSOTE TQQAA - "WmSA873GL. 2. THE INSTALLATION WAS MADE PER SHADEN REPORT NUMBERS 4648.AND 4O72FLIGHT MANUAL SUBPLEMENI.DATED FEERDARI.ZEL.1985 LATER FAA REVISION WAS PLACED INTO THE AIRCRAFT. A w. --.- -. - .- LOG BOOK ENTRY AND EODIRMENT LIST UPDATES WERE MADE. THE AIRCRAFT WAS WEIGHTED AND-TEE WEIGHT AND BALANCE WAS-UPDATED.- no-r ?41- v- .. 5. THE AIRCRAFT STRUCTURAL AND METAL WORK WERE. ACCORDANCE WITH AC CHAPTER 2, PAR 22, CHAPTER 3, AND ..13-1A, CHARTER 2, USED WAS IN ACCORDANCE WITH AC CHAPTER 5, SECTION 1. w? 6r THE ELECTRICAL LOADPCIRCUITLPROTECTION WERE ACCOMPLISHED IN ACCORDANCE WITH AC CHAPTER SECTIONS pant . .1. A INWTHI 7 Y. EHE OBERATIORJSIAS JAB- .. mm DID .1921..- h? 2-: a:an 3:125 .m?wii . A AIRCRAFT~52 fr? m?n? D?mq" -. 7 new?Jr? A, u-I. w" r?ec?23:35:35 La: ==nu errmax. 3992Rw93'i mic {39:15:11 51:9?, Then Gena-Wmaux-?4 Id9:15?ugh-39? ma-svou?? .2- w" wwugm . a 2?31: 7M- Itineu use an: w; a?'?eiitetlz maker: new .3 ?Pius-:95 ~31: --: :uEaemq Nu .. a AA- Ensign 3-: ASL- Laura -w -., . . 4:4i" Ahx-7.- mr- 1* :1 1 a hub" - . v: - row nan- 13?4me ME ., i -- . .v net- A. - 1 ha fit: rh 3.:331Hang??mm r- a ?3121;: 5159? 3-. 1-. ?42? - ., - ?0 'lf Are A?ached Additional Sheets an- i 19 i ?.9103 a Ai-?Il . . .r Jun Hamill-?Kim I. .3. lingual-L run? rm.? A . . Any alteration of {In} punix?ablr by a an! (xi-?ding 31;000, or :?mprir nu Imcllo-nlo-dli 11mm! guru cf 3min of transportation Qdminnmn?on alignments! ??ligpz OZErti?tatz' Adm/W Shadin Company, Inc. 6950 Wayzata Boulevard Minneapolis, MN 55426 .- 4Q 49- SESISGL faW?Mb Mm See Type Certificate Data .Sheet No. E4EA for complete certification basis. g; . Pratt and Whitney, Aircraft of Canada A - PTGA-S, -6A, -63, - 1M;-i -15AG, uao, -20A, -21, -25, -25A, -27, -28, -28A, -29, I :34. -34AG, ?35, -38, -41AG, -42, -45, -453, ~50, -553, -112, -13s, Pres-9 Incorporation of a Fuel Flow Transducer in accordanc with Shadin Company Report Number 4MB, revised September 6, 1985 or other FAA approved revision. This approval should not be extended to other engines of these models that incorporate any other previously approved modification, unless it is determined that the interrelationship between this change and any other previously approVed modification will introduce no adverse effect on the aimorthiness of these engines. was; a. as .Wauwwm?cgm a 45.4 a. fag-ma.- ?amass/J, .anna lav/n)! 2Wm4;wmuuhm. ,z?wdmna?: Ma 8, 1932 mnw/ 9:14 a dduantl June gel/I ?mandr/ October 30, 1985 Wave/1' . f/r/m I- N. F. /H0m (33mm?) Manager, Chicago Ai rcraft Certification Offi ce Central Region . - annual no! ?reading Bran. 0: 50M: In: ?m?mlr ma] 6: lramfrrud ag_ucardan(t mu FAR 21.47 W- .. . Inn-mm? um?r. o-clr' - as! I 5? git: 1 i I . fw?efr? 7 . 11mm! Sam at m; Experiment of transportation Emotion administration ?Giggle (Enti?catz SA873GL Shadin Company, Inc. 3723 'm?M/o 6950 Nayzata Boulevard Minneapolis, MN 55426 ?nr?xftm?- do 4/49 Federal Avi a1 My? dc! f1,- mMarm'Iy A24CE for complete certification basis See Type Certificate Data Shee @Wmcz?guW: Azactf A A5: Beech Aircraft Corporation 200, 200C, A200, 200T. ZDUCT. AZDOC fix? Installation of a Shadin Edinpany Fuel Flow Indicating System in accordance with Shadin Company Report Nunjber 4072, dated August 20, 1984 on, other FAA approved revision. 1- 'Jj imawmd?n/a?bms FAA approved Airplane Flight Manual Supplement dated February 26, 1985 or subsequent FAA appr0ved revision is required. This approve .should not be extended to other airplanes of this model that incorporate any other previously approved it is determined that the inter? modification relationship between this change and an}; other previously approve will introduce no adverse effect thiness of these airplanes. on the a mo Warafuaa may; a. are Wimp/44,. 1mm? one: 4'4- .Jy, .915?;th ywmmeM/am, August 20.. 1984 "Haul {Ala/Mm". February 25. 1985 . 171?}. ya, H. F. Horn (Signal-m! 1, Manager, Chicago Aircraft Certification 01" Central Region, ACE-115C (Tth years. or 31,000. or imprisonment nu! nrudmg 3 (admire fll'll'n?l FAR .4 alrcralr'an ofthl'x Callahan punrshubtr b; a [Mr of no! tundra 'Ilm mn?ral: may in -- .. LM It 7 . DEPARTMENT or TRANSPORTATION FEDERAL AVIATION ADMINISTRATION MAJOR REPAIR AND ALTERATION (Airframe, Poworploni, Propeller, or Appliance) Form A ?ed Budget ureau Na. 04-R060.1 FOR FAA USE ONLY IDENTIFICATION 7rd Scat? INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 45.9?1 (or subsequent revision thereof) for instructions and disposition of this orm. - MAKE Beech MODEL 200 SERIAL NO. NATIONALITY AND REGISTRATION MARK USA N6507B NAME (As shown on rogisfroiion certi?cate) ADDRESS (As shown on regisfro?on certi?cate) 2, OWNER U.S. Customs Service 1301 Constitution Avenue N.W. Office of Patrol Washington, DC 20229 - 3. FOR FAA USE ONLY 4. UNIT IDENTIFICATION 5. TYPE UNIT Ice MODEL SERIAL No. ALTER- - REPAIR mo" AIRFRAME WW (As described In item I aboveJWum POWERPLANT PROPELLER 'mt APNANFE MANUFACTURER 6. STATEMENT C. CERTIFICATE NO. A. NAME AND ADDRESS KIND OF AGENCY Dean W. Bennett 92 Belaire San Angelo, TX. 76903 we. CERTIFICATED MECHANIC Air?rame 78: FOREIGN MECHANIC Powerplant CE RTIFICATED. REPAER STATION 1292128 MANUFACTURER D. I certify attachmen that the repair. and/or alteration made to the unit(s) identi?ed in item 4 above andAdesCtibed on the reverse or ?tg hereto have been made in accordance with the requirements of Part 43 of the us. Federal Aviation Regulations and chit the information furnished.herein is true and correct to the best of my knowledge. DATE 7 22 ?MarCh 1993 SIGNATURE OF AUTHORIZED INDIVIDUAL 7. APPROVAL FOR RETURN TO SERVICE, Pursuant. to the authority given persons speci?ed below, the unit identi?ed in item 4 was i the Adrmnistrator of the Federal Aviation Administration and is nsgected in the manner prescribed by OTHER (spocim MANUFACTURER INSPECTION AUTHORIZATION INSPECTOR BY CANADIAN DEPARTMENT DESIGNEE REPAIR sum?: or TRANSPORT INSPECTOR or AIRCRAFT DATE OF APPROVAL OR REJECTION 22 March 1993 CERTIFICATE OR DESIGNATION NOSIGNATURE OF AUTHORIZED INDIVIDUAL FAA Form 337 (7-67) (8320) 5 - 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 (lt more space is required, attach additional sheets. identity with air- craft nationality and registration mark and date work completed.) The following landing damage repairs were made on this aircraft: All parts were supplied?by_Beech Aircraft Corporation. . i The left?wing spar web3 at the landing gear actuator opening, was repaired by an' added doubler as per Beech Engineering drawing SRV .015,3copy attached. Damage area was dye checked.before adding doubler. A hard landing inspection was completed as per maintenance manual Chpt. 5?50, pages 207?213. I The left wing was removed.and wing fitting were dye checked. No cracks-or defects were found. Due to a dent, the lower skin from Sta. 184 to Sta. 212 was replaced with a Beach supplied skin p/n 50?110023?131. Original rivet spacing usedfwith a double-raw of rivets at inboard edge. Removed leading edge of left wing and_spliced'a nine inch section of leading_edge hinge strip at wingistation 190, using Beech splice procedure for hinge strip. Wing reassembled using new hinge?pins p/n 50-110000?2 4. Wing reinstalled using bolt kits 101e4024?1 S, 2 each kit 101?4026?3 S, and 101?4025-1 S. Bolts torqued to spec?? ifications. . i The left aft nacelle was repaired using new bulkhead p/n 101?980019?1, former 101? 980010?19, bulkhead 101?980020~1, stringer 99-980000?21, and skin 101?980022?9. Original rivet fastner pattern was used. Left wing tip was replaced using p/n 1017 170001?653. Ventral fin was replaced using p/n 101?440018?85, 50,440051-9 and 50? 440051732. . END {Zr ADDITIONAL SHEETS ARE ATTACHED FAA AC 72-4908 6 Th U.S. GPO: 1981 475-33214? i l. 1 :mm mm mm ?mm .mcmvomq 233.1. 9.1956: arm gm 3.: . awn??01 .00 max mm 1 ?Ban. unamouu Ff an W?n?hl n. 5.23 5.33 xw mum?a?m :34 .. - .i - canSwarm? to 9.3.53 gauwanaan was: ,3 5m $335 It! . mimumw i I'll.- m. . .. a . Inc-nammzn?znau . . .Lm +.0Kt 5mm: . . urnc?wncb . $.13..9-3? 9.2 a I 1 I. 3233 wanna"..3..refm??u ulilmm be," ?tinmolwsv main MW . rat? 4. 00' 1-. 11.. c- 10? .I . a firing/nub vm mrurm mmn??rm w. a no Dunn.? kn?. 49.: human Su?sm." . . I Ilu 1-..unn .- . "um. 35? 0 I 0 'u Dnubg?lk'. E. 9&11' ins-fc? 1'1? $l-l shut Y?ugun 5.7? n?q .w inn-snag}. I All 9N0 L?tn?Ii? ?3 . - 1. I bun rut-?20. WEISL UH Sledan? (Luna-Run. Imus. AIICALuann ALL 2Pvt-u!) ?1:3 to {?x-admin Ln? 130?.1 moo Swan? nun-u .3. . 9m. ?vq. NE. Chi.? ?wanna. ?nu. Iii-Iktlut. urns-13.1.3. i3 - . Q. Z1T1~tm dagL'I-Qr f'qi'? . - - 13. .- 5.5mq-o in? Inw'rlumuw1?an 3mm: - . . gum? JANE . - I - 0 \nthLaw? ?13 9915?!? 1 udm?l?lu - u.bash?? mac?. 0 [in una- 3.011 Its-m. I . 413- Mu qua: . . nu.- run-u an?. {um ?LU-nth?. 2 . ?1 I nLto~? halt? mnaiwt. I I. . "samm??. m: .- Q?'Setf'? 3?70! - WW, M. nee we on; 3:.3 mac M95) 01:) 96V 9.1V sass-ms ws 09:: mo 866?. 9 ??il?d 030 020 03113333 033 can: cm mo Wde ov ms owi Sic! 93.3 r? *1 3 can 31.8 31,1; .1 oa'ArmsN'r or TRANSPORTATION FEDERAL AVIATION ADMINISTRATION MAJOR REPAIR AND ALTERATION (Airframe, Poworplont, Propeller, or Appliance) Form A Budget arena N9. O4-R060.1 FAA USE ONLY OFFICE IDENTIFICATION 2a waspo s? INSTRUCTIONS: Print or type all entries. for instructions?nd disposition of this form. 43.9, PAR 45' Apoendix B, and AC 4333-! (or subsequent revision thereof) MAKE MODEL BEECH KINGAIR 200 A . AIRCRAFT SERIAL NO. NATIONALITY AND REGISTRATION MARK BB-498 N23707 . NAME (As shown on registration certificate) ADDRESS (As shown on registration certi?cofo) 2. OWNER U.S. CUSTOMS SERVICE 1301 CONSTITUTION AVE NW OFFICE OF PATROL DC 20229 3. FOR FAA 1 4. UNIT IDENTIFICATION . 5, ma; UNIT MAKE MODEL NO. Ass: A AIRFRAME described In item 1 XX POWERPLANT FROPELLER MANUFACTURER 6. STATEMENT A. NAME AND ADDRESS 3. KIND OF AGENCY C. CERTIFICATE NO. U.S. CERTIFICATED MECHANIC FOREIGN CERTIFICATED MECHANIC 9N MILO, 76906 CERTIFICATED REPAER STATION CBS 210-81 MANUFACTURER D. I certify that the repair. and/or alteration made to the unit unachtnents hereto have been made in accordance with the and that the information furnishedherein is true and correct to the best of my knowledge. (5) identi?ed in item 4 above and described on the reverse or equiretnents of Part 43 of the U.S. Federal Aviation Regulations DATE Jamary 17, 1989 SIGNATURE OF AUTHORIZED INDIVIDUAL 7. APPROVAL FOR RETURN TO SERVICE the Administrator of the Federal Aviation Administration and is Pursuant to the authority given persons speci?ed below, the unit identi?ed in item 4 was ins ected in the manner prescribed by APPROVED FAA Form 337 (7-67) MANUFACTURER INSPECTION AUTHORIZATION OTHER (swim INSPECTOR BY CANADIAN DEPARTMENT REPAIR snuon or TRANSPORT INSPECTOR or AIRCRAFT DATE OF APPROVAL OR CERTIFICATE SIGNATURE OF AUTHORIZED INDIVIDUAL REJECTION DESIGNATION NO. Jamary 17, 1989 CPS 210431 MK (8320) 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. lldentify with air- craft nationality and registration mark and date work completed.) Removed the Ni?Cad Battery and installed a lead?acid battery Teledyne Gill Installation accomplished per STC Airplane Flight Manual revised. No weight change. . . - i [0-1 on (3-15 6-2 a9 34-. A . '23 {-32 I 201933 We; - . - . ADDITIONAL SHEETS ARE ATTACHED Ir . ta \ru A- . . . . 1 1 198B DEPARTMENT OI: TRANSPORTATION Form A ved FEDERAL AVIATION ADMINISTRATION 04430504 FOR FAA USE ONLY 1ND ?nikAEo': OFFICE IDENTIFICATION I name, owerp an rope or, or pp lance) sw_ann.m INSTRUCTIONS: 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. MAKE MODEL BEECHCRAFT 200 KING AIR 1' AIRCRAFT SERIAL NO. NATIONALITY AND REGISTRATION MARK 1 1313498 23707 NAME (As shown on registration cerii?taie) ADDRESS (As shown on re isfrafion certi?cate) 2_ OWNER U. . SERVICE 1301 CONSTITUTI AVE. I AIR DIVISION 1 WASHINGTON . . 20229 IDENTIFICATION 5_ mg UNIT MAKE I MODEL NO. REPAIR AME: I ATIO AIRFRAME WM: described in Item 1 I XX POWERPLANT PROPELLER TYPE APPLIANCE MANUFACTURER J, -, ulna - ,5 - .. 6. STATEMENT A. NAME AND ADDRESS 8. KIND OF AGENCY C. CERTIFICATE NO. NORTHROP WORLDWIDE AIRCRAFT 6812 NORTHROP DR. FOREIGN CERTIFICATED MECHANIC 5 2? EL PASO, TX. 79925 CERTIFICATED REPAIR - MANUFACTURER 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 U.S. Federal Aviation Regulations and that the information, furnishedherein is true "and correct to the of my knowledge. If - I, 7. APPROWFOR RETURN TO SERVICE Pursuant to the authority given persons speci?ed below, the unit identi?ed in item 4 was ins ected in the manner prescribed by the Administrator of the Federal Aviation Administration and is APPROVED FM MANUFACTURER XX INSPECTION AUTHORIZATION OTHER (swim INSPECTOR BY CANADIAN DEFZRTATENT FAA DESIGNEE REPAIR OF TRANSPORT INSPECTOR I OF AIRCRAFT DATE OF APPROVAL OR CERTIFICATE OR SIGNATURE OF AUTHORIZE INDIVIDUAL DESIGNATION NO. XL 6573242714ng ,7 . FM Form 337 I747) (8320) 4 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 cgpformity with the applicable airworthiness requirements. 8. DESCRIPTION OF WORK ACCOMPLISHED (It more Space is required, attach additional sheets. ldentity with air- craft nationality and registration mark and date work completed.) Removed Texas Instrument F.L.I.R.) which had been installed under S.T.C. SA 1811C-E. Manufactured cover plate for existing box in cabin floor between F.S. 248 and 273. Cover made from 2024-5133 aluminum .063. Installed one 3/4" anglei.067 thick and one angle L125 thick "for support. angle installed under seat track. Angles were secured with machine screws and nuts. Plate sealed with rubber seal and attached with machine screws and nuts. Bottom fuselage covered with .063 aluminum plate that was obtained when the S.T.C. was installed . Plate was fastened with existing screws and nut plates. 55,23:32.173 Stir i: 2 Di'i'i? [3 ADDITIONAL SHEETS ARE ATTACHED AC 72-4906 . . a U5. GPO: 1931 475332147 . it? 3 a FEDERAL AV. AGENCY 3- MAJOR REPAIR AND ALTERATION (Airframe, PowerpIani, Propeller, or Appliance) 7? [g I I I 't'l Bureau Nu. liq?Rabat FOR FAA USE ONLY OFFICE IDE FIC TI 1 Co INSTRUCTIONS: Print or type all entries. for instructions and disposition of this form. See FAR 45.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) MAKE MODEL BEECH 2 0 0 1' AIRCRAFT SERIAL NO. NATIONALITY AND. REGISTRATION MARK . BB498 -N23707 - NAME {As shown on registration certificafe) ADDRESS (As shown on registration certificate) 2. OWNER 1301 ON AVE . . . CUSTOMS SERVICE . . 2 0 229 3. FOR FAA USE ONLY A. FEB 27.1987 ?ne. A - . 4. UNIT IDENTIFICATION UNIT MAKE MODEL SERIAL NO. FS Vg?? ATION AIRFRAME (As described in ?em I above)ewmem POWERPLANT PROPELLER TYPE APPLIANCE MANUFACTURER 6. CONFORMITY STATEMENT A. NAME AND ADDRESS B. KIND OF AGENCY C. CERTIFICATE NO. (1.5. CERTIFICATED MECHANIC A. 358465487 GARRY A. SEGAL FOREIGN CERTIFICATED MECHANIC MAXFIELD 1 I CE RTI FICATED REPAIR STATION WACO TEXAS 76 7 05 MANUFACTURER certify that the repnlr?and/or alteratxnn made to the umt(s) Identi?ed In Item 4 above and on the reverse or h?ereto hayc been made In ectordance With the requirements of Part 45 of the us. Federal Aviation Regulations and that the InformatIon furmshed herein is true and correct to the best of my knowledge, ?It A DATE SIGNATURE OF AU HOR ED INDIV UAI. ,4de . ea 7. T0 APPROVED Pursuant-II.) the authority given pers?ons speci?ed below, the unit identi?ed in item 4 was ins acted in the manner prescribed by the of the Federal Aviation Agency and is REJECTE FAA FLT. STANDARDS MANUFACTURER INSPECTOR INSPECTION AUTIIORIZATION OTHER (swim BY FAA DESIGNEE REPAIR STATION 2 CANADIAN DEPARTMENT OF TRANSPORT INSPECTOR 0F AIRCRAFT REJECTION DESIGNATION N0. 11'- 3 ?53 Co 174. 22/3570 ?gm? tn BAIT BI 1? i I 6di%m ?41 #0 WI FAA Form 337 (1-65) OBSOLETE PREVIOUS EDITION (8320) .1 *3 a NOTICE . - ?Weight and balance or operating limitation changes shall be entered in the appropriate aircraft recorcl. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8? DESERIPTION 6F Wilt AECGMFUSHED {it more space te required; lettaeh eet?tittenel sheets; identity with air: craft nationality and registration inark and date work completed.) - . - AFT BODY STRAKES PER RAISBECK ENGINEERING STC SA 3519NM. BALANCE 15 c? 9 0.5. GOVERHMIHT PRINTING OFFICE :1955 ADDITIONAL SHEETS ARE ATTACHED .- FEDERAL A AGENCIY . MAJOR REPAIR AND ALTERATION (Airframe, Pobwerpionf, Propeller, or Appliance) I Ala/Ir? rm! Bureau Na. FOR 1":le USE ONLY OFFICE IDENTIFICATION INSTRUCTIONS: Print or type entries. for instrucrions and disposition of this form. See FAR 45.9, PAR 43 Appendix B, and AC 43.9?1 (or subsequent revision thereof) MAKE MODEL BEECH 2 0 0 1' MRCRAFT SERIAL NO. . NATIONALITY REGISTRATION MARK NAME (As shown on registration certificate) ADDRESS (As sh_own on registration certificate) 2 OWNER 1301 AVE. U.S. CUSTOMS SERVICE WASHINGTON D.C. 20229 3. FOR FAA USE ONLY RECEEVED DEC 4 1986? u?zfmiw?? 7 4. UNIT IDENTIFICATION UNIT MAKE MODEL SERIAL No. REPAIR MYER- ATION AIRFRAME (As described in item 1 above) momma-wow POWERPLANT PROPELLER TYPE APPLIANCE MANUFACTURER 6. CONFORMITY STATEMENT A. NAME AND ADDRESS B. KIND OF AGENCY C. CERTIFICATE NO. .5. CE RTIFICATED MECHANIC A- 358465487 GARRY A . SEGAL FOREIGN CERTIFICATED MECHANIC 6 1 0A MAXFIELD CERTIFICATED REPAIR STATION WACO TEXAS 76 7 05 MANUFACTURER that the repaIr?and/Or alteration made, to the umt(s) Identi?ed In Item 4 above and on the reverse or ';Itt;tchments hereto have been made in accordance with the requirements of Part 43 Of' the U.S. Federal Aviation Regulations .and that the information furnished herein is true and correct to the beat of my knowledge. a. DATE Joe-see SIGNATURE ED INDIV UAL 44W I 7. FOR RETURN TO Pursuant?? the authority given persons speci?ed below, the unit identi?ed in item 4 was in the of the Federal Aviatton Agency and is APPROVED [j REJECTE sgected in the manner prescribed by FAA FLT. STANDARDS INSPECTOR MANUFACTURER INSPECTION AUTFIORIZATION OTHER (Specify) BY FAA DESIGNEE REPAIR STATION I CANADIAN DEPARTMENT OF TRANSPORT INSPECTOR OF AIRCRAFT REJECTION DESIGNATION NO. 3 ?8 (a 1.74. 22/3570 un- 22/222 6% $ng . 1.-. m. I- M. .7 FAA Form 337 (1?65) OBSOLETE PREVIOUS EDITION 005 2-0%000 (8320) NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. A'n alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. DESERWTIOH OF WORK (it more spaee terequired; attaeh additional sheets: ldeatity with air: craft nationality and registration mark and date work completed.) AFT BODY STRAKES PER RAISBECK ENGINEERING STC SA 3519NM. BALANCE ADDITIONAL SHEETS ARE ATTACHED GOVERNMENT PRINIING OFFICE I355 5? FER 131955 or TRANSPORTATION FEDERAL AVIATION ADMINISTRATION MAJOR REPAIR AND ALTERATION (Airframe, Power-plant, Propeller, or Appliance) Farm Applet/ed Budge! Bureau Na. 04-R060.1 FOR FAA USE ONLY OFFICE IDENTIFICATION INSTRUCTIONS: Print or type all entries. for instrucrions and disposition of this form. See FAR 43.9, FAR 43 Appendix B, and AC 43.9?1 (or subsequent, revision thereof) MAKE MODEL I AIRCRAFT 200 SERIAL NO. NATIONALITY AND MARK 498 N23707 NAME (As shown on registration certi?cate) ADDRESS (As shown on registration certi?cate) 2. OWNER U.S. CUSTOMS AIR DIVISON 1301 CONSTITUTION AVE. NJJ. OFFICE OF PATROL WASHINGTON. 11.6. 20229 GOVT. 3. FOR FAA USE ONLY 7? "The data Identified herein complies with the nppucnmu airworthiness requirements and Is approved for Ihn above described aircraft, sublet: to conformity Imoec?on by a person authorized by FAR Part 43 tion 43.7.? I ?mm. - Sta/:5 gob! to Signature of 4. UNIT IDENITFICATION 5. TYPE UNIT MAKE MODEL SERIAL N0. REPAIR :32: AIRFRAME described in ?em I above)Wmomu POWERPLANT PROPELLER TYPE APPLIANCE MANUFACTURER 6. CONFORMITY STATEMENT A. NAME AND ADDRESS B. KIND OF AGENCY C. CERTIFICATE NO. EL PASO. TEAS NQBIHROP wonaninE Atacaart sauntcas 6812 NORIHROP DRIVE - . 79.925 - . CERTIFICATED MECHANIC FOREIGN MECHANIC CERTI FICATED REPAIR STATION MANUFACTURER 203-17 D. I certify that the repair and/or alteration made to the unit(s) identi?ed in item 4 above and described on the reversc 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 correcr to the best of my knowledge. DATE teas a OF AUTHORIZ INDIVIDUAL - . 7. APPROVAL tot RETURN. TO SERVICE ED Pursuant to the authority" given persons speci?ed below, the unit identi?ed in item 4 was inrsIPected in the manner prescribed by INSPECTOR a FAA FLT. STANDARDS I 1 I - MANUFACTURER the Administrator of'rhe Federal Aviation Administration and is ,8 APPROVED DREJEC INSPECTION AUTHORIZATION omen (Specify) BY FAA DESIGNEE REPAIR STATION CANADIAN DEPARTMENT OF TRANSPORT INSPECTOR OF AIRCRAFT DATE OF APPROVAL 0R REJECTION 14 FEBRAURY 1986 CERTIFICATE OR - DESIGNATION NO. 203-1? SIGNAT RE F, AUTHORIZED INDIVIDUAL FAA Form 337 (7-673? ?15? U.S. Government Printing OIIice 1977?772-5461141 (8320) THE you.on mums mum WAS. minim 1N -mcnm 3123707 ON TOTAL TIME WAS 2750.7.. WEIGHT AND BALANCE WAS RECOMPUTED AND ENTERED IR LOB BOOK. cl 8. DESCRIPTION OF WORK ACCOMPLISHED (if more space is required, attach additional sheets. Identity with air- ?crat't nationality and registration mark and date work completedADDITIONAL SHEETS ARE ATTACHED 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 as?ure continued conformity with the :applicable airworthiness requirements. WAS woman ON A LOCAL MANUFACTED SHEETMETAL WENT A643-13-2AIn", my}. Hr; . Mn: ?g 13 "I?n?e . IUUJ OEPART TRANSPORTATION I Approved FEDERAL A ADMINISTRATION udget Bureau Na. FOR FAA USE ONLY . a . MAJOR REPAIR AND ALTERATION. - OFFICE IDENTIFIQNION (Arrframe, Powerplanf, Propeller, or Appliance) SW-FSDO-BI INSTRUCTIONS: Print or type all entries. See FAR 43.9, PAR 43 Appendix B, and 43.9?1 (or?subseque t/revision thereof) for instructions and disposition of this form. MAKE MODEL SERIAL NO. . NATIONALITY REGISTRATION 498 N23707 I NAME (As shown on regisiraiion certificafe) ADDRESS (As shown on registration certificate) 2. OWNER U.S. CUSTOMS AIR DIVISON . z: 1301 CONSTITUTION AVE. OFFICE OF PATROL I - . WASHINGTON, D..C. 20229 GOVT. A 3. FOR FAA USE ONLY . . I ?the data Identi?ed herein comphes With the oppIIcnmu airworthiness requirements and is approved for The aboue described aircraft, subject To coniormify inspection by a 3 person authorized by FAR Part 42 ion 43.7.? ?at, I6 I xDI'sIrIct Offic- Signaiure diPAAInspwor 4. UNIT IDENTIFICATION i I: 5. UNIT MAKE 7 MODEL SERIAL No. REPAIR AIRPRAME described in item I abbve)W POWERPLANT I I 5 PROPELLER TYPE I MANUFACTURER 6. IONFOIIMITY STATEMENT A - A. NAME AND ADDRESS KIND OF AGENCY a c. CERTIFICATE NO. NORTHROP WORLDWIDE AIRCRAFT SERVICES .X CERTIFICATED EL PASO, TEXAS 79925 I -. MANUFACTURER - 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 U.S. Federal Aviation Regulations and that the Information furnished herein is true and correcr to the best of my knowledge. DATE OF AUTHORIZ INDIVIDUAL 'r I I, 7. APPROVAL TOR 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 APPROVED DREJECTED I . . OTHER 5 i FAA STANDARDS MANUFACTURER AUTHORIZATION INSPECTOR .- I I BY . DEPARTMENT FAA DESIGNEE REPAIR OF TRANSPORT INSPECTOR OF AIRCRAFT - DATE OF APPROVAL 0 CERTIFICATE OR SIGNAT RE AUTHORIZED INDIVIDUAL REJECTION DESIGNATION NO. . 14 FEBRAURY 1986 203-17 ., I, \r Pom 337 (7-622. U.S. Government Printing 0ffice1977?772-546I141 (8320) NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. A:n alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. OF WORK ACCOMPLISHED (It more space is required, attach additional sheets. Identity with air- craft nationality and registration mark and date work completed.) THE FOLLOWIG AVOINICS EQUIPMENT WAS. INSTALLED IN AIRCRAFT N23707 ON FEB 14,1986. TOTAL AIRCRAFT TIME WAS 2750.7.. WEIGHT AND BALANGE WAS RECOMPUTED AND ENTERED IN LOB BOOK. KY 58 RADIO PANEL . . . . . . . . . .., FLOOR MOUNTED EQUIPMENT WAS MOUNTED ON A LOCAL MANUFACTED SHEETMETAL MOUNT AC43-13-2A, CHAPTER 2 21-22-2403ii? $353k lag; I ?11.11??er harmtitle?;- a; I ?J?nuugraUh?. 101.: f'au? *4 :3 .ADDITIONAL SHEETS ARE ATTACHED NSPORTATION Approved . 57/ .2 I FEDERAL . .dget Bureau FM MAJOR REPAIR AND ALTERATION (9:133? (Airframe, Powerplant, Propeller, or Appliance) See FAR 43.9, FAR 43 Appendix B, and AC 43.9?1 (or subsequent revision thereof) INSTRUCTIONS: Print or type all entries. for instructions and disposition of this form. MAKE MODEL AIRCRAFT BEECHORAFT 200 SERIAL NO. NATIONALITY AND REGISTRATION MARK - . United States .60h0 NAME (As shown on registration cer??tate) ADDRESS (As shown on regisfrafion ceriificaie) 2- OWNER BEECH AIRCRAFT conponnion aig?iggx ?g 67201 3. FOR FAA USE ONLY 5. TYPE 4. UNIT IDENTIFICATION UNIT MAKE MODEL SERIAL N0. REPAIR ALTER- ATION AIRFRAME WW (As described in Item I POWERPLANT PROPELLER TYPE APPLIANCE MANUFACTURER 6. CONFORMITY STATEMENT A. NAME AND ADDRESS B. KIND OF AGENCY C. CERTIFICATE NO. U.s. CERTIFICATED MECHANIC INCO FOREIGN CERTIFICATED MECHANIC 202-20 BOX 1056 CERTIFICATED REPAIR STATION CLASS MANUFACTURER IV 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 U.S. Federal Aviation Regulations to the best of my knowledge. and that the information furnished herein is true and correct SIGNATURE OF AUTHORIZED IN DUAI. DATE I . . 30 SEPTEMBER 1981 . . . .. 7. APPROVAL FOR RETURN TN SERVICE given persons speci?ed below, the unit identi?ed in item 4 was inspected in the manner prescribed by Federal Aviation AdminiStration and is DREJECTED Pursuant to the authorit the Administrator of the OTHER (5 eci FAA LT- STANDARDS MANUFACTURER INSPECTION AUTHORIZATION INSPECTOR BY CANADIAN DEPARTMENT FAA DESIGNEE REPAIR OF TRANSPORT INSPECTOR OF A CERTIFICATE OR SIGNATURE OF AUTHORIZED I IV UAL DATE OF APPROVAL OR REJECTION DESIGNATION NO. 30 SEPTEMBER 1981 202-20 1M (8320) 1% us. Government Printing Office FAA Form 337 (7-67) 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 (It more space is required, attach. additional sheets. Identity with air? craft nationality and registration mark and date works-completed.) STATES Ill 6010 I. 30 SEPTMER 1931 1. Accomplished installation of VIE Omega. 'Naiv System IAN E-Systems Diet-ring number 7160-00000, SA hh75 sw._ .