el fr MAJOR REPAIR AND ALTERATION US Dess-rrnm

el fr MAJOR REPAIR AND ALTERATION US Dess-rrnm of Tr systukn (Airframe, Powerplant, Propeller, or Appliance) Pram /Matron AthillnlitiliCOO cwa ne.2120402) Ey S414011I neves Tweet wear MA Um One INSTRUCTIONS: Mint or type See Tide 14 CFR Part 43 Append; B, AC 43.9-1 (or subsequent thereof) for as entries. §43.9. and revision instruceons and caposidon of Ws form. Ms report Is rewired by law µ9 U.S.C. §44701). Falun) to report can result in pen" for each such violation. (49U.S.C.§41001(a)) 1. Aircraft NadanalitY and Registrebon Mark N727KB Serial No. RK-260 Make Beech Model 400A Sancta 2. Owner Name (As shown on registraton certincate) PUMPJACK AVIATION LLC Address (As shown on registration certificate) banns 1511 W EPA 91 CA) Caoo. Stab WY LA 026014203 Couruy USA 3. For FM Use Only 4. Type S. Unit Identification Repair Mention Unit Make Made( Serial No. O in AIRFRAME .both (As described fn non? I above) RX. 410 O O POWERPLANT O O PROPELLER O O APPLIANCE Type stsmeaclunar 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency sere ShresiAter a Clones Moon 4 U. S. Ciellfirsiteci ~ado 1 Manufacturer we. Amino* ForrionCernacesso Mechanic C. Certificate No. orr SS Or KS Swoon 3437625 SI 0117 convi 115A ms s; nence Organize:al 0. !entry that the repair and/or alteration made to the unit(s idenefled at tarn 5 above and described on the ravens or attachments hereto have been made in accordance with the requirements of Pan 43 c4 the U.S. Federal Aviation Regulations and that the information furnished heroin es bye and correct to ere bast of my knowledge. per t4 CFR Part 43 ❑ Extended range fuel 91 APP. B of horized Inctrvidual t -1q4020 7. Approval for Return to Simko Pursuant to the authority 9 ven persons specked below. the Unit identified in sera 5 wee inspected in the manner ;ascribed by the Administrator of me Federal Aviation Administration and is plApproved nitelectee BY FM FF. Standards Inspector Manufacturer Maintenance Organization Panora ApPreNed KY Canna" Department of Trooper FAA Designee Repair Station X Inspection AUtlailtrilial Other (SpeCd4 Certificate Cf Designation No.3437625 SigrultufWDEKEI of Authonzod Individual a ff C'S Iti - 20/30 FAA Form 337 (10/06) Page I SDNY_GM_02758010 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244932 EFTA01261592 NOTICE Weight and balance or operating limitation changes shalt be entered in the appropriate aircraft Ward. An alteration must be COnwabble with all previous alterations to assure continued conformity MO the applicable airworthiness requirements. S. Descapdan of Work Accomplished (If more space is tallied. attach odoloons) 31100t3 Identify wen efroWt netiOneety end regiavellon mem end Wife *or* completed.) .4777101 •1420 Netionelty and Registration PAWS Dale Installed copilot windshield P/N: LA45AS31001-024, S/N: 10013 under STC no. ST018935WI. Weight and balance revision no factor. ClAddelonal Sheets An Attached FM Form 337 (10/06) Page 2 SDNY_GM_02758011 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244933 EFTA01261593 0 MAJOR REPAIR AND ALTERATION u s Deaemmintof (Airframe, Powerplant, Propeller, or Appliance mmert moos *ewe Awnwaw Fano Amend CAM No 2i20.4020 r30,2C07 Meannic IRON Nods Fos FAA Me Only INSTRUCTIONS. Print or type all entries Soo FAR 43.9. FAR 43 Append.% B. and AC 43.9-1 (or subsequent Rowe therocif) for mabuctions and discos/Son of tie limn. This nowt is required by ern (49 U S C 1421) Faikrra ki. report can result In CM pearly not to exceed x1.000 far tab such Waco (Section 901 Federal Anton Act 1958) 1 . Aircraft Natonallty and Regisastion Mark N727KB WW1 No RK-260 Make Raytheon Aircraft Company Model 400A 1 See. 2. Owner Name (Ai Mown on registration corterain) Flight Options .LLC Moss, Awe) Anson t PKWY Ct, wt. OH no USA 3. For FAA Use OW 4. Type E. Unit itiontincatlon Repair Maralke Unit Make MOW sone Number CI El AIRFRAME PM described In ;tern I above) 0 0 POWERPLANT 0 0 PROPELLER El ElAPPLIANCE Taw mieuracam IL Conformity Statement A Agency's Name and Address B. KM of Arcot OH Ma 0 U.S. Ceraficated Mechanic 0 IMenufacturer 0 Foreign Ceraicated Mechanc C. Certificate No. 0 CsnAcale0 Rose Staten CRS # VVC7R34SJ 0 Centime:0 MaIntonanCe OnoWitation o made to the uni(s) Idwitlfied In Nam 5 atcre• and deleted on the reline or attaChmentS hatid0 have been made n aCCOrdatiOn wet the niquiromeras d Part 43 of Me U.S. Facet* Adam Repulsions and IoM Urbana/ion furnished herein is true and coned to the best of my ImoMedpe. Extended rano fuel Wisea 14 CFR Pal 43 0 MostireiDete al AtOorIzed Irdni3ual Anton J. Koprivnik r 02/24/2020 7. Approval for Return ba Pursuant to the authority given persons maned below. the uM klenakid ii Rem 5 was Impacted in to manner presorted by the Admmotrator of ale Federal Aviation Adrnolinranal and is El rePROWO 0 REJECTED BY FM Fit Standards inspector Manutactutw Maintenance Orponitaton Parson Approwdl by Camden Department of Tranapon FM Oesagnee X Repot staton Meg SOW) Impecte Aultiorttabon Grant* or Desianatfon No CRS I VVC7R348.) Sgricurelosto Of Author/ad Irendual oy zzz ,/' An on J. Koprivnik 02/24/2020 A/ FAA Fort 337 IOW SDNY_GIv10275801 2 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244934 EFTA01261594 SDNY_GM_02758013 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244935 EFTA01261595 NOTICE woof and balance or operating limitation changes shall b e entered in Me appropriate aircraft word. An alteration must be compatible with ail pievfous mentions to assure continued conformity with the applicable ainvorthiness requirements S. Description of Work Accomplished (if mote space Is required, attach additional sheets Identity with *cab nationably and registration mark and date work completed) N727KB Nationality and Registration Mark 02/24/2020 Data This 337 is to correct the original Dated 01/04/2013. Corrected block ti I, Registration number from N746TA to N787TA and fills in the serial number to Ft/C-260. All other data is correct. Part I of 3 The Following Equipment was removed along with Associated Hardware. EFD-871 622-9345-203 Electronic Flight Display EFD-871 622.9345.203 Electronic Flight Display MFD-871 622.9434.213 Multi Function Display ICU-85 6224189-002 Internal Compensation Unit ICU-85 622-6189-002 Internal Compensation Unit AHC-85E 622-9336.400 Attitude/Heading Computer AHC-85E 622-9336-400 Attitude/Heading Computer SDU-640B 622-9735-001 Sensor Display Unit SDU-6408 622-9735-001 Sensor Display Unit SDU-6408 622.9735-001 Sensor Display Unit DCP-5000 822-1028-011 Display Control Panel DCP-5000 822-1028-011 Display Control Panel ARP-851 622.9500-011 Altitude Reference Panel ARP-851 622.9500-011 Altitude Reference Panel AAP-851 822-0328-011 Altitude Awareness Panel AAP-851 822-0328-011 Altitude Awareness Panel CHP-850 622.7397-002 Course Heading Panel DBU-4100 822-0014-002 Data Base Unit DAU-650 622.9344.101 Data Acquisition Unit SOD-640A 622-9347-001 Sensor Display Driver IOC-4000 ( 4) 622-9814.514 Card Assembly MDC-4000 622-9818-751 Maintenance Computer CSU-4000 (2) 822-0049-002 Configuration Strapping Unit FMC-5000 (2) 822-0891-008 Flight Management Computer PWR-4000 (4) 622.9945-021 IAPS Power Card GPS-4000 822-0931-003 GPS Receiver Mounts 622-9430-002 EFD /MFD Mounts EFB Electronic Flight Bag Mounting EAdditional Sheets Are Attached Form 337 0046) SDNY_GM_02758014 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244936 EFTA01261596 SDNY_GM_02758015 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244937 EFTA01261597 NOTICE Weight end balance or operating limitation changes shag be entered In the appropriate aircraft record. A n alteration must be compatible with all previous alterations to assure continued conibmity with the applicable aimorthiness requirements S. Description of Work Accomplished (If more space is required, attach additional sheets Identify with aircraft nationality and ragisfrabon mark end date work completed) N727KB Nationality and Registration Ma* Page 2 of 3 Installed the Following Equipment along with Associated Hardware. 02/24/2020 Date Model Part Number Description Weight Arm CCP-3000 822-1746-002 Cursor Control Panel 2.60 90.0 CCP-3000 822-1746-002 Cursor Control Panel 2.60 90.0 DCU-3001C 822.2362.003 Data Concentrator Unit 5.0 325 DCU-3001C 822-2362-003 Data Concentrator Unit 5.0 325 ECU-3000 822-1200-209 External Compensation Unit 0.40 57.5 ECU-3000 822-1200-209 External Compensation Unit 0.40 57.5 FSU-5010 822-1543-101 File Server Unit fig IFIS) 6.5 60.83 ECU-3000 822-1200-998 File Server Unit (1st IFIS) 0.40 57.5 AFD-3010E 822-1753-416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822.1753.416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822-1753.416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822-1753-416 Adaptive Flight Display 12.90 89.2 IMT-3010 822.1140401 AFD Mounting Rack 4.40 85.0 IMT-3010 822.1140-401 AFD Mounting Rack 4.40 85.0 IMT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 IMT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 10852301700 Fuel Quantity Conditioner 0.90 324 PC920-2A2000PH-2A1 Fuel Flow Conditioner 1.10 325 GPS-40005 822-2189-004 GPS 6.0 37 CI 429.200 GPS/XW Antenna 1.0 166.14 Amp Cluster N241100-002 DC Voltmeter 1.5 97.4 373.93.1501-1 Speed Switch x2 0.25 89.2 D8U-5010E 822-2215-202 Data ease Unit 1.60 134.5 PS-835D 501-1228-004 Power Supply 12.5 52.9 MMT•5000 822-1811-003 File Server Unit Rack 0.30 57.5 MMT-3010 822-1290-003 AHS Mounting Rack 1.80 57.5 MMT-3010 822.1290-003 AHS Mounting Rack 1.80 57.5 CHP-3010 822-1280-002 Course Heading Panel 1.30 92.5 Options Configuration Module OCM-4103 822.1463.228 0.30 57.5 WAAS/I.PV OCM4100 822.1463.228 Options Configuration Module 0.30 57.5 WAAS/tPV El AddlilOnil Shuts Ni Attar:hart Form 337 (won SDNY_GM_02758016 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244938 EFTA01261598 SDNY_GM_02758017 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244939 EFTA01261599 NOTICE Weight and balance or operating Amitatlon changes shall be entered in the vampish, airtualt record. M alteration must be canoe:Age wait at previous alterations ro assure continued calamity with the applicable einvorthiness requirements. 8. Description of Work Accomplished Of more specs is required, attach additional sheets, identify with aircraft natbnally and registration ma* and date yak completed.) N727KB Nationmay and Registration mark Page 3 of 3 02/24/2020 Date Model Part Number Description Weight Arm CSU-4100 (2) 822-1364-002 Configuration Strapping Unit 1.60 55.7 MDC-3110 822.1987-006 Maintenance Data Computer 0.80 55.7 FMC-6000 (2) 822-0868-123 Flight Management Computer 1.90 55.7 ADC-850D (2) 822-0389-468 Air Data Computer 5.30 60.83 AMC-3000A (2) 822.1378-001 Attitude Heading Computer 4.80 57.5 DCP-3030 (2) 822.1828-002 Display Control Panel 1.90 89.96 PWR-4000 (4) 622-9945-022 IAPS Power Card 1.3 55.0 IOC-4100(4) 822.1362.511 Input/output Concentrator 0.8 55.0 XM WR-1000 822-2031-002 XM Weather 41.0 LT-4001-010 Master Caution Panel 1.3 87.0 Rev. Panel 373-91.3203-1 Pilot Reversion Panel 0.2 88.0 Rev. Panel 373.91.3203.3 Co-pilot Reversion Panel 0.2 88.0 9-PEG 373-91-3203-9 9-Pedestal Panel 1.8 92.89 345-6169 ELT Switch 0.2 88.0 Annunciator 2-F840233-I AUX BATT (1/2) Annunciator 0.05 88.0 Annunciator (2) 2-F840232-I Pull Up/ Terrain Annunciator 0.05 88.0 Annunciator 2-F840231-I TERR INHBT/ TERR Fall 0.05 88.0 In Accordance with SIC ST10959SC. See Attached Copy AFM Supplement, Nextant Aerospace Doc. No. 373-00-0023 Rev IR Dated 09/02/2011 or later FM approved revision, Installed on Aircraft. Equipment Pilot Guides are Installed in the Aircraft as Portable Document Format (.pdf) via supplied I-Pad. NOTE: Portable electronic devices used to store required aircraft records required by Part 91.9 are considered Electronic Flight Bags (EFB) per FAA Advisory Circular AC 120-768 par 4-g. Commercial operators are required to obtain authorization for their use from their managing Flight Standards District Office. Instructions for Continued Airworthiness (ICA) Ref Nextant Aerospace Document 373-00-0002.Rev C or Later are Included in the Aircraft Maintenance Records Carried out System Ground Test Plan IAW Master Drawing list (MDL) 373-00-004 Rev C. Carried out Hawker Beechcraft Service Bulletin 34-3431 Reduced Vertical Separation Minimum (RVSM) Airframe Inspection / Modification. Performed FAR 91.411Inspection per Part 43 appendix "E" Pitot Static & FAR 91.413 Inspection per Part 43 appendix "F" Transponder System checks. Aircraft Weighed see Report Dated 12/21/2012 ❑ Additonal Sheets Are Attached town 337 hoes) SDNY_GM_02758018 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244940 EFTA01261600 SDNY_GM_02758019 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244941 EFTA01261601 0 MAJOR REPAIR AND ALTERATION Js : v.:m.3,n cl "rvdp:cisi.., (Airframe, Powerplant, Propeller, or Appliance) Nam! anon Adrileilaatlen Fan /wares ONO PO 2,10490 Metal (Yawn 'wiry Naas Fee MAIM 0.1. eNSTRUCTiCtiS: Pala w tyre all entnes See Tee 74 CFR 1.3.0. Pan 43 Appendix S. IS AC 13.91 (or subtentinni tensing' Pew!) be inStilietan and dillmalllon of Ws fern This report la required by law (49 U.S.C. §44701). Failure lo report can resutt in a civil penalty for OaCh such Vidalia,. (49 U.S.C. 946301(1)) Nationality and ReptilitIon Mark USA N727KS Serial No. RK-2S0 1. Micron Make Raytheon Aircraft Company uaaa Saes 4 Name (As shown on rep/groom contecale) Ad 2. Corner Co Nan MN. XT Leasing CO. LLC as 3. For FAA Use Only I The data identified herein complies with the applicable DALE E sinvoithiness requiremenu and ts approved for the above ••••••••••••••••••pos desenbed aircraft, subject to oonfomilty Inspection by a person DRENCKHAHN """aa an authorised in I4CFR 13.7 FAA Inspector MSP-FSDO•GLI5 4- WM & UMIldentlflealon Repair Minion Urn Make Model Serial No • RI AIRFRAME kern 1 (4.5 deserts : f in above) 0 0 POIM1ERPtANT 0 0 PROPELLER CI O APPLIANCE Tape wanutaawar 4. Confonwity 91altenteril I 0 Kind of Agency S. knorwrie U. Canes I Menufedurin Falign Canicard Mahe* C. Catibleale NO. / CankaMORaork Simon I cartileand Malnwenos OrganiaMlon KX5R005N I have been made in accordance lurnnhed Wain Is bee and coned ( ) Centime in awn el above antleemotied on ma reverse orattadtrnents hereto with the repukemenla of Pert 43 of Me U.S. Federal Analog, Regulannte and that the information to Me best of my knowledge. Extended range Net pee 14 CFR Pan 43 O APO a Signature/Dele orMed Intivkluil .5- /1-.2o ( f-^ 7. Approval for Return to Service le Pursuard to the eugmnty Yuen persons spec-Fed below. Me unit Identified in nem 5 was impeded in Ma manner pretabged by Admenstralor of me Federal Aviation Acknostiaten and is 2 Appienied 0 Rejected SY FAA Mt Standards Inspector Manufacturer Maintenance COMnizabon Parkin AppeNed by tannin Demotion ce Troweat FAA Designee / Reba, Sleben Inspection Audit:enamel OthW (SPonF)7 Ceatificalo or Designation NO KX5R005N Sigratunut of Aulbeetzed tridrenualz, --e---g-7......--dezn S^I )-2o /i.--FAA Form 337 rrcm. SDNY_GM_02758020 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244942 EFTA01261602 SDNY_GM_02758021 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244943 EFTA01261603 NOTICE Weight end balance or operating Mutation changes Shea be entered in the appropnale aircraft record An alteration must be COmpebblit with el previous *Aerations to assure continued conlomety whir the applicable airworthiness requirements. IL DewSart of Work Accomplished (If ma were re reaaed each actitaned sheets leen* rani entre natfoneity end movie:Kra malt and date tarkCariplered) USA 14727 KI3 Nakielity and Realltretren Mark [ Date 1. Installed Gamin Automatic Dependant Surveillance -Broadcast (ADS-6) system referencing Elliott Aviation Technica Products Development Inc. drawings 121.3761-M0560.60 revision IR, and 121-4070-E0560-000 revision PA. A satisfactory ground test of the ADS-8 Out system was completed using a Aerofiek IFR-6000. checking for proper configuration and equipment performance requirements. The Installed ADS-B Out system has been shown to meet the equipment requirements of 14CFR 91.227. 2. The following LRU's are installed and interfaced referencing the previously approved equipment pairing of the GTX-3000 Mode '5' transponders and the GDL-88 Universal Access Transceiver by STC ST04214CH. a) Removed existing Rockwell Collins TOR-94D Mode "S" Transponders pin 622.9210-004. sin's 3MPD. and 6053 from right hand upper avionics shelf at sta 48. Installed two Gamin GTX-3000 Mode "S. Transponders (TSO-C112d), pin 011-01997-00, on right hand upper avionics shelf, s/n 20S008042 at sta. 49.7. and s/n 20S008050 at ste. 52.95. b) Installed a Garmin GDL-88 Universal Access Transceiver (TSO-C154c), p/n 010-00860-30. s/n 22U000700 on right hand upper avionics shelf at sta 46.95. The G0L-88 is connected to a GA-36 Antenna (TSO-C144), p/n 013-00244-00 s/n 14145 at sta. 128.7 through the GPS port and a UAT Antenna (TSO-C86c) p/n CI710.40.30. s/n 522354 at Ma. 35.1 for the FIS-B weather function. c) Installed a Garmin Flight Stream 110 (TSO-C157), p/n 010-01194-01. s/n 3G0000731 on the co-pilots manual holder at sta 136, interfaced to the GDL-88 UAT. The Flight Stream 110 provides FIS-B weather, ADS-B traffic, and GPS position data. 3. The FAA Approved Airplane Flight Manual Supplement for the Garmin Automatic Dependant Surveillance (ADS-B) Transponder installation ReporNumber FMS-4079-560 Revision IR, dated was placed in the Aircraft Flight Manual and must be available to the pilot at all times. 4. Structural work performed referencing the following: Elliott Aviation Technical Products Development Inc. drawing 121-3761-M0560-60 revision IR. Beechcraft Corporation Model 400/400A Maintenance Manual p/n 128-590001.9 Revision C29, Beechcraft Corporation Structural Repair Manual phi 128590001.17 Revision C16. and acceptable methods contained in AC43.13-1B. chapter 4, si.c.uon 4, and AC43.13-28, chapters 1,2,and 3. 5. The electrical interface of the Garmin Automatic Dependant Surveillance (ADS-8) Transponders was performed referencing Elliott Aviation Technical Products Development Inc. drawing 121-4070-E0560-000 revision PA. Wiring fabrication and interface performed in accordance with Beechcraft Corporation Beechjet 400/400A series wiring manual pin 128-590001-79 Revision 0, and acceptable practices contained in AC43.13.18, change 1, chapter 11. I 6. Weight and balance and equipment list have been revised to reflect this installation. 7. Instructions for Continued Airworthiness, Elliott Aviation Technical Products Development Inc Report ICA-4079-560 Revision IR , provided in aircraft records. END AOrlibcoad Sheets Are Attached FAA Form 337 imam SDNY_GM_02758022 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244944 EFTA01261604 SDNY_GM_02758023 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244945 EFTA01261605 le 41; Elliott Aviation Technical Products Development, Inc. 6601 74m Ave Building A Milan. IL 61264 ELLKYIT AVIATION Instructions for Continued Airworthiness For Garmin ADS-8 System Installation Report No.: ICA-4079- Revision Dated 05/01121 1 01 60 IR 18 19 Instructions for Continued Airworthiness For Garmin ADS-B Out System Installation (Type Certificate A16SW) 0 Z018 ELUOTT AVIATION TECHNICAL PRODUCTS DEVELOPMENT. INC. Elliott Aviation Technical Products Development. Inc. reserves the copyright of all information and illustrations in this publication which is provided in confidence and which may not be used for any purpose other than for which it was onginally supplied. The pubica - may not be reproduced in part or in whole without the consent in writing of Elliott Aviation Technical Products Development. Inc II SDNY_GM_02758024 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244946 EFTA01261606 SDNY_GM_02758025 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244947 EFTA01261607 • Elliott Aviation Technical Products Development Inc. 6601 74" Ave Building A Milan, IL 61264 EWOTT AVIATION Instructions for Continued Airworthiness for Garin ADS•8 S tem Installation Report No.: ICA-4079-660 Revisi• :IR Dated 05/0112 8 2. 19 REVISIONS PAGE Rev Description Page (S) Date Approved By IR Initial Release ALL SDNY_GM_02758026 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244948 EFTA01261608 SDNY_GM_02758027 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244949 EFTA01261609 Elliott Aviation Technical Products Development. Inc. C7, 6601 74m Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No.: ICA-4079-560 Revision: IR Dated 05/01/2018 3 of 19 TABLE OF CONTENTS COVER PAGE 1 REVISIONS PAGE 2 TABLE OF CONTENTS 3 Chapter 1 Introduction 4 Chapter 2 Maintenance Instructions and Shedules 6 Chapter 3 Access 13 Chapter 4 Lifting and Shoring 14 Chapter 5 Loving and Weighing 14 Chapter 6 Towing and Taxing 14 Chapter 7 Parking and Mooing 14 Chapter 8 Placards and Markings 14 Chapter 9 Servicing 14 Chapter 10 Air worthiness Limitations 15 Appendix A Al SDNY_GM_02758028 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244950 EFTA01261610 SDNY_GM_02758029 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244951 EFTA01261611 t:t7 Elliott Aviation Technical Products Development. Inc. C=J 6601 74" Ave Building A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No.: ICA-4079- 60 Revision IR i Dated 05/01/2 18 4019 Chapter 1 INTRODUCTION 1.1 Scope/Purpose/Applicability/Distribution The Instructions for Continued Airworthiness (ICA) described herein are applicable only to RK-260 modified with Gamin ADS-8 System. These ICA describe the recommended and required maintenance procedures for the installation of Gamin ADS-8 System. The maintenance information provided by this document must be included in the operator's Aircraft Maintenance Manual and the operator's Aircraft Scheduled Maintenance Program. All documents listed in the required documents section must be maintained with this document. FM accepted revisions to this document will be distributed by mail to the applicable certifying authorities and operators of legally modified aircraft. 1.2 System Description The features of this modification include the removal of both Collins TDR-94D transponders and replacement win Garmin GTX 3000 transponders, reusing the existing aircraft wiring. This modification also includes a Garmin G 88 GPS / UAT and optional Flight Stream 110 Bluetooth FIS-B installation. A GPS and UAT-SBS antenna is installed. Annunciation is added for ADS-B status. New circuit breakers are installed in the copilot's circuit break r panel. New wiring is added to supply the GTX 3000 transponders with GPS position for the GUI. 88. The Flight Stream 110 (if installed) supports properly equipped FIS-8 capable Bluetooth devices 1.3 Required Data All requited data is located in Appendix A of this document. 1.4 Referenced Gamin documents: 1.5 Nomenclature Drawing Number Rev Date GTX 3000 Transponder Installation Manual 190-00926-01 L Oct 2015 GDL 84/88 TSO Installation Manual 190-01122-00 H Dec 2014 Flight Stream 110/210 TSO Installation Manual 190-01700-00 E Dec 2015 Systems Control: 1.5.1 The GTX 3000 transponders replace the Collins TDR-94D transponders. AN control is via the existing Colli s Pro Line 21 cockpit Control Display Units. No changes to operational control are imposed by this STC. 1.5.2 The GDL 88 is a GPS sensor and FIS-B UAT receiver. The Gni. 88 has no external control. 1.5.3 The Flight Stream 110 is a Bluetooth repeater for the GDL 88 FIS-B products and has no external control. 1.8 Document administration: 1.6.1 This document will be revised by Elliott Aviation Engineering when revisions to descriptive or approval da warrant. 1.6.2 When this document is revised, all pages will be revised to indicate the current level. Chapter 10 will have own revision status embedded. FM approved revisions to the document wiN be distributed by mail to the applicable certifying authorities and operations of legally modified aircraft. is SDNY_GM_02758030 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244952 EFTA01261612 SDNY_GM_02758031 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244953 EFTA01261613 Elliott Aviation Technical Products Development, Inc. G:7 6601 74m Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No: ICA-4079- 60 Revision IR 1 Dated 05/01/2 18 5o 19 1.7 Abbreviations and Definitions: 1090ES A transponder distinction. 1090 is the classic frequency of Secondary Surveillance Radar (SSR) transponders. The addition of 'E5 at the end signifies that the transponder is equipped with Extended Squitter used by the ADS-B aircraft segment. Note that this class of transponder supports Class 'A" airspace (altitudes above 18,000 feet) operations. Typically, no FIS•B or TIS-8 functionality is included, compared to UAT. AMM Aircraft Maintenance Manual DAH Design Approval Holder. The FAA term that includes STC holders such as Elliott Aviation. FIS-B Flight Information System broadcast. A radio frequency service that transmits weather and aeronautical products, either by satellite or ground based systems. Refer to FM Advisory Circular 20-149A for thorough explanation. Latency The total time between when the position is measured and when the position is transmitted by the aircraft. A 14 CFR §91.227 performance requirement for ADS-8 broadcast systems. The collection of specific equipment, interface and testing represented by this STC comprises an approved Latency OEM Original Equipment Manufacturer. SBS Surveillance and Broadcast Service. Provided by the FAA. Ground based transmission at a frequency of 978 MHz. SDA System Design Assurance. A 14 CFR §91.227 performance requirement for ADS-8 broadcast systems. The collection of specific equipment, interface and testing represented by this STC comprises an approved SDA. UAT Universal Access Transceiver. A new device that supports the ADS-8 aircraft segment at lower altitudes (below 18,000 feet) Allows smaller aircraft that operate below Class 'A' airspace a more 1.8 Precautions Typical precautions are to be taken when accessing. removing, replacmg, testing or inspecting these modificatio's. Specific precautions will be addressed in context throughout this document. 1.9 Units of measurement: Non- metric. English units including Inches, feet, etc SONY_GM_02758032 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244954 EFTA01261614 SDNYGM02758033 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244955 EFTA01261615 Elliott Aviation Technical Products Development, Inc 6601 74"' Ave Building A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Chapter 2 MAINTENANCE INSTRUCTIONS AND SCHEDULES: 2.1 Mandatory Replacements: The GTX 3000 1090ES Transponder, GDL 88 GPS / UAT and optional Flight Stream 110 systems' electrical components and installation is "On Condition" as determined by routine surveillance and there is no mandatory replacement time for any aspect of this system. Refer to 400A OEM AMM, Wiring Procedures and Repair — Description and Operations - chapter 20. for comprehensive wiring harness surveillance concerns. See Chapter 10 Airworthiness Limitations for antenna installation inspections. 2.2 Recurring Maintenance: 2.2.1 Antenna Installations Antenna installations require special inspection requirements and shall be maintained using Chapter 10 o this document. Report No.: ICA-4079.580 Revision; IR Dated 05/01,2018 6 119 2.2.2 Bulkhead Feedthrough Installation The bulkhead feedthrough installation requires no special inspections requirements and shall be maintained using normal OEM maintenance manual procedures 2.2.3 Basic Mode S Transponder functions: The instalation of the GTX 3000 transponders must continue to meet the operational requirements of 14 CFR §§ 91.413, 91.215, and 91.217 and comply with the transponder system tests and inspections called out in 14 CFR § 43. appendix F. The Collins Pro Line 21 altitude reporting equipment connected to the Gamin ADS-B transponders must comply with all applicable 14 CFR §§ 91.217. 91.411, and part 43 appendix E test and inspection requirements. If the altimetry system is compliant with the Reduced Vertical Separation Minimum (RVSM standards, the requirements and tolerances stated in the approved RVSM maintenance program must be met. ADS-B installation does not alter these requirements. 2.2.4 ADS-8 functions: Compliance with aircraft equipage requirements imposed by the operational requirements of 14 CFR §§ 91.225 and 91.227 is achieved by these STC modifications. ADS-B Maintenance is "On Condition" as determined by routine surveillance during Mode S maintenance, by the flight crew as well the FAA Air Tr c Control system. 2.2.5 FIS43 functions: This modification has an optional installation that supports ground based SBS FIS-B reception. UAT/FIS-B Maintenance is "On Condition'. 2.3 Setup and Configuration in Service 2.3.1 Garmin GDL 88 2.3.1.1 Confrm Garmin GDL 88 line replaceable unit part number from the Elliott Aviation wiring diagra 121-3781-E0580-000 located in Appendix A. 2.3.1.2 Obtain Elliott Configuration Instructions located in Appendix A. Read Section 5 of Configuration Instructions before proceeding with reconfiguration of the GDL 88. Take special note of the specific instructions for laptop computer interface, software effectivity and maintenance record details. The GDL-88 will not function property until software setup and configuration is accomplished. SDNY_Givi_02758034 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244956 EFTA01261616 SDNY_GM_02758035 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244957 EFTA01261617 Cc--t2 Elliott Aviation Technical Products Development, Inc. 6601 74" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No.: ICA-4079-660 Revision: IR Dated 0510112 718 7 or 19 PRECAUTION: -1 I Part number, configuration and electrical interface has been evaluated I and approved for ADS-B Latency and SDA requirements. Any deviations I will require additional approval. _I 2.3.1.3 While using the Elliott Configuration Instructions Section 5. access to the CDL 88 Diagnostics section is available. Real time GPS information is presented. 2.3.1.4 For setup and configuration, GPS reception must be confirmed using the diagnostic page. Use known GPS position to validate the GDL 88 diagnostic position readout such as the aircrafts navigation GPS. This information is presented on the Pro Line 21 cockpit control display unit un r the IDX pages. Sample page below show typical GDL 88 GPS data. 2.3.1.5 After GPS reception is verified aircraft maybe returned to service. 2.3.1.6 For troubleshooting an in-service system, GPS activity may be confirmed using this diagnostic I. page. Lack of GPS position may be due to disconnect antenna coax. faulty antenna or faulty GD 88. Neither the GDL 88 nor GPS antenna is field serviceable. If faulty, the CDL 88 line replaCeable unit may only be repaired by Garmin. Replace a faulty GPS antenna with new. Sample page: • 001.114411wall hal: 11.30 p. 0 . n _ as speoks CoonsfinaleS La Sams Una InIsmutios in *SWUM flea (3) OnonsfeS • ISOM a E: Pbt WO awatiCausi isinOOSAKU0. Os Vats au isle 3.MI 42I M 06.422 IPS mpoplinfann I masa. DWI Wean WC Ons I 110.1).121 moan MTh= I nail /Sat US, I .trasiCri4 MIMI AS lapin i WV.= al ARMCO. it4233/0/01 atiC vati EMIC aunt St:sitar° I it SOW^ Una* OPInICIMTIOPeCk I al Upload Software moat We RN I la Teel gays . Miltilutkolt I Ma MO.40416free I Sara Cantor/Nab- 1.44.10Sfrallea— Ana CoollarOme , SDNY_GM_02758036 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244958 EFTA01261618 SDNY_GM_02758037 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244959 EFTA01261619 Elliott Aviation Technical Products Development, Inc. 6601 74m Ave Building A Milan. IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B S stem Installation Report No.: ICA-4079-560 Revision IR Dated 05/01 18 8" 19 2.3.2 GTX 3000 Transponder 2.3.2.1 Confirm Garrnin GTX 3000 line replaceable unit part number from the Elliott Aviation wiring diagram 121.4079-E0560-000 located in Appendix A. 2.3.2.2 Obtain Elliott Configuration Instructions located in Appendix A. Read sections 2 and 4 of this document before proceeding with reconfiguring of the GTX 3000. Take special note of the requirements for laptop computer interface and software effectivity details. The CDC 3000 will not function properly until software setup and configuration is accomplished. -PRECAUTION: i Part number, configuration and electrical interface has been evaluated I I and approved for ADS-B Latency and SDA requirements. Any deviations i will require additional approval. 2.3.2.3 While using the Elliott Configuration Instructions, access to the GTX 3000 status is available. Real time information is presented. 2.3.2.4 For setup and configuration, the following items must be verified: • GPS Position • Magnetic • Weight on wheels is operating correctly. • ADS-B mode indicated. • 4096 code agrees with Pro Line 21 RTU ATC settings. • Flight ID agrees with Pro Line 21 RTU Alt settings.(note: Dynamic (pilot set) Flight ID t available on aircraft all.) • TCAS status correct for aircraft. Most aircraft will have TCAS installed. 2.3.2.5 GPS position is confirmed using the 'Info / ADS-B Out' page. Confirm GPS position from the GDL 88. Sample page follows to show typical GTX 3000 GPS source information. 2.3.2.6 Heading is confirmed using 'Info I EHS' page. Confirm heading from the Pro Line 21 system. Sample page follows to show typical GTX 3000 Heading source information. 2.3.2.7 WOW. ADS-B mode. 4096 Code, FligM ID, and TCAS status is confirmed using the 'Status' pave in the GTX 3000 configuration tool. Sample page follows to show typical GTX 3000 'Status* page information. 2.3.2.8 After these have been verified perform 14 CFR 43 App F I A-..I. 11 2.3.2.9 The aircraft may now be returned to service. SDNY GIvl02758038 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244960 EFTA01261620 SDNY_GM_02758039 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244961 EFTA01261621 Elliott Aviation Technical Products Development, Inc. 6601 74" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness for Garmin ADS-B System Installation GTX 3000 Configuration GPS Sample page: In Amon ••••• •Stmolo. 04 .1.4-1.••• .11.•••••••••••• .• • . ._+S•11041 Crammelmusamsamirm tammotsmaaantammeammilmai.- 01160.•••••••Ir= . 1.001••••••••• • 411••••••••••••••C IPP•sHeimoneo roe. in...1...w Wl Pec•••••••••••••C Inwm.•••••• •• Somn•••••••••••C almmentwe - 1 soistis•-•rob..... .... . ..........--.......„..,,,,........... .“....r......._ . 'MO Do.. Is *nes run° r . a ...,.. 1 I /nee , P•11014a.celel .. enn",.:Z.N.I..* . ••ranyiza 4....za ji: ...is .. roma..." I I II.W.HPA I l: ssaas".4". iity-ipn. lanitt..,.re1~0.101••••• r ilevaaaelle-lelliall • Oa cam r anassai •14...6... - - -. "--. 0•••=er irtn.nni. Crorn•...... 'lett.. • ,LC___Po , I resins •.1. avow, r .0....3...0. oirm••••••VU ' /a ma. • iirealliessoNst. r. GTX 3000 Configuration Heading Sample page: I. NM Ii ..i.':.:... ..;-- f..., '... D...., Si. ....0. kw: i,....., __ _ W.L.-.:•,...;••=••••••••••••rup -1 1 / I ••••••asftern •••••••=.•••••••Ci opa.bmr., r .allierib.PC = 1 WaradmiliWin ••••••• •••taell••••••• '1 i ..........,..rr 1•••••••.••••• I tImbr "— .....M.P, ' • ' • J 1..4e lionsia•slamplMC- 71. ..wry • eon Traramma aro.. • - isiona cos rof.......nuar.:4.••• lc wawa. rif.. r It Kan.. rith.:ribrii. I I r ""4" na. 1.1• ern r Sara. r OsirMaISIS/ I "a" FIVa•Plem •Il'anitil•MOO•f• ma 011•14ll CIESIoll itrIMMOSIT'rr e" rens ttttttttttttwReport No.: ICA-4079.560 Revision: IR Dated 05/01/2018 9 of 9 SDNY_GM_02758040 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244962 EFTA01261622 SDNY_GM02758041 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244963 EFTA01261623 Elliott Aviation Technical Products Development, Inc. 6601 74th Ave Building A Milan. IL 61264 ELIJOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B System Installation Report No ICA-4079-560 Revision: IR Dated 05/0112018 10 of 19 GTX 3000 Configuration Status Sample Page Seen& 0.••••Setse. 000 eta tio40.“1 'red orreman •ersetiox 6.17412.-1 net oars; Poem: I r nt.tau roam ; GEM =III r sway runt= r D.:cram P Nana rucef r Ilia. a., r..aCu -ram r 'Cato r For.U.T..-;MgJe vans,swam I r UrRInfixaMM r J s • r vuortemitbai r ttaltentif-312=1Iial — 00.2.T CO lag •PosalidelP)—• Psepporitamis ftatecaripti-la P sena atiblIP•atlap sad.— r r r r r IP 2.3.2.10 For troubleshooting an in-service system, GPS activity may be confirmed using this 'Info! ADS Out' page. Lack of GPS position may be due to G0L 88 issues such as disconnect antenna faulty antenna or faulty G0L 88. See 2.5 above. If the GIDL 88 is not suspect, suspect RS 232 interface, configuration or GTX 3000 transponder. The GTX 3000 is not field serviceable. If taut the GTX 3000 line replaceable unit may only be repaired by Garmin. 2.3.2.11 For troubleshooting an in-service system, heading activity may be confirmed using this "Info I E S' page. Lack of heading may be due to suspect 429 interface or configuration. The GTX 3000 heading source is the same as is used for the Flight Crew presentations The GTX 3000 is not fie d serviceable. If faulty, the GTX 3000 line replaceable unit may only be repaired by Garmin. 2.3.2.12 For troubleshooting an in-service system, the above may be confirmed using this 'Status' page: • Weight on wheels is operating correctly. (squat switch. wiring and config). • ADS-B mode indicated. (GDL 88, valid 429 data, wiring and config). • 4096 code agrees with Pro Line 21 CDU ATC settings. Access the Pro Line control display unit and exercise the squawk codes, the GTX 3000 should indicate correctly almost immediately. (wiring and config). • Flight ID agrees with Pro Line 21 CDU ATC settings. Select reversionary mode on the associated instrument panel to enable off-side control display unit GTX 3000 control. (CD . wiring and config). • TCAS status correct for aircraft Most aircraft will have TCAS installed. Confirm TCAS by visual observation of directional antennas and / or Pro Line control display unit TCAS pag . Confirm no faults if TCAS installed and the ADS-B system is interfaced properly. (wiring a config). 2.3.2.13 The GTX 3000 is not field serviceable. If faulty. the GTX 3000 line replaceable unit may only be repaired by Garmin. SDNY_GM_02758042 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244964 EFTA01261624 SONYGM02758043 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244965 EFTA01261625 • Elliott Aviation Technical Products Development, Inc. 6601 74th Ave Building A Milan, II. 61264 ELUOTT AVIATION Instructions for Continued Ainvorthiness For Garmin ADS-8 S ern Installation Report No.: ICA-4079- 0 Revision IR Dated 05/01 18 11 19 2.3.3 GTX 3000 "N" number Registration change. 2.3.3.1 Obtain Elliott Configuration Instructions located in Appendix A. Using sections 2 and 4 of the Configuration Instructions Access the 'Aircraft" tab on the GTX 3000 configuration tool. Modify e registration as needed and press enter to set the configuration. Shutdown the configuration tool and verify registration number change using WR 6000 or similar transponder test set. Sample page: GTX300a 6k Berl irdo Aircraft I Airframe Walla 'Rtg!orta; yogurt log r &cart Configuration i Aircraft Registration 'r•; lAtA Airfai e Designate L VFR Code 3209.2..: ,7 f 1-7C AVGQty KAOAddrea (hoc) II [Set ICA: Address from Reid:ration Courtly United States SDNY_GM_02759044 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244966 EFTA01261626 SDNY_GM_02758045 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244967 EFTA01261627 • Elliott Aviation Technical Products Development, Inc. 6601 74th Ave Budding A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B S ern Installation Report No.: ICA-4079-560 Revision IR Dated 05/0112018 12 •19 2.4 GTX 30001 GDL 881 Pro Line 21 Troubleshooting Reported Issue Steps Transponder reporting: Altitude Observe or determine Collins flight displays for air data indications. If present and correct. GTX 3000 suspect wiring or configuration. Transponder reporting: Heading Observe or determine Collins flight displays for heading indications. If present and correct. GTX 3000 suspect wiring or configuration. Transponder reporting: ADS-B - Air Observe or determine the ADS-B annunciator status. If ADS-8 annunciation OFF. suspect GTX 3000 in use. If ADS-B annunciation ON, suspect GDL 88 LRU. wiring or configuration. Transponder reporting: ADS-B - Surface Not seen by flight crew. report will come from ATC Ground. Same as above for ADS-B annunciation status. Transponder reporting: Mode C Observe or determine the Collins CDU annunciations. If alternate GTX 3000 can be controlled using Collins CDU. suspect the GTX 3000 LRU. TCAS Collins CDU: Navigate to ATC page and observe status. Access the Collins MFD status page. TCAS faults with ATC faults point to transponder malfunction. TCAS faults alone point to TCAS. r GCommercial Off The Shelf ADS-B receiver devices are suitable for GO NO GO confirmation that the TX 3000 transponders are transmitting GPS position. HOWEVER, on y approved calibrated test devices, such as the IFR 6000, may be used to confirm transponder output power and minimum trigger levels as well as diversity isolation. To conduct an in-depth as-Installed complete functional check including UAT, qualified test equipment such as IFR 6000 will be required. Refer to specific test set instructions for operation and testing. SDNY_GM_02758046 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244968 EFTA01261628 SDNY_GM_02758047 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244969 EFTA01261629 Elliott Aviation Technical Products Development, Inc. CZ-3 6601 74''' Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garrnin ADS-B System Installation Report No • ICA-4079-560 Revision IR Dated 05/01/2018 13 of 19 Chapter 3 ACCESS: 3.1 Overview: The information contained herein supplements the basic Maintenance Manuals only in those areas listed, when aircraft is modified in accordance with Elliott Aviation drawings and diagrams specified in Section 1.3 of this document. 3.1.1 GTX 3000s are located in the forward right avionics bay upper equipment shelf. A configuration module i also located inside the J3302 connectors. 3.1.2 GDL 88 is located in the forward left avionics bay lower equipment shelf. A configuration module is also located inside the J811 connector. 3.1.3 Fight Stream 110 (if installed) is located on the back of the Pilots chart holder cabinet. 3.1.4 ADS-B 1/2 annunciator is located in the cockpit panel 3.1.5 GA36 GPS Antenna is located on top of the aircraft fuselage above the cockpit headliner at FS 128.74 rig of center line 3.1.6 UAT Antenna is located on the belly of the aircraft fuselage below the left forward avionics bay at FS 35.1 3.1.7 Wiring follows existing aircraft wire routes in the nose and cockpit area. 3.2 Equipment and wiring access: No new access is required from the installation of this modification. Access to all equipment and wiring is gained using existing aircraft maintenance manual techniques. 3.2.1 GDL 88 and GTX 3000 rack mounted Line Replaceable Units (LRU): 3.2.1.1 No hand tools are required. The coax and wire harness connectors knurled and are intended to be removed and tightened by hand. Should assistance in the form of pliers be used, take care to n distort or over tighten. 3.2.1.2 Observe typical avionics systems precautions including: • Coax connectors. Do not bend or kink the coax, avoid bending the center pin, inspect for debris prior to reinstallation. • Wire harness connectors. Disengage associated circuit breakers first. Use care when handl ng connectors to ensure shield drain integrity, alternate locking screw tightening sequence and ensure proper alignment during re-installation. 3.2.1.3 Each LRU rack uses a lock down mechanism to secure the LRU in the rack. • To remove, pull while twisting counter clockwise until the LRU hook is clear. The LRU show now be free. • To install, align the LRU in the rack. Slide the LRU until the foot is firmly engaged in the rack LM the lockdovm mechanism over the LRU hook. Tighten firmly until secure. • Conduct necessary checkout procedures described elsewhere in this document. 3.2.1.4 Configuration Modules are located inside the J881 GDL 88 connector and inside each J3302 G X 3000 connector. Hand tools are required to gain access inside the backshell. Retain hardware after removal. To install secure retained hardware and Reconnect to applicable unit. Conduct necessary checkout procedure described elsewhere in this document. d SDNY_GM_02758048 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244970 EFTA01261630 SDNY_GM_02758049 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244971 EFTA01261631 Elliott Aviation Technical Products Development, Inc 6601 74" Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garman ADS-8 System Installation Report No.: ICA-4079-680 Revision: IR Dated 05/0112C 8 14 of 19 3.2.3 Flight Stream 110 (if installed) Line Replaceable Unit (LRU), GPS and UAT antennas: Hand tools are required. These components are secured with screws and nuts. To remove, remove this hardware and retain. Disconnect the electrical / coax connector. To install, secure with the retained hardware. Reconnect electrical /coax connector. 3.2.4 ADS-8 1/2 Annunciator: Hand tools are required. This component is secured with locking paws. To gain access to these locking paws gently pull the annunciator lens out. Screws located inside loosen the upper and lower screw. Once locking paw has been loosened pull annunciator body out of the annunciator housing and instrument pane To install insert annunciator body back through the instrument panel and annunciator housing. Tighten locking paws until annunciator body and housing are tight against the instrument panel, then press annunciator lens firmly into the annunciator body. Conduct necessary checkout procedures described elsewhere in this document. Chapter 4 LIFTING AND SHORING: Not applicable this modification. Chapter 5 LEVELING AND WEIGHING: Not applicable this modification Chapter 6 TOWING AND TAXIING: Not applicable this modification. Chapter 7 PARKING AND MOORING: Not applicable this modification Chapter 8 PLACARDS AND MARKINGS: Not applicable this modification. Chapter 9 SERVICING: Not applicable this modification SDNY_GliA_02758050 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244972 EFTA01261632 SDNY_GM_02758051 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244973 EFTA01261633 Elliott Aviation Technical Products Development, Inc. CZ, ifQC7 6601 7451Ave Building A Milan, IL 61264 ELLIOTT AVIATION Instructions for Continued Airworthiness For Garmin ADS-B S tern Installation Report No.: ICA-4079-560 Revision: IR Dated 05/0112018 15 of 19 Chapter 10 AIRWORTHINESS LIMITATIONS 10.1 FAA Approval of Airworthiness Limitations This chapter of this supplement must be attached to the Airplane Maintenance Manuals. The information contained herein supplements the basic Maintenance Manuals only in those areas listed, when the aircraft is modified in accordance with FM Form 337 for the installation of Garmin ADS-B System. For limitations and procedures not contained in this supplement, consult the basic Airplane Maintenance Manuals. The Airworthiness Limitations Section is FAA approved and specifies maintenance required and un 14CFR §§ 43.16 and 91.403, unless an alternative program has been FAA approved. FAA APPROVED: Principal Avionics Inspector Minneapolis — St. Paul FSDO FM Approved Date: SDNY_GM_02758052 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, a