US Department of Transportation Federal Aviation Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form Approved OMB No. 2120-0020 2I28I201 1 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. N508RB 20885008 1' Aircraft Make Model Series Cessna 2088 Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) Address Box 18517 2' Owner City West Palm Beach State FL Five Point Aerial Survey Zip 33406 Country USA. 3. For FAA Use Only 4. Type 5. Unit identification Repair Alteration Unit Make Model Serial No. AIRFRAME (AS described in Item 7 above) POWERPLANT PROPELLER Type APPUANCE Manufacturer 6. Conformity Statement A. Agency?s Name and Address B. Kind of Agency Name Pro Star Aviation LLC Zip 03053 Country U.S.A. Address 5 Industrial Drive, Manchester Airport City I Stale NH Certi?cated Repair Station U. S. Certi?cated Mechanic I Manufacturer Foreign Certificated Mechanic C. Certi?cate No. Certi?cated Maintenance Organization P6UR006Y D. I certify that the repair andlor 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. 8 Signature/Date of Authorized individual Daren Remmert (4?09?2444 7. Approval for Return to Service Pursuant to the authority given persons speci?ed below, the unit identi?ed in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is Approved Rejected FAA FIL Standards . . . Persons Approved by Canadian Inspector Manufacturer Maintenance Organization Depanmentof Transport BY Other (Speciijr) FAA Designee Repair Station Inspection Authorization Certi?cate or Signature/Date of Authorized Individual Designation No. P6UR006Y Scott Shamel 09-24-14 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.) N508RB 09-24-2014 Nationality and Registration Mark Date -- AIRCELL ST 3100 SATELLITE TELEPHONE SYSTEM INSTALLATION - Installed the Aircell ST 3100 Satellite Telephone System, consisting of the ST 3100 Transceiver, all associated electrical wiring, cabling and components, per the Pro Star Aviation electrical drawing 3145, revision IR. Completed a functional hazard assessment, as recorded on the Functional Hazard 8. Safety Assessment, document 21286-FHA-01, revision IR. Completed the Testing and Setup of the Aircell ST 3100 Satellite Telephone System, per the Aircell ST 3100 Installation Manual, document 800-10680, revision IR, noted on the Pro Star Aviation electrical drawing 3145, revision IR. Accomplished the installation of the Aircell ST 3100 Satellite Telephone System, per DER Approval on FAA Form 8110?3, dated 09-22-14. - The Flammability Test Results, Design Data 8259302, revision NC, for the Coaxial Cable (PN 311201) has been accomplished per DER Approval on FAA Form 8110-3, dated 09-18-14. 0 Determined that the electrical load does not exceed the aircraft's capacity, per FAA AC 43.13-28, chapter 2, page 18, paragraph 207(a)(b). - Accomplished the Test for the installation of the Aircell ST 3100 Satellite Telephone System, per FAA AC 43.13-28, chapter 2, page 19, paragraph 209(c), as recorded on Pro Star Aviation document revision IR. - For continued airworthiness of the Aircell ST 3100 Satellite Telephone System Installation, refer to Pro Star Aviation Instructions for Continued Ainivorthiness, document 21286-ICA-01, revision A. supplied to the operator. - Refer to the Updated Aircraft Computed Weight and Balance, and Aircraft Equipment List Supplement, dated 09-23-14, for further information re?ecting this modi?cation. - Pertinent details of the above modi?cations are retained on work order 21286, on ?le at Pro Star Aviation. END Additional Sheets Are Attached FAA Form 337 (10-06) DME092214-001 US. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION 09/22/14 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft, Engine, Propeller, etc.) 5. NAME OF APPLICANT Cessna Aircraft Company 2088 Airplane Pro Star Aviation Londonderry, NH LIST OF DATA 6. 7. TITLE Pro Star Aviation Drawing No. 3145 "Aircell ST3100 Wiring Diagram" Revision IR Drawing No. 3153 "Churchill G1000 GPS Input Wiring Diagram" Revision IR Document No. "Functional Hazard Safety Assessment - Installation of an AirCell ST 3100" 21286-FHA-01 Revision IR Notes: END 1) This approval is for engineering design data only. It indicates the data listed above demonstrates compliance only with the regulations speci?ed by paragraph and subparagraph listed below as "Applicable Requirements". Compliance with additional regulations not listed here may be required. 2) This form does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. 3) This approval covers electrical details only. structural aspects of this alteration are not included in this approval and require separate approval. 4) Functional testing of the system is required to verify proper operation of associated systems. 5) On aircraft testing is required. The operation of the systems can not affect the operation of essential or critical aicraft systems. In themsleves the systems should not be interfered with by other systems to the point that it does not function properly. END 3. PURPOSE OF DATA Ih support of a Major Alteration for Cessna 208B s/n 20885008 9. APPLICABLE REQUIREMENTS (List specific sectionsi TCDS A37CE Revision 20 14CFR [Amdt 23-20], ?23.1307 [Amdt 23-23], [Amdt 23-49], [Amdt 23-43], ?23.1365(a) [Amdt 23-49] and [Amdt 23-49] 10. CERTIFICATION - Under authority vested by direction of the Administrator and In accordance with conditions and limitations of appointment under 14 CFR Part 183. date listed above and on attached sheets numbered NIA 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 Give) Therefore Approve these data 11. OF DESIGNATED ENGINEERING 12. DESIGNATION 13. Systems and Equnpment 1 Av I Douglas M. England (Electrical) FAA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION US. Department of Transportation 1. DATE Federai Aviation Administration 09/18/14 STATEMENT OF COMPLIANCE WITH THE AIRWORTHINESS STANDARDS AIRCRAFT 0R AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft, Engine. Propeller. 5. NAME or= APPLICANT etc.) Cessna 2088 Aircraft Pro Star Aviation LLC LIST OF DATA 6. IDENTIFICATION 7. TITLE Design Data $259302 Skandia, Inc. Flammability Test Results Rev, NC Bunsen Burner Testing Carlisle Interconnect Technologies: 50 Ohm, PIN 311201, Coax Cable, Clear Jacket, 12 AWG, Ref. Drawing 3145 Notes: - This report approval is in support of a Major Alteration with previously tested and approved data. This alteration is the installation of a Aircell ST3100. - The PIN 311201 coax cable was originally tested to 14 CFR Amendment 25-113 Appendix Part which is the same test as 14 CFR 23.1359(c) Amendment 25-49 - This approval is for the flammability aspect only. This approval is for aircraft s/n 20885008 only. - Pro Star purchase order 23672. - Skandia?s sale order 279148-14 8. PURPOSE OF DATA Demonstration of compliance with material flammability requirements in support of a Major Alteration on aircraft s/n 20885008. 9. APPLICABLE REQUIREMENTS (List specific sections) 14 CFR PART 23.1359(c) Amendment 23-49 10. CERTIFICATION Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Part 183. 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 Airworthiness Standards listed. Recommend approval of these data 2) Therefore Approve these data 11. SIGNATUREIS) OF DESIGNATED ENGINEERING 12. DESIGNATION 13. CLASSIFICATIONS) KW BERT-605430-CE Structural Special Gary K. ?J/mer Form 8110-3 (03/10) Supersedes Previous Edition PRO TAR AVIATION 5 INDUSTRIAL DRIVE LONDONDERRY, NH 03053 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Installation of an AirCelI ST 3100 Aircraft Make Model: Cessna Aircraft Company 2088 Aircraft Serial Number: 20885008 Aircraft Registration: N508RB PRO STAR AVIATION PROPRIETARY INFORMATION This document contains Proprietary Information of Pro Star Aviation, LLC. Disclosure to others, and the use or copying by others, without the express authorization of Pro Star Aviation, LLC is strictly prohibited. Date 09/23/14 Document Number Revision A Sheet Intentionally Left Blank Pro Star Aviation. LLC. Londonderry, NH 03053 Instructions For Continued Airworthiness AirCell ST 3100 - Cessna Aircraft Company 2083 Revision index Revision Date Sheet(s) Description Prepared By Reviewed By . . Previously Signed by Previoust Signed by IR 09/23/14 Ail initial Release Jeffrey Kahn Douglas M. Engiand Updated Screw and Washer Part A 9/23/14 4 Numbers Jeffrey J. Kahn Douglas M. England Certi?cation Enginee Certi?cation Manager . . . . .V . Note: Changes in document for the latest revrsion are indicated by a line in the left margin adjacent to change. except on the cover page, header, and footer. Date 091231'14 Sheeti Document Number 21286-ICA-01 Revision A Pro Star Aviation. LLC. Instructions For Continued Airworthiness Londonderry, NH 03053 ST 3100 - Cessna Aircraft Company 2088 Sheet Intentionally Left Blank Date 09/23/14 Sheet ii Document Number Revision A Pro Star Aviation. LLC. Instructions For Continued Airworthiness Londonderry. NH 03053 ST 3100 - Cessna Aircraft Company 2088 Table of Contents Revision Index List of Tables .. iv List of Figures .. iv 1. Purpose ..1 1.1.Aircraft Description .. 1 1.2. Scope .. 1 1.3.Applicability .. 1 1.4. Definitions and Abbreviations .. 1 1.5. Precautions .. 1 1.6. Units of Measure .. 1 1.7. Referenced Publications .. 1 1.8. Distribution .. 2 2. Description ..2 3. Control, Operation Information ..3 4. Servicing Information ..3 5. Maintenance Instructions ..3 6. Troubleshooting Information ..3 7. Removal and Installation Information ..3 7.1.ST 3100 Removal .. 4 7.2. ST 3100 Installation .. 4 7.3. Cockpit Dialer Removal .. 4 7.4. Cockpit Dialer Installation .. 4 7.5. System Test .. 5 Diagrams ..5 Special Inspection Requirements ..5 10. Application of Protective Treatments ..5 11. Data ..5 12. Special Tools ..5 13. For Commuter Category Aircraft ..5 14. Recommended Overhaul Periods ..5 15. Airworthiness Limitations ..5 16. Assistance ..6 17. Implementation and Record Keeping ..6 Appendix A - Installation Drawings ..A-1 Date 09/23/14 Sheet Document Number 21286-ICA-01 Revision A a 3.1 n? i ?-91 15?. r. 1.31.! i .P Ovar?l. (.1. A: Jcovll. . .y .tE.5. lrI. .I. i. .5 -. :01. Ill v. If .Frlrurb II rl >n bu . .3613? 1.11; Ital}. its. n. (in! 5.1.2. I?ll TIE. it. llil . all! .2 . ?all? i. .I IF I it"- . li?xilx? 1.. LI. I). Ella-Illicit. .l l) 1: 13h Pro Star Aviation. LLC. Instructions For Continued Almorthiness Londonderry. NH 03053 AirCell ST 3100 - Cessna Aircraft Company 2088 List of Tables Table 3.1 AirCell Iridium Phone System Circuit Breakers ..3 Table 4.1 - SATCOM System LRU Details ..3 Table 8.1 AirCell Iridium Phone System Installation Drawing ..5 List of Figures Figure 2.1 AirCell Iridium Phone System Diagram ..2 Figure A.1 AirCell ST 3100 Wiring Diagram ..A-1 Date 09l23/14 Sheet iv Document Number 21236-ICA-01 Revision A 41:11 331??! nlial 1 . Pro Star Aviation, LLC. Londonderry. NH 03053 Instructions For Continued Airworthiness AirCelI ST 3100 - Cessna Aircraft COmpany 208B 1. Purpose 1.1. Aircraft Description Make: Cessna Aircraft Company Model: 2088 1.2. Scope This document identi?es the instructions for Continued Airworthiness for the modification of the above aircraft by the installation of an ST 3100. This ICA satisfies the requirements of 14 CFR ?23.1529. 1.3. Applicability This document applies to aircraft altered by the installation of an AirCeIl ST 3100. 1.4. Definitions and Abbreviations The following terminology is used within this document: AC Advisory Circular AMM Aircraft Maintenance Manual CF Code of Federal Regulations CFS Canted Fuselage Stations FAA Federal Aviation Administration FS Fuselage Station FWD Forward ICA Instructions for Continued Ainzvorthiness IR lnitial Revision LH Left Hand PIN Part Number RBL Right Butt Line RH Right Hand UHF Ultra High Frequency VHF Very High Frequency 1.5. Precautions This section is not applicable. 1.6. Units of Measure This section is not applicable. 1.7. Referenced Publications The current issue is to be assumed if the revision or date of issue is not stated. 14 CFR Part 23 Airworthiness Standards: Normal, Utility, Aerobatic, and Commuter Category Airplanes 14 CFR ?23.1529 Instructions for Continued Airworthiness 14 CFR ?23 Appendix Instructions for Continued Airworthiness AC43.13-1B Acceptable Methods, Techniques, and Practices Aircraft Inspection and Repair AC 43.13-2B Acceptable Methods, Techniques, and Practices Aircraft Alterations CD2078 Model 208 Maintenance Manual CD2079 Model 208 Wiring Diagram Manual 800-10680 AirCeIl ST 3100 Installation Manual SM55-2 Cobham Avionics Installation and Operation Manual PTA12-100 POTS Telephone Adapter with Display Date 09123114 Sheet 1 Document Number 21286-ICA-01 Revision A Ill ?9,1 lull liiul?ll lute; 5t. 4 .35.: .15.!3529 13:39.3! I Ii). .. . . It: 1945.. i;l.lil 1 A. ill-L . . Al-ruillall! . Null-v .li. .. ll .- 1.5.4 it"rv Ir J: 11'? 11' .P. in! . nifl.u.r.l cl. 4 1 IIE'riI-ibtn pr}..o irl 5 kl. 1h. E- .vl-ll tittb.? .. .I I . Hilts-??nij 1' a i Pro Star Aviation, LLC. Instructions For Continued Airworthiness Londonderry. NH 03053 AirCell ST 3100 - Cessna Aircraft Company 208B 1.8. Distribution The Instructions for Continued Airworthiness is furnished to the owner of this aircraft modified by the installation of an AirCell ST 3100. This ICA is to become part of the permanent aircraft records. To revise this ICA, complete an FAA Form 337 and as applicable submit it to the FAA along with the revised ICA. 2. Description The AirCeIl Satellite Transceiver (ST) 3100 system (AirCell ST 3100) allows for two-way voice communications from the aircraft. This service is available when the aircraft is in the air or on the ground. On the ground or in the air, the satellite communications link is provided using the Iridium LEO (Low Earth Orbit?485 miles altitude) array of 66 satellites that enable total earth coverage. The Aircell ST 3100 connects to an existing Iridium-approved antenna mounted on the top of the aircraft to provide the Radio Frequency (RF) interface for the aircraft to satellite connection. The AirCell ST 3100 system will interface to a PTA dialer on the flightdeck, allowing the user to make SATCOM voice calls through the existing audio system. Pro Star Aviation electrical drawing 3145 documents the electrical modi?cations performed for this installation. As installed, this system consists of the following components: - 400-10680-001 - AirCell ST 3100 SATCOM Transceiver Cobham Avionics Cockpit Dialer 1616-880-01 Honeywell (Skyconnect) Iridium Satellite Antenna (existing) Refer to Figure 2.1 for a system diagram. Satcom Transceiver Satellite Antenna 6; a(feminine) . tmOiUM. I i can; i Dialer I I I I 1 Figure 2.1 AIrCell Iridium Phone System Diagram Date Sheet 2 Document Number Revision A .1 Pro Star Aviation, LLC. Instructions For Continued Aimorthiness Londonderry. NH 03053 AirCelt ST 3100 - Cessna Aircraft Company 208B 3. Control, Operation Information The AirCell ST 3100 system provides worldwide SATCOM telephone service utilizing the iridium Satellite network. Service can be accessed once the ?ight crew has turned on the Avionics 2 switch on the pilot?s waterfall panel. Table 3.1 AirCell Iridium Phone System Circuit Breakers Component Circuit Breaker Label Circuit Breaker Size Bus ST 3100 SAT . . 5 Cockpit Dia er PHONE amp 28 VDC AVIonics 2 Bus 4. Servicing Information The AirCell and Cobham do not require any routine servicing. In the event of a component failure, return the affected unit to the manufacturer or an approved manufacture's authorized repair station. Refer to Table 4.1 for equipment information and mounting locations. Table 4.1 SATCOM System LRU Details Qty Manufacture Equipment Part Number Location . . STA 174.5 in the 1 ST 3100 SATCOM Transceiver 400-1068-001 Mission Console 1 Cobham Avionics Cockpit Dialer PTA12-100 STA 115 5. Maintenance Instructions Design and manufacturing of the installed as part of this modification system allows for ?On Condition Maintenance." On condition maintenance means that no periodic service requirements are necessary to maintain continued airworthiness of the system. No maintenance is required until the equipment does not perform the intended function. inspect all installed items (including the wiring and hardware) for damage, excessive wear, security, chafing, etc. Also, inspect these items at the routine inspection intervals that apply to the aircraft 100 hour inspection, annual inspection, or other scheduled inspection). LRU replacement can be accomplished in the field. Refer to Section 7 of this document for additional details. After replacing a defective LRU with a serviceable LRU, consult the applicable Installation Manual listed in Section 1.7 of this document for operationally testing the affected LRU. Refer to Section 15 Airworthiness Limitations for additional inspection methods and intervals. 6. Troubleshooting Information Refer to Appendix A of the AirCelI ST 3100 installation Manual listed in Section 1.7 of this document. If the fauit cannot be resolved, contact AirCell Technical Support to help evaluate the discrepancy. See Section 9 of this document for drawings to further assist in troubleshooting. 7. Removal and Installation Information Prior to removal or installation of equipment, verify that all circuit breakers that supply power to the system components are open. During removal of any LRU associated with the system, bag, label, and set aside all associated hardware and parts for use during installation. As applicable, visually inspect the associated hardware, connectors, and wiring prior to installing equipment; and replace or repair as necessary, prior to installation procedures. Place protective covers on the connector after disconnecting. Remove the protective covers just prior to reconnecting with the mating connector or fitting. Connectors on electronic LRUs should be protected utilizing plastic ESD covers. Date 09/23/14 Sheet 3 Document Number Revision A :irin: 1! I H.111 ?Nw.1.:r11 :Iuc 1 . .1 ?iv??uy?l?ualulalnqli .. ?.Irll .. .- A 'I?llial limitli:ll. ryUt. I f?y I it]! illfl i. 3 ll . 4.11? Ill. 0.1.3.4 ?illn :1lulijlnil I I). . in. L. I 512111;. A?m.1 Pro Star Aviation, LLC. Londonderry, NH 03053 Instructions For Continued Airworthiness AirCell ST 3100 Cessna Aircraft Company 2088 Refer to FAA AC 43.13-1B during the installation procedures of the following equipment for fastening hardware torque values unless otherwise stated. After installation of the system components, perform the system tests, as necessary, to verify the proper operation of the applicable portions of the system affected by the component removal and installation, referring to Section 7.5 of this document. Refer to Table 4.1 of this document to determine component installation locations. It may be necessary to refer to the Aircraft Maintenance Manual listed in Section 1.7 of this document for guidance on accessing the associated components within the aircraft. 7.1. ST 3100 Removal 1. Refer to the beginning of Section 7 of this document for general guidelines associated with the removal and installation of the ST 3100. Remove the forward and aft access out panels from the mission console to gain access to the ST 3100. Disconnect electrical connector PP1001 and TNC coaxial connector PP1002. While supporting the ST-3100 from below remove the six (6) #8-32 Machine Screws (M835206- 245) and #8 washers from the mounting brackets securing the ST 3100 to the bottom of the mission console shelf. Carefully lower the ST 3100 and slide it out of the mission console. Remove the three (3) #6-32 Machine Screws (M835206-228) and #6 washers (AN960-6L) securing each mounting bracket (2x) to the ST 3100 and set both the brackets and screws aside for use during installation. 7.2. ST 3100 Installation 1. Refer to the beginning of Section 7 of this document for general guidelines associated with the removal and installation of the ST 3100. 2. Secure the two (2) mounting brackets to the ST 3100 using the #6-32 Pan Head Screws(M835206? 228) and #6 washers (AN960-6L) set aside during removal. 3. Gently place the ST 3100 onto the mounting points on the bottom of the mission console shelf. 4. While supporting the ST 3100 secure it to the bottom of the mission console shelf using six (6) #8?32 Machine Screws (M835206-245) and #8 washers (AN960-8L) set aside during removal. 5. Secure electrical connector PP1001 and TNC coaxial connector PP1002 to the ST 3100. 6. Apply power to the system and perform system test in accordance with Section 7.5. 7. Secure the forward and aft access panels to the mission console. 7.3. Cockpit Dialer Removal 1. Refer to the beginning of Section 7 of this document for general guidelines associated with the removal and installation of the Cockpit Dialer. 2 Loosen the unit?s four (4) Dzus fasteners turn counter-clockwise. 3 Slide the unit out of the panel until the rear unit connector is accessible. 4. Disconnect electrical connector PP1003 from the rear of the unit. 5 Remove the unit completely from the panel. 7.4. Cockpit Dialer Installation 1. Refer to the beginning of Section 7 of this document for general guidelines associated with the removal and installation of the Cockpit Dialer. Mate the harness connector PP1003 to the connector on the back of the unit. Slide the unit into the panel and align the four (4) Dzus fasteners to the appropriate holes in the Dzus rail. Date 09/23/14 Sheet 4 Document Number Revision A Iii]! l?iillr It." sll. . L. .Illi :1 slliui ll q. :1Ilil I (I?ll: I- I .i At .l .11. .I?llililul. . Pro Star Aviation. LLC. Instructions For Continued Ainnrorthiness Londonderry, NH 03053 - AirCell ST 3100 - Cessna Aircraft Campany 2088 4. Secure the unit?s Dzus fasteners 1Aturn clockwise. 5. Apply power to the system and perform system test in accordance with Section 7.5. 7.5. System Test If a component of the system is removed and reinstalled, it is necessary to verify the systems operation. 1. Position the aircraft at a location on the airfield where the SATCOM antenna has a clear view of the satellite constellation. Apply electrical power to the aircraft's electrical system. Switch on the Avionics 2 Bus. Allow a minimum of five (5) minutes for the ST 3100 system to establish a SATCOM connection. Referencing the operation section of the PTA-12 Installation and Operation Manual listed in Section 1.7 of this document, make an outgoing call and receive an incoming call from the pilot and co-pilot sides utilizing the PTA-12 cockpit dialer. Verify that the system is providing a clear communications link. 91.45.03!? 8. Diagrams Table 8.1 AirCell Iridium Phone System Installation Drawing Drawing Number Title 3145 AIRCELL ST-3100 WIRING DIAGRAM 9. Special Inspection Requirements This section is not applicable. 10.Application of Protective Treatments This section is not applicable. 11.Data This section is not applicable. 12.Special Tools No special tools are required for maintenance and testing. 13. For Commuter Category Aircraft This section is not applicable. 14. Recommended Overhaul Periods This section is not applicable. 15.Airworthiness Limitations 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. There are no new or additional ain~orthiness limitations associated with this equipment and/or installation. Date 09I23l14 Sheet 5 Document Number 21286-ICA-01 Revision A .11 11.314 1'11 1?01. 3 ul- ill.77 {Fri .. . .331. a 5.. .. .. 3,0ng 15' . :25' :Ht. . I likely-pi i 11111 ?I?ll?lialPro Star Aviation. LLC. Instructions For Continued Aimonhiness Londonderry. NH 03053 AirCeIl ST 3100 - Cessna Aircraft Company 2088 16. Assistance For questions or assistance regarding this ICA. contact: Pro Star Aviation 5 Industrial Drive Londonderry. NH 03053 Phone: (603) 627-7827 17.lmplementation and Record Keeping This ICA is to become a part of the aircraft maintenance manual. An entry must be made in the permanent aircraft maintenance record referring to this document. Date 09123114 Sheet 6 Document Number 21286-ICA-01 Revision A v3 ma: >35? Ern. roaoana. 2: 303 . 0323mm Um? use; val03!; 283: 9.333. nemm air: t: :51. as .5. ammo. ?m5 .32@Lna I 1 a . Barty-.881 .. age! .. . . ??okuuqoinnu?w. El.ui.! g5 IN: ?Agxiar? Esta. ?39.63.35 g??ig Iwhnb*nw pain .- gain-=8! I EPA-E lulu-r pad-Qua aanuf?uuoag??linv 0 ?Bale-?d. Iv?vsa 0 Eva 8513]?. a. 5 3? Rib! ?623.? Riusg in Ga?1??uo?u?a In: 95 IP- Mb .13 15:. rules 5.35.3.1; (Cg luv?sunk.? @530 a! 303.5. EgaFa A523 Earn; Egan? gin. rang 33 H.an- .51: MGMOQ (?Mm?20 grow}! I 39:9 Pd I ?Soc $213. 9333 manna Duncan:? 2553 Inigo: Form Approved Electronic Tracxing Number OMB No. 21200020 US Depanmem MAJOR REPAIR AND ALTERATION Mm? mmuwomy ofTransportation (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 thereot) 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. N508RB 20885008 1- A'rcra? Make Model Series Cessna 2088 Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) Address Box 18617 2- Owner City West Palm Beach State FL Five Point Aerial Survey Zip 33406 Country USA 3. For FAA Use Only 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model Serial No. POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind ongency Name Pro Star Aviation LLC U. S. Certi?cated Mechanic I Manufacturer Address 5 industrial Drive, Manchester Airport Foreign Certificated Mechanic 0. Certi?cate No. City Slate NH Certi?cated Repair Station Zip 03053 Country U.S.A. Certi?cated Maintenance Organization PSUROOSY 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 SignatureiDate of Authorized individual per 14 CFR Part 43 El App- 3 Daren Remmert My- 09?24?14 7. Approval for Return to Service Pursuant to the authority given persons speci?ed below. the unit identi?ed in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is Approved Rejected FAA Flt. Standards . . . Persons Approved by Canadian Inspector Manufacturer Maintenance Organization Department ?Transport I I Other (Specify) FAA Designee Repair Station Inspection Authorization Certi?cate or Signature/Date of Authorized Individual Designation No. PBUROOSY Scott Shamei 09-24-14 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 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.) N508RB 09?24-2014 Nationality and Registration Mark Date -- GARMIN GIA 63W TO CHURCHILL NAVIGATION INTERFACE - interfaced the Copiiot?s GIA 63W to the Churchill ARE-5000. Con?gured the Copilot?s (31000 R8232 Channel 8 Output to Aviation. Accomplished per the Pro Star Aviation electrical drawing 3153, revision IR, DER Approved on FAA Form 8110-3, dated 09-22-14. Pertinent details of the above modi?cations are retained on work order 21286, on ?le at Pro Star Aviation. END Additional Sheets Are Attached FAA Form 337 (10-06) DME092214-001 US. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION 09/22/14 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL N0. 4. TYPE (Aircraft, Engine, Propeller, etc.) 5. NAME OF APPLICANT Cessna Aircraft Company 2083 Airplane Pro Star Aviation Londonderry, NH LIST OF DATA 6. IDENTIFICATION 7. TITLE Pro Star Aviation Drawing No. 3145 "Airceil ST3100 Wiring Diagram" Revision IR Drawing No. 3153 "Churchill G1000 GPS Input Wiring Diagram" Revision IR Document No. "Functional Hazard Safety Assessment - Installation of an ST 3100? 21236-FHA-D1 Revision IR Notes: END 1) This approval is for engineering design data only. It indicates the data listed above demonstrates compliance only with the regulations speci?ed by paragraph and subparagraph listed below as "Applicable Requirements". Compliance with additional regulations not listed here may be required. 2) This form does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. 3) This approval covers electrical details only. structural aspects of this alteration are not Included in this approval and require separate approval. 4) Functional testing of the system Is required to verify proper operation of associated systems. 5) On aircraft testing is required. The operation of the systems can not affect the operation of essential or critical alcraft systems. In themsleves the systems should not be interfered with by other systems to the point that it does not function properly. END 8. PURPOSE OF DATA in support of a Major Alteration for Cessna 2088 sin 20885008 9. APPLICABLE REQUIREMENTS (List speci?c sections) TCDS ABTCE Revision 20 14CFR [Amdt 23-20], ?23.1307 [Amdt 23?23]. [Amdt 2349], [Amdt 23-43], ?23.1365(a) [Amdt 23-49] and [Amdt 23-49] 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 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 (We) Therefore Approve these data 11. DESIGNATED ENGINEERING REPRESENTATIVHS) 12. DESIGNATION 13. CLASSIFICATIONS) Systems and Equipment DERY-830903-NE . I A /Douglas M. England (Electncal) l' FAA Form 8110-3 (03110) SUPERSEDES PREVIOUS EDITION Form Approved Electronic Tracking Number OMB No. 2120-0020 US Dapamm MAJOR REPAIR AND ALTERATION mm" meuwmy gfgragiif?d?gm (Airframe. Powerplant, Propeller, or Appliance) 3 Br 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. N508RB 20835008 1' Aircraft Make Model Series CESSNA 2083 Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) FIVE POINT AERIAL SURVEY Address P-O- 30" 13517 2- Owner cny WEST PALM BEACH State Zip Country 3. For FAA Use Only 4, Type 5. Unit Identification Repair Alteration Unit Make Model Serial No. AIRFRAME (As described in Item 1 above) Cl POWERPLANT Ci PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Name ROBERT u. s. Certi?cated Mechanic Manuiacmrer Address 11550 AVIATION STE 4 Foreign Certi?cated Mechanic C. Certi?cate No. City WEST PALM BEACH State FLORIDA Certi?cated Repair Station Zip 33412 Country UNITED STATES Certificated 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. Extended range fue Signature/Date of Authorized Individual [3 KM a/a 9/0 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 [2 Approved [1 Rejected FAA Flt. Standards . . . Persons Approved by Canadian Inspector Manuracturer mamtenance orgamzat'on Department of Transport BY Other (Specify) FAA Designee Repair Station Inspection Authorization Certi?cate or Signature/Date of Authorized Individual Designation No. AP324746066IA KM 95" 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 confermity with the appicable airworthiness requirements. NSOBRB bans/13 Nationality and Registration Mark Date INSTALLED AERO ACOUSTICS AIRCRAFT SYSTEMS, INC. AIRCRAFT PAYLOAD EXTENDER MODIFICATION PER STC SAO121SSE AND INSTALLATION MANUAL AA1636. REVISED WEIGHT AND BALANCE AS REQUIRED. 8. Description of Work Accomplished END I Additional Sheets Are Attached Wafme - O. (Ezr?fimte (la ?h22? SAO1213SE s8) (29) AeroAcoustics Aircraft System, Inc. .A 08 ?da?a? May 21, 2003 Co 2) @445sz \d 6/20i03; 12/9/08; 3/13/13 (bx 5331/4241;be 6 QN Limitations Pertaining to all Eligible Models Limit Speeds (IAS): Maneuvering Speed at 9062 ib ?2.143 ES 0 Maxlmum Weights Ramp: . p? Takeoff: .. . .. po 5 Lending: 00 Limit Factor Flaps up: -1. Limits Flaps down (ali settings): .. . owqgmark DO NOT JACK OR I AT GROSS WEIG A 0 87 LB (b Near the airspeed indicatovvgs eye" airspeed limitation placard: 0. a, Piacards: On each side of nose strut fairing "143 Any alteration ofthis cem'ficate is punishable by a ?ne ofnot exceeding 000, or not exceeding .3 yams, or bot/1. Wink certi?es re may be transferred in accordance with FAR .21. 47. 31:02 (10-63) PAGE 4 or: 4 paces tame-mam - Eight (Eartth ?awed?? SA01213SE a .7553 magi/?Ma; Mama/to AeroAcoustics Aircraft System, In? 9302 29th Avenue Hangar 3-10 . Cg Everett, WA 98204 69 'i air/(aired [Kai wild/aye: (SM [12$ (Katya/5r Mid/A, ?it; .1 mma?'a'avw 23 deral Aviation ad J/Ma??m/ liar/15w; generate/a. 9 A3705 @??yka?g?g?ar?aal Like: g?l?kmf, 11/12 Mar.- 0 0 @2122.- Cessna 208 godagkaJ/avz, $46 gee-7a tg?fmya; Fabrication of Ae (AASI) AeroAcoustics Payload Extender System in accordance with AeroAcous Dohc??nlent 42, Revision F. dated January 3, 2013, or later Federal Aviation Administration )appniyed ion. This modification to be dated January 3, 2013, and installed in accordance with AASI Installation Manual No? 1636\3ev' maintained in accordance with Section 3.0 of AASI on ark ai ance Manual No. M16536. 5 0 Revision G. dated January 3. 2013, or later FAA-approv revfG . applies to the above model aircraft only. which other previously approved $ma24zaa/aa mz/ awake/w.- Approval of this ch ?933 i 63%: This approval should not be extended to other ai mo th he modifications are incorporated unless it is deter 0 ip between this change and any of those other previously approved modifications, incluwill introduce no adverse effect upon the airworthiness of that aircraft. 0 A copy of this certificate and FAA Appro irpi ligh QEpplement as listed on Page 3. must be maintained as part of the permanent rec for mod?ed (5&0r?gion?et 3 of 4 pages) i?d cal-[Wale a/za/ri?e! ?m?fymre 14-; jam/4o: gem/?edged; M: Mar/Z; JIMM/za?maf retro/(ea; a .- Qa/ae ?ayyzt?mlzbax No?mber a) 2006 gale mead/Mn.? Q?a gala wide/Me?c? 6/20/03; 12/9/08; 3/13/1 3 egg}: ?kemJ/Jwa ox/ 6 (Signature) Actinq Manader. Seattle Aircraft Certification Of?ce (A Xb (TitleAny alteration of tk?gmhca to IS punishable by a fine of not exceeding 000, or imprisonment not exceeding 3 years, or bot/L . . . This certi?cate may transferred accordance Wit/1 FAR 4 7. FM Foam 8110-2 (lo-6 o?szJd/ma: PAGE 1 OF 4 PAGES warhead/Aim IFMAuiu?nnAhmit?m-a?ml hymen/211ml 6gp: Olerttf? . . . ((Eunttnuatum $11221) 659 {656 ?27 c2} AeroAcoustics Aircraft System, inc. Q) 255324644 May 21, 2003 Q) 26 Jaem?g' 6/20/03; 12/9/08; 3/13/13 9% (wad ?22??me (W/dezalddf' The conditions and limitations of the Type Certificate Data et the following: Applicability: This modification is limited to the folio Ian ane y: apply except where superseded by Model: Serial Numbers 6k by Cessna Kit SK208-80, 20885000 and Up .k LIMITATIONS for SN 20830179, 2083023%?d u$nd ~?aft modi?ed by Cessna Kit SK208-80 . ES ONLY) CG Range: (Takeoff and Fl 6 (D +1795 inche a 50 gaunt/{9) le +1933+199.15i sat po?ls +200.23 es 6 eoff only) +2043 e?tfos nd keoff oniy above 9000 pounds) Straig vi: Io given Required Flight Manual 4A (675 SHP engine) Document No. AFMS-C208-16 3 ed un Supplement: 6 20, 20 3, or later FAA approved revision LIMITATIONS for SN $21sgyoae?goo and up (LAND PLANES ONLY) KI ?an??ggm) +1 0 i?es at 6500 pounds or less \0 es at 8000 pounds 9.1% as at 8807 pounds 0 ches at 9062 pounds (Takeoff only) +20% inches at 9062 pounds (Takeoff only above 9000 pounds) line variation between points given 0 0 3?0? Requlr?ght?nua\ Aircraft with (867 SHP engine) Document No. t: Supple dated March 13, 2013, or later FAA approved revision e? 2088 20880179, 20830230 CG Range: Any oft/51's certi?cate is punishable: by a ?ne ofnot exceeding $1,000, or imprisonment not exceeding 3 years, Or both. 7711's certificate may be transform/1 in accordance with FAR 21. 47. FAA Form 8110-2-1 (1069) PAGE- 3 OF 4 PAGES a Form Approved Electronic Tracking Number - 2120-0020 US 0.8mm MAJOR REPAIR AND ALTERATION For FAA Use Only ofTransportauon (Airframe, Powerplant. Propeller, or Appliance) Fedora! 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 and disposition of this form. This report is required by law (49 U.S.C. ?44701). Failure to such violation. (49 U.S.C. ?46301(a)) report can result in a civil penalty for each Nationa?'tyand Registration Mark Serial No. . N508RB 20835008 1' A'rcra? Make Model Series Cessna 2088 Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) Address LO Box 18517 2. Owner City W??t Palm BegclL State FL Five Point Aerial Survey Zip 33406 Country U.S.A. 3. For FAA Use Only 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model Serial No. AIRFRAME (As described in Item 1 above) [3 [j POWERPLANT El PROPELLER Type APPLIANCE Manufadurer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Name Pro Star Aviation LLC Address 5 Industrial Drive, Manchester Airport U. S. Certi?cated Mechanic I Manufacturer Foreign Certi?cated Mechanic C. Certi?cate No. City Londonderry State NH Certi?cated Repair Station Zip 03053 Country U.S.A. Certi?cated Maintenance Organization P6UR006Y 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. 8 Signature/Date of Authorized lndividu Daniel Boisvert i. 08-13-13 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 [3 Approved [3 Rejected :12: Manufacturer Maintenance Organization BY . Other (Specify) FAA Designee Repair Station Inspectlon Authorllallon Certi?cate or Signature/Date of Authorized Individual Designation No. . P6UR006Y Kurt Kltner 08-13-13 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 (lf more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N508RB 08-13-2013 Nationality and Registration Mark Date PAGE 1 (Corrections to FAA Form 337, Dated 08-06-13) MISSIONS POWER SYSTEM INSTALLATION - Installed, routed, secured and terminated the wiring for the Missions Power System, per PSA electrical drawing 2976, revision IR. - The installation of the Missions Power System has been accomplished per Design Engineering Report, document 00002135008, revision IR, DER Approved on FAA Form 8110-3, dated 08-02-13. -- TECHNISONIC TDFM-7000 SYSTEM INSTALLATION - Installed, secured and sealed the VHF Whip Antenna Doubler Assembly and CI-292 VHF Antenna on the Lower Fuselage, at F8 404.00 (referenced on PSA mechanical drawing P813071, revision IR. Installed, secured and sealed the Doubler and CI-285 Antenna on the Lower Fuselage, at F8 391.60 (referenced on PSA mechanical drawing P813074, revision IR). The installation of the Antennas has been accomplished per AC 43.13-2B, chapter 1, page 1, paragraph 100, 101, 102, 103, 105, 106, 107, 108, 109, 110, 111 and 112, and chapter 3, page 23, paragraphs 300, 301, 302, 303, 304, 305, 306, 307, 308 and 309. - Installed, routed, secured and terminated the wiring and electrical provisions, for the TDFM-7000 System, per PSA electrical drawing 2979, revision IR. The installation of the Technisonic TDFM-7000 System has been accomplished per Design Engineering Report, document DD00213.5008, revision IR, DER Approved on FAA Form 8110-3, dated 08-02?13. SATELLITE PHONE INSTALLATION PROVISIONS - Installed, secured and sealed the Iridium Antenna Doubler Assembly and Iridium Antenna on the Upper Fuselage, at FS 181.20 (referenced on PSA mechanical drawing P813075, revision IR, per AC 43.13-28, chapter 1, page 1, paragraph 100, 101, 102, 103, 105, 106, 107, 108, 109, 110, 111 and 112, and chapter 3, page 23, paragraphs 300, 301, 302, 303, 304, 305, 306, 307, 308 and 309. IMT DOWNLINK INSTALLATION PROVISIONS - Installed, secured and sealed the Downlink Antenna Doubler Assembly and Downlink Antenna on the Lower Fuselage, at FS 441.00 (referenced on PSA mechanical drawing P813073, revision IR, per AC 43.13-28, chapter 1, page 1, paragraph 100, 101, 102, 103, 105, 106, 107, 108, 109, 110, 111 and 112, and chapter 3, page 23, paragraphs 300, 301, 302, 303, 304, 305, 306, 307, 308 and 309. - Installed and secured the Skymaster Shelf, Inboard Support Zee Assembly (2 each), Outboard Support Zee, Mounting Zee (2 each), Mounting Tray and IMT Skymaster Downlink Transceiver (as referenced on PSA mechanical drawing P813076, revision IR), in the Aft Fuselage (at FS 422.60), per AC 43.13-2B, chapter 1, page 1, paragraph 100, 101, 102, 103, 105, 106, 107, 108, 109, 110, 111 and 112, and chapter 2, page 9, paragraphs 200, 201, 202, 205 and 206. G-3 MISSION CONSOLE INSTALLATION PROVISIONS - Installed and secured the Mission Console on the LH side of the Cabin, at FS 174.50, per Trine mechanical drawing P63-008-103, revision C, DER Approved on FAA Form 8110-3, dated 08-06-13. CONTINUED ON PAGE 2 Additional Sheets Are Attached 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 (lf more space is required, attach additional sheets. identify with aircra?? nationality and registration mark and date work completed.) N508RB 08-13-2013 Nationality and Registration Mark Date PAGE 2 (Corrections to FAA Form 337, Dated 08-06-13) -- GENESIS 3 RETRACTABLE CAMERA MOUNT INSTALLATION PROVISIONS - Installed, secured and sealed the Doubler and Feedthru Connectors (10 each). on the lower Fuselage, at FS 251.41, per Genesis 3 mechanical drawing P63-008-108, revision IR, DER Approved on FAA Form 8110?3, dated 08-06-13. - Modified the Cargo Pod Bulkhead, by replacing the existing nutplates with Dome Nutplates, per Genesis 3 mechanical drawing revision IR, DER Approved on FAA Form 8110-3, dated 08?05-13. - Modi?ed the Cargo Pod, per Genesis 3 mechanical drawing P63-001-102, revision A, DER Approved on FAA Form 8110-3, dated 06-28-13. - Installed and secured the Outboard Frame Attachment, Horizontal Tee (2 each) and Vertical Tee (2 each), to the Retractable Camera Mount. Installed and secured the Outboard Tee (4 each), to the Cargo Pod. Installed and secured the Retractable Camera Mount to the Cargo Pod. The installation of the Retractable Camera Mount, at FS 239.75, has been accomplished per Genesis 3 mechanical drawing P63-001-116, revision B, DER Approved on FAA Form 8110-3, dated 08-05-13. - Installed, routed, secured and terminated the wiring and electrical provisions, for the Genesis 3 Retractable Camera Mount System, per Genesis 3 electrical drawing revision A and Engineering Order E01, revision A, DER Approved on FAA Form 8110-3, dated 08-13-13. 0 The Retractable Camera Mount System has been disabled by pulling and collaring the circuit breakers, and labeling DEACTIVATED. -- MX-15HDI CAMERA INSTALLATION PROVISIONS - Installed, secured and sealed the GPS Antenna Doubler Assembly and GPS Antenna on the Upper Fuselage, at FS 160.00 (as referenced on PSA mechanical drawing P813072, revision IR), per AC 43.13?28, chapter 1, page 1, paragraph 100, 101, 102, 103, 105, 106, 107, 108, 109, 110, 111 and 112, and chapter 3, page 23, paragraphs 300, 301, 302, 303, 304, 305, 306, 307, 308 and 309. RETURN TO SERVICE - Accomplished an electrical load analysis, as documented on per Design Engineering Report, document DD00213.5008, revision IR, DER Approved on FAA Form 8110-3, dated 08-02-13. - Accomplished a structural analysis of the Retractable Camera Mount Installation Cessna 2083 Aircraft, as documented on Structural Analysis Report, document P63-001-005, revision IR, DER Approved on FAA Form 8110-3, dated 08-05-13. - Accomplished a structural analysis of the Interior Reconfiguration and Mission Console Cessna 208B Aircraft, as documented on Structural Analysis Report, document P63-008-003, revision IR, DER Approved on FAA Form 8110-3, dated 08?06-13. - Accomplished a structural analysis of the Feed Through Installation Cessna 2088 Aircraft, as documented on Structural Analysis Report, document P63-008-006, revision IR, DER Approved on FAA Form 8110-3, dated 08-06-13. - The Instructions for Continued Airworthiness, document 21179-ICA-01, revision IR, has been supplied to the operator. CONTINUED ON PAGE 3 Additional Sheets Are Attached FAA Form 337 (1006) 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 aircraft nationality and registration mark and date work completed.) N508RB 08-13-2013 Nationality and Registration Mark Date PAGE 3 (Corrections to FAA Form 337, Dated 08-06-13) - The Aircraft Flight Manual Supplement, document 21179-FMS-01, revision IR, DER Approved on 8110-3, dated 08-06-13, has been inserted into the existing Aircraft Flight manual. - The aircraft has been weighed and the Aircraft Weight and Balance Report. dated 08-03-13, has been inserted into the existing Aircraft Flight Manual. - The Aircraft Equipment List Supplement has been inserted into the existing Aircraft Flight Manual. - Pertinent details of the above modifications are retained on work order 21179, on ?le at Pro Star Aviation. END Additional Sheets Are Attached FAA Form 337 (10-06) U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION Aug 13 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft, Engine. Propeller, etc.) 5. NAME OF APPLICANT Cessna 2088 Aircraft Pro Star Aviation 5 Industrial Drive Londonderry, NH 03053 LIST OF DATA 6. IDENTIFICATION 7. TITLE Genesis 3 Engineering Drawing; RETRACTABLE CAMERA MOUNT SYSTEMWIRING Rev: A Date: April 08 2013 Drawing: 63-A0000-W01 RETRACTABLE CAMERA MOUNT SYSTEM-WJRING INTERCONNECT Rev: A E0: E01 Date: June 27 2013 Drawing: WIRE HARNESS ASSY Rev: A Date: April 22 2013 Drawing; GS-A0000-U01 WIRE HARNESS ROUTING Rev: IR Date: April 2 2013 End of Date of Data-m-m] Notes:- 1. This approval is for engineering design data only. It indicates the data listed above demonstrates compliance only with the regulations speci?ed by paragraph and subparagraph listed below as "Applicable Requirements". 2. Electrical aspects are approved only. Structural and ?ammability aspects are not included. 3. Compiiance with additionai regulations not listed here may be required. 4. This form does not constitute FAA approvai of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. 5. This 8110*3 approval is for engineering design data only and does not constitute instaliation approval. 8. PURPOSE OF DATA In support of a major alteration to SIN 20885008 (Registration N508RB) by FAA repair station certi?cate number P6UR006Y. Data approval only. does not constitute approval of the physical installation. 9. APPLICABLE REQUIREMENTS (List speci?c sections) Federal Aviation Regulations {amendment level in brackets] 14 CFR 23.1301 (3) [23-20] 14 CFR 23.135? [23-43) 14 CFR 23.1365 (3) [23-49] 14 CFR 23.1367 (3) [23-0] 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CF Part 183, data listed above and on attached sheets numbered NIA haVe been examined in accordance with established procedures and found to comply with applicable requirements of the Aimerthiness Standards listed. Recommend approval of these data I Wherefore ~E'Approve these data 11. SIGNATUREMF DESIGNATED ENGINEERING 12. DESIGNATION 13. I Nigel Stewart - Systems Equipment? 5 Electrical FAA Form 8110-3 (03? O) SUPERSEDES PREVIOUS EDITION (2 US Department of Transportation Federal Aviation Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form Approved Electronic Tracking Number OMB No. 2120-0020 '21281201 1 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 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. 1 Al N508RB 20885008 - ma? lMake Model Series Cessna 2083 Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) Address 0 Box 18517 2. Owner cu, w??I Eglm Egach . State FL Five Point Aerial Survey le 33406 Country U.S.A. 3. For FAA Use Only 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model Serial No. (AS described in item 1 above) POWERPLANT El El PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Name Em?taLAviation LLC Address 5 Industrial Drive, Manchester Airport City State Zip Country U. S. Certi?cated Mechanic Manufacturer Foreign Certi?cated Mechanic C. Certi?cate No. Certi?cated Repair Station Certi?cated Maintenance Organization P6UR006Y D. certify that the repair andlor 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 fueI SignaturelDale 0f lndiVidua? per 14 CFR Part 43 Am Daniel BOIsvert 08?06-1 3 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 [3 Approved Rejected FAA Fu- Standards . . . Persons Approved by Canadian Inspector Manufacturer Maintenance Organization Department omenspon BY Other (Specify) FAA Designee I Repair Station inspection Authonzallon Certi?cate or Signature/Date of Authorized Individual Designation No. PBUROOSY Kurt Kltner . it? 08-05-13 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.) N508RB 08?06-201 3 Nationality and Registration Mark Date PAGEI -- MISSIONS POWER SYSTEM INSTALLATION - Installed, routed, secured and terminated the wiring for the Missions Power System, per PSA electrical drawing 2976, revision IR. - The installation of the Missions Power System has been accomplished per 8. Design Engineering Report, document 00002135008, revision IR, DER Approved on FAA Form 8110-3, dated 08-02-13. TECHNISONIC SYSTEM INSTALLATION Installed, secured and sealed the VHF Whip Antenna Doubler Assembly and Cl-292 VHF Antenna on the Lower Fuselage, at FS 404.00 (referenced on PSA mechanical drawing P813071, revision IR. Installed, secured and sealed the Doubler and Cl-285 Antenna on the Lower Fuselage, at FS 391.60 (referenced on PSA mechanical drawing P813074, revision IR). The installation of the Antennas has been accomplished per AC 43.13-2B, chapter 1, page 1, paragraph 100, 101, 102, 103, 105, 106, 107, 108, 109, 110, 111 and 112, and chapter 3, page 23, paragraphs 300, 301, 302, 303, 304, 305, 306, 307, 308 and 309. - Installed, routed, secured and terminated the wiring and electrical provisions, for the TDFM-7000 System, per PSA electrical drawing 2979, revision IR. - The installation of the Technisonic TDFM-7000 System has been accomplished per Design Engineering Report, document 00002135008, revision IR, DER Approved on FAA Form 8110-3, dated 08?02-13. -- SATELLITE PHONE INSTALLATION PROVISIONS - Installed, secured and sealed the Iridium Antenna Doubler Assembly and Iridium Antenna on the Upper Fuselage, at F8 181.20 (referenced on PSA mechanical drawing P813075, revision IR, per AC 43.13-2B, chapter 1, page 1, paragraph 100, 101, 102, 103, 105, 106. 107, 108, 109, 110, 111 and 112, and chapter 3, page 23, paragraphs 300, 301, 302, 303, 304, 305, 306, 307, 308 and 309. IMT DOWNLINK INSTALLATION PROVISIONS Installed, secured and sealed the Downlink Antenna Doubler Assembly and Downlink Antenna on the Lower Fuselage, at 8 441.00 (referenced on PSA mechanical drawing P813073, revision IR, per AC 43.13-28, chapter 1, page 1, paragraph 100, 101, 102, 103, 105, 106, 107, 108, 109, 110, 111 and 112, and chapter 3, page 23, paragraphs 300, 301, 302, 303, 304, 305, 306, 307, 308 and 309. - Installed and secured the Skymaster Shelf, Inboard Support Zee Assembly (2 each), Outboard Support Zee, Mounting Zee (2 each), Mounting Tray and IMT Skymaster Downlink Transceiver (as referenced on PSA mechanical drawing P813076, revision IR), in the Aft Fuselage (at FS 422.60), per AC 4313-23, chapter 1, page 1, paragraph 100, 101, 102, 103, 105, 106, 107, 108, 109, 110, 111 and 112, and chapter 2, page 9, paragraphs 200, 201, 202, 205 and 206. -- G-3 MISSION CONSOLE INSTALLATION PROVISIONS - Installed and secured the Mission Console on the LH side of the Cabin, at FS 174.50, per Trine mechanical drawing P63-008-103, revision C, DER Approved on FAA Form 8110?3, dated 08-06-13. CONTINUED ON PAGE 2 Additional Sheets Are Attached 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.) N508RB 08-06?2013 Nationality and Registration Mark Date PAGE 2 GENESIS 3 RETRACTABLE CAMERA MOUNT INSTALLATION PROVISIONS - Installed, secured and sealed the Doubler and Feedthru Connectors (10 each), on the lower Fuselage, at FS 251.41, per Genesis 3 mechanical drawing P63-008-108, revision IR, DER Approved on FAA Form 8110-3, dated 08-06-13. - Modified the Cargo Pod Bulkhead, by replacing the existing nutplates with Dome Nutplates, per Genesis 3 mechanical drawing P63-008-106, revision IR, DER Approved on FAA Form 8110-3, dated 08-05-13. - Modified the Cargo Pod, per Genesis 3 mechanical drawing P63-001-102, revision A, DER Approved on FAA Form 8110?3, dated 06-28-13. - Installed and secured the Outboard Frame Attachment, Horizontal Tee (2 each) and Vertical Tee (2 each), to the Retractable Camera Mount. Installed and secured the Outboard Tee (4 each), to the Cargo Pod. Installed and secured the Retractable Camera Mount to the Cargo Pod. The installation of the Retractable Camera Mount, at FS 239.75, has been accomplished per Genesis 3 mechanical drawing P63-001-116, revision B, DER Approved on FAA Form 8110-3, dated 08-05-13. - Installed, routed, secured and terminated the wiring and electrical provisions, for the Genesis 3 Retractable Camera Mount System, per Genesis 3 electrical drawing G3-A0000-W01, revision A and Engineering Order E01, revision A, DER Approved on FAA Form 8110-3, dated 07-08-13. - The Retractable Camera Mount System has been disabled by pulling and collaring the circuit breakers, and labeling DEACTIVATED. -- L-3 MX-15HDI CAMERA INSTALLATION PROVISIONS - Installed, secured and sealed the GPS Antenna Doubler Assembly and GPS Antenna on the Upper Fuselage, at FS 16000 (as referenced on PSA mechanical drawing P813072, revision IR), per AC 43.13-28, chapter 1, page 1, paragraph 100, 101, 102, 103, 105, 106, 107, 108, 109, 110, 111 and 112, and chapter 3, page 23, paragraphs 300, 301, 302, 303, 304, 305, 308, 307, 308 and 309. RETURN TO SERVICE - Accomplished an electrical load analysis, as documented on per Design Engineering Report, document DD00213.5008, revision IR, DER Approved on FAA Form 8110-3. dated 08-02-13. - Accomplished a structural analysis of the Interior Reconfiguration and Mission Console Cessna 208B Aircraft, as documented on Structural Analysis Report, document P63-008-003, revision IR, DER Approved on FAA Form 8110-3, dated 08-05-13. - Accomplished a structural analysis of the Interior Recon?guration and Mission Console Cessna 208B Aircraft, as documented on Structural Analysis Report, document P63-008-003, revision IR, DER Approved on FAA Form 8110-3, dated 08-05-13. - Accomplished a structural analysis of the Feed Through Installation Cessna 208B Aircraft, as documented on Structural Analysis Report, document P63-008-006, revision IR, DER Approved on FAA Form 8110-3, dated 08-06-13. - The Instructions for Continued Airworthiness, document revision IR, has been supplied to the operator. CONTINUED ON PAGE 3 Additional Sheets Are Attached 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 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.) N508RB 08-06-2013 Nationality and Registration Mark Date PAGE 3 - The Aircraft Flight Manual Supplement, document 21179-FMS-01, revision IR, DER Approved on 8110-3, dated 08-06-13, has been inserted into the existing Aircraft Flight manualj - The aircraft has been weighed and the Aircraft Weight and Balance RepOrt, dated 08-03-13, has been inserted into the existing Aircraft Flight Manual. - The Aircraft Equipment List Supplement has been inserted into the existing Aircraft Flight Manual. - Pertinent details of the above modifications are retained on work order 21179, on ?le at Pro Star Aviation. END Additional Sheets Are Attached FAA Form 337 (10-06) US. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS 1. DATE 2, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Airptane. Engine. Propeller. etc.) 5. NAME OF APPLICANT Cessna Aircraft Company 2088 Airplane DB Integrations. LLC LIST OF DATA 6. IDENTIFICATION 7. TITLE Repell:DD00213.5008. Rev.lR, ?Avionics Modification" Date: 08l02l2013 NOTES: Installation approval. above data. Requirements" 1. This approval covers electrical, design aspects only on Airplane Model 2088. sin 20885008 and Is not 2. The authorized agency returning the aircraft to service is responsible to determine compliance with the 3. This approval is for engineering design data only. It indicates the data listed above demonstates compliance only with the regulations speci?ed by paragraph and subparagraph listed below as "Applicable 8. PURPOSE OF DATA To support Major Alteration FAA Form 337 for sin 20885008. The approval is design data approval only and is not instalaltion approval. 9. APPLICABLE REQUIREMENTS (List speci?c sections) 14 CFR Part 23.0; Amdt 23-49; 23.1357 Amdt 23-43 El Recommend approval of these data 1W6) Therefor [2 Approve these data 10. - 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 in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards Iisted. have been examined 11. SIGNATURES) 12. DESIGNATION 13. CLASSIFICATIONS) DERT Systems and Equipment Electrical DavidJ Richards%4/? FAA Form 8110-3 (03110) SUPERSEDES PREVIOUS EDITION ?2e 4 Design, Inc: Engineering Department Report No. DD00213.5008 Title: Avionics Modi?cation, on Cessna Aircraft, Model 208B, N508RB, Rev: IR Prepared by: DavidJ Richards Design, Inc. August 2,20l3 PO Box I 127 Hewitt, NJ 0742] (973) 728-8814 This document contains proprietary information of Design, Inc. and neither the document nor said proprietary information shall be published, reproduced, copied, disclosed or used for any purpose without the express written permission of a dub: authorized representative. Design, inc. Report No. Engineering Department Date: March 07, 2012 Rev. 1R Page.2 REVISION CONTROL PAGE ?Rev. Page's" "-7Ai'pproval .. Date IR All Original DJR August 2,2013 This document contains proprietary information of Design, Inc. and neither the document nor said proprietary information shall be published, reproduced, copied, disclosed or used for any purpose without the express written permission of a tin! authorized representative. Design, Inc. Report No. Engineering Department Date: March 07, 2012 Rev. IR Page.3 TABLE OF CONTENTS REFERENCE: .. 6 SUMMARY: .. 7 1.0 TASK: .. 7 1.1 DOCUMENTS .. 7 1.2 ELECTRICAL LOAD ANALYSIS: .. 7 3.0 AIRCRAFT CERTIFICATION BASIC: .. 7 This document contains proprietary information of Design, Inc. and neither the document nor said proprietary information shall be published, reproduced, copied, disclosed or used for any purpose without the express written permission of a duly authorized 0&0 representative. Design, Inc. Report No. Engineering Department Date: March 07, 2012 Rev. Page}; Sec. 23. I35 I General. (3) Electrical system capacity. Each electrical system must be adequate for the intended use. In addition?- (1) Electric power sources, their transmission cables, and their associated centrol and protective devices, must be able to furnish the required power at the proper voltage to each load circuit essential for safe Operation; and (2) Compliance with paragraph of this section must be shown as follows-- For normal, utility, and acrobatic category airplanes, by an electrical load analysis or by electrical measurements that account for the electrical loads applied to the electrical system in probable combinations and for probable durations; and (ii) For commuter category airplanes, by an electrical load analysis that accounts for the electrical loads applied to the electrical system in probable combinations and for probable durations. Function. For each electrical system, the following apply: (1) Each system, when installed, must be-- Free from hazards in itself, in its method of operation, and in its effects on other parts ofthe airplane; (ii) Protected from fuel, oil, water, other detrimental substances, and mechanical damage; and So designed that the risk of electrical shock to crew, passengers, and ground personnel is reduced to a minimum. Electric power sources must function properly when connected in combination or independently. (3) No failure or malfunction of any electric power source may impair the ability of any remaining source to supply load circuits essential for safe operation. (4) In addition, for commuter category airplanes, the following apply: Each system must be designed so that essential load circuits can be supplied in the event of reasonably probable faults or Open circuits including faults in heavy current carrying cables; (ii) A means must be accessible in ?ight to the ?ight crewmembers for the individual and collective disconnection of the electrical power sources from the system; The system must be designed so that voltage and frequency, if applicable, at the terminals of all essential load equipment can be maintained within the limits for which the equipment is designed during any probable operating conditions; (iv) If two independent sources of electrical power for particular equipment or systems are required, their electrical energy supply must be ensured by means such as duplicate electrical equipment, throw over switching, or multichannel or loop circuits separately routed; and For the purpose of complying with paragraph of this section, the distribution system includes the distribution busses, their associated feeders, and each control and protective device. (0) Generating system. There must be at least one generator/alternator if the electrical system supplies power to load circuits essential for safe operation. In addition-- (I) Each generator/alternator must be able to deliver its continuous rated power, or such power as is limited by its regulation system. (2) Generator/alternator voltage control equipment must be able to dependably regulate the generator/alternator output within rated limits; Automatic means must be provided to prevent damage to any generator/alternator and adverse effects on the airplane electrical system due to reverse current. A means must also be provided to disconnect each generator/alternator from the battery and other This document contains proprietary information of Design, Inc. and neither the document nor said proprietary information shall be published, reproduced, copied, disclosed or used for any purpose without the express written permission of a duly authorized representative Design, Inc. Report No. Engineering Department Date: March 07, 2012 Rev. IR Page.5 generators/alternators. (4) There must be a means to give immediate warning to the ?ight crew ofa failure of any generator/alternator. (5) Each generator/alternator must have an overvoltage control designed and installed to prevent damage to the electrical system, or to equipment supplied by the electrical system that could result if that generator/alternator were to develop an overvoltage condition. Instruments. A means must exist to indicate to appropriate flight crewmembers the electric power system quantities essential for safe operation. (I) For normal, utility, and acrobatic category airplanes with direct current systems, an ammeter that can be switched into each generator feeder may be used and, if only one generator exists, the ammeter may be in the battery feeder. (2) For commuter category airplanes, the essential electric power system quantities include the voltage and current supplied by each generator. Fire resistance. Electrical equipment must be so designed and installed that in the event of a ?re in the engine compartment, during which the surface ofthe ?rewall adjacent to the ?re is heated to 2,000? for 5 minutes or to a lesser temperature substantiated by the applicant, the equipment essential to continued safe operation and located behind the ?rewall will function satisfactorily and will not create an additional ?re hazard. (0 External power. If provisions are made for connecting external power to the airplane, and that external power can be electrically connected to equipment other than that used for engine starting, means must be provided to ensure that no external power supply having a reverse polarity, or a reverse phase sequence, can supply power to the airplane's electrical system. It must be shown by analysis, tests, or both, that the airplane can be operated safely in VFR conditions, for a period of not less than ?ve minutes, with the normal electrical power (electrical power sources excluding the battery and any other standby electrical SOurces) inoperative, with critical type fuel (from the standpoint of ?ameout and restart capability), and with the airplane initially at the maximum certi?cated altitude. Parts ofthe electrical system may remain on if?- single malfunction, including a wire bundle orjunction box ?re, cannot result in loss ofthe part turned off and the part turned on; and (2) The parts turned on are electrically and mechanically isolated from the parts turned off. Amdt. 23-49, Eff. O3/l 1/96 This document contains proprietary information of Design, Inc. and neither the document nor said proprietary information shall be published, reproduced, copied, disclosed or used for an purpose without the express written permission of a duly authorized representative. Design, Inc. Report No. DD002l2.0l2l Engineering Department Date: March 07, 2012 Rev. lR Page.6 Sec. 23.1357 Circuit protective devices. Protective devices, such as fuses or circuit breakers, must be installed in all electrical circuits other than-- Main circuits of starter motors used during starting only; andl (2) Circuits in which no hazard is presented by their omission. A protective device for a circuit essential to ?ight safety may not be used to protect any other circuit. Each resettable circuit protective device ("trip free" device in which the tripping mechanism cannot be overridden by the operating control) must be designed so that-- (1) A manual operation is required to restore service after tripping; and (2) lfan overload or circuit fault exists, the device will open the circuit regardless ofthe position of the operating control. lfthe ability to reset a circuit breaker or replace a fuse is essential to safety in flight, that circuit breaker or fuse must be so located and identified that it can be readily reset or replaced in ?ight. For fuses identified as replaceable in ?ight-- There must be one spare of each rating or 50 percent spare fuses of each rating, whichever is greater; and (2) The spare fuse(s) must be readily accessible to any required pilot. Amdt. 23?43, 05/lO/93 RE E: 14 CFR Part 23. 23.1351 23.1357(a) This document contains proprietary information ofD&D Design, Inc. and neither the document nor said proprietary information shall be published. reproduced, copied, disclosed or used for any purpose without the express written permission of a duly authorized representative. Design, Inc. Report No. DD00212.0I2I Engineering Department Date: March 07, 2012 Rev. IR Page] SUMMARY: This report covers the installation ofTechnisonic Industries Limited Model TDFM-7000 multiband transceiver and Mission +28 Power Bus on a Cessna model 208B. This report is to support a major alteration installed under FAA form 337. This report covers the installation of upgraded avionics modi?cation on a Cessna Model 2088, s/n 20885008. This report is to support an amended major alteration installed under FAA form 337. 1.0 TASK: The Technisonic Industries Limited Model TDFM-7000 multiband transceiver was installed in accordance with Technisonic Industries Limited installation manual 05RE3 75, Rev Issue 3. The Mission power bus (+28Vdc) is controlled by a remote switch "Mission located in the existing pilots switch panel. The current load is Samps. 1.1 DOCUMENTS Pro Star Wiring Document: 2976, dated August 1,2013, Rev. IR Pro Star Wiring Document: 2979, dated August l,20l 3, Rev. IR 1.2 ELECTRICAL LOAD ANALYSIS: PAR 23. I 351 This Electrical load statement identi?es loads that have been removed or added to the aircraft as a result of an alteration. These listed loads are calculated based on the maximum valve published in the manufacture?s technical manual. A) REMOVED LOAD: None B) ADDED LOAD Mission Bus Item . Amps Per Number CB Tltle Unit 1* 5.00 Total Load 5.00 C) CONCLUSION: (Minor Change) Addition loads to Main Bus will not exceed the demand. 3.0 AIRCRAFT CERTIFICATION BASIC: CERTIFICATION BASIS This document contains proprietary information of 0&0 Design, Inc. and neither the document nor said proprietary information shall be published, reproduced, copied, disclosed or used for any purpose without the express written permission of a duly authorized representative. Design, Inc. Report No. Engineering Department Date: March 07, 2012 Rev. Page.8 A37CE, Revision 20, Cessna Aircraft Company, June 20,2013 This document contains proprietary information of Design, Inc. and neither the document nor said proprietary information shall be published, reproduced, copied, disclosed or used for any purpose without the express written permission of a duly authorized representative. U.S. DEPARTMENTOF TRANSPORTATION FEDERAL AVIATION ADMINSTRATION 1. DATE STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 05 August 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE fAirpIane. Radio, Helicopter, etc.) 5. NAME OF APPLICANT Cessna 2088 Airplane Pro Star Aviation Londonderry. NH LIST OF DATA 6. IDENTIFICATION 7. TITLE Initial Release Structural Analysis, Interior Recon?guration and Mission Console Cessna 2088 Aircraft June 5. 2013 Initial Release Structural Analysis. Retractable Camera Mount Installation Cessna 2088 Aircraft June 28, 2013 Rev RCM AND CAGE INSTALLATION 18 Jul 13 Rev CONSOLE INSTALLATION 05 AUG 13 P63-008-203 Rev CONSOLE SHELL PLATES AND BRACKETS 05 AUG 13 PBS-008406 Rev IR BULKHEAD MODIFICATION 05 AUG 13 NOTES: 1. Applicable to TCDs 2. Only the structural aspects of the above listed data are approved herein. Electrical. Flammability and Aerodynamic aspects may require separate approval. 3. 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 4. This form does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire installation. 3. PURPOSE OF DATA: TO support a major alteration to a Cessna 2088 serial number 20885008 (registration N508RB) only, by FAA repair station P6UR006Y. 9. APPLICABLE REQUIREMENTS (List speci?c sections) 14 CFR Part 23, Subparts and D, paragraphs: 23.301 [Amdt 23.43} 23.303 [Amdt 23-01 23305 [Amdt 23-45] 23.307(a) [Amdt 230] 23.601 [Amdt 23.0} 23.603 [Amdt 23-23] 23.605(a) [Amdt 23.231 23.607 [Amdt 23.17] 23.609 [Amdt 230] 23.611 [Amdt 23-7] [Amdt 23-23] 23-7] 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 NIA have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed. :1 Recommend approval of these data i (We) Therefore Approve these data 11. 12. DESIGNATION 13. CLASSIFICATIONIS) Lonnie F. Davidson 1} BERT-833075-NIVI STRUCTURES v1 FAA Form 8110-3 P63-008 U.S. DEPARTMENTOF TRANSPORTATION FEDERAL AVIATION ADMINSTRATION 1. DATE STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 06 August 2013 AIRCRAFT 0R AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Airplane. Radio. Helicopter. etc.) 5. NAME OF APPLICANT Cessna 2088 Airplane Pro Star Aviation Londonderry, NH LIST OF DATA 6. IDENTIFICATION 7. TITLE P63-008-108 Rev IR FEED THROUGH INSTALLATION 06 Aug 13 NOTES: 1, Applicable to TCDS 2. Only the structural aspects of the above listed data are approved herein. Electrical aspects may require separate approval. 3. This approval is for engineering design data only, and is not an installation approval. It indicates the date listed above demonstrates compliance only with the regulations speci?ed by paragraph and subparagraph listed below as 4. This form does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire installation. 3. PURPOSE or DATA: To support a major alteration to a Cessna 2088 serial number 20885008 (registration N508RB) only. by FAA repair station P6UR006Y. 9. APPLICABLE REQUIREMENTS (List speci?c sections) 14 CFR Part 23, Subparts and D, paragraphs: 23.301 [Amdt 23-48] 23.303 [Amdt 23-0] 23.305 [Amdt 23?45] 23.307(a) [Amdt 23-0] 23.601 [Amdt 23-0] 23.603 [Amdt 23-23] 23.605(a) [Amdt 23?23] 23.607 [Amdt 23-17] 23.609 [Amdt 23-0] 23.611 [Amdt 23-7] [Amdt 23-23] 23-7] 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 NIA have been examined in accordance with established procedures and found to comply with applicable requirements of the Ainvorlhiness Standards listed. Recommend approval of these data I Therefore Approve these data 11. OF DESIGNATED ENGINEERING 12. DESIGNATION 13. CIASSIFICATIOMS) Lonnie F. Davidson DERT-B33075-NM STRUCTURES FAA Form 8110-3 PBS-008 U.S. DEPARTMENTOF TRANSPORTATION FEDERAL AVIATION ADMINSTRATION 1. DATE STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 06 August 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Airplane. Radio, Helicopter, etc.) 5. NAME OF APPLICANT Cessna 2088 Airplane Pro Star Aviation Londonderry. NH LIST OF DATA 6. IDENTIFICATION 7. TITLE P63-008-003 Initial Release Structural Analysis. Interior Recon?guration and Mission Console Cessna 2088 Aircraft June 5, 2013 P63-008-103 Rev CONSOLE INSTALLATION 06 AUG 13 NOTES: 1. Applicable tO TCDS 2. Only the structural aspects of the above listed data are approved herein. Electrical. Flammability and Systems aspects may require separate approval. 3. 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 4. This form does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire installation. 8. PURPOSE OF DATA: To support a major alteration to a Cessna 2088 serial number 208B5008 (registration N508RB) only, by FAA repair station PSURDOESY. 9. APPLICABLE REQUIREMENTS (List speci?c sections) 14 CFR Part 23, Subparts and D, paragraphs: 23.301 [Amdt 2343] 23.303 [Amdt 230] 23.305 [Amdt 23-45] 23.307(a) [Amdt 230] 23.601 [Amdt 230] 23.603 [Amdt 23-23] 23.605(a) [Amdt 2323] 23.607 [Amdt23-17] 23.609 [Amdt 230] 23.611 [Amdt 23?7] [Amdt 23?23] 23-7] 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 NIA 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 11. OF ENGINEERING 12, DESIGNATION 13. CLASSIFICATIONS) Lonnie F. Davidson STRUCTURES I FAA Form 8110-3 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS U.S. DEPARTMENTOF TRANSPORTATION FEDERAL AVIATION ADMINSTRATION 1. DATE 28 June 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE {Airpiane. Radio. Helicopter, etc.) 5. NAME OF APPLICANT Cessna 2088 Airptane Pro Star Aviation Londonderry, NH LIST OF DATA 6. IDENTIFICATION 7. TITLE PBS-008003 Initial Release June 5, 2013 P63-001-005 Initial Release June 28, 2013 Rev PBS-008403 Rev A 12 Jun 13 P63-008-104 Rev IR 10 Jun 13 Rev 3-21?13 Structural Analysis, Interior Recon?guration and Mission Console Cessna 2088 Aircraft Structural Analysis. Retractable Camera Mount installation Cessna 2088 Aircraft POD MODIFICATION CAGE. RCM AND DOOR ASSEMBLY CONSOLE INSTALLATION CONSOLE EQUIPMENT INSTALLATION RCM CONTROL PANEL ASSEMBLY NOTES: 1. Applicable to TCDS 2. Only the structural aspects of the above listed data are approved herein. Electrical, Flammability and Aerodynamic aspects may require separate approval. 3, 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 4. This form does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire installation. 8. PURPOSE OF DATA: To support a major alteration to a Cessna 2088 serial number 20885008 (registration N508RB) only, by FAA repair station PBUROOBY. 9. APPLICABLE REQUIREMENTS (List speci?c sections) 14 CFR Part 23, Subparts and 8, paragraphs: 23.301 [Amdt23-48] 23.601 [Amdt 23-0] 23.609 [Amdt 23-0] 23.303 [Amdt 23-0] 23.603 [Amdt 23-23] 23.611 [Amdt 23?7] 23.305 [Amdt 23-45} 23.605(a) [Amdt 23-23] [Amdt 23?23] 23.307(a) [Amdt 23-0] 23.607 [Amdt23~17] 23?7} 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 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 IE Approve these data 11: OF DESIGNATED ENGINEERING 12. DESIGNATION 13. CLASSIFICATIONS) BERT-833075-NM STRUCTURES Lonnie F. Davidson FAA Form 8110-3 P63-008 U.S. DEPARTMENTOF TRANSPORTATION FEDERAL AVIATION ADMINSTRATION 1. DATE STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 06 August 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Airplane, Radio. Helicopter. etc.) 5. NAME OF APPLICANT Cessna 2088 Airplane Pro Star Aviation Londonderry, NH LIST OF DATA 6. IDENTIFICATION 7. TITLE P63-008-006 Rev IR Structural Analysis - P63-008-106 Feed Through Installation - Cessna C2088 06 Aug 13 NOTES: 1. Applicable to TCDS 2. Only the structural aspects of the above listed data are approved herein. 3. 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 4. This form does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements f0r the entire installation. 8. PURPOSE or oA'rA: To support a major alteration to a Cessna 2088 serial number 20885008 (registration N508R8) only. by FAA repair station P6UR006Y. 9. APPLICABLE REQUIREMENTS (List speci?c sections) 14 CFR Part 23, Subparts and D, paragraphs: 23.301 [Amdt23?48] 23.303 [Amdt23-0] 23.305 [Amdt23-45] 23.307(a) [Amdt23-O] 23.601 [Amdt23-0] 23.603 [Amdt23-23] 23.605(a) [Amdt23?23] 23.607 [Amdt23-17] 23.609 [Amdt 23-0] 23.611 [Amdt 23-7] [Amdt 23?23] 23-7] 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accmdance with conditions and limitations of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered NIA have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed. El Recommend approval of these data I (We) Therefore Approve these data 11. SIGNATURES) OF DESIGNATED 12. DESIGNATION 13. Lonnie F. Davidson DERT-833075-NM STRUCTURES FAA Form 8110-3 P63-008 us. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION Ju y? 08 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft. Engine. Propeller, etc.) 5. NAME OF APPLICANT Cessna 2088 Aircraft Pro Star Aviation 5 Industrial Drive Londonderry, NH 03053 LIST OF DATA s. IDENTIFICATION 7. TITLE Genesis 3 Engineering Drawing; RETRACTABLE CAMERA MOUNT SYSTEM-WIRING INTERCONNECT Rev: A Date: April 08 2013 E0: E01 RETRACTABLE CAMERA MOUNT INTERCONNECT Rev: A Date: June 27 2013 Drawing: G3-A0000-K01 WIRE HARNESS ASSY Rev: A Date: April 22 2013 Drawing: WIRE HARNESS ROUTING Rev: IR Date: April 2 2013 I End of Data --End of N03353- 1. This approval is for engineering design data only. It indicates the data listed above demonstrates compliance only with the regulations speci?ed by paragraph and subparagraph listed below as "Applicable Requirements". 2. Electrical aspects are approved only. Structural and flammability aspects are not included. 3. Compliance with additional regulations not listed here may be rectuired. 4. This form does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. 5. This 8110-3 approval is for engineering design data only and does not constitute installation approval. 8. PURPOSE OF DATA In support of a major alteration to SIN 20885008 (Registration N508RB) by FAA repair station certi?cate number P6UR006Y. Data approval only, does not constitute approval of the physical installation. 9. APPLICABLE REQUIREMENTS (List speci?c sections) Federal Aviation Regulations [amendment level In brackets] 14 CFR 23.1301 (23-20] 14 CFR 23.135? [23-43] 14 CFR 23.1365 [23-49] 14 CFR 23.1367 [23-0] 10. - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Part 183: date listed above and on attached sheets numbered NIA have been examined in accordance with established procedures and Iound to comply with applicable requirements of the Airworthiness Standards listed. Recommend approval of these data I Me) Therefore g?tpprove these data 11. SIGNATUREMOF DESIGNATED ENGINEERING REPRESENTATIVE-Q: 12. DESIGNATION 13. CLASSIFICATIONEX Nigel Stewart DERT-BB2571-NE Systems Equipment- Electrical FAA Form 8110-3 (03f10) SUPERSEDES PREVIOUS EDITION .W. Hurt-h i cups?n war a PRO STAR A 1 A C) MANCHESTER AIRPORT 5 INDUSTRIAL DRIVE LONDONDERRY, NH 03053 FAA P6UR006Y FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT ".mxn INSTALLATION OF THE MISSIONS POWER SYSTEM CESSNA 2083 Serial Number: 20835008 Registration: N508RB This supplement must be attached to the FAA approved Aircraft Flight Manual when this airplane is modified by the installation of the Missions Power System in accordance with FAA Form 337 dated 08 - 06 13 The information contained herein supplements or supersedes the basic Aircraft Flight Manual, only in those areas listed herein. For limitations, procedures, and performance information, not contained in this supplement, consult the basic Aircraft Flight Manual. PRO STAR AVIATION PROPRIETARY INFORMATION This document contains Proprietary Information of Pro Star Aviation, LLC. Disclosure to others. and the use or copying by others, without the express authorization of Pro Statr Aviation, LLC is strictly prohibited. SHEET 1 of FAA APPROVED DATE DOCUMENT NUMBER 21179-FMS-01 REVISION IR PRO STAR AVIATION. LLC. AIRPLANE FLIGHT MANUAL SUPPLEMENT NH 03053 CESSNA 2083 MISSIONS POWER SYSTEM US. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION August 06 201 3 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft, Engine, Propeller, etc.) 5. NAME OF APPLICANT Cessna 2088 Airplane Pro Star Aviation LIST OF DATA 6, IDENTIFICATION 7. TITLE Pro Star Aviation Document 21179-FMS-01 FAA Approved Airplane Flight Manual Supplement Revision IR Installation of the Missions Power System The approval of this Airplane Flight Manual Supplement is valid for Cessna 2088, serial number 20885008 only 3. PURPOSE or DATA In support of a Major Alteration Q. APPLICABLE REQUIREMENTS (List speci?c sections) 14CFR Part 23 (Through Amendment 23-55) 23.1581; 23.15850) 10. CERTIFICATION Under authority vested by direction of the Adminlsuator and in accordance with conditions and llmitatlons of appointment under 14 CFR Part 183, date listed above and on attached sheets numbered have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed. Recommend approval 0! these data I (We) Therefore Approve these data 11. OF DESIGNATED ENGINEERING REPRESENTATIVES) 12. DESIGNATION 13. CLASSIFICATIONS) BERT-5001 iz-CE Flight Analyst Mark D. Haycock FAA Form 8110-3 (03l10) SUPERSEDES PREVIOUS EDITION ELECTRONIC FORMAT (4-11) SHEET 2 of 6 FAA APPROVED DATE DOCUMENT NUMBER REVISION IR PRO STAR AVIATION, LLC. AIRPLANE FLIGHT MANUAL SUPPLEMENT LONDONDERRY, NH 03053 CESSNA 2083 MISSIONS POWER SYSTEM REVISION INDEX Revision Date Sheets Description Approved By IR All Initiai Release MD Haycock Note: Changes in document for the latest revision are indicated by a line in the left margin adjacent to change, except on the cover page, revision index, table of contents, header, and footer. SHEET 3 of 6 FAA APPROVED DATE DOCUMENT NUMBER 21179-FMS-01 REVISION IR PRO STAR AVIATION. LLC. AIRPLANE FLIGHT MANUAL SUPPLEMENT LONDONDERRY, NH 03053 CESSNA 2083 -- MISSIONS POWER SYSTEM TABLE OF CONTENTS COVER SHEET ..1 TABLE OF CONTENTS ..4 1. GENERAL ..5 2. LIMITATIONS ..5 3. EMERGENCY PROCEDURES ..5 3A. Missions System Malfunction ..5 3B. MISSION CTL Circuit Breaker Trips ..6 BC. Electrical Fire in Flight ..6 4. NORMAL PROCEDURES .. ..6 4A. Operations ..6 5. PERFORMANCE ..6 6. WEIGHT AND BALANCE ..6 LIST OF FIGURES Figure 3.1 Location of MISSION CTL Circuit Breaker (Pilot?s Circuit Breaker Figure 4.1 Location of MISSION PWR Switch (Pilot?s Switch Panel) ..6 SHEET 4 of 6 FAA APPROVED DATE 3 DOCUMENT NUMBER 21179-FMS-01 REVISION IR PRO STAR AVIATION. LLC. AIRPLANE FLIGHT MANUAL SUPPLEMENT LONDONDERRY. NH 03053 CESSNA 2083 - MISSIONS POWER SYSTEM 1. GENERAL The Missions Power System is installed to provide 28 VDC electrical power to the Missions Console for missions capable equipment. As installed, the system includes: - Relay (Located in LH Nose Junction Box) - Fuse Block and 60 Ampere Fuse (Located in LH Nose Junction Box) Switch (Located on Pilot?s instrument Panel) - Associated wiring and interface connections As installed, the Missions Power System provides 28 VDC electrical power to the LH Sidewall Disconnect, which is interfaced to the Missions Console for mission capable equipment. 2. LIMITATIONS No change to basic AFM. 3. EMERGENCY PROCEDURES The Mission System is protected by the following circuit breaker and fuse. . 3 MISSION CTL 2 (Circuit Breaker) Pilot?s Cg?:ietlBreaker Avionics Bus 2 60 AMP 60 (Fuse) LH Nose Junction Box 28 VDC Bus Figure 3.1 Location of MISSION CTL Circuit Breaker (Pilot?s Circuit Breaker Panel) 3A. Missions System Malfunction a) Set the MISSION PWR Switch OFF (On the Pilot's Switch Panel). b) Puii (Open) the MISSION CTL Circuit Breaker (Located on the Pilot?s Circuit Breaker Panel). SHEET 5 of 6 FAA APPROVED DATE DOCUMENT NUMBER 21179-FMS-01 REVISION IR PRO STAR AVIATION. LLC. AIRPLANE FLIGHT MANUAL SUPPLEMENT LONDONDERRY. NH 03053 CESSNA 2088 MISSIONS POWER SYSTEM 33. MISSION CTL Circuit Breaker Trips a) Set the MISSION PWR Switch OFF (On the Pilot?s Switch Panel). b) Pull (Open) the MISSION CTL Circuit Breaker. NOTE: Do not close (reset) the circuit breakers more than once and only after 2 minute cool off penod. 3C. Electrical Fire in Flight a) Refer to the Cessna Model 2088 Airplane Flight Manual (Section 3, Page 3-19). 4. NORMAL PROCEDURES 4A. Operations a) Set the MISSION PWR Switch ON, to allow the Missions Console to be powered up. D) Set the MISSION PWR Switch OFF, to discontinue power to the Missions Console. Figure 4.1 Location of MISSION PWR Switch (Pilot?s Switch Panel) 5. PERFORMANCE No change to basic AFM. 6. WEIGHT AND BALANCE No change to basic SHEET 6 of 6 FAA APPROVED DATE DOCUMENT NUMBER 21179-FMS-01 REVISION IR 0 STAR MANCHESTER AIRPORT 5 INDUSTRIAL DRIVE LONDONDERRY, NH 03053 FAA P6UR006Y INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 1 Installation of the Missions Equipment Cessna 208B 208B5008 N508RB PRO STAR AVIATION PROPRIETARY INFORMATION This document contains Proprietary Information of Pro Star Aviation, LLC. Disclosure to others, and the use or copying by others, without the express authorization of Pro Star Aviation, LLC is strictly prohibited. SHEET 1 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 REVISION INDEX INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2088 - MISSIONS EQUIPMENT REVISION DATE SHEET DESCRIPTION PREPARED REVIEWED BY IR 08-06-13 ALL Original Daren . Remmert Installation Manager George A. Brown Avionics Technician Note: Changes in document for the latest revision are indicated by a line in the left margin adjacent to change, except on the cover page, header and footer. SHEET 2 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRYE NH 03053 CESSNA 2088 a MISSIONS EQUIPMENT TABLE OF CONTENTS COVER SHEET ..1 REVISION INDEX ..2 TABLE OF CONTENTS ..3 1. INTRODUCTION .. 5 1.1 Aircraft Description ..5 1.2 Scope ..5 1.3 Applicability ..5 1.4 De?nitions and Abbreviations ..5 1.5 Precautions ..5 1.6 Units of Measure ..5 1.7 Reference Publications ..5 1.8 Distribution ..6 2. DESCRIPTION .. 7 2.1 Missions Equipment ..7 2.2 Circuit Protection ..8 3. CONTROL and OPERATION INFORMATION .. 9 4. SERVICING INFORMATION .. 9 5. MAINTENANCE INSTRUCTIONS .. 10 6. INSPECTIONS .. 11 7. TROUBLESHOOTING INFORMATION .. 11 8. REMOVAL AND INSTALLATION INFORMATION .. 11 8.1 Missions Power System Components ..11 8.2 Comant 800 Antenna ..11 8.3 Comant CI-292-3 VHF Antenna ..12 8.4 Technisonic TDFM-7000 ..12 8.5 NAT-247 Audio Mixing Ampli?er ..13 8.6 Iridium Antenna ..13 8.7 P-2 Audio Advisory Computer ..14 8.8 AAS Annunciator Switch ..14 8.9 IMT Skymaster TX ..14 8.10 Downlink Antenna ..15 8.11 Downlink Controller ..15 8.12 L-3 MX-15HDI Camera ..16 8.13 GPS Antenna ..16 8.14 L-3 MX Hand Controller ..17 8.15 Churchill Navigator ..17 8.16 Boland Monitor ..17 8.17 AJA HA5 Converter ..18 8.18 AJA Ampli?er ..18 8.19 Pulse Balun Adapter ..19 8.20 Teradek Cube ..19 8.21 KGS LT-53 Light Dimmer Power Supply ..19 9. SPECIAL INSPECTION REQUIREMENTS .. 20 10. APPLICATION OF PROTECTIVE TREATMENTS .. 20 11. DATA .. 20 12. SPECIAL TOOLS .. 20 13. COMMUTER CATEGORY AIRCRAFT .. 20 SHEET 3 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA ZOBB MISSIONS EQUIPMENT 14. RECOMMENDED OVERHAUL PERIODS .. 20 15. AIRWORTHINESS LIMITATIONS .. 20 16. ASSISTANCE .. 20 17. IMPLEMENTATION AND RECORD KEEPING .. 20 18. Diagrams .. 21 LIST OF TABLES Table 2.1 Circuit Breakers .. 8 Table 4.1 Component Data .. 10 Table 18.1 - Mechanical and Electrical Diagrams .. 21 SHEET 4 of 39 DATE 08-06-13 DOCUMENT NUMBER REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2083 MISSIONS EQUIPMENT 1. INTRODUCTION 1.1 Aircraft Description Make: Cessna Model: 2088 Serial Number: 20885008 1.2 Scope This document identi?es the Instructions for Continued Airworthiness for the modi?cation of the above aircraft by the installation of the Missions Equipment. This ICA satisfies the requirements of 14 CFR 25.1529. 1.3 Applicability This ICA applies to Cessna 208B, serial number 208B5008 incorporating the installation of the Missions Equipment. 1.4 Definitions and Abbreviations The following terminology is used within this document: 0 AC Advisory Circular 0 AFMS Airplane Flight Manual Supplement - CFR Code of Federal Regulations 0 FS Fuselage Station 0 Gigahertz ICA Instructions for Continued Airworthiness 0 IPC Illustrated Parts Catalog 0 IR Initial Revision - LRU Line Replaceable Unit - Megahertz MM Maintenance Manual 0 PSA Pro Star Aviation - RCM Retractable Camera Mount - SRM Structural Repair Manual 0 VHF Very High Frequean 0 VDC Volts Direct Current 0 WDM Wiring Diagram Manual 1.5 Precautions This section is not applicable. 1.6 Units of Measure This section is not applicable. 1.7 Reference Publications 1. 14 CFR Part 23 AinNorthiness Standards: Normal, Utility, Acrobatic and Commuter Category Air lanes 2. Acceptable Methods, Techniques and Practices Aircraft Inspections and Repair 3. AC 43.13-2B Acceptable Methods, Techniques and Practices Aircraft Alterations 4. AJA HA5 Converter User Manual 5. AJA HD10DA Ampli?er User Manual 6. Boland High Definition User Manual, document 121908 7. Boland Outline Diagram and Mounting Dims, document (3722xx.dwg) 4906, revision A1 SHEET 5 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 1.8 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 208B MISSIONS EQUIPMENT High Definition User Manual, document 121908 Cessna Model 208 Maintenance Manual, revision 26 or later Cessna Model 208 Structural Repair Manual, revision 6 or later Cessna Model 208 Wiring Diagram Manual, revision 10 or later Churchill Installation Diagram, document ARS-SOOC-201210, revision 6 Genesis 3 RCM Operations and Maintenance Manual, document P63-001-019, revision IR IMT Nano Controller Software User Guide, document M27-0001-00A, revision 1.0 IMT SkymasterTX User Manual, document M30-5KTX-1M1, revision 1.0 KGS LT-45 Removal/Installation manual, document 45106, revision L-3 Outline and Installation, MX-ISHDI Turret, document 90187-06, revision L-3 Integration Guide for MX Series Digital Products, document 61684-03, revision NAT-247 Installation and Operation Manual, document 5M247, revision 2.00 Nucomm Access RC User Manual, document M20-00003-00A, revision 1.01 P2 Hardware Installation Manual, document 6601-04, revision Pro Star Aviation electrical drawing 2976, revision IR or later, Missions Power Wiring Diagram Pro Star Aviation electrical drawing 2977, revision IR or later, IMT Downlink Provisions Wiring Diagram Pro Star Aviation electrical drawing 2978, revision IR or later, Ops Console Lighting Wiring Diagram Pro Star Aviation electrical drawing 2979, revision IR or later, TDFM Radio Wiring Diagram Pro Star Aviation electrical drawing 2980, revision IR or later, MX15HDI Camera Provisions Wiring Diagram Pro Star Aviation electrical drawing 2997, revision IR or later, Satphone Provisions Wiring Diagram Pro Star Aviation mechanical drawing P513071, revision IR or later, Installation VHF Whip Antenna Pro Star Aviation mechanical drawing P513072, revision IR or later, Installation GPS Antenna Pro Star Aviation mechanical drawing P513073, revision IR or later, Installation Downlink Antenna Pro Star Aviation mechanical drawing P513074, revision IR or later, Installation Wide Band UHF Antenna Pro Star Aviation mechanical drawing P513075, revision IR or later, Installation, Iridium Antenna Pro Star Aviation mechanical drawing P513076, revision IR or later, Installation, SkymasterTX Pro Star Aviation Missions Power System Airplane Flight Manual Supplement, document 21179- revision IR Pulse Electronics High Frequency Balun Adapter, document M146, revision Technisonic TDFM-7000 Installation and Operating Instructions, document 05RE375, revision 9 Teradek Cube Reference Guide, revision 2 Vivisun LED Switch Data Sheet, document 12-2001-04, revision Note: The current issue is to be assumed if the revision or date of issue is not stated. Distribution The Instructions for Continued Airworthiness is furnished to the owner of this aircraft, modi?ed by the installation of the Missions Equipment. This ICA is to become part of the permanent aircraft records. To revise this ICA, submit the revised ICA along with the original FAA Form 337 to the Aircraft Registration Branch in Oklahoma City. SHEET 6 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 2. DESCRIPTION INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2083 - MISSIONS EQUIPMENT 2.1 Missions Equipment As installed, the Missions Equipment includes provisions for the following systems; 1. Missions Power System a. b. The Mission Power System has been installed to provide 28 VDC power for the mission capable equipment. The system is wired directly from the 28VDC Bus through a Relay/Contactor to power the Missions Console. The power is actuated through the MISSIONS PWR Switch, located in the Pilot?s Switch Panel. The Missions Power circuit is protected by a 60 Ampere Fuse, located in the Electric Power Box, on the Forward LH Firewall. PSA electrical drawing 2976 provides the data necessary for troubleshooting the Missions Power System. 2. Technisonic TDFM-7000 System a. The TDFM-7000 System has been installed to allow the Missions Crew to communicate using VHF and UHF Frequencies. The TDFM-7000 is interfaced to the existing aircraft audio system utilizing COM 3 port. The Technisonic TDFM-7000 System consists of the following components; 1. CI-292-3 VHF Antenna 2. CI-285 800 Antenna 3. TDFM-7000 Transceiver 4. NAT-247 Audio Mixing Ampli?er PSA electrical drawing 2979 provides the data necessary for troubleshooting the TDFM-7000 System. Satellite Phone System Provisions a. The Satellite Phone System Provisions have been installed to provide the operator with a electrical and antenna interface, to allow for the use of a satellite phone. The Satellite Phone System consists of the following components; 1. Iridium Antenna 2. Cable interface for the Iridium Satphone PSA electrical drawing 2997 provides the data necessary for troubleshooting the Satellite Phone System. PSA mechanical drawing P513075 provides the data necessary for replacing the Iridium Antenna. P-2 Camera Retraction Warning System a. The Camera Retraction Warning System has been installed to provide warning to the flight crew that the camera is extended during takeoff and landing, utilizing aural and visual annunciation. The Camera Retraction Warning System consists of the following components; 1. Audio Advisory Computer 2. AAS Annunciator Switch PSA electrical drawing 2980 provides the data necessary for troubleshooting the Camera Retraction Warning System. IMT Downlink System Provisions a. The IMT Downlink System Provisions have been installed to allow the operator the ability of transmitting digitally encoded video signals to a ground facility. The IMT Downlink System consists of the following components; 1. Skymaster Transmitter 2. Sensor Systems 4-8 Antenna SHEET 7 0f 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2083 MISSIONS EQUIPMENT 3. Nucomm Controller PSA electrical drawing 2977 provides the data necessary for troubleshooting the IMT Downlink System. PSA mechanical drawing P813073 provides the data necessary for replacing the Downlink Antenna. PSA mechanical drawing P513076 provides the data necessary for replacing the SkymasterTX. 6. L-3 MX-15HDI Camera System Provisions a. The L-3 MX-15HDI Camera System Provisions have been installed to allow the Operator to display and record high de?nition video from the aircraft. The L-3 MX-15HDI Camera System consists of the following components; L-3 MX-15HDI Camera GPS Antenna L-3 MX Hand Controller Churchill ARSSOO-C Navigator Keyboard Boland Monitor, 20" AJA HA5 Converter AJA HD10DA Amplifier . Balun Adapter (3 each) 10. Teradek Cube HD-SDI Encoder PSA electrical drawing 2980 provides the data necessary for troubleshooting the L-3 MX- 15HDI Camera System. PSA mechanical drawing P513072 provides the data necessary for replacing the GPS Antenna. 7. Ops Lighting System Provisions a. The Ops Lighting System Provisions have been installed to allow the operator of the Missions console to adjust the lighting of the console equipment under various lighting conditions. The Ops Lighting System consists of the following components; 1. KGS LT-45 Lighting Dimmer Supply 2. Potentiometer PSA electrical drawing 2978 provides the data necessary for troubleshooting the Ops Lighting System. 2.2 Circuit Protection Refer to Table 2.1 for the circuit protection of the Missions Equipment. Table 2.1 Circuit Breakers Missions Relay MISSION CT 2 Amperes 28 VDC Avionics Bus 2 Pilot Circuit Breaker Panel . . Mission Console Circuit TDFM-7000 TDFM 7.5 Amperes 28 VDC Bus Breaker Panel NAT?Z?ng'figg?rM'x'?g AUDIO MIXER 2 Amperes 28 VDC Avionics Bus 2 Pilot Circuit Breaker Panel Satphone Interface SATPHONE 2 Amperes 28 VDC Avionics Bus 2 Pilot Circuit Breaker Panel Audio Advisory Computer CAMERA WARN 2 Amperes 28 VDC Bus 1 Pilot Circuit Breaker Panel . . Mission Console Circuit SkymasterTX DOWNLINK 10 Amperes 28 VDC Mi55ion Bus Breaker Panel SHEET 8 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2083 - MISSIONS EQUIPMENT . . Mission Console Circuit KGS LT-45 OPS LITES 5 Amperes 28 VDC Bus Breaker Panel . . Mission Console Circuit L-3 Camera MX 15 25 Amperes 28 VDC Bus Breaker panel Churchill . . Mission Console Circuit Navigator MAP 10 Amperes 28 VDC Bus Breaker Panel . . . Mission Console Circuit Boland Monitor, 20 MONITOR 10 Amperes 28 VDC BUS Breaker Panel Teradek Cube HD-SDI VIDEO STREAM 10 Amperes 28 VDC Mission BUS Console Encoder Breaker Panel 3. CONTROL AND OPERATION INFORMATION 1. Missions Power System a. For operating and control information of the Missions Power System, reference the Missions Power System AFMS, listed in section 1.7. Technisonic TDFM-7000 System a. For operating and control information TDFM-7000 System, reference the Technisonic TDFM- 7000 Installation and Operating Instructions and NAT-247 Installation and Operation Manual, listed in section 1.7. Satellite Phone System Provisions a. Connect the Satellite Phone to the power and antenna connector, located in the Glove Box. b. For operating and control information of the Satellite Phone System, reference the operator?s instructions for the speci?c Satellite Phone being used. P-2 Camera Retraction Warning System a. For operating and control information of the Camera Retraction Warning System, reference the Audio Advisory System Operator?s Manual, listed in section 1.7. IMT Downlink System Provisions a. For operating and control information of the Downlink System, reference the IMT SkymasterTX User Manual and Nucomm Access RC User Manual, listed in section 1.7. Camera System Provisions a. For operating and control information of the L-3 reference the Integration Guide for MX Series Digital Products, listed in section 1.7. b. For operating and control information of the Boland Monitor, reference the Boland High De?nition User Manual, listed in section 1.7. c. For operating and control information of the Teradek Cube, reference the Teradek Cube Reference Guide, listed in section 1.7. Ops Lighting System Provisions A. For operating and control information of the Ops Lighting System, rotate the Dimmer Control on the Missions Console to adjust the lighting on the controllers in the Missions Panel to a comfortable level for the operator. 4. The Missions Equipment do not require any routine servicing. In the event of a component failure, return the affected unit to the manufacturer or an approved manufacturer?s authorized repair station. Refer to Table 4.1 for the component data for the Missions Equipment SHEET 9 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Table 4.1 Component Data CESSNA 208B MISSIONS EQUIPMENT Missions Relay 6041H202 Peerless Electifrg?g?r? LH Fuse Block/60 Ampere Fuse Cessna LH Comant CI-285 800 Antenna CI-285 Cobham Lower Fuselage, at PS 391.60 Comant CI-292 VHF Antenna CI-292-3 Cobham Lower Fuselage, at FS 404.00 Technisonic TDFM-7000 Technisonic Industries Mission Console, at FS 174.50 NAT-247 Audio Mixing Ampli?er NAT247 Northern Airborne Technology ?$332333? She'f' at Antenna, Iridium 1616-880-01 Honeywell Upper Fuselage, at FS 181.20 Audio Alert System 6601-04 P2 Top of Glove Box, at FS 113.00 Annunciator Switch, AAS 2110391 Vivisun ?Strulnl?gf?gopaneh at F5 IMT Skymaster'lX 65-SKIX-3-SD4-M02-B3-FP413 IMT Aft Fuselage, at FS 422.60 Downlink Antenna 565-5366-60 Sensor Systems Lower Fiste'Fasgj?ggss Pane" Downlink Controller 900-ARC-0003 IMT Mission Console, at FS 174.50 MX-15HDI Model 80224 42580-84 L-3 Cargo Pod, at FS 239.75 Antcom GPS Antenna Antcom Upper Fuselage, at FS 160.00 L-3 MX Hand Controller 42228-06 L-3 Mission Console, at FS 174.50 Churchill Navigator ARS-SOOC Churchill Mission Console, at FS 174.50 Boland View Port 20 Monitor Boland Mission Console, at FS 174.50 HDMI to HD-SDI Converter AJA HA5 AJA Video Systems Mission Console, at FS 174.50 HD-SD Video Ampli?er AJA HD10DA AJA Video Systems Mission Console, at FS 174.50 Balun (3 each) HFBO751008 L-3 Af?t side of RCM, at FS 252.00 Teradek HD-SDI Encoder 10-0155 Teradek Mission Console, at FS 174.50 KGS LT-45 Rheostat Control LT-45 KGS Electronics Mission Console, at FS 174.50 5. MAINTENANCE INSTRUCTIONS Design and manufacturing of the Missions System components allow for ?On Condition Maintenance.? On condition maintenance means that no periodic service requirements are necessary to maintain continued airworthiness of the system. No maintenance is required until the equipment does not perform the intended function. Unscheduled maintenance may include upgrade of the individual system program software contained in the If an LRU is replaced and/or the software changed, the configuration settings should be checked and amended as necessary, in accordance with the instructions contained in the applicable manuals. LRU replacement can be accomplished in the ?eld. Refer to the section 8 of this document for additional details. After replacing a defective LRU with a serviceable LRU, consult the appropriate manual, listed in section 1.7, for operationally testing the affected system for return to service. SHEET 10 of 39 DOCUMENT NUMBER 21179-ICA-01 REVISION IR DATE 08-06-13 PRO STAR AVIATION, LLC. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA 2083 MISSIONS EQUIPMENT 6. INSPECTIONS Inspect all installed items (including the wiring and hardware) for damage, excessive wear, security, chafing, corrosion, delamination, etc. Inspect these items at the routine inSpection intervals that apply to the aircraft (Le. 100 hour inspection, annual inspection or other scheduled inspection that may be applicable). 7. TROUBLESHOOTING INFORMATION 1. Missions Power System A. For troubleshooting the Missions Power System, refer to the Cessna 208 MM, chapter 24 (listed in section 1.7) and Pro Star Aviation electrical drawing 2976 (in section 18). 2. Technisonic TDFM-7000 System A. For troubleshooting the TDFM-7000 System, refer to the Technisonic TDFM-7000 Installation and Operating Instructions (listed in section 1.7) and Pro Star Aviation electrical drawing 2979 (in section 18). 3. Satellite Phone System Provisions A. For troubleshooting the Satellite Phone System, refer to Pro Star Aviation electrical drawing 2997 (in section 18). 4. Camera Retraction Warning System A. For troubleshooting the P2 Camera Retraction Warning System, refer to the P2 Hardware Installation Manual (listed in section 1.7) and Pro Star Aviation electrical drawing 2980 (in section 18). 5. IMT Downlink System Provisions A. For troubleshooting the IMT Downlink System, refer to Pro Star Aviation electrical drawing 2977 (in section 18). 6. L-3 MX-15HDI Camera System Provisions A. For troubleshooting the L-3 MX-15HDI Camera System, refer to the L-3 Integration Guide for MX Series Digital Products and Pro Star Aviation electrical drawing 2980 (in section 18). 7. Ops Lighting System Provisions A. For troubleshooting the Ops Lighting System, refer to Pro Star Aviation electrical drawing 2978 (in section 18). 8. Component troubleshooting A. When troubleshooting system components, refer to the applicable manual and/or manufacturer?s technical support. Return defective components to the manufacturer or appropriately rated repair facility for proper repair and return to service. 8. REMOVAL AND INSTALLATION INFORMATION 8.1 Missions Power System Components 1. Removal and Installation a. Refer to the Cessna 208 MM, chapter 24 (iisted in section 1.7), Cessna 208 IPC, chapter 24 (listed in section 1.7) and Pro Star Aviation electrical drawing 2976 (in section 18). 8.2 Comant CI-285 800 Antenna 1. Removal a. Open the circuit breaker, which supplies power to the TDFM-7000 (reference electrical drawing 2979). b. Gain access to the CI-285 Antenna on the Lower Fuselage, at FS 391.60 (reference mechanical drawing P813074). SHEET 11 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 C. d. swarm INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2088 - MISSIONS EQUIPMENT Using a phenolic scraper, clean the sealant from the base of the CI-285 Antenna and Lower Fuselage. Remove 6 mounting screws (PN MSZ4694C-XX), securing the CI-285 Antenna to the Lower Fuselage. Bag and label the hardware. Carefully remove the CI-285 Antenna (do not pull on antenna cable). Remove the connector from the Antenna and bag. Remove the CI-285 Antenna from the aircraft. 2. Installation slows? rate-en Clean and prep the mounting area for installation (mating surface must be free from paint). Visually inspect the mounting area for signs of damage or corrosion. Attach and secure the antenna cable to the CI-285 Antenna. Secure the CI-285 Antenna to the Lower Fuselage using the 6 mounting screws (PN MSZ4694C-XX). Seal the CI-285 Antenna base fillet utilizing PR-1422 81/2 or equivalent. After installation, verify that the bonding path does not exceed 2.5 milliohms. Touch up paint as required. Close the circuit breaker. Accomplish the operational test procedure per the Technisonic TDFM-7000 Installation and Operating Instructions, listed in section 1.7. 8.3 Comant CI-292-3 VHF Antenna 1. Removal a. Open the circuit breaker, which supplies power to the TDFM-7000 (reference electrical drawing 2979). b. Gain access to the CI-292-3 Antenna on the Lower Fuselage, at FS 404.00 (reference mechanical drawing P513071). c. Using a phenolic scraper, clean the sealant from the base of the CI-292-3 Antenna and Lower Fuselage. d. Remove 4 mounting screws (PN M524694C-XX), securing the CI-292-3 Antenna to the Lower Fuselage. e. Bag and label the hardware. f. Carefully remove the CI-292-3 Antenna (do not pull on antenna cable). 9. Remove the connector from the CI-292-3 Antenna and bag. h. Remove the CI-292-3 Antenna from the aircraft. 2. Installation a. Clean and prep the mounting area for installation (mating surface must be free from paint). b. Visually inspect the mounting area for signs of damage or corrosion. c. Attach and secure the antenna cable to the CI-292-3 Antenna. (1. Secure the CI-292-3 Antenna to the Lower Fuselage using the 4 mounting screws (PN M524694C-XX). e. Seal the CI-292-3 Antenna base ?llet utilizing 81/2 or equivalent. f. After installation, verify that the bonding path does not exceed 2.5 milliohms. 9. Touch up paint as required. h. Close the circuit breaker. I. Accomplish the Operational test procedure per the Technisonic TDFM-7000 Installation and Operating Instructions, listed in section 1.7. 8.4 Technisonic TDFM-7000 1. Removal a. b. Open the circuit breaker, which supplies power to the TDFM-7000 (reference electrical drawing 2979). Gain access to the TDFM-7000 on the Mission Console, at FS 174.50. SHEET 12 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 C. 9. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2083 MISSIONS EQUIPMENT Loosen the Dzus Fasteners (4 each) to release the TDFM-7000 from the rails, on the Mission Console. Carefully slide the from the Mission Console (do not pull on wire harness). Ensure that each connector (4 each) attached to the TDFM-7000 is labeled for ease of installation. Detach 2 electrical connectors and 2 antenna connectors from the and bag. Carefully remove the TDFM-7000 from the Mission Console. Remove the TDFM-7000 from the aircraft. 2. Installation a. c. d. Attach and secure the connectors (4 each) to the TDFM-7000. Carefully slide the TDFM-7000 into the Mission Console Secure the Dzus Fasteners (4 each). Close the circuit breaker. Accomplish the operational test procedure per the Technisonic TDFM-7000 Installation and Operating Instructions, listed in section 1.7. 8.5 NAT-247 Audio Mixing Ampli?er 1. Removal a. b. c. d. e. f. Open the circuit breaker, which supplies power to the TDFM-7000 (reference electrical drawing 2979). Gain access to the NAT-247, on the Copilot?s Lower Sidewall Shelf, at FS 123.00, by removing the Copilot?s Sidewall Panel, per the Cessna 208 MM. Detach the connector from the NAT-247 and bag. Remove the screws (PN M527039-1-XX, 4 each) and washers (PN NAS620-8, 4 each), securing the Model 247 to the Sidewall. Bag and label the hardware. Remove the NAT-247 from the aircraft. 2. Installation a. @9013 Secure the NAT-247 to the Sidewall utilizing screws (PN M527039-1-XX, 4 each) and washers (PN NAS620-8, 4 each). Attach and secure the connector to the NAT-247. Install and secure the Copilot?s Sidewall Panel, per the Cessna 208 MM. Close the circuit breaker. Accomplish the operational test procedure per the Technisonic TDFM-7000 Installation and Operating Instructions, listed in section 1.7. 8.6 Iridium Antenna 1. Removal a. Open the circuit breaker, which supplies power to the Satellite Phone (reference electrical drawing 2997). b. Gain access to the Iridium Antenna on the Upper Fuselage, at FS 181.20 (reference mechanical drawing P513075). c. Using a phenolic scraper, clean the sealant from the base of the Iridium Antenna and Upper Fuselage. d. Remove 4 mounting screws (PN securing the Iridium Antenna to the Upper Fuselage. a. Bag and label the hardware. b. Carefully remove the Iridium Antenna (do not pull on antenna cable). c. Remove the connector from the Iridium Antenna and bag. d. Remove the Iridium Antenna from the aircraft. 2. Installation a. Clean and prep the mounting area for installation (mating surface must be free from paint). b. Visually inspect the mounting area for signs of damage or corrosion. c. Attach and secure the antenna cable to the IRIDIUM Antenna. SHEET 13 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 d. 7.3207th INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2085 - MISSIONS EQUIPMENT Secure the Iridium Antenna to the Upper Fuselage using the 4 mounting screws (PN MSZ7039-1-XX). Seal the IRIDIUM Antenna base ?llet utilizing or equivalent. After installation, verify that the bonding path does not exceed 2.5 milliohms. Touch up paint as required. Close the circuit breaker. Accomplish the operational test procedure per the operator?s instructions for the specific Satellite Phone being used. 8.7 Audio Advisory Computer 1. Removal a. Open the circuit breaker, which supplies power to the Audio Advisory Computer (reference electrical drawing 2980). b. Gain access to the Audio Advisory Computer on the top of the Glove Box, at PS 113.00. c. Detach the connector, pitot line and static line from the Audio Advisory Computer and bag. (1. Remove the knurl nut, securing the Audio Advisory Computer to the Mounting Tray. e. Bag and label the hardware. f. Carefully slide the Audio Advisory Computer from the Mounting Tray and from Instrument PaneL 9. Remove the Audio Advisory Computer from the aircraft. Installation a. Secure the Audio Advisory Computer to the Mounting Tray utilizing the knurl nut. b. Attach and secure the connector, pitot line and static line to the Audio Advisory Computer. c. Close the circuit breaker. Accomplish an operational test of the P-2 Audio Advisory Computer per the P2 Hardware Installation Manual. e. Accomplish a static leak, pitot leak and altitude reporting test per the Cessna 208 MM and FAR Part 43, Appendix E. 8.8 AAS Annunciator Switch Removal 1. 2. a. Open the circuit breaker, which supplies power to the Audio Advisory Computer (reference electrical drawing 2980). Gain access to the AAS Annunciator Switch on the Pilot?s Instrument Panel, at FS 112.00. c. Remove the AAS Annunciator per the Vivisun LED Switch Data Sheet, listed in section 1.7. d. Bag and label the AAS Annunciator Switch and hardware. e. Bag the connector. Installation a. Install and secure the AAS Annunciator Switch per the Vivisun LED Switch Data Sheet, listed in section 1.7. b. Close the circuit breaker. c. Accomplish an operational test of the P-2 Audio Advisory Computer per the P2 Hardware Installation Manual, listed in section 1.7. 8.9 IMT Skymaster TX Removal 1. a. b. Open the circuit breaker, which supplies power to the SkymasterTX (reference electrical drawing 2977). Gain access to the SkymasterTX in the Aft Fuselage, at FS 422.60 (reference mechanical drawing P513076) Ensure that each connector (4 each) attached to the SkymasterTX is labeled for ease of installation. Remove 1 electrical connector and 3 antenna connectors from the SkymasterTX and bag. Loosen the hold down mechanism (2 each). SHEET 14 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 f. 9. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2088 MISSIONS EQUIPMENT Carefully remove the SkymasterTX from the Mounting Tray. Remove the SkymasterTX from the aircraft. 2. Installation negnca Carefully slide the SkymasterTX into the Mounting Tray. Attach the hold down mechanism (2 each) to the SkymasterTX attach points. Tighten the hold down mechanisms, until clicking is heard. Connect and secure 1 electrical connector and 3 antenna connectors to the SkymasterTX. Close the circuit breaker. Accomplish an operational test per the IMT SkymasterTX User Manual and Nano Controller Software User Guide, listed in section 1.7. 8.10 Downlink Antenna 1. Removal a. Open the circuit breaker, which supplies power to the SkymasterTX (reference electrical drawing 2977). b. Gain access to the Downlink Antenna on the Lower Fuselage Panel, at FS 441.00 (reference mechanical drawing P513073). c. Using a phenolic scraper, clean the sealant from the base of the Downlink Antenna and Lower Fuselage Panel. - d. Remove 6 mounting screws (PN securing the Downlink Antenna to the Lower Fuselage Panel. Bag and label the hardware. f. Carefully remove the Downlink Antenna (do not pull on antenna cable). 9. Remove the connector from the Downlink Antenna and bag. h. Remove the Downlink Antenna from the aircraft. 2. Installation a. Clean and prep the mounting area for installation (mating surface must be free from paint). b. Visually inspect the mounting area for signs of damage or corrosion. c. Attach and secure the antenna cable to the Downlink Antenna. d. Secure the Downlink Antenna to the Lower Fuselage Panel utilizing the 6 mounting screws (PN e. Seal the DOWNLINK Antenna base ?llet utilizing PR-1422 81/2 or equivalent. f. After installation, verify that the bonding path does not exceed 2.5 milliohms. 9. Touch up paint as required. h. Close the circuit breaker. Accomplish an operational test per the IMT Skymaste?X User Manual and Nano Controller Software User Guide, listed in section 1.7. 8.11 Downlink Controller 1. Removal a. b. c. @ne Open the circuit breaker, which supplies power to the SkymasterTX (reference electrical drawing 2977). Gain access to the Downlink Controller on the Mission Console, at FS 174.50. Loosen the Dzus Fasteners (4 each) to release the Downlink Controller from the rails, on the Mission Console. Carefully slide the Downlink Controller from the Mission Console (do not pull on wire harness). Detach the connector from the Downlink Controller and bag. Carefully remove the Downlink Controller from the Mission Console. Remove the Downlink Controller from the aircraft. 2. Installation a. b. c. Attach and secure the connector to the Downlink Controller. Carefully slide the Downlink Controller into the Mission Console Secure the Dzus Fasteners (4 each). SHEET 15 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 d. e. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2083 - MISSIONS EQUIPMENT Close the circuit breaker. Accomplish an operational test per the IMT SkymasterTX User Manual and Nano Controller Software User Guide, listed in section 1.7. 8.12 L-3 MX-15HDI Camera 1. Removal a. Open the 15? circuit breaker, which supplies power to the L-3 MX-15HDI Camera (reference electrical drawing 2980). b. Gain access to the MX-15HDI Camera in the Cargo Pod, at FS 239.75 (reference mechanical drawing P513072). c. Extend the MX-15HDI Camera on the RCM (reference the Genesis 3 RCM Operations and Maintenance Manual). d. Support the MX-15HDI Camera from below utilizing padding and a platform (keep the MX- 15HDI Camera from tipping during removal). e. Ensure that each connector (3 each) attached to the MX-15HDI Camera is labeled for ease of installation. f. Detach the 3 electrical connectors from the MX-15HDI Camera and bag. 9. Remove 6 mounting fasteners (PN securing the MX-15HDI Camera to the RCM (ensure the Camera is soundly supported). h. Bag and label the hardware. i. Carefully remove the MX-15HDI Camera from the RCM. j. Remove the Camera from the aircraft. 2. Installation a. Support the MX-15HDI Camera from below utilizing padding and a platform (keep the MX- 15HDI Camera from tipping during removal). b. Position the Camera so that the connectors are located in the aft position. c. Install and secure the Camera to the RCM utilizing the 6 mounting fasteners (PN d. Torque the mounting fasteners to 100 inch/pounds. e. Attach and secure the 3 electrical connectors to the Camera. f. Accomplish the Functional Test per the L-3 Integration Guide for MX Series Digital Products, listed in section 1.7. 8.13 GPS Antenna 1. Removal a. Open the 15? circuit breakers, which supplies power to the MX-15HDI Camera (reference electrical drawing 2980). b. Gain access to the GPS Antenna on the Upper Fuselage, at PS 160.00 (reference mechanical drawing P513072). c. Using a phenolic scraper, clean the sealant from the base of the GPS Antenna and Upper Fuselage. d. Remove 4 mounting screws (PN securing the GPS Antenna to the Upper Fuselage. e. Bag and label the hardware. f. Carefully remove the GPS Antenna (do not pull on antenna cable). 9. Remove the connector from the GPS Antenna and bag. h. Remove the GPS Antenna from the aircraft. 2. Installation a. Clean and prep the mounting area for installation (mating surface must be free from paint). b. Visually inspect the mounting area for signs of damage or corrosion. c. Attach and secure the antenna cable to the GPS Antenna. cl Secure the GPS Antenna to the Upper Fuselage using the 4 mounting screws (PN MSZ7039- e. Seal the GPS Antenna base fillet utilizing PR-1422 81/2 or equivalent. SHEET 16 of 39 DOCUMENT NUMBER 21179-ICA-01 REVISION IR DATE 08-06-13 PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 rater? INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2088 MISSIONS EQUIPMENT After installation, verify that the bonding path does not exceed 2.5 milliohms. Touch up paint as required. Close the circuit breakers. Accomplish the Functional Test per the Integration Guide for MX Series Digital Products, listed in section 1.7. 8.14 L-3 MX Hand Controller 1. Removal a. c. d. Open the 15? circuit breaker, which supplies power to the L-3 MX-15HDI Camera (reference electrical drawing 2980). Gain access to the MX Hand Controller on the Mission Console, at PS 174.50. Detach the connector from the Mission Console. Carefully remove the MX Hand Controller from the Hand Controller Mount. Remove the MX Hand Controller from the aircraft. 2. Installation a Install and secure the MX Hand Controller to the Hand Controller Mount. Attach and secure the connector to the Mission Console. Close the circuit breaker. Accomplish the Functional Test per the L-3 Integration Guide for MX Series Digital Products, listed in section 1.7. 8.15 Churchill Navigator 1. Removal a. Open the circuit breaker, which supplies power to the Navigator (reference electrical drawing 2980). b. Gain access to the Navigator in the Mission Console, at FS 174.50. c. Ensure that each connector 11 each) attached to the Navigator is labeled for ease of installation. d. Detach the 7 electrical connectors, 2 HDMI connectors and 2 video connectors from the Navigator and bag. e. Remove 4 mounting screws (PN ARS-SOOC-102) and 4 washers (PN ARS-SOOC-103), securing the Navigator to the Mission Console. f. Bag and label the hardware. 9. Carefully remove the Navigator from the Mission Console. h. Remove the Navigator from the aircraft. 2. Installation a. Install and secure the Navigator to the Mission Console utilizing 4 mounting screws (PN and 4 washers (PN ARS-SOOC-103). b. Attach and secure the 7 electrical connectors, 2 HDMI connectors and 2 video connectors to the NavigatOr. c. Close the circuit breaker. d. Accomplish the Functional Test per the L-3 Integration Guide for MX Series Digital Products, listed in section 1.7. 8.16 Boland Monitor 1. Removal a. b. c. Open the circuit breaker, which supplies power to the Monitor (reference electrical drawing 2980). Gain access to the Monitor on the Mission Console, at FS 174.50. Ensure that each connector (4 each) attached to the Navigator is labeled for ease of installation. Detach the 1 electrical connector, 1 HDMI connector and 2 video connectors from the Navigator and bag. Remove 4 mounting screws (PN 1032), securing the Monitor to the Mission Console. SHEET 1? of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 f. g. h. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2083 MISSIONS EQUIPMENT Bag and label the hardware. Carefully remove the Monitor from the Mission Console. Remove the Monitor from the aircraft. 2. Installation a. b. Install and secure the Monitor to the Mission Console utilizing 4 mounting screws (PN 10?32). Attach and secure 1 electrical connector, 1 HDMI connector and 2 video connectors to the Monitor. Close the circuit breaker. Accomplish an operational test per the Boland High Definition User Manual and L-3 Integration Guide for MX Series Digital Products, listed in section 1.7. 8.17 AJA HA5 Converter 1. Removal a. Open the circuit breaker, which supplies power to the Navigator (reference electrical drawing 2980). b. Gain access to the HA5 Converter in the Mission Console, at FS 174.50. c. Detach the 1 electrical connector, 1 HDMI connector and 1 video connector from the HA5 Converter and bag. d. Remove 4 mounting screws (PN 10-32), securing the HAS Converter to the Mission Console. e. Bag and label the hardware. f. Carefully remove the HA5 Converter from the Mission Console. 9. Remove the HA5 Converter from the aircraft. 2. Installation a. Install and secure the HA5 Converter to the Mission Console utilizing 4 mounting screws (PN 10-32). b. Attach and secure 1 electrical connector, 1 HDMI connector and 1 video connector to the HA5 Converter. c. Close the circuit breaker. d. Accomplish an operational test per the AJA HA5 Converter User Manual and L-3 Integration Guide for MX Series Digital Products, listed in section 1.7. 8.18 AJA Ampli?er 1. Removal a. Open the circuit breaker, which supplies power to the Navigator (reference electrical drawing 2980). b. Gain access to the HD10HA Amplifier in the Mission Console, at FS 174.50. c. Ensure that each connector (4 each) attached to the HD10HA Amplifier is labeled for ease of installation. d. Detach the 1 electrical connector and 3 video connectors from the HD10HA Amplifier and bag. e. Remove 4 mounting screws (PN 10-32), securing the HD10HA Amplifier to the Mission Console. f. Bag and label the hardware. 9. Carefully remove the HD10HA Ampli?er from the Mission Console. h. Remove the HD10HA Amplifier from the aircraft. 2. Installation a. Install and secure the HD10HA Ampli?er to the Mission Console utilizing 4 mounting screws (PN 10-32). b. Attach and secure 1 electrical connector and 3 video connectors to the HD10HA Ampli?er. c. Close the circuit breaker. d. Accomplish an operational test per the AJA HD10HA Amplifier User Manual and L-3 Integration Guide for MX Series Digital Products, listed in section 1.7. SHEET 18 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2088 - MISSIONS EQUIPMENT 8.19 Pulse Balun Adapter 1. Removal a. Open the 15" circuit breaker, which supplies power to the MX-15HDI Camera (reference electrical drawing 2980). b. Gain access to the Balun Adapter on the Aft Side of the RCM, at FS 252.00. c. Ensure that each connector (3 each) attached to the Balun Adapter is labeled for ease of installation. Detach the 1 electrical connector and 2 video connectors from the Balun Adapter and bag. e. Loosen the connector B-nut to release the Balun Adapter from the Mounting Bracket. f. Carefully remove the Balun Adapter from the RCM. 9 Remove the Balun Adapter from the aircraft. 2. Installation a. Install and secure the Balun Adapter to the Mounting Bracket on the RCM, by tightening the connector B-nut. b. Attach and secure 1 electrical connector and 2 video connectors to the Balun Adapter. c. Close the 15? circuit breaker. d. Accomplish an operational test per the L-3 Integration Guide for MX Series Digital Products, listed in section 1.7. 8.20 Teradek Cube 1. Removal a. Open the circuit breaker, which supplies power to the Cube (reference electrical drawing 2980). b. Gain access to the Cube on the Mission Console, at FS 174.50. c. Detach the 1 electrical connector and 1 video connector from the Cube and bag. 01. Remove 1 mounting bolt, securing the Cube to the Mission Console. e. Bag and label the hardware. f. Carefully remove the Cube from the Mission Console. 9. Remove the Cube from the aircraft. 2. Installation a. Install and secure the Cube to the Mission Console utilizing 1 mounting bolt. b. Attach and secure 1 electrical connector and 1 video connector to the Cube. c. Close the ST circuit breaker. d. Accomplish an operational test per the Teradek Cube Reference Guide and L-3 Integration Guide for MX Series Digital Products, listed in section 1.7. 8.21 KGS LT-53 Light Dimmer Power Supply 1. Removal a. Open the circuit breaker that supplies unit power for the LT-53 (reference PSA electrical drawing 2978). b. Gain access to the LT-53, in the Mission Console, at FS 174.50. c. Detach the connector from the LT-53 and bag. d. Remove the screws (PN MS35206-256, 2 each) and washers (PN NAS620-8, 2 each), securing the LT-53. e. Bag and label the hardware. f. Remove the LT-53 from the aircraft. 2. Installation a. Secure the LT-53 to the Mission Console utilizing the screws (PN MS35206-256, 2 each) and washers (PN NAS620-8, 2 each). b. Attach and secure the connector to the LT-53. c. Close the circuit breaker. d. Accomplish the operational check of the Dimmer circuit, per the Cessna 208 MM. SHEET 19 0f 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA 2083 - MISSIONS EQUIPMENT 9. SPECIAL INSPECTION RE UIREMENTS This section is not applicable. 10. APPLICATION OF PROTECTILIE TREATMENTS This section is not applicable. 11. This section is not applicable. 12. SPECIAL TOOLS This section is not applicable. 13. COMMUTER CATEGORY AIRCRAFT This section is not applicable. 14. RECOMMEILDED DEERHAUL PERIODS This section is not applicable. 15. AIRWORTHINESS LIMITATIONS The Aimorthiness Limitations section is FAA Approved and speci?es maintenance required under FAR Parts 43.16 and 91.403 of the Federal Aviation Regulations, unless an alternative program has been FAA Approved. There are no Airworthiness Limitations associated with this modi?cation. 16. ASSISTANCE For questions or assistance regarding this ICA, contact: Pro Star Aviation 5 Industrial Drive Manchester Airport Londonderry, NH 03053 17. IMPLEMENTATION AND RECORD KEEPING This ICA is to become a part of the aircraft maintenance manual. An entry must be made in the permanent aircraft maintenance record referring to this document. 20 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 18. For troubleshooting, system maintenance and system interface, refer to the following diagrams: DIAGRAMS INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2083 - MISSIONS EQUIPMENT MISSIONS POWER WIRING DIAGRAM IMT DOWNLINK PROVISIONS WIRING DIAGRAM 2977 IR 23 OPS CONSOLE LIGHTING WIRING DIAGRAM 2978 IR 24 TDFM RADIO WIRING DIAGRAM 2979 IR 25 MX15HDI CAMERA PROVISIONS WIRING DIAGRAM 2980 IR 25 SATPHONE PROVISIONS WIRING DIAGRAM 2997 IR 31 INSTALLATION, VHF WHIP ANTENNA P513071 IR 32 INSTALLATION, GPS ANTENNA P513072 IR 33 INSTALLATION, DOWNLINK ANTENNA P513073 IR 34 INSTALLATION, WIDE BAND UHF ANTENNA P513074 IR 35 INSTALLATION, IRIDIUM ANTENNA P513075 IR 36 INSTALLATION, SKYMASTERTX P513076 IR 37 SHEET 21 of 39 DATE 08-06-13 DOCUMENT NUMBER 21 REVISION IR PRO STAR AVIATION, LLC. 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MON SNOISSIW - 8802 VNSSED ?5050 HN SSENIHLHOMHIV 80:! HVJS 03d PRO STAR AVIATION, LLC. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA 2088 MISSIONS EQUIPMENT PR MOM I'll?u umuu?uu?I?n?t- NOIES: SET I Tana?A V?Wil?33? 5 me ?he-rt ii 9 I- 1 .1115 FFsa=w9? Inns; 5 Luau. MM 21:35.} 8 mm TM WM DATA [3-99 an] mane MIA 85"? TI MXISHDI CAMERA PROVISIONS WIRING DIAGRAM "Dim NEINE C2088 lmfl?'l SHEET 29 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. INST RUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA 2088 MISSIONS EQUIPMENT NOTES: IO 2 5? arm_ [on mln?{m an m?bl{am 53] i mama-Ammo. M, (mm CAMERA PROVISIONS WIRING DIAGRAM Inn NDNEImns?ao I DOCUMENT NUMBER 21 179-ICA-01 DATE 08-06-13 REVISION IR SHEET 30 0f 39 PRO STAR AVIATION, LLC. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA 2085 MISSIONS EQUIPMENT PRWRIETARY NONE LTR. IR WESI 273004 mum 11E WW um mu: mem mum Lm mun?l [j Imam munmm A LCD 0 "out: Immune-Ian mum nets-mm mmmu{m ?3 .II 91mm um . mm?$ 9mm um .. mum?$ 2 um yum m1 II SATPHONE PROVISIONS WIRING DIAGRAM NONE I?m SHEET 31 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA 2083 - MISSIONS EQUIPMENT ITEM REVISIONS PIN - ch. NO DESCRIPTION VENDOR CITY. F-S- 400-40 N0. I ENG. APPROVAL AIRCRAFT Raul DATE I"m DESCRIPTION F.S. 404m VHF WHIP ANTENNA MANUFACTURE PER I I IP [07mm mac 1 INITIALREIEASE I PSI307 I-I DOUBLER ASSEMBLY DWG NOTES: 2 6 . ALL WORK SHALL BE IN AND 23. AIRCRAFT STRUCTURAL REPAIR MANUAL. CHAPTER 5] AND AIRCRAFT STANDARD PRACTIC E5. CHAPTER 20. 3 wm470AD4 RNET . '5 WHERE APPI IN THE CASE OF A CONFLICT IN DOCUMENTATION. THE AIRCRAFT MAINTENANCE MANUAL TAKES PRECEDENCE. . ALL RIVETTNG WORK SHALL TIE DONE IN ACCORDANCE WITH AC43.I3-I 3 CHAPTER 4. SECTION 4. PARAGRAPH 4-57 AND CHAPTER 7, SECTION I. PARAGRAPHS 7-I AND 7-2. . ALL MATING SURFACES MUST BE FREE FROM PAINT. . WEI INSTALL RIVETSUIILIUNG PR-I422 BII2 OR EQUIVALENT. . AFTER INSTALLATION PILLET SEAL EDGE OF ANTENNA 5- DOUBLER UTILITING PR-I422 OR EQUIVALENT. . AFTER INSTALLATION FILL ANTENNA COUNTERBCRES UTILTUNG DOW CORNING 732 MULTI-PURPOSE. NON-CORROSIVE RTVSEALANT 0R EQUIVALENT. . AFTER INSTALLATION PRIME PAINT TO MATCH AIRCRAFT AS REQUIRED. USE EPOXY PRIMER CONFORMING To EITHER TYPE I. CLASS C2 0R BN5 IGII, TYPE I. CLASS A. GRADEA. 3. AFTER INSTALLATION VERITY BONDING OT EQUIPMENTTO AIRCRAFT STRUCTURE DOES NOT EXCEED 2.5 NIILLIOHMS. 9. FASTENER LENGTH DETERMINED UPON INSTALLATION. IU.UNLESS OTHERWISE SPECIFIED ALL DIMENSIONS ARE IN INCHES. 4 IM520470AD 3) RIVEI - ISI I I 2.5) ?0 SCREW - 3 A VHF WHIP ANTENNA (COMANT) ?0 ANTENNA INSTALLATION VIEW LOOKING DOWN SYMBOL KEY F0 RWAR BILL OF MATERIALS ITEM NUMBER .. I (XX) FOR REFERENCE ONLY En I INSTALLATION NOTES I. SHOWN IS FOR REFERENCE. ANTENNA 6 TO BE LOCATED AIRCRAFT SKIN BETWEEN FRAME STATIONS AND 415.20 AS SHOWN. 2. OUT EXBIING RIVFIS IN STRINGERS TO BE OVERLAPPED BY DOUBLER. 3. MATCH DRILL DOUBLER IO AIRCRAFT. ENSURE PROPER EDGE DBTANCE FOR HOLES. 4. ATTACH DOUBLER TO AIRCRAFT USING SAME EQUIVALENT RIVET AS REMOVED, LONGER LENGTH AS REQUIRED. ANTENNA DOUELER TO BE ROLL FORMED IO AIRCRAFT SKIN. AFTER POSITIONING ANTENNA DOUBLER. MATCH DRILL AIRCRAFT SKIN I0 ANTENNA DOUBLER. I. INSTALL ANTENNA PER MANUFACTURERSSPECIFICATIONS. dd VHF WHIP ANTENNA PIN LBS. UP ANTENNA INSTALLATION VIEW LOOKING RIGHT I I A FORWARD AIRPORT 5 Dims BERRY. NH 03133 mo hazy-STAR [7827] ANGLES: IOIHMCE: ewes-Huck: INSTALLATION. ANTENNA 1H5 Docun?? comnu "Wm nu! ISTHEFFDPEPTF or ?o?mn 32' ?735 PFC) SIIP nunou Amman! mantras MM on: comme us; EXCEPHOF mam: Ears? - (ammo av conmcu-uspocmm "450 ANGLE mu ..--.. I {7 oxen mama F307 KWO m) I ?AEAwlm wc-Icovnum 00 I1: Mammy-II ?wsmmu p513)? 5 l2 SHEET SHEET 32 0f 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2088 MISSIONS EQUIPMENT ITEM No PIN - DWG NO DESCRIPHON VENDOR QTY. CPS ANTENNA DOUBLER ASSEMBLY MANUFACTURE PER DWG PSI3072-I 2X NAS I 097AD 4-XX RIVET - 22 3 M527039-I-XX IO SCREW - 4 GPS ANTENNA 0 PIN 35C WT.: 6.5 OZ. CPS ANTENNA (NOVATELJ AIRCRAFT SKIN 0.032 THK. UP GPS ANTENNA INSTALLATION VIEW LOOKING TO THE RIGHT FORWARD AIRCRAFT CENTERLINE IFS. 160.00] (I25) LEFT GPS ANTENNA INSTALLATION VIEW LOOKING UP FORWARD NOT ES: I. ALL WORK SHALL BE DONE IN ACCORDANCE WITH AC43J3-IB AND 28. 2. ALL RIVETTNG WORK SHALL BE DONE IN ACCORDANCE WITH 3. ALL MATING SURFACES MUST BE FREE FROM PAINT. 4. WEI INSTALL RIVETS UTILIZING BIIZ OR EQUIVALENT. 5. AFTER INSTALLATION HLLEI SEAL EDGE OF ANTENNA 8. UOUBLER UTILIZING 6. AFTER INSTALLATION FILI ANTENNA COUNTERSORES UTILIZING DOW 8. AFTER INSTALLATION VERIFY BONDING OF EQUIPMENT T0 AIRCRAFT FEMSIONS REV. I one I mgr" DESCRIPTION I ENG. APPROVAL I: IonwnaJ MHC I INITIALRELEASE I . AFTER INSTALLATION PRIME IL PAINT TO MATCH AIRCRAFT AS REQUIRED. AIRCRAFT STRUCTURAL REPAIR MANUAL. CHAPTER 51 AND AIRCRAFT STANDARD PRACTICES. CHAPTER 20. WHERE APPLICABLE. IN THE CASE OF A CONFLICT IN DOCUMENTATION. THE AIRCRAFT MAINTENANCE MANUAL TAKES PRECEDENCE. CHAPTER 4. SECTION 4, PARAGRAPH 4-57 AND CHAPTER 7, SECTION I, PARAGRAPHS 7-1 AND 7-2. PR-I422 Bll2 OR EQUIVALENT. CORNING 732 MULTI-PURPOSE. NON-CORROSTVE RTV SEALANT 0R EQUIVALENT. USE EPOXY PRIMER CONFORMING IO EITHER TYPE I. CLASS C2 OR BMS ID-II, TYPE I. CLASSA. GRADE A. STRUCTURE DOES NOT BICEED 2.5 MLLIOHMS. 9. FASTENER LENGTH DETERMINED UPON INSTALLATION. I D.UNLESS OTHERWISE SPECIFIED ALL DIMENSIONS ARE IN INCHES. INSTALLATION NOTES I. SYMBOL KEY BILL OF MATERIALS ITEM NUMBER IX.X I FOR REFERENCE ONLY IOCATION SHOWN 6 FOR REFERENCE. ANTENNA ISTO BE LOCATED BETWEEN FRAME STATIONS l54.00 AND I66.45. ANTENNA DOUBLER TO BE ROLL FORMED TO AIRCRAFT SKIN. AFTER POSITIONING ANTENNA DOUBLER, MATCH DRILL AIRCRAFT SKIN TO ANTENNA DOUBLER. INSTALL ANTENNA PER SPECIFICATIONS 1m I?m-?c3513 A 732% nun-run- voca- m?z?smg (1527. m: ?annel '1 NOth 35cm "own-In [15 MPEW Of F70 HAFAWIDNIID 5TOEE 0150 If RS Ema? A COHFDEMTIM THFDANGII DH CF ln': mm ID 07 PM can FD. FETUEI AND ALL :0 SAR ANGLE: MACH. tl' 1 I27 MACH. ED EURIAQI nu IQLRANCIS: INSTALLATION, GPS ANTEN NA .101 42055 msasnaa P513072 5 Int?, I I lam-u y?w STEEIOTI SHEET 33 0f 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2088 MISSIONS EQUIPMENT ITEM FEW IONS PIN - DWG NO DESCRIPTION VENDOR QTY. NO. one I0 RAWN a, I ENG. APPROVAL (F5. 44 LOO) re [07/15/13 I MHC I I MANUFACTURE PER DWG DOWNLINK ANTENNA Ps's?m" DOUBLER ASSEMBLY 2 NASI 097A04-XX RIVET - 3 W24694CXX #8 SCREW 6 4 (565-5366-6IJI DOWNLINK ANTENNA (SENSOR AIRCRAFT CENTERLINE 26x RIGHT DOWNLINK ANTENNA INSTALLATION VIEW LOOKING DOWN FORWARD I AFT ACCESS PANEL DOWNLINK ANTENNA PIN 565?5366-60 2 01. I I A DOWNLINK ANTENNA INSTALLATION FORWARD VIEW LOOKING TO THE RIGHT NOTES: I. Ali WORK SHAII BE DONE IN AND 23. AIRCRAFT STRUCTURAL REPAIR MANUAL, CHAPTER SI AND AIRCRAFT STANDARD PRACTICES. CHAPTER 20. APPLICABLE. IN TIIE CASE OF A CONFLICT IN DOCUMENTATION. THE AIRCRAFT MAINTENANCE MANUAL TAKES PRECEDENCE. . ALL RIVETTNG WORK SHALL BE DONE IN ACCORDANCEWTTH CHAPTER 4. SECTION 4. PARAGRAPH 4-51 AND CHAPTER 7. SECTION I. PARAGRAPITS AND 7-2. ALL MATINO SURFACES MUST BE FREE FROM PAINT. . WET INSTALL RIVETS UTILIZING [2 OR EQUIVALENT. . AFTER INSTALLATION FILLEI SEAT. EDGE OF ANTENNA DOUBLER UTILIZING OR EQUIVALENT. . AFTER INSTALLATION FILT. ANTENNA COUNTERBORES UTILIZING DOW CORNING 732 MULTI-PURPOSE. RTV SEALANT OR EQUIVALENT. . AFTER INSTALLATION PRIME 8 PAINT TO MATCH AIRCRAFT AS REQUIRED. USE EPOXY PRIMER CONFORMING TO EITHER TYPE I. CLASS C2 OR BNLS I. TYPE I. CLASS A. GRADE A. AFTER INSTALLATION VERIFY BONDING OF EQUIPMENT TO AIRCRAFT STRUCTURE DOES NOT EXCEED 2.5 MILLIOHMS. FASTENER LENGTH DETERMINED UPON INSTALLATION. IO.UNLESS OTHERWISE SPECIFIED ALL DIMENSIONS ARE IN INCHES. 8. SYMBOL KEY INSTALLATION NOTES 6) BILL OF MATERIALS ITEM NUMBER (XX) FOR REFERENCE ONLY LOCATION SHOWN IS FOR REFERENCE. ANTENNA IS TO BE LOCATED BETWEEN FRAME STATIONS 436.68 AND 452.60. ANTENNA DOUBLER TO BE ROLL FORMED T0 AIRCRAFT SKIN. AFTER POSITIONING ANTENNA DOUBLER. MATCH DRILL AIRCRAFT AFT ACCESS PANEL IO ANTENNA DOUBIER. INSTALL ANTENNA PER SPECIFICATIONS Hum Mmcuesatn ?zoom A DRIVE [?9311 any 983 PRO FAX: may-ml ant-Allu- "01c! @43- TRED ANGIE . .. . PROTECTION HIE 0" :80? or PRO 5319 OF TIE OK WET Elm AND Ill core ANGLES: AMEN. .X '67 IR IQEFMES INSTALLATION, DOWNLINK ANTENNA HIE 1.. lac-nu 202me 5 ITEM DATE 08-06-13 SHEET 34 0f 39 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA 2083 MISSIONS EQUIPMENT F.s. 385.60 mums PIN 0W5 NO DESCRIPTION VENDOR QTY. NO- REV. I DATE DBCEIPTION I ENG. APPROVAL 5 WIDE BAND UHF MANUFACTURE PER CENTERLINE I 07mm I we I mwmmE I DWG NOTES: I PSI3074-I ANTENNA DOUBLER I. AIL WORK SHALL BE DONE IN ACCORDANCE WITH AC43J3-IB AND 26. AIRCRAFT STRUCTURAL REPAIR MANUAL. CHAPTER ST AND AIRCRAFT STANDARD PRACTICES. CHAPTER 20. . WHERE APPLICABLE. IN THE CASE OF A CONFLICT IN DOCUMENTATION. ?520470004 25 TILE AIRCRAFT MAINTENANCE MANUAL TAKES PRECEDENCE. 0 2. ALL RIVETING WORK SHALL BE DONE IN ACCORDANCE WITH IMSZOHOAMI RIVEI IBI CHAPTER 4. SECTION 4, PARAGRAPH 4-57 AND CHAPTER 7. IT LU) SECTION I. PARAGRAPIIS 7-l AND 7-2. . ALL MAIING SURFACES MUST BE FREE FROM PAINT. . WET INSTALL RIVETS UTILITING OR EQUIVALENT. . AFTER FILLET SEAL EDGE OF ANTENNA a. DOUBLER PR-I422 Bl]? OR EQUIVALENT. 5. AFTER INSTALLATION FILL ANTENNA UTILIZING DOW CORNING 732 MULTI-PURPOSE. NON-CORROSIVE RTVSEALANT OR EQUIVALENT. 7. AFTER INSTALLATION PRIME s. PAINT To MATCH AIRCRAFT As REQUIRED. USE EPOXY PRIMER CONFORMINC- TO EITHER MIL-PRF-23377. TYPE I. CLASS c2 0R BN6 I. TYPE I, CLASS A. GRADE A. 8. AFTER INSTALLATION VERIFY BONDING OF EQUIPMENT To AIRCRAFT STRUCTURE DOES NOT EXCEED 2.5 MILLIOHMS. 9. FASTENER DETERMINED UPON INSTALLATION. IO.UNLESS OTHERWISE SPECIFIED ALL DIMENSIONS ARE IN INCHES. RIVET - 7 N524694C-XX 88 SCREW 6 (CI-7.85) UHF ANTENNA ICOMANI) (II ANTENNA INSTALLATION SYMBOL KEY VIEW LOOKING DOWN FORWARD BILL OF MATERIALS ITEM NUMBER I X.X I FOR REFERENCE ONLY INSTALLATION NOTES I . LOCATION SHOWN IS FOR REFERENCE. ANTENNA IS TO BE LOCATED BETWEEN FRAME STATIONS 385.60 AND 400.40 AS SIIOWN. 2. DRILL OUT EXISTING RIVETS IN STRINGERS TO BE OVERIAPPED BY 3 DOUBLER. 3. MATCH DRILL DOUBLER T0 AIRCRAFT. ENSURE PROPER EDGE DSTANCE I I I I I FOR HOLESI 4. ATTACH DOUBLER TO AIRCRAFT USING SAME OR EQUIVALENT RIVET AS REMOVED, WITH LONGER LENGTH AS REQUIRED. 5. ANTENNA DOUBLER TO BE ROLL FORMED T0 AIRCRAFTSKIN. 6X 6 6. AFTER POSITIONING ANTENNA DOUBLER. MATCH DRILL AIRCRAFTSKIN TO ANTENNA DOUBLER. 7. INSTALL ANTENNA PER MANUFACTURERS WIDE BAND UHF ANTENNA PIN INIJOJO 18$. ?Curr AIRPORT A 5 INDUSTRIAL DRIVE LONDONDERRY, NH UP mo IRE-EOEIRIWWI ANTENNA INSTALLATION ANGIE: Touuwcss: VIEW LOOKING RIGHT mas mm m, INSTALLATIO N, WIDE BAND UHF ANTENNA FORWARD MB Domain-Lemmas ISTIIE "cram 0: ?mm 3? FOF MEET GPANTE IV lela. mm! IHRD Imu- wv no: momma." mm or rm. Io Am PROMOTION I FE ?0 R7 02066 manna: MIC mm BAR ur?'N comm won a m: '0 In": I lsmmul'm or a rule9455 Ion SHEET 35 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA 2083 MISSIONS EQUIPMENT REVISIONS REV. DATE I Mgr? DECRIFTION I ENG.APPROVAI. IR 0mm: MHC INITIALRELEASE I NOTES: . ALL WORK SHALL BE DONE IN ACCORDANCE WITH AC43.I3-IB AND 28. AIRCRAFT MANUFACTURERS STRUCTURAL REPAIR MANUAL. CHAPTER 5 0 ITEM PIN - DWG NO VENDOR QTY. IRIDIUM ANTENNA MANUFACTURE PER DOUBLER ASSEMBLY ch RIVET - 30 IRIDIUM ANTENNA PIN IISI 6.3mm I I0 SCREW - 4 5 oz. oi IRIDIUM ANTENNA UP rs AND AIRCRAFT STANDARD PRACTICES. CHAPTER 20. THE AIRCRAFT MAINTENANCE MANUAL TAKES PRECEDENCE. ALL RIVEIINO WORK SHALL BE DONE IN ACCORDANCE wmI NRCRAH SKIN PARAGRAPHS 7-1 AND 7-2. 0032 . ALL MATING SURFACES MUST BE FREE FROM PAINT. . AFIER INSTALLATION FILLEI SEAL EDGE OF ANIENNA a. DOUBIER BIIZ 0R EQUIVALENT. I CORNINO 732 MULTI-PURPOSE. NON-CORROSIVE RTV SEALANT OR EQUIVALENT. USE EPOXY PRIMER CONFORMING To EITHER MIL-PRF-23377. TYPE 1. CLASS IRIDIUM ANTENNA INSTALLATION C2 OR EMS IO-I I, I. Cl ASS A. GRADE A. FORWAR STRUCTURE DOES NOT EXCEED 2.5 MILLIOHMS. 9. FASTENER LENGTH DETERMINED UPON INSTALLATION. WHERE APPLICABLE. IN THE CASE OF A CONFLICI IN DOCUMENTATION. CHAPTER 4, SECTION 4. PARAGRAPH 4-57 AND CHAPTER 7. SECTION I. . WET INSTALL UTILITINO PR-I422 BI 12 OR EQUIVALENT. (9 - 6. AFTER INSTALLATION FILL ANTENNA COUNTERIIORES DOW . AFTER INSTALLATION PRIME PAINT To MATCH AIRCRAFT AS REQUIRED. VIEW LOOKING TO THE RIGHT a. AFTER INSIAILAIION VERIFY BONDING OF EQUIPMENT IO AIRCRAFT I0.UNLESS OTHERWISE SPECIFIED ALL DIMENSIONS ARE IN INCHES. AIRCRAFT CENTERIINE (F5. IBIZOI SYMBOL KEY -. BILL OF MATERIALS ITEM NUMBER (xx) FOR REFERENCE ONLY (3.5) INSTALLATION NOTES 1. SHOWN IS FOR REFERENCE. ANTENNA ISTO BE LOCATED FRAME STATIONS ?5.95 AND I86.45. ANTENNA DOUBLER TO BE ROLL FORMED TO AIRCRAFTSKIN. AFTER POSITIONING ANTENNA DOUBLER. MATCH DRILL AIRCRAFT SKIN I0 ANTENNA DOUBLER. 4. INSTALL ANTENNA PER SPECIFICATIONS N?n? LEFT mm 1 5 DRIVE A IRIDIUM ANTENNA INSTALLATION PRO (7527I VIEW LOOKING UP . AVIATION NHGLES: Pmrm-wmms MACH. min INSTALLATION. IRIDIUMANTENNA Ir: W941 prowl-rim THAI 51H: OT mm? ??95 1,0530? ?ll: 31 ?5 926.1541 0' I Mm EXCEPT 5029139115 mam! GRANTS, IT mm? WHO ?56surname". upoucounswuonv-EREEXD PETAnmsmuyn.c= "Ammo par?5 -.. uwoevw.&1uw DOCu-Iiul AnoAucwESIovm SAFAWDON. 514:2 lotrun- SHEET 36 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. LONDONDERRY, NH 03053 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CESSNA 2083 - MISSIONS EQUIPMENT I I ITEM NO. PIN - DWG NO DESCRIPTION VENDOR QTY. PSI3076-I-I SKYMASTER SHELF MANUFACTURE PER DWG PS I3076r2 INBOARD SUPPORT TEE ASSEMBLY MANUFACTURE PER DWG PS I3076-7. PS I307b-3 OUTBOARD SUPPORT TEE ASSEMBLY MANUFACTURE PER DWG P513076-3 INLSZO470AD4-XXI IVET I5I IIAS 27 039-XX SCREW 23 PS 3076~+ I MOUNTING TEE MANUFACTURE PER DWG NLS2I 059L3 OR M52I059-3 I I0 NUTPLATE OR IO NUTPLATE RIVET 20 W24694SXX OR #10 FH SCREW MOUNTING TRAY IECSI Iss?sxrx-s-sm- Moz-aa-rpns) SKYMASTER TX (IMT) CENTERLINE I I 03917 SKYMASTER SHELF INSTALLATION VIEW LOOKING DOWN UP 4X EEV. I DATE 1 023"" ENG. APPROVAL [a omen: I we Imam 221.955 1 NOTES: ALL WORK SHALL BE DONE IN ACCORDANCE WITH AND 28. AIRCRAFT STRUCTURAL REPAIR MANUAL. AND AIRCRAFT STANDARD PRACTICE WHERE APPIICABIE. IN THE CASE OF A CONFLICTIN DOCUMENTATION. THE AIRCRAFT STRUCTURAL REPAIR MANUAL AND AIRCRAFT STANDARD PRACTICES TAKES PRECEDENCE. 2. GROUND AND BOND ALL EQUIPMENT IN ACCORDANCEWITH 8 CHAPTER II. SECTION 1.5. PARAGRAPH +57 AND CHAPTER 7. SECTION I. PARAGRAPHS P-T AND 7-2. 3. ALL RIVEIING WORK SHALL BE DONE IN ACCORDANCE WITH AC43.I3-I 3 CHAPTER 4. SECTION 4. PARAGRAPH 4?57 AND CHAPTER 7. SECTION I. PARAGRAPITS 7-I AND 7?2. 4. ALL PARTS I0 8E PRIMED WITH 2 COATS UP EPOXY PRIMER CONFORMING TO EITHER MTL-PRF-23377. TYPE I. CLASS C2 OR EMS IO-I I. TYPE I. CLASS A. GRADE A AND PAINTED TO MATCH AIRCRAFT AS REQUIRED. 5. ALL MATING SURFACES TO BE TREE 0F PAINT. 6. FASTENER LENGTH AND ORIENTATION OF NUTPLATES DETERMINED UPON INSIALLAIION. SYMBOL EY BILL OF MATERIALS ITEM NUMBER I X.X I FOR REFERENCE ONLY INSTALLATION 5 TO BE LOCATED BETWEEN FRAME STATIONS 0.5.20 AND 430.00 AS SHOINN. 2. DRILL OUT EXISTING RIVETS IN STRINGERS TO BE OVERLAPPED SUPPORT TEES. 3. MATCH DRILL SUPPORT TEES TO AIRCRAFT. ENSURE PROPER EDGE A DISTANCE FOR HOLES. . ATTACH SUPPORT TEES TO AIRCRAFT USING SAME 0R EQUIVALENT RIVEI AS REMOVED. WITH LONGER AS REQUIRED. 5. POSITION SHELF 0N SUPPORT TEES APPROX. AS SHOWN AND MATCH DRILL SHELF TO TEES. 6. ATTACH WITH SCREWS AS INDICATED. 7. MAICH DRILL MOUNTING IEES I0 MOUNTING TRAY. AIIACH NUTPLATES TO MOUNTINGS TEES AS INDICATED. 8. LOCATE AFT MOUNTING TEE ON SHELF IN LOCATION OF EXISTING SCREWS ASSHOWN. MATCH DRILL MOUNTING IEE T0 SHELF (20. 9. DRILL ADDITIONAL FASTENER HOLE IN FLANGE APPROX SHOWN. ENSURE PROPER EDGE DBTANCES AND CLEARANCE OF SUPPORT TEES. MATCH DRILL SHELF AND ATTACH NUTPLATE TO UNDERSIDE OT SHELF. IO. LOCATE FORWARD MOUNTING AS IO ATTACH NIOUNTNG TRAY AND MATCH DRILL MOUNTING TEE AND SHEIF IJX) FOR FASTENER. ENSURE PROPER EDGE DISIANCES AND CLEARANCE OF SUPPORT TEES. I I. ATTACH ALL TEES AND MOUNTING TRAY 5C REWS AS INDICATED. I2. INSTALL SKYMASTER UNIT PER SPECIFICATIONS. "(an WNCEESTER ?Rm 5 I. DRIVE LONWNDEF RT. NH (13353 mo VOCE: 6-03-627ASTAR (7827] SKYMASTER SHELF INSTALLATION LEFT VIEW LOOKING FORWARD ?'45 LE5: E: man. u- :91: 5' unnon?nmuiou ?[1051 ISEEGEHICHACOWL -L.I N1 EICEPI FOP. ?0953? OM 931W PACT. IWMWT Inf!) PEDETDN MAC ?lt? MACE INSTA LLATION. SKYMASTERTX (2-2085 2065000 PSINN .. I a 1-3 I 4 3 SHEET 37 of 39 DATE 08-06-13 DOCUM ENT NUMBER 2 1 1 79-ICA-01 REVISION IR PRO STAR AVIATION, LLC. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA 2083 MISSIONS EQUIPMENT 3" CENTERUNE I DRILL 00201 HOLE \1 00.098 HOLE DRILL 90.20] HOLE 2X C532 IO NS. 2X DRILL 00.098 HOLE I 0.15 to 4x DRILL 00.201 HOLE 3x DRILL 00.098 HOLE 0.15 10 100? NS. 6X 1 VIEW B-B VIEW LOOKING FORWARD SKTMASIERTX PIN 65-SKIX-3-SD4-M02-83-FP413 00 00 MOUNING TRAY PIN zoo-13775101 i FORWARD I DRILL @0201 HOLE DRILL (00.098 HOLE CSK 9J5 IO 100? NS. 2X 0? CENTERUNE I Nu I-?m mum-155152 ~er12: Imusan DRIVE LON DONOEHV. NH 03053 PRO I SKYMASTER SHELF WI MOUNTING ZEES 902?" LEFT VIEW LOOKING DOWN DRILL 00.098 HOLE INC SIRUCTURE AND SUPPORT 2E5 NOT SHOWN CSK 0.15 101000 NS. 4X FOR nu DRILL 00.201 HOLE 0512ng (?933 03555 2x INSTALLATION, SKYMASTERTX VIEW A -A misbo SI At: 5 '10 a: Iaprm [mg IV. A nu ?can (954.4.? Vl?w LOOKING FORWARD Genoa {mm 20525005 mnvunou. wanton-Inch onus ?Don la- DOCWN SFEEI Zol 3 SHEET 38 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR PRO STAR AVIATION, LLC. - INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LONDONDERRY, NH 03053 CESSNA 2088 MISSIONS EQUIPMENT SKYMASTERIX PIN 65-SKTX-3-SD4-MOZ-BS-FP413 TRAY FIN VIEW c-c ,m A FORWARD VIEW LOOKING RIGHT mgg-?migacn Rum mo 3 v1.1 I In none: INSTAL LATION. SKYMASTERTX Luis oocuuem Momma-v.1 a; Ihih. :?xcoxrovmrm mun -- an not IE 0651058: 02068 I roams suuvnmu. "m nmrm. amr-zn nocmim um All comm rmmn?SHEEI 3 6'3 39 of 39 DATE 08-06-13 DOCUMENT NUMBER 21179-ICA-01 REVISION IR Form Approved Electronic Tracking Number MAJOR REPAIR AND (Airframe, Powerplant, Propellerl or Appliance) For FAA Use Federal Aviation Administration m. INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B, and AC 43.9-1 (or subsaquent 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) - - .. Nationality and Registration Mark Serial No. USA N508RB 20885008 1. Aircraft . Make Model Series CESSNA 2083 GRAND CARAVAN Name (As shown on registration certi?cate) Address (As shown on registration certificate) 2_ Om, CESSNA AIRCRAFT COMPANY Address P.O. BOX 7704 DEPT 095 City State KANSAS Zip 57277 Country USA 3. For FAA Use Only the dais identified herein compiles with tippiictiim ainvoritiliirtes cognizant-his rind ?t?g?ib?t?d? tint: for the above described 'ty inspection by a poison enlivened In FAR tit? APR 1 92 1 1 Bate Wing Inseam HS I 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model Serial Number . . I - AIRFRAME . - (As described in Item 1 above) POWERPLANT - El PROPELLER Type APPLIANCE El Manufacturer I If 6. Conformity Statement A. Agency's Name and Address 8. Kind of Agency Name AVIATION r] us. certi?cated Mechanic (Manufacturer Addre552010 AIRPORT ROAD Foreign Certi?cated Mechanic C. Certi?cate No. City State a Certi?cated Repair Station YN8R621 Zips?7221 Country Certi?cated Maintenance Organization RADIO CLASS 1'2'3 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 Signature/D to of Authorized Indi ual A per Part 43 I 1" 'l 4/ ?ea-z; 7. Approval for! Return to Service Pursuant to the authority given persons speci?ed beiow. 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 . . . Person Approved by Canadian Inspegttoflandards Manufacturer I Maintenance Organization Depanmen? of Transport BY Other (Specify) FAA Designee Repair Station Inspection Authorization Certi?cate or Signatu of Authorized I idual Designation No. 7 3 I) YN8R621Y Mp 4/323 AD FAA Form 337 (10-06) ?7 . n9+vlt I41 - H. nonce 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 N508RB :25 4.3 Nationality and Registration Mark Date CESSNA 2083- SIN 20885008-N508RB Installed Equipment: The following systems were installed in accordance with the manufacturer?s component installation instructions adapted as required using A.C. 43.13-28 par.202, 203 and 204 guidelines. - 0 Mid Continent InverterM del MDSO 3.9 arm 134.5 - I Main Inverter OniOff switch is located on Pilots outboard switch panel (upper section of the Pilots instrument panel), labeled ?Power Outlets 115 VAC ON - 2 ea AC Power Outlets are located in the passenger compartment. Placards are located at each outlet, labeled ?115 Power outlets protected with Pass Seymour OFCI Receptacle?P/N 340557 located at the co-pilot?s right kick panel. 0 Astron DC to DC Converter N2412-24, 1.8 132.0 under cockpit center ?oor panel) 0 2 ea Power Outlets 392903 8-2 (with caps W-39623) are located in the passenger compartment at arm 266.5 (right side and left side of passenger compartment). Outlets are labeled ?Power Outlet WIRING: Wire used was installed in accordance with the manufacturer?s installation instructions adapted as required with 2B par.207 guidelines, and of the appropriate gauge required by par.l 1-76 77.. Wire was installed in accordance with Chapter II, Section 5 par. lI_-66 through _1 1:69; Section 8 par 11-96; Section 9 par. 11-1 15 through Il-l26; Section 11 par Il-l46 through 11-l47,? and Section-16pm. 11-205 through Electrical lo-ads have been evaluated in accordance with AC. 43.13-IB Chapter I 1, Section 3 par. 11-35 and 11-36 and were found to be within limits. All installed equipment was tied to ship?s power via in-Iinc fuses, pull-type or switch type circuitbreakers with locations and labels as follows: - Astron DC to DC Converter N2412-24, 10 Amp Electrical Buss 2, (located in left side circuit breaker panel labeled 12VDC 2" Astron Converter Output, 2 ea 10 Amp fuse, (located at Connector PC 049 under the co-pilot ?oor), labeled ?Right Hand 12VDC Outlet and ?Left Hand 12VDC Outlet 10 respectively - MDSO Inverter, 30 Amp Battery Bus, (located in nose compartment electrical panel), labeled ?1 MDSO Inverter Contactor Control, IAmp Fuse, Avionics Bus 2, (located forward of the left hand circuit breaker panel), labeled CTL AC Power Outlets, 5 Amp MDSO Inverter Output, (located at the co-pilot?s right kick panel), labeled I SVAC 60HZ Wiring Diagrams and installation instructions used for reference were from the following manuals: Cessna Model 208 Wiring Diagram Rev 10. December I, 2012 Astron Corporation N2412-24 DC to DC Converter Product Sheet True Blue Power Series Static Electrical Power Inverter MDSO Static Inverter Yingling Aviation Drawing"?2083' 12V DC-Power-Converter" Yingling Aviation Drawing 1 Inverter Manual 9017039 Rev August 29, 2012 rowing No: WD-20835008-I-5122-2 Rev A 7 Drawing No: WD-20885008-15122-3 Rev A OPERATIONAL GROUND CHECKS: Post installation ground function and accuracy tests were performed in accordance with manufacturer instructions, all systems operated normally. Standard EMURFI ground test completed AC 43.13-IB pa I l-106 and 11-107 no adverse effects noted. test completed Yingling Aviation-Avionics Standard EMUEMC Test Procedures dated - 3. CONTINUED AIRWORTHINESS INSTRUCTIONS: As per the Installation Manuals listed, no regular periodic maintenance is required. Maintenance is ?On Condition" and service or repair is required only when a malfunction is detected. Reference the aircraft maintenance manual, and this FAA 337. Inspect all equipment in accordance with FAR 43, App. D. All maintenance to be performed will be in accordance with and applicable manufacturer?s service instructions. WEIGHT BALANCE and EQUIPMENT LIST: Revised Aircra? Weight Balance and?Equipment List. . . . The above installation meets the requirements for static loading in accordance with A.C.43.13-2B Chapter I par. 106 through 114. Nochanges were noted to the compass system. Further details are on ?le at Yingling Aircraft under W.O. ii ITR 15122. 7 r_ I Additional Sheets Are Attached a .- FAA Form 337 (10-06 mi saw '1 i A ?rue-e 4 .VJI. . nthvuru .1 . Hun,? 0 US Department of Transportation Federal Aviation Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form Approved Electronic Tracking Number OMB No. 2120-0020 1 "30/2007 For FAA Use Only 1 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 oi 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) Nationality?and Registration Mark Serial No. USA N508RB 20885008 1. Aircraft - Make Model Senes CESSNA 2088 GRAND CARAVAN Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) 2, 0m, CESSNA AIRCRAFT COMPANY Address so. BOX 7704 DEPT 095 City WICHITA State KANSAS Zip 67277 Country USA 3. For FAA Use Only Tiredataiderrtliied for the above described slammed t0 pontormity impaction by a person 3mm in FAR 4&7 APR 1 9 ZUI3 4- Date improving inspector WId?l'lZa. KS Daniel Orpin 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model Serial Number AIRFRAME (As described in Item 1 above) POWERPLANT El PROPELLER Type APPLIANCE El E1 Manufacturer 6. Conformity Statement A. Agency?s Name and Address 8. Kind of Agency - Name YINGLING AVIATION US. Certi?cated Mechanic 'Clj?anufacturer - - . - I Addre352010 AIRPORT ROAD Foreign Certi?cated Mechanic C. Certi?cate N0- City WICHITA State a Certi?cated Repair Station YN8R621 2mm ?um? 9?8-5 Certificated Maintenance Organization RADIO CLASS 1'2'3 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. A per 14 CFR Part 43 Extended range fuel SignatureIDate fAuthorizedlndi "dual agate; .e .v ?1 /?a?c3 ~73 7. Approval for Return to-Service Pursuant to the authority given persons speci?ed below, thez'unit identi?ed in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is" APPROVED REJECTED - FAA Standards . . . Person Approved by Canadian Inspector Manufacturer Maintenance Organization Depanmem of Transport BY . Other (Specify) FAA Designee Repair Station Inspection Authorization Certi?cate or SignaturerDate of Authorized Designation No. YN8R621Y I FAA Form 337 (10-06wan-A4,-- 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 I . (lf more space is required. attach additional sheets. identify with aircraft nationality and registration mark and date work completed.) I a USA nsosna 4'5 Nationality and Registration Mark Date CESSNA 2088- SIN 20885008-N508RB INSTALLED SYSTEM: The following components were installed in accordance with the manufacturer?s component installation instructions adapted as required using A.C. 43.13-23 par.202, 203 and 204 guidelines #2 Audio System: Garmin GMA 1347 Audio Panel PIN 010-00276-00, 1.7 arm 115.4 Marker Beacon Splitter CI 509, .15 arm 113.5 WIRING: Wire used was installed in a?c'c?citid?iiri?'ia?Withl the manufacturer?s installation instructions adapted as required with A.C.43.13-ZB par.207 guidelines, and of the appropriate gauge required by A.C.43. 13-IB par.l 1-76.& 77. Wire was installed in accordance with Chapter 11, Section 5 par. 11-66 through 11-69; Section 8 par 11-96; Section 9 par. 11-115 through 11-126; Section 11 par 11-146 through 11-147, and Section 16 par. 11-205 through 11-210. Electrical loads have been evaluated in with AC. 43.13-13 Chapter, l__1,_Section 3_par. 11-35_ar_1_d 11-36 and were. found to be within limits. All installed equipment was tied to ship's power via in-line fuses, pull-type and switch type circuit breakers with locations and labels as follows: 1 Garmin GMA13i47Audio Panel, 5 AmP,_Avionics Bus .2,Av_ionicsCircuit Breaker Panel, labeled_?_fAudiq a, Wiring Diagrams used for reference and installation were from the following manuals: GarminGMAl347 Installation Manual . Number 190-00303-20 July 2011 Rev. G. Garmin 01000 Cessna Caravan Line Maintenance Manual 190-00869-00 Revision May 2012 Yingling Wiring Diagram WD-20835008-15122-1 Rev A OPERATIONAL GROUND CHECKS: Post installation ground function and accuracy tests were performed in accordance with manufacturer instructions. All systems operated normally. Standard ground test IAW AC 43.13-lB par 11-106 and 11-107 performed using Yingling Standard (Rev 1) procedures completed on 2122 with no adverse effects noted. A Placard: The following placards are installed above the pilot and co-pilot?s GMA 1347 Audio Panel. COM. interference may occur during transmissions of opposite transceiverswithin 2 of each other" CONTINUED AIRWORTHINESS INSTRUCTIONS: As per the Installation Manuals listed, no regular periodic maintenance is required. Maintenance is ?On Condition? and service or repair is required only when a malfunction is detected. Reference the aircraft maintenance manual, and this FAA 337. Inspect all equipment in accordance with FAR 43, App. D. All maintenance to be performed will be in accordance with A.C.43. 13-1 and applicable manufacturer?s service instructions. WEIGHT BALANCE and EQUIPMENT LIST: Revised Aircraft Weight Balance and Equipment List. The above installation meets the requirements for static loading in accordance with A.C.43.13-2B Chapter 1 par. 1044 through 112. No changes were noted to the compass system. Further details are on file at Yingling Aircraft under W.O. 15122. I El Additional Sheets Are Attached FAA Form 337 (10-3.3m . ?sa?_f . . hi: slam?mama] .. -[ls .np. Ale. .. call?; u. ,n ?august. a -. . .2 ?but. I 0 US Department of Transportation Federal Aviation Administration a MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form ApprOved OMB No. 2120-0020 1113012007 Electronic Tracking Number For FAA Use Only 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 few (49 U.S.C. 1421). Failure to report can resui for each such violation (Section 901 Federal Aviation Act 1958) tin a civil penalty not to exceed $1,000 I Nationality and Registration Mark Serial No. 1. Aircraft USA NSOBRB 208B5008 Make Model Series CESSNA 2088 GRAND CARAVAN Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) 2. Owner FIVE POINT AERIAL SURVEY Address p_0_ Box 13517 City WEST PALM BEACH State FLORIDA Zip 33406 Country USA 3. For FAA Use Only 4. Type 5. Unit identi?cation :Repair Alteration Unit Make Model Serial Number AIRFRAME (As described in Item 1 above) 3 i] POWERPLANT PROPELLER El Type APPLIANCE El Manufacturer 6. Conformity Statement A. Agency's Name and Address Name YINGLING AVIATION Addr9532010 AIRPORT ROAD City WICHITA 2ip672 77 State Country B. Kind ongency- [3 us. Certi?cated Mechanic El [Manufacturer El Foreign Certi?cated Mechanic C. Certi?cate No. El Certi?cated Repair Station YN8R621Y Certi?cated Maintenance Organization RADIO CLASS 1'2'3 D. I certify that the repair and/oraiteration made to the unii(s) identi?ed in item 5 above and described 0n 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 SignatureIDat of Authorized Individual - per14 CFR Part 43 44-02515 7. Approval for Return to Service Pursuant to the authority given persons speci?ed befw. the unit identi?ed in items was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is I APPROVED REJECTED 1 FAA Form 337 (10-06) FAA Fit Standards . . . Person Approved by Canadian .lnspecmr Manufacturer Maintenance Organization Department of Transport BY . Other (Specify) FAA Designee Repair Station lnspection?Authorizalion . Certi?cate or SignaturetDate of Authorize ividual Designation No. YN8R621Y I I 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 ofWork Accomplished - (if more space is required, attach additional sheets. identify with aircraft nationality and registration mark and date work completed.) . $4 Nationality and Registration Mark Date LISA Hanson CESSNA 208B- 208B5008-N508RB . INSTALLED SYSTEM: The following avionics equipment was installed IAW GARMINAT, Inc. STC Number SA01487SE-D and STC Master Data List DWG Number 005-C0217-Receiver 13m in 1-00987-00, 2.60 (with modular-rack) arm 115.0' 0 GASS Antenna 010-10600-01, .25 arm 149.0 OPERATIONAL GROUND CHECKS: Required ground tests were performed and all equipment was found to Operate properly. CONTINUED AIRWORTHINESS INSTRUCTIONS: Reference GARMIN GDL XM Satellite Radio Instructions for Continued Aimorthiness DWG Number 190-00355-00 Rev dated 05/09/11. WEIGHT BALANCE and EQUIPMENT LIST: Revised Aircra? Weight Balance and Equipment List. See Yingling Aircraft INC Major Alteration Weight Balance/ Equipment List Revision for detailsThe above in?tallation meets the requirements for static loading in accordance with A.C.43.13-ZB Chapterl par; 106 through 114. No changes were-noted to-the compass system. Further details are on-?le YN8R621Y underrW.O. it ITR.15122.. Additional Sheets Are Attached FAA Form 337 (IO-06 147: 2 li "till 71! I l? li?ll?i" . ?Ir . I I Form Approved - . Electronic Tracking Number 0? MAJOR REPAIR AND ALTERATION gillgoggoemozo u.Propeller, or Appliance) For FM Use Only Federal Aviation Administration? INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 439-1 (or subsequent revisionthereot) 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 Aviati'on?A'ct'i 958) i man's-5 Nationality and Registration Mark Serial No. USA N508RB 208B5008 1. Aircraft Make Model Series CESSNA 2085 GRAND CARAVAN Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) 2. Owner FIVE POINT AERIAL SURVEY Address P.O. BOX 18517 City WEST PALM BEACH Slate FLORIDA Zip 33406 Country 3. For FAA Use Only 4. Type 5. Unit Identi?cation Repair Alteration Unit Make Model Serial Number I AIRFRAME i I . (As described in item 1 above) I: POWERPLANT El PROPELLER Type APPUANCE El [3 Manufacturer 6. Conformity Statement A. Agencys Name and Address B. Kind of Agency AVIATION US. Certi?cated Mechanic IManufacturer Addre352010 AIRPORT ROAD Cl Foreign Certi?cated Mechanic (3- Certi?cate N0- Citv State ?5 Certi?cated Repair Station YN8R621Y mpg?67277 Country USA Certi?cated Maintenance Organization RADIO CLASS 1 '2'3 D. certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the US. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel SignaturelDate of uthorized lndividu per 14 CFR Part 43 i .. App. a? 27 7. Approval for Realm to Service Pursuant to the authority given persons speci?ed below, the unit identi?ed in items was inspected in the manner prescribed by the Administrator or the Federal Aviation Administration and is APPROVED REJECTED FAA ta :1 . . . Person Approved by Canadian inspect: arcs Manufacturer Maintenance Organization Department ?Transport BY . Other (Specify) FAA Designee Repair Station inspection Authorization Certi?cate or SignaturelDate of Authorized i ividuai Designation No. YN8R621Y f/{Zkg 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.) USA N508RB 5 43 Nationality and Registration Mark I I Date CESSNA 2088- SIN 20885008-N508RB Installed Equipment: The following system was installed using existing factory wiring and in a Space provided by the aircraft manufacturer. Installation was completed in accordance with the manufacturer?s component installation instructions adapted as required using A.C. 43.13-2B par.202, 203 and 204 guidelines. Honeywell KRA405B Altimeter System: 0 Radar Altimeter Receiver/Transmitter (with mounting tray) PIN 066-01153-0101, 3.3 F.S.S. 377.90 Antenna Installation: The following antennas were installed in accordance with the manufacturer?s component installation instructions adapted as required using A.C. 43.13-28 chapter 3 guidelines. 0 Radar Alt Antenna (FWD) 867-2002, .2 (alt bottom of fuselage) F.S.S. 393.0 0 Radar Alt Antenna (AFT) 367-2002, .2 (aft bottom of fuselage) F.S.S. 403.0 Interface: The KRA 405 Altimeter information is displayed on the #1 #2 PFD of the Garmin G1000 System. The Aural alert is heard 7' through the existing Garmin GMA 1347 Audio Panel as unmuted audio. WIRING: Wire used was installed in accordance with the manufacturer?s installation instructions adapted as required with A.C.43.13-ZB par.207 guidelines, and of the appropriate gauge required by par.1 1-76 77. Wire was installed in accordance with Chapter 11, Section 5 par. 11-66 through 11-69; Section 8 par 11-96; Section 9 par. 11-115 through 11-126; Section ?11 par 11-146 through 11-147, and Section 16 par. 11-205 through 11-210. Electrical loads have been evaluated in accordance with A.C. 43.13-lB Chapter 11, Section 3 par. 11-35 and 11-36 and were found to be within limits. All installed equipment was tied to ship?s power via in-line fuses, pull-type and switch type circuit breakers (013) with locations and labels as follows: KRA 405B Amp Avionics Bus 1 (located on the Avionics Panel), labeled ?Radio Alt? Wiring Diagrams and installation instructions used for reference were from the following manuals: I Honeywell KRA 405B Installation Manual Number 006-10536-0010 Rev 11 dated 30 July 2010 Cessna Model 208 Wiring Diagram Manual Rev 9 OPERATIONAL GROUND CHECKS: Post installation?ground function and accuracy tests were performed in accordance with manufacturer instructions, all systems Operated normally. Standard ground test completed LAW AC 43.13-1B par 1 1-106 and 11- 107 no adverse effects noted. EMUEMC test completed IAW Yingling Aviation-Avionics Standard Test Procedures dated ?gs ~43 CONTINUED AIRWORTHINESS INSTRUCTIONS: As per the Installation Manuals listed, no regular periodic maintenance is required. Maintenance is ?On Condition? and service or repair is required only when a mal?inction is detected. Reference the aircraft I maintenance manual, and this FAA 337. Inspect all equipment in accordance with FAR 43, App. D. All maintenance to be performed Will be in accordance with A.C.43.13-1B and applicable manufacturer?s service instructions. WEIGHT BALANCE and EQUIPMENT LIST: Revised Aircraft Weight Balance and Equipment List. The above installation meets the requirements for static loading in accordance with A.C.43.13-2B Chapter 1 par. 106 through 114. No changes were noted to the compass system; Further details are on ?le at Yingling Aircraft under W.O. 15122. Additional Sheets Are Attached FAA Form 337 (10-06 Hag-qrny 4- .rri I'll Il?l?'lt? l' Ii ll) mews-.2.- Form Approved Electronic Tracking Number . MAJOR REPAIR AND ALTERATION 33343232120002" (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Federal Aviation Administration INSTRUCTIONS: Prim or type all entries. See Title 14 CFR ?43.9, Part 43 Appendix B. and 43.9-1 (or subsequent revision thereof) tori _-=instructions and disposition of this form. v-This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty for each 5 such violation. (49 use. ?46301(a)) - Nationality and-Registration Mark. - - Serial No. N508RB 20885008 1' Aircraft Make Model Series CESSNA CARAVAN 2088 Name (As shown on registration certi?cate) Address (As shown on registration certificate) 2 0 FIVE POINT AERIAL SURVEY Addresspo' BOX 18517 . wner PALM BEACH Zip33406 CountryUSA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number I PE AIRFRAME . (As described in Item 1 above) POWERPLANT I PROPELLER Type APPLIANCE [3 Manufacturer 6. Conformity Statement A. Agency?s Name and Address B. Kind of Agency NameYingling Aviation, Inc. US. Certi?cated Mechanic Manufacturer AddressZO?I 0 Airport Road Ci Foreign Certi?cated Mechanic 0- certi?cate N0- CityWiChita State?? [gt Certi?cated Repair Station YN8R621 th67277-0248 - [j Certificated Maintenance Organization D. I certify that the repair and/or alteration made to the unitts) 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 U.S. 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 In a pert4CFR Part43 ??93 4?25-2243 7. Approval for P?urn 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 I APPROVED REJECTED FAA "7 . .i . - - Person Appr?o'v?d byCanadian Inspector Manufacturer MaintenanceOrganization Departmemonranspon BY . . . . .. Other?i?Specitjx) FAA Designee RepairStation [1 Inspection Authorization Certificate or Signature/Date of Authorized Individual Designation No. YN8R621Y 04/25/2013 Robert Hays FAA Form 337 (10-05) '0 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.) USA N508RB 04/25/2013 Nationality and Registration Mark Date Installed Millennium Concepts Inc. Executive Interior with (floorplan) FP-102C in accordance with STC SAO1160WI. Reference Master Drawing List 2015-MDL022. Rev AC, FAA approved 09/14/2009 Aircraft speci?c documents approved by Kevin R. BERT-230295-CE on 8110-3 dated 04/05/2013 are listed as follows: 2015-2500000-5008 Rev IR, "Index Drawing and Installation Instructions. Cessna Model 2088 ?Executive Interior Installation. Serial 20885008", Rel. dated 04/05/2013. 2015-2520999~5008 Rev IR, ?Interior Materials and Finish Requirements, Cessna Model 2088 Executive Interior Installation, Serial 20885008", Rel. date 04/05/2013. 2015-FR20835008 Rev. IR, "Flammability Test Report - Cessna Model 2088. 20885008", Rel. date 04/05/2013. Inspected installed seats per "Acceptance Test Procedure? 2015-ATP003. Rev. B. Rel. date 11-01-2012. Instructions for Continued Ainrvorthiness provided by Millennium Concepts Inc. as contained in document Rev L, dated 09/30/2009. Installed new manufacture 3 point restraints wireel which meet TSO C-114. 617 Light Taupe webbing with Standard Chrome Plating on buckles. MFG date 07-2012. Crew Seats refurbished with same materials as passenger seating. see 8130-3'5 dated Reference Weight and Balance and Equipment List Supplement dated 04/25/2013. END Additional Sheets Are Attached FAA Form 337 (10-05) FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Form Approved OMB. No. 2120-0018 Expiration Date APPLICATION FOR INSTRUCTIONS - Print or type. 00 not write in shaded areas; these are for FAA U.S. Department use only. Submit original only to an authorized FAA Representative. If additional of Transportation AIRWORTHINESS space is required use attachment. For special ?ight permits complete Sections Federal Aviation CERTIFICATE II, VI and VII as applicable. Administration 1. REGISTRATION MARK 2. AIRCRAFT NAME (Make) 3. AIRCRAFT MODEL DESIGNATION 4. YR MFR FAA CODING N508RB Cessna Aircraft Company 2088 2013 5. AIRCRAFT SERIAL NO. 6. ENGINE BUILDERS NAME (Make) 7. ENGINE MODEL DESIGNATION 20835008 Pratt Whitney Canada Corp. PT6A-140 5. NUMBER OF 9. PROPELLER NAME (Make) 10. PROPELLER MODEL DESIGNATION 11_ AIRCRAFT ,3 (Check gamma?) I. AIRCRAFT DESIGNATION ?5 80 peldeoov One Hartzell Propeller, Inc. HC-BSTN-3AFIT1089CICNB-2 El IMPORT APPLICATION IS HEREBY MADE FOR: (Check applicable items) A 1 STANDARD AIRWORTHINESS CERTIFICATE (indicate category) NORMAL CI UTIUTY TRANSPORT El COMMUTER BALLOON OTHER SPECIAL AIRWORTHINESS CERTIFICATE (Check appropriate items) 7 PRIMARY 9 LIGHT-SPORT (Indicate Class) AIRPLANE POWER-PARACHUTE WEIGHT-SHIFT-CONTROL GLIDER LIGHTER THAN AIR 2 LIMITED Class I 5 PROVISIONAL (Indicate class) Class II AGRICULTURE AND PEST CONTROL 2 AERIAL SURVEY 3 AERIAL ADVERTISING RESTRICTED (indicate operationfs) (a be conducted) FOREST (Wridiife Conservation) 5 6 WEATHER CONTROL OTHER (Specify) RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION AIR RACING 5 CREW TRAINING 6 MARKET SURVEY DbAOthd TO SHOW COMPLIANCE WITH THE CFR 7 OPERATING (Primary Category) KIT BUILT AIRCRAFT BA Existing Aircraft without an airworthiness certi?cate do not meet 5103.1 EXPERIMENTAL {Indicate aperafion(s) to be comm) 8 OPERATING BB Operating Light-Sport Kit-Built ll. CERTIFICATION REQUESTED LIGHT-SPORT BC Operating light-sport previously issued special light-sport category airworthiness certi?cate under 21.190 UNMANNED 9A RESEARCH AND DEVELOPMENT SC ICREWTRAINING 9 AIRCRAFT 90 MARKET SURVEY FERRY FLIGHT FOR REPAIRS, ALTERATIONS, MAINTENANCE. OR STORAGE SPECIAL FLIGHT PERMIT (Indicate EVACUATE FROM AREA OF IMPENDING DANGER operation to be conducted then a comma Sew-on V, a, OPERATION IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT as applicable on reverse side) DELIVERING OR EXPORTING 5 FLIGHT TESTING 03th4 CUSTOMER DEMONSTRATION FLIGHTS 6 MULTIPLE AIRWORTHINESS CERTIFICATE (Check ABOVE: 'Restn?cted Operation'and 'Standaro'" or 'Umited'as applicable) A. REGISTERED OWNER (As shown an certi?cate oraimrari registration) IF DEALER, CHECK HERE IX NAME ADDRESS Cessna Company One Cessna Boulevard, B. AIRCRAFT CERTIFICATION BASIS (Check appiicabie blacks and complete items as indicated) AIRCRAFT SPECIFICATION 0R TYPE CERTIFICATE DATA SHEET (Give No. and AIRWORTHINESS DIRECTIVES (Check Ifeli' applicable AD's complied with the Revision No.) number attire test AD SUPPLEMENT available in the biweekly series as or the date of apdlm?on) A37CE Revision 19 2013-06 Mar. 11, 2013 AIRCRAFT LISTING (Give page numbeds? SUPPLEMENTAL TYPE CERTIFICATE (List number of each STC incorporated) NIA SA3S49NM C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS CHECK IF RECORDS IN TOTAL AIRFRAME HOURS IEXPERIMENTAL ONLY (Enter hours ?own since last certi?cate issued COMPLIANCE WITH 1.0 3 or renewed) 14 CFR section 91.417 D. CERTIFICATION - I hereby certify that I am the registered owner (or his agent) of the aircraft described above, that the aircraft is registered with the Federal Aviation Administration in with ?tie 49 of the United States Code 44101 et 5g. and applicable Federal Aviation regulations, and that the aircraft has been inspected and is airworthy and eligible for the airworthiness certi?cate requested. A 1 A A DATE OF APPLICATION NAME AND TITLE (Print or type) SIGNATURE Mar. 29, 2013 Ralph Cabrera, Quality Supervisor A. THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY (Complete the section only if 14 CFR part 21. fem) applies. 7 2 14 CFR PART 121 CERTIFICATE HOLDER (Give 1 3 ICERTIFICATED MECHANIC (Give Certi?cate No.) 6 I ICERTIFICATED REPAIR STATION (Give Certi?cate No.) CERTIFICATION Certi?cate No.) AIRCRAFT MANUFACTURER (Give name or ?rm) 5 AGENCY VERIFICATION IV. INSPECTION DATE TITLE SIGNATURE (Check ALL applicable blocks items A and a) THE CERTIFICATE REQUESTED A I ?nd that the aim? described in or meets reqUiremems ?If 4 AMENDMENT 0R MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE B. Inspection for a special ?ight permit under Section VII V. FAA REPRESENTATIVE CERTIFICATE HOLDER UNDER 14 CFR part 65 14 CFR part 121 or 135 14 CFR paw DATE MIDOIFSDO FAA SIGNATURE or FAA CERTIF TION FILE REVIE OFFICE 4 SIGNATURE AND NO 1 SIGNATURE 047.29, 20!) CE-43 19 A la] ODA-100129-CE 35/ CERTIFICATION FAA Form 8130-6 (04-2011) All Previous Editions Superseded Page 1 of 2 A MANUFACTURER NAME ADDRESS 2 e. PRODUCTION BASIS (Check applimbie items) a, . 3 PRODUCT CERTIFICATE (Give pmduc?on certi?mle number; :9 TYPE CERTIFICATE OTHER: 0. GIVE QUANTITY OF CERTIFICATES REQUIRED FOR OPERATING NEEDS DATE OF APPLICATION NAME AND TITLE (Print or type) SIGNATURE A. DESCRIPTION OF AIRCRAFT REGISTERED OWNER ADDRESS BUILDER (Make) MODEL SERIAL NUMBER REGISTRATION MARK B. DESCRIPTION OF FLIGHT CUSTOMER DEMONSTRATION FLIGHTS El (Checkifapplimbie) FROM TO VIA DEPARTURE DATE DURATION C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EQUIPMENT PILOT FLIGHT ENGINEER Cl OTHER (Specify) D. THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINES REQUIREMENTS AS FOLLOWS: VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT TEST E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION (Use attachment ifneoessary) airworthy for the ?ight described. F. CERTIFICATION - I hereby certify that I am the registered owner (or his agent) or the aircraft described above: that the aircraft is registered with the Federal Aviation Administration in accordance with Title 49 of the United States Code 44101 cm. and applicable Federal Aviation Regulations, and that the aircraft has been inspected and is DATE NAME AND TITLE (Print or type) .. SIGNATURE . - . . . IggitatIDns and Markings In Compliance 14 CFR Seetion 91.9 G. Statemem of Conformity. FAA Form 813% (Mach when required) . . . . H. Foreign Airworthiness Certi?cation for Import Aircraft 2 8. Current OperatIng LImItatIons Attached (Ma when required) 2 a I: C. Date. Drawin s. Phot ra he. etc. Attach when re uired . cg I. Prewous CertI?cate Issued In Accordance With 3 8 . . . 14 CFR Section CAR (Original attached) a: a D. Current Weight and Balance InformatIon Availble In Aircraft 3 ID 3 E. Major Repair and Alteration, FAA Form 337 (Attached when required) :54m22lqenistgjam?cate Issued Accordance amcmd) . F. This Inspection Recorded in Aircraft Records FM 813045 FAA Form 8130-6 (04-2011) All Previous Editions Superseded Page 2 of 2 UNITED STATES OF AMERICA. DEPARTMENT OF ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND 2 MANUFACTURER AND MODEL 3 AIRCRAFT SERIAL 4 CATEGORY REGISTRATION MARKS NUMBER N508RB Cessna Aircraft Company 2088 20885008 Normal 5 AUTHORITY AND BASIS FOR ISSUANCE This airworthiness certi?cate Is issued pursuant to 49 U.S.C. 44704 and certi?es that. as of the date at issuance. the aircraft to which issued has been inspected and found to conform to the type certi?cate therefor. to be in condition for safe operation. and has been shown to meet the requirements at the applicable comprehensive and detailed airworthiness code as provided by Annex to the Convention on Intemationai Civil Aviation. except as noted herein. Exceptions: . DUPLICATE 6 TERMS AND CONDITIONS - - Unless sooner surrendered. suspended. revoked. or a Iennination date is otherwise established by the FAA. this airworthiness certi?cate is effective as long as the maintenance. preventative maintenance. and atterations are performed in accordance with Parts 21. 43. and 91 of the Federal Aviation Regulations. as appropriate. and the aircraft is registered in the United States. DATE OF ISSUANCE FAA REPRESENTATIVE DESIGNATION NUMBER Mar. 29, 2013 Ken Gould y-v Any alteration. reproduction. or misuse at this certi?cate may be punishabte 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 8100-2 (04-11) Supersedes Previous Edition US of Transportation Federal Aviation Administration 0 Department MAJOR REPAIR AND ALTERATION (Airframe, Powerplant. Propeller, or Appliance) Form Approved OMB No. 2120-0020 2128/2011 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 repon can result in a civil penalty for each such violation. (49-U.S.C. ?46301(a)) Nationality and Registration Mark Serial No. N508RB 20835008 1- ?ma? Make Model Series Cessna 208 Name (As shown on registration certi?cate) Address (As shown on registration certi?cate) Adm? mules 2' owner City Wichita State sas Cessna Aircraft Company Zip 67277 Counuv United States 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No, AIRFRAME (As described in Item 1 above) POWERPLANT El PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Name Wit Comnany U. S. Certi?cated Mechanic I Manufacturer Address 3 Cessna Foreign Certi?cated Mechanic C. Certi?cate No. city Wichita State Kansas Certi?cated Repair Station Zip 67215 Country United States Certi?cated Maintenance Organization PC-4 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 c0rrect to the best of my knowledge. Extended range fuel per 14 CFR Part 43 App. . Kenneth F. Patrick Signature/Date of Authorized Individual 03/29/2013 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 FAA Fit. Standards - . . Persons Approved by Canadian Inspector Manufacturer Maintenance Organization Depanme?lgt Transpon Other (Specify) FAA Designee Repair Station Inspection Authorization PC-4 Certi?cate or Designation No. Signature/Date of Authorized Individual Kenneth F. Patricj??D 03/29/2013 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. identity with aircraft nationality and registration mark and date work completed.) N508RB 0309/2013 Nationality and Registration Mark Handbook (POH). END [3 Additional Sheets Are Attached Reference, Aero Twin decument number AT-RL-1001-ICA for instructions for continued ainivorthiness. Dale STC SA3649NM, Aero Twin Rudder Gust Lock Kit. PIN 001 was installed in accordance with Aero Twin Installation Instructions document number Weight and balance for this installation is included in the original weight and balance for this aircraft. Aero Twin Flight Manual Supplement was added to the Pilot's Operating FAA Form 337 (10-06) 9 US Department of Transportation Federal Aviation Administration MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form Approved OMB No. 2120-0020 228001 1 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. $544701). 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. I N508RB 20885008 1 . Aircraft Make Model Series Cessna 2088 Name (As shown on registration certificate) Address (As shown on registration certi?cate) Address Box 7704 2' owner City Wichita State Kansas Cessna Aircraft Company Zip 67277 Country United States 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteratlon Unit Make Model Serial No. AIRFRAME described in item 1 above) POWERPLANT El PROPELLER Type APPUANCE Manufacturer 6. Conformity Statement A. Agency?s Name and Address 8. Kind of Agency Name Cessna Aircraft Company U. S. Certificated Mechanic I Manufacturer Address 3 Cessna Btvd. Foreign Certl?cated Mechanic C. Carti?cate No. City Wichita suaiu Kansas? Certi?cated Repair Station Zip 67215 Country United States Certi?cated Maintenance Organization X07R071 D. I certify that the repair andlor alteration made to the unitis) 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 U.S. Federat Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range feet per 14 CFR Part 43 App. Signature/Ba Matt iranow A Au anym? idual 14% ad! - 03/30/2013 7. Approval for Return to Service Pursuant to the authority given persons specified below. the unit Identi?ed in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is Approved Rejected FAA Flt. Standards Ins ector BY Manufacturer Maintenance Organization Persons Approved by Canadian Department of Transport FAA Designee Repair Station Inspection Authorization Other (Specify) Certi?cate or Designation No. X07R071Y 03/30/2013 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 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.) NSOBRB 03/30/2013 Nationality and Registration Mark Date installed Aero Twin Exhaust De?ector PIN EDS-100 per STC SAOZOBOAK-D. Installation was in accordance with Aero Twin Drawing No; EBB-100. Weight and Balance has been updated'to re?ect this installation and hasbeen inserted into the Cessna Maintenance Manual, Chapter 78 is recommended for the continued ainivorthiness requirements. END- Additional Sheets Are Attached FAA Form 337 (10-05)