PHI Inc. 2001 SE Evangeline Thruway Lafayette. La. 70508 PH1S76-ICA-0005 Revision A February It 2014 instrument panel or center console. Electrical power is supplied to the number one transponder unit from the Radio Master No. I DC Primary bus through a 3 amp circuit breaker labeled NO. I XPDR. This circuit breaker also supplies power to the 28VDC IN NO I pin of the CTL-92E control unit. The number two transponder unit if installed is supplied electrical power from the 28VDC Essential bus through another existing 3 amp circuit breaker labeled NO. 2 XPDR. This circuit breaker also supplies power to the 28VDC IN NO 2 pin of the CTI.-92E control unit. CTL-92E Transponder Control Unit The transponders) TDR-94D(s) are controlled by a single Rockwell Collins CTL-92E Transponder Control Unit. When a single TDR-94D is installed, the number I transponder must be selected on the CTL-92E. When dual transponder systems arc installed, each system is separate of the other except that both TDR-94D transponders are controlled by the single CTL-92E Transponder Control Unit. The CTL-92E provides a means for entering the flight identification code into the TDR-94D transponder(s). The flight identification code is one of the additional requirements for ADS-B functionality. Software in the Rockwell Collins CTL-92E is controlled by Rockwell Collins assigning a specific part number to the CTL-92E. ffegie 88.66° ON ALT OFF ATC 0 Om % Rockwell Collins CTL-92E transponder control head ADS-B Fail Annunciators With the installation of the Rockwell Collins TDR-94D Pan Number 662.9210.550 transponders, an "ADS-B Fail- annunciator is added (one for each transponder system). The annunciator(s) are located in the center section of the instrument panel in clear view of the pilot. If dual transponders are installed, the d2 ADS-B annunciator is located adjacent to the NI annunciator. These annunciators will illuminate when the ADS-B function of the particular transponder fails or if the position source data supplied to the ADS-B function of the transponder fails or is considered inaccurate or invalid. ADS-B NO. 1 LDS 92 FAR ADS-B NO. 2 Transponder System I Transponder Sys em 2 ADS-B Fall Annunciators 4 0070120A SDNY_GM_02757729 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244651 EFTA01329514

SDNY_GM_02757730 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002444552 EFTA01329515

P111 Inc. PHI-S76.1CA-0005 2001 SE Evangeline Thruway Revision A Lafayette. La. 70508 February 21.2014 With the single TDR-94D ATC/Mode-SIADS-B transponder installation, only the number 1 annunciator is installed. In the figure above, note that the number 2 ADS-B 2 Fail annunciator is shown with illuminated amber text as an example of indicating an ADS-B function failure. Aircraft Sensors The ADS-B function of the transponder(s) is transmitting of additional information derived from several aircraft sensors. These sensors include the Air Data Computer(s) (ADC) [altitude and air pressure data], the Attitude Heading and Reference System(s) (AHRS) [heading information], and the Flight Management System (FMS) [GPS position data]. With dual TDR-94D transponders installed, the number I transponder receives sensor information from the number I sensors and the number 2 transponder receives sensor information from the number 2 sensors. Heading information is supplied by both number I and number 2 AHRS through the FMS. With the single existing Universal Avionics UNS-I Fw FMS /GPS P/N. 3192-00-111102 installed, the transponder receives position data from that single FMS GPS. When dual TDR-94D transponders are installed, both transponders receive position source data from that single FMS. Maintenance To Interfacing Components (Aircraft Sensors! When maintenance is performed on or design changes are made to interfacing components or systems, those components or systems must be inspected and tested to ensure validity of the data to the transponders. If it can be verified with system checks that the interfacing system data is valid, it is not necessary to test the ADS-B out functions of the transponders. If that data cannot be verified through system checks, perform ADS-B testing in accordance with paragraph 2.5.5. °untitled Position Source This installation of the Dual Rockwell Collins TDR-94D mode S transponders with activation of the ADS-B extended squitter functions is approved for interfacing with the existing Universal Avionics UNS-IFw FMS /GPS with WAAS P/N. 3192.00.111102. See Appendix B for electrical drawings and installation details. FMS Software Requirements The Universal Avionics UNS-IFw FMS /GPS with WAAS P/N. 3192-00-111102 software control number must be I 000.X (where X is equal to or greater than 7). ADS-B Functionality The TDR-94D 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 Part 43, Appendix E and Appendix F. See AC 43.6, Altitude Reporting Equipment and Transponder System Maintenance and Inspection Practices. For testing of the ADS-B function, see paragraph 2.5.5. 2.2 Component Removal and Installation Instructions NOTE: Following any transponder installation or maintenance where data correspondence error could be introduced. the integrated system shall be tested, inspected. and found to comply with 14 CFR. Part 91. Section 91.411. and Section 91.413 by complying with the following: • Paragraph (c). Appendix E of Part 43 and • Appendix F of Part 43. 5 0070120A SDNY_GM_02757731 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244653 EFTA01329516

SDNY_GM_02757732 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244654 EFTA01329517

PHI inc. PHI-S76-1CA-0006 200! SE Evangeline Amway Revision IR Lafayette, La. 70508 Febnavy 4. 2014 Also. the transponder ADS-B system shall be functionally tested in accordance with paragraph 2.5 of this ICA. A log book entry is required for accomplishment of this test. When maintenance is performed on aircraft systems that provide data to the ADS- B portion of the transponders (Source Data). those systems must be functionally checked to verify the data being supplied is valid. 2.2.1 Removal and installation of TDR-94D transoonders Removal and installation of the system I and, if installed, system 2 TDR-94D transponders arc identical except that the number 2 transponder is stacked on top of the number I transponder using two mounting frames. The transponder(s) are located stacked on the lower shelf in the right side nose avionics compartment. Removal Ensure all aircraft electrical power is deenergized. Gain access to the transponders by removing the right side avionics compartment access panel. Locate the TDR-94D transponder, loosen the two retaining knurl nuts, lift the retaining sleeves from the tabs, and pull the transponder from the rack. Installation Ensure all aircraft electrical power is deenergized. Inspect the transponder rack and retaining system, and the tandem adapter assemblies, for general condition, security, and serviceability. Inspect exposed system wiring behind the transponder racks for general condition and serviceability. Slide the serviceable transponder into the rack ensuring engagement of the wiring connectors. Lift the retaining sleeves up and over the tabs on the TDR-94D and secure with the two retaining knurl nuts. Reinstall the avionics access panel. If the transponder is being replaced, perform functional checks in accordance with paragraph 2.5.4 and 2.5.5. 2.2.2 Removal and installation of transponder antennas DNIN150_-6-2 Each transponder, system I and system 2 (if installed), have two antennas (diversity setup consisting of a lower antenna and an upper antenna). The transponder system I lower antenna is located on the lower surface of the aircraft, left of the aircraft centerline at fuselage station 140.00. Transponder system 2 lower antenna is located on the lower surface of the aircraft left of centerline at station 126.00. Transponder system I upper antenna is located left of the aircraft centerline on the top surface of the aircraft at fuselage station 143.67 and transponder system 2 upper antenna is located right of the aircraft centerline on the top surface of the aircraft at fuselage station 143.67. Removal and installation procedures for the transponder system antennas are typical and are as follows: Removal I. Turn off all electrical power. 2. Use a phenolic or plastic scraper and remove the sealing compound from the screws and around the edge of the antenna. 3. Remove the antenna attachment screws and remove the antenna from the fuselage enough to disconnect the antenna coax connector. 4. Disconnect the coax connector from the antenna and remove the antenna. 6 0070120A SDNY_GM_02 757733 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244655 EFTA01329518

SDNY_GM_02757734 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244656 EFTA01329519

PM Inc. PHI-576-1CA-0005 2001 SE Evangeline Thruway Revision A Lafayette. La. 70508 February 21.2014 5. Using the plastic scraper, remove all sealing compound and gasket material from the fuselage mounting area. Discard the used gasket. Installation I. Ensure all electrical power is turned off. 2. Clean mounting screws and screw contact surfaces of the antenna base and structure with methyl-ethyl-ketone to maintain electrical bond thru mounting hardware. 3. Inspect the skin surface of the aircraft to ensure it is free of corrosion. If necessary reapply chemical film treatment MIL-DTL-5541. 4. Remove AG247000-0 I gasket from protective packaging, taking care not to fold or bend it. Verify that fastener holes and connector cutouts in the gasket will align with antenna when positioned for installation. Trim the perimeter of the gasket flush with antenna if needed. 5. Remove release film from the side of the gasket marked "antenna side". 6. Beginning at one side or corner of the antenna, place gasket in position, carefully aligning gasket fastener holes with antenna fastener holes. Note: Release film should remain on exposed "aircraft side" of gasket until immediately prior to antenna installation. 7. Remove release film from the aircraft side of the gasket and connect coaxial connector to the antenna. 8. Position the antenna and gasket on the fuselage and install attachment screws. 9. Allow gasket to flow into place for approximately 15 minutes then re-tighten screws. 10. Apply a bead of sealing compound, AMS-S-8802, Class B2, around the edge of the antenna. II. Perform an electrical bonding check from one antenna attachment screw head to a known airframe ground. Resistance shall not be greater than 0.005 ohms. 12. Apply corrosion preventative compound MIL-PFtF-I6173E over the attachment screw heads. 13. Perform tests and inspections in accordance with paragraphs 2.5.4. 2.23 Removal and installation of ADS-B fail annunciator(s) ADS-B NO. 1 MSS/ FAR ADS-B NO. 2 Transponder System I Transponder System 2 ADS-B Fall Annunciators With the single TDR-94D ATC/Mode-S/ADS-B transponder Installation, only the number I annunciator is installed. 7 0070120A SDNY_GM_02757735 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244657 EFTA01329520

SDNY_GM02757736 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241658 EFTA01329521

Mina PHI-S76-ICA-0005 2001 SE Evangeline Ihnnvay Revision IR Lafayette, La. 70508 February 4.2014 Removal 1. Ensure all aircraft electrical power is de-energized. 2. Gain access to the back of the annunciator. 3. Remove the annunciator cap by applying finger pressure on the two sides of the annunciator cap pulling the cap from the switch body and hinging the cap down. 4. Remove the wiring plug from the back of the annunciator using the plug extraction tool (Vivisun part number 18-234). 5. Loosen the two internal locking screws and slide the locking sleeve off the back of the annunciator. 6. Slide the annunciator out front the front of the instrument panel. Installation I. Ensure all aircraft electrical power is de-energized. 2. Install the annunciator body into the cutout with the orientation stencil "up" in the up position. 3. With access to the back of the instrument panel, slide the locking sleeve onto the back of the annunciator and secure by tightening the two internal locking screws from the front of the annunciator body. 4. From the back side of the instrument panel, install the wiring plug into the back of the annunciator body to the locked position. 5. Swing the annunciator cap into position and push it into the switch body until it snaps in place. 6. Test the annunciator lamp by applying electrical power to the aircraft and pushing the pilot's side IIDS TEST button. The ADS-B fail annunciator(s) should illuminate. INSTRUMENT PANEL CAP AND LAMP MOUNTING SLEEVE LOCKING TAB EDDY TYPICAL ANNUNCIATOR PLLG CONNECTOR UNS-1Fw FMS Configuration The UNS- I Fw Flight Management System (FMS) configuration must be changed to send ARINC 429 data to the ADS-B transponders. A spare FMS ARINC 429 port will be set to GPS/XPDR to send data to the transponders. The configuration data must be entered through the FMS Control Display Unit (CDU). 8 0070120A SDNY_GM_02757737 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244659 EFTA01329522

SDNYGM02757738 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244660 EFTA01329523

PM Inc. PH1476-1CA-0005 200! SE Evangeline Thruway Revision A Lafayette, La. 70508 February 21, 2014 UNE smacr KEYS - L) (IR) - : - (2L) (2R) - 8, a- — (M.) (3R) (4R) - qsi.) (SRI', 9 LEI HEE =oaao HEEEDEIEICIEI EICIECIEEEMEICI EITIE= HEI EMIEEEITEI ti'oa0000 NITER UNS-IFw FMS Control Display Unit LINE SELECT KEYS Action Display Lint Select Rations: VOL) left / (MR) right. Result/Note I. Press the ON/OFF DIM button on FMS Navigation Computer Unit. Navigation Computer Unit will power up and undergo a built-in-test. 2. If the Tactical Waypoints page is displayed press KEEP TACTICAL WPTS (4L) to display NIT I/I page. The MIT I/I page is displayed. 3. Press ACCEPT (5L) to initialize the EMS. The position, date, and time do not matter. 4. Press Date (IR). The date field is highlighted. 5. Type 4.5.6, 7, 8, 9 and press the ENTER button. 6. Press the DATA button to display DATA 1/4 page. The DATA 1/4 page is displayed. 7. Press MAINT (5R) to display MAINT 1/1 page. The MAINT 1/I page is displayed. 8. Press CONFIG (IL) to display CONFIG 1/2 page. The CONFIG 1/2 page is displayed. 9. Press EDIT( IR) once. The word EDIT will change to STORE. 10. Press ARINC (4L) to display ARINC OPT Ill page. The ARINC OPT 1/1 page is displayed. 9 0070120A SDNY_GM_02757739 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244661 EFTA01329524

SDNY_GM_02757740 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244662 EFTA01329525

PHI Inc. 200! SE Evangeline Thruway Lafayette, La. 70508 P111-576-1CA-0005 Revision A February 21. 2014 Action Display Line Select Buttons: (IL) left / (1R) right. Resalt/Note I I. Press TRANSMIT (2L) to display AMC XMIT I/I page. The ARINC XMIT I/I page is displayed. 12. Set the ARINC XMIT port option as follows: (4L) Port 3 = GPS/XPDRHS (High Speed) Press ENTER key on FMS Navigation Computer Unit keypad to accept this option before going on to the neat step. 13. Press RETURN (5R) to display ARINC OPT 1/I page. The ARINC OPT I/I page is displayed. 14. Press RETURN (SR) to display CONFIG 1/2 page. The CONFIG I/2 page is displayed. IS. Press NEXT button to enter FMS CONFIG 212 menu. Do not change the SCN (software control number)or the Aircraft Identification number displayed on this page. 16. Do nor pits RETURN (510 If "RETURN" is pressed the FMS will display the MAINT I/I page and the new configuration data will not be stored in the configuration module. 17. Press STORE (I R) twice to save the new configuration The first time STORE is pressed to save the new configuration the field is highlighted. When you push store a second time, the system will reset itself and initiate the power-up self test. IS. Verify all sections of FMS Self Test Pass: CPU = PASS RAM =i PASS DATABASE = PASS CONFIG MODULE = PASS AUXILIARY = PASS WAAS / ARINC = PASS A Self test page displays the results of each test performed. 576 is displayed on the second line at the top of the page. If the self test is successful the copyright page is displayed. The self test page will remain on the display if a serious failure of the FMS occurs. Failures of a minor nature will allow you to continue other alerting you of the failure. Press the MSG key to view the message. 19. If the WAAS Config Unconfirmed message is on, the GPS/WAAS Dynamic Test will have to be performed as per section 6. This is required only if the WAAS Config Unconfirmed message is on the message page. 20. If the Tactical Waypoints page is displayed; press KEEP TACTICAL. WPTS (4L) The Initialization page is displayed 21. Press ACCEPT (L5) to complete initialization. The Accept prompt is only available when all data fields display valid data. 22. Turn off the FMS. Press the ON/OFF/DIM. Press (5R) OFFISTBY. Press ( I R) CONFIRM OFF. Power/Display Control Page is displayed. Confirm Off page is displayed. The FMS will shutdown. 10 0070120A SDNY_GM_02757741 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0O244663 EFTA01329526

SDNY_GM02757742 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241664 EFTA01329527

PHI Inc. PHI-S76-ICA-0005 200! SE Evangeline Thruway Revision IR Lafayette. La. 70508 February 4, 2014 2.4 Inspections Daily Inspection Visually inspect all antenna installations for general condition and security. 300 Hours of Operation Remove the right side nose avionics bay access panel and visually inspect the TDR-94D transponder(s) and mounting racks for general condition, security of attachment, and deformation. If dual TDR-94D transponders are installed, pay particular attention to the general condition, attachment, and security of the tandem adapter assemblies. Also visually inspect all associated exposed electrical wiring and harnesses for general condition and security. Further disassembly is not required unless discrepancies are found. Reinstall the right side nose avionics bay access panel. Visually inspect the ADS-B instrument panel annunciators for general condition, security, and legibility of the decals. 24 Month Inspection Test the TDR-94D transponder system(s) in accordance with the functional test procedures in paragraphs 2.5.4 and 2.5.5 of this ICA. Transponder function modes A, C, and S must meet the two year requirements of 14 CFR Part 43, Appendix E and Appendix F. ADS-B functions must continue to meet the operational requirements of 14 CFR 91.2 I 7. Special Inspections Post lightning strike inspection: In the event that a lightning strike occurs, perform inspections and functional checks as required by the appropriate Sikorsky S-76 Maintenance Manual. Visually inspect the transponder antennas for signs of arc damage. If any signs of arcing are found, the entire transponder(s) system must be inspected in accordance with a 300 hour inspection and must be tested in accordance with a 24 month inspection as noted above. Any components showing signs of arcing must be replaced with a serviceable component. Hard landing inspection: In the event of a hard landing, perform hard landing inspections as required by the appropriate Sikorsky S-76 Maintenance Manual. In addition to the hard landing inspection required by Sikorsky S-76 Maintenance Manuals, visually inspect the TDR- 94D transponder(s) mounting racks for general condition, security, and deformation. Pay particular attention to the tandem adapter assemblies for the number 2 TDR-94D transponder system installation (if installed). Replace any component showing signs of deformation. 2.5 Functional Tests and Troubleshooting 2.5.1 Functional checks are applicable to both number 1, and if installed, number 2 transponder systems. If failures or discrepancies are discovered during the functional checks, correct those failures or discrepancies prior to continuing the checks. These functional tests are also intended to provide information to help with troubleshooting the systems. These functional tests are intended to show that the installed transponder system(s) are functioning properly and that the system(s) meet the minimum requirements for a 2 year recertification in accordance with 14 CFR Part 43 Appendixes E and F, and to ensure the extended &ruiner with ADS-B functions meet the requirements of 14 CFR Part 91.227. I 0070120A SDNY_GM_02757743 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244665 EFTA01329528

SONY_GM 02757744 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244666 EFTA01329529

Pill Inc. P111-576-1CA-0005 2001 SE Evangeline Thruway Revision B Lafayette. La. 70508 AMC 5. 2014 2.5.2 Aircraft equipment requirements The aircraft must be equipped with at least the following: I. A single or dual Rockwell Collins TDR-94D transponderts) part numbers 622- 9210-550 installed in accordance with drawing list PHI-576-DL-0015. Revision IR. 2. A single CTL-92E Rockwell Collins transponder control head part number 822- 1807-004. 3. Qualified operational single Flight Management Systems with WAAS Global Positioning System(s). 4. All other standard type certificated navigation and communications equipment. All associated aircraft systems must be functioning properly before testing is initiated. Observe all applicable safety precautions for the systems being tested and for aircraft operations during all test procedures. 2.5.3 Required test equipment I. Aeroflex IFR 6000 ATC Transponder tester or equivalent test equipment with the capabilities of testing transponder modes A, C, S, and the extended squitter ADS- B. The Aeroflex IFR 6000 ATC Transponder tester must have software version 02.09.00 or later. 2. Laversab Model 6300 Automated Pitot Static Tester or an equivalent tester capable of performing all applicable altimeter system tests required in 14 CFR Part 43. Appendix E. 2.5.4 Transponder TDR-94D mode S testing This test applies to both TDR-94D transponder system I and system 2 (if installed). Note: For ADS-B testing. if the ADS-B Register BDS 0, 5 Airborne Position Message Code 9 -18 is to be tested concurrently with the mode S testing, the aircraft must be located outside where the FMS GPS will acquire valid position data. For mode A, mode C, and mode S testing, perform the following: I. Install safety lock pins (red flag attached) in main and nose landing gear before applying electrical power to the helicopter. Refer to the S-76 Maintenance Manual. 2. Connect external electrical power to the aircraft. Refer to applicable S-76C Rotorcrati Flight Manual, Normal Procedures. 3. Make sure all circuit breakers are pushed in except those noted as being pulled for maintenance or safety. 4. Place the CTL-92E ON and select the respective transponder to be tested. 5. Pull LDG GR CTL circuit breaker. (Airborne) 6. Verify the FMS is ON and has acquired satellites. Note: Turning on the FMS and acquired satellites is only necessary if the ADS-B Register BDS 0, 5 Airborne Position Message Code 9 -18 is to be tested concurrently with the mode S testing. 12 0070120A SDNY_GM_02757745 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002 44667 EFTA01329530

SDNY_GM 02757746 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA _00244668 EFTA01329531

PHI Inc. PHI-576-1O1-0005 2001 SE Evangeline Thruway Revision B Lafayette, La. 70508 June 5, 2014 7. Set up and configure the transponder test set and antenna. Set the test set to check the top antenna. Attenuate the bottom antenna for this test. 8. On transponder test set, initiate the Auto Test Sequence by pressing the Run Test soft key. Antenna: 9. Verify the following: Top / Bottom • Respective Transponder selected on CTL-92E control • Hexadecimal code (Flight ID) on CTL-92E • Transponder test set INTERR light illuminates • Transponder test set REPLY light illuminates • CTL-92E control TX annunciator illuminates • Transponder test set ATC code matches CTL-92E control • Transponder test set altitude matches CTL-92E control • Transponder test set frequency approximately 1090 MHz • Transponder test set tail number matches aircraft • Transponder test set — Mode S UFO Test, RI =I I • Transponder test set — Mode S UF5 Test, FS =0 10. Reset the LDG GR CTL circuit breaker. (On Ground) I I. On transponder test set, initiate the Auto Test Sequence by pressing the Run Test soft key. 12. Verify the following: • Transponder being tested is selected on CTL-92E control • CTL-92E control Flight ID set to aircraft registration number • CTL-92E control TX annunciator off • Transponder test set mode S ATC code matches CTL-92E control • Transponder test set mode S altitude matches CTL-92E control • Transponder test set indicates ON Ground • Transponder test set — Mode S UFO Test, RI =I I • Transponder test set — Mode S UF5 Test, FS - I 13 0070120A Antenna: Top/Bottom SDNY_GM_02757747 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244669 EFTA01329532

SONY_GM 02757748 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244670 EFTA01329533

PHI Inc. PHI-576-1CA-0005 2001 SE Emmeline Thruway Revision B Lafayette. La. 70508 June 5. 2014 13. Set the transponder test set to Mode A/C and X PDR-S ALL-CALL and press the Run Test soft key. 14. Verify the transponder test set does not indicate a valid reply Antenna: Top/Bottom 15. Pull LDG GR CTL circuit breaker. (Airborne) 16. Set up transponder test set for bottom antenna. Attenuate the top antenna for this test. 17. Repeat steps 9 thru 13 of this section to check bottom antenna. 18. Set up pressure altitude test equipment to check the barometric altitude reported by the mode S and ADS-B transponder. Note: Checking the ADS-B Register BDS 0, 5 Airborne Position Message Code 9 -18 Barometric Altitude is not required for transponder mode S testing: however, if the ADS-B portion of the transponder will be tested, it will save time if the tests are done concurrently. 19. Check the mode S altitude and the A DS-B Register BDS 0,5 Airborne Position Message Code 9 -18 Barometric Altitude at each of these altitudes. Note: Checking the ADS-B Register BDS 0, 5 Airborne Position Message Code 9.18 Barometric Altitude is not required for transponder mode S testing; however, if the ADS-B portion of the transponder will be tested, it will save time if the tests are done concurrently. Altitude (ft.) Mode S (ft.) ADS-B (ft.) -1,000 0 500 1,000 1,500 2,000 3,000 4.000 6,000 8,000 10,000 12,000 14,000 16,000 18,000 14 0070120A SDNY_GM_02757749 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244671 EFTA01329534

SDNY_GM 02757750 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244672 EFTA01329535

PHI Inc. 2001 SE Evangeline Thruway Lafayette, La. 70508 0070120A PHI-S76-ICA-0005 Revision B June 5. 2014 20. If the ADS-B functions of the transmitter are to be tested, proceed to 2.5.5. 21. If the ADS•B functions of the transmitter are not to be tested, turn off avionics as required, and disconnect external electrical power. Refer to the applicable S-76 Rotorcraft Flight Manual, Normal Operations. 22. Shutdown all test equipment and remove from aircraft. 2.5.5 Transponder TDR-94D ADS-B testing This test applies to both TDR-94D transponder system I and system 2 (if installed). For ADS-B testing, the aircraft must be located outside where the FMS GPS will acquire valid position data. For ADS-B function testing, perform the following: 1. Install safety lock pins (red flag attached) in main and nose landing gear before applying electrical power to the helicopter. Refer to the S-76 Maintenance Manual. 2. Verify all circuit breakers are pushed in except those noted as being pulled for maintenance or safety. 3. Place the CTL-92E ON and select the respective transponder to be tested. 4. Pull the LDG GR CTL circuit breaker. (Airborne). 5. Verify the ADS-B position source (GPS, EMS) is operational and acquiring valid position data. 6. Setup and configure the transponder test set and antenna to check the ADS-B. Verify that the transponder test set REPLY light illuminates. 7. On transponder test set, initiate auto test sequence by pressing RUN TEST soft key. 8. The transponder test set INTERR indicator illuminates. 9. The transponder test set the RPLY indicator illuminates. 10. The CLT-92E control TX annunciator illuminates. NOTE: An AUTO TEST — FAILED indication can be caused by the close proximity to other aircraft or hanger signal reflection. I I. If the transponder test set indicates AUTO TEST — FAILED, list the failed tests. 12. FAA assigned Mode S Code: 13. On transponder test set, press XPDR button to access the XPDR ADS-B page. 14. On transponder test set, go to Aircraft Identification and Type Message. BDS 0,8 Type Code 1-4. 15. Type Code must be "4": 15 SDNY_GM_02757751 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244673 EFTA01329536

SONY_GM 02757752 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244674 EFTA01329537

PHI Inc. PH1S76-1CA 4005 2001 SE Evangeline Thruway Revision 8 Lafayette. La. 70508 June 5.2014 16. Aircraft identification (8 characters octal) must match the Mode S Code in step 12. Record 8 character octal: 17. ADS-B Flight ID must match the Flight ID as entered in the CTL- 92E. 18. ADS-B Emitter Category Set must be "A": 19. ADS-B Emitter Category must be "Rotorcraft": 20. Reset the LDG GR CTL circuit breaker. (On Ground) 21. On transponder test set go to Surface Position Message, BDS 0,6 Type Code 5-8. 22. Record Type Code: 23. Record Latitude and Longitude from the position source (UPS, FMS): Latitude Longitude 24. Record ADS-B reported latitude and Longitude from test set: Latitude Longitude 25. Verify ADS-B reported LAT/LONG in Step 24 is the same as the Position Source LAT/LONG in Step 23: 26. Verify movement is "I" or "Stopped": 27. Verify that the Time Sync is not used "N/UTC". 28. Verify the ADS-B heading is reported. 29. Verify ADS-B reported position decoding is "Global": 30. Record NIC Supplement "7 or 8": 31. On transponder test set, go to Aircraft Operational Status Message, BDS 6,5 Type Code 31. 32. Type Code must be "3I": 33. Aircraft Operational Status Subtype must be "I or Surface": 34. Verify Version Number Subfield is "2 or DO-260B". 35. Verify Class B2 Transmit Power is (B2 LOW) "0 or a 70 watts": 36. Verify that System Design Assurance (SDA)"2": 37. Verify that the Single Antenna Flag (SAF) is "0 or Dual": 38. Verify Resolution Advisory (RA) is "0 or not active": 39. Verify Ident is "0 or Not active": 40. Activate [dent on transponder system; Verify ADS-B reported Ident is "I or active" for approximately 18 seconds: 41. Verify Antenna Offset is "0 meters lateral and 10 meters longitudinal": 42. Verify Horizontal Reference Direction (HRZ) is "0 or True North": 16 0070120A SDNY_GM_02757753 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244675 EFTA01329538

SONY_GM 02757754 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244676 EFTA01329539

PHI Inc. PHI-S76-1O1-0005 2001 SE Evangeline Thruway Revision 8 Lafayette. La. 70508 June 5. 2014 43. Verify that Surveillance Integrity Level (SIL) is "3": 44. Verify that NACP ≥ 8: 45. Verify Aircraft Length and Width is "2 or Length <25.0m, Width < 28.0m": 46. Pull the LDG GR CTL circuit breaker. (Airborne). 47. On test set, go to Airborne Position Message, BDS 0,5 Type Code 9 - 18. 48. Record Type Code: 49. Record NIC Supplement "7 or 8": 50. On test set go to Airborne Velocity Message, BDS 0,9 Type Code 19. 51. Record Type Code: 52. Verify East - West, North - South Velocities and Directions. For a stationary aircraft: East - West • "0": / North - South "0": 53. For a WAAS position source, verify NACv is I or 2: 54. Verify Airborne Velocity Subtype is "I or ground speed normal": 55. Verify ADS-B reported Vertical Rate is the same as aircraft indication, stationary aircraft should be zero: 56. Record ADS-B reported Geometric Height Difference from Barometric Altimeter 57. Verify ADS-B Vertical Rate Source is "0 or Geometric": 58. Turn Transponder Altitude reporting OFF. 59. On test set, go to Airborne Position Message, BDS 0,5 Type Code 22 - 20. 60. Record Type Code: 61. Record ADS-B reported Altitude: 62. Turn Transponder Altitude reporting ON. 63. On transponder test set go to Extended Squitter Aircraft Status BDS 6,1 Type Code 28. Note: Attenuate transponder RF output or notify ATC that the following emergency tests will be accomplished. 64. On the CTL-92E control input Mode 3/A code "7700": 65. Verify Type Code is "28": 66. Verify the ADS-B Mode 3/A code is "I or General emergency": 67. Verify Emergency/Priority Status Subtype Coding is "1 or Emergency/Priority Status": 17 0070120A SDNY_GM_02757755 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244677 EFTA01329540

SDNY_GM 02757756 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244678 EFTA01329541

Mine, PHIS76-ICA•0005 2001 SE Evangeline Thruway Revision 8 Lafayette. La. 70508 June S. 2014 68. On the CTL-92E control input Mode 3/A code "7600": 69. Verify the ADS-B Mode 3/A code is "4 or No communications": 70. Verify Emergency/Priority Status Subtype Coding is "I or Emergency/Priority Status": 71. On the CTL-92E control input Mode 3/A code "7500": 72. Verify the ADS-B Mode 3/A code is "5 or Unlawful Interference": 73. Verify Emergency/Priority Status Subtype Coding is " I or Emergency/Priority Status": 74. On the CTL-92E control input Mode 3/A code "1200". End Of Emergency Code Testing 75. On transponder test set go to Aircraft Operational Status Message, BDS 6,5 Type Code 31. 76. Verify Type Code is "31": 77. Verify Aircraft Operational Status Subtype is " 0 or Airborne": 78. Verify Navigation Accuracy Category for Position (NACP) is >8: 79. Verify that SDA "2": 80. Verify that the Single Antenna Flag (SAF) is "0 or Dual": 81. Verify Resolution Advisory is "0 or TCAS II or ACAS RA not active": 82. Verify (dent is "0 or Not active": 83. Activate Ident on transponder system; Verify ADS-B reported (dent is "I or active" for approximately 18 seconds: 84. Verify that Traffic Alert and Collision Avoidance System Status is "Not TCAS", "TCAS ON 0", "TCAS not installed", or "TCAS not operational": 85. Verify Navigation Integrity Category for Baro (NICBARO) is "I or crossed checked": 86. Switch off the GPS/FMS. 87. Verify Navigation Accuracy Category for Position (NACP) goes to "0" within S seconds: 88. Verify that the transponder(s)ADS-B Fail annunciator(s) illuminates. Note: If dual transponders are installed, both ADS-B Fail annunciators illuminate. 89. Switch on the FMS and acquire satellites. 90. Verify the transponder ADS-B Fail annunciator(s) extinguish. 91. Pull the XPNDR circuit breaker to the transponder being tested. 92. Verify that the appropriate transponder ADS-B Fail annunciator illuminates. 18 0070 I20:\ SDNY_GM_02757757 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244679 EFTA01329542

SDNY_GM_02757758 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244650 EFTA01329543

P111 Inc. 200! SE Evangeline Thntuvy Lafayene, La. 70508 PH1476-1CA-0005 Revision B June 5. 2014 93. Reset the XPNDR circuit breaker. 94. Verify that the appropriate transponder ADS-8 Fail annunciator extinguishes. 95. Reset the LDG GR CTL circuit breaker. (On Ground) 96. Pull the FMS circuit breaker. 97. Verify that the transponder(s) ADS-B Fail annunciator(s) illuminates. 98. Reset the FMS circuit breaker and acquire satellites. 99. Verify that the transponder(s) ADS-B Fail annunciator(s) extinguish. 100. Turn off avionics as required, and disconnect external electrical power. Refer to the applicable S-76 Rotorcraft Flight Manual, Normal Operations. 101. Shutdown all test equipment and remove from aircraft. 2.6 Decals and Placards No. 1 TRANSPONDER (BOTTOM) I. PHI P/N PHID-1757, located on the avionics shelf in front of the #1 transponder. No. 2 TRANSPONDER (TOP) 2. PHI P/N P1110-1756, located on the avionics shelf in fron of the #2 transponder. ADS-B NO. 1 3. PHI P/N P1110-1913, located on the instrument panel adjacent to the number 1 transponder ADS-B I fail annunciator. ADS-B NO. 2 4. PHI P/N P1110-1914, located on the instrument panel adjacent to the number 2 transponder ADS-B 2 fail annunciator. 3.0 SERVICING INFORMATION No servicing is required. 19 0070120A SDNY_GM_02757759 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 0024468I EFTA01329544

SDNY GM 02757760 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241682 EFTA01329545

PHI Inc. PHI-S76-ICA-0005 2001 SE Evangeline Thruway Revision Lafayette. La. 70508 June 5, 2014 4.0 AIRWORTHINESS LIMITATIONS The Airworthiness Limitations section is FAA approved and specifies maintenance required under Sections 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 installation. 5.0 COMPONENT OVERHAUL Components within the TDR-94D transponder system(s) are considered to be on condition items and no overhaul requirements are associated with the installation. 6.0 GENERAL MAINTENANCE INFORMATION AND STANDARD PRACTICES 6.1 Weight and Balance Requirements When equipment changes are made, the aircraft weight and balance record shall be corrected, and the equipment list amended as necessary to reflect those changes. The weight and location shall be determined for the equipment being removed or installed. This information (weight, station, and butt line) shall be recorded and used to calculate a new aircraft empty weight center of gravity. This new empty weight center of gravity shall be recorded in the aircraft permanent records and made available to the pilot. System/Component Weight OW Lon 'tudinal Lateral Arm (io.) I Moment 1 (lb.-In.) Arm (1n) Moment (I0.-In.) TDR-94D Transponder System I Rockwell Collins TDR-94D 8.5 48.30 410.5 RBL-17.19 -146.1 TDR-94D Mounting Tray 1.0 48.30 48.3 RBL -17.19 -17.2 NI ADS-B Annunciator, see Note 2 0.1 77.00 7.7 LBL 8.00 0.8 System I upper antenna. see Note 1 1.0 143.67 143.7 LBL 27.00 27.0 System I lower antenna. see Note I 1.0 140.00 140.0 LBL 14.50 14.5 TDR-941) Transponder System 2 Rockwell Collins TDR-94D 8.5 48.30 410.5 RBL -17.19 -146.1 TDR-94D Mounting Tray 1.0 48.30 48.3 RBL -17.19 -17.2 Tandem Adapter Assembly (2 frames) 1.0 48.30 48.3 RBL -17.19 -17.2 #2 ADS-B Annunciator, see Note 2 0.1 77.00 7.7 RBL -8.00 -.08 System 2 upper antenna, see Note I 1.0 143.67 143.7 RBL -27.00 -27.0 System 2 lower antenna. see Note I 1.0 126.00 126.0 LBL 14.50 14.5 Rockwell Collins CTL-92E Transponder Control CIL-92E, see Note 3 I 1.3 I 79.62 I 103.5 I LBL 1.65 I 2.1 No e: 1 Actual antenna station locations may very up to 3 inches depending on the installation. No e: 2 Actual ADS-B Annunciator locations may very within the instrument panel, see FIGURES A-2 and A-3. No e: 3 Actual CTL-92E location may very within the center console and instrument panel, see FIGURE A-4. 20 0070120A SONY_GM_02757761 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244683 EFTA01329546

SDNYGM_02757762 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA _00244684 EFTA01329547

PHI Inc. PHI-S76-1CA-0005 2001 SE Evangeline Thruway Revision A Lafayette. La. 70308 February 21. 2014 6.2 Consumable Materials Additional consumable materials are noted in Appendix A and 6 of this document. Only those consumable materials noted herein shall be used. If necessary, the SIC holder can be contacted for approval to use alternate materials. 6.3 Torque Information For hardware torque values, refer to Appendix A. Where torque values arc not specifically addressed in this ICA, the Sikorsky S•76 Maintenance Manual, Chapter 20, may be used as a guideline for fastener torque values and techniques. 21 0070120A SDNY_GM_02757763 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244685 EFTA01329548

SDNY_GM_027577. SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241686 EFTA01329549

PHI Inc. PH1-576-1CA-0005 2001 SE Evangeline Thruway Revision IR Lafayette. La. 70308 February 4. 2014 Appendix A APPENDIX A. MECHANICAL INSTALLATION INFORMATION Appendix A Table of Contents Title Page/Contents A I General Notes A I FIGURE A-I, Component Locations A2 Transponder TDR-94D, Single Transponder Installation Parts List, FIGURE A-2. Single Transponder Installation A4 FIGURE A-2, Single Transponder Installation A5 Transponder TDR-94D, Dual Transponder Installation Parts List. FIGURE A-3. Dual Transponder Installation A9 FIGURE A-3, Dual Transponder Installation AIO Transponder Control CTL-92E Single or Dual Installation FIGURE A-4, Transponder Control CTL-92E Al4 General Notes: I. Application of sealant around mating surfaces: A. Remove all dust, dirt, oil, grease, wax, loose paint, etc. By wiping surface with methyl ethyl ketone (MEK) using a clean cloth. B. Mask off perimeter of area to be scaled. C. Apply 1/8"-I/4" bead of sealant around mating surfaces. D. Remove excess sealant and masking materials. E. Allow sealant to cure at room temperature (for full cure, allow approximately 72 hrs. @ room temperature). 2. Antenna gasket installation: reference paragraph 2.2.2. 3. Chemical film all aluminum pans and assemblies with materials conforming to MIL-DTL- 5541. If parts become scratched, re-apply chemical film to the scratched surfaces. Following any drilling or cutting operation, remove all burrs and metal particles, re-apply chemical film to bare surfaces prior to part or fastener installation. 4. Prime exposed surfaces with MIL-PRF-23377 epoxy polyamide primer. 5. Application of corrosion preventive compound: A. Remove all dust, dirt, oil, grease. wax, loose paint, etc. By wiping surface with methyl ethyl ketone (MEK) using a clean cloth. B. For best results, the ambient and product temperature should be 50-95°F (I0-35°C) at time of application. Ensure uniform consistency prior to use. Brush a thin coat of compound over head of screws ensuring edges of screws and mating surfaces are sealed. C. Allow compound to cure for 24 hours at room temperature. AI 0070120A SDNY_GM_02 757765 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244687 EFTA01329550

SDNY_GM_02757766 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002444588 EFTA01329551

co H n -0 xlO n 7DO C PO 7D G) -o Io i-a P 1-11O • IM r CD_ T., I-a PIM Me !MI St &won.. TArinuy lailsrmtie la 7O,NY 00704 NCO*, RELAY MOUNT. NO 1 TEWEEPONDER (sorra! RELAY MOUNT. NO. l TAM:WONDER MP) TRANSPONDER TOR 440 NO. I ibOTIOM VNII r011Y NVALIAIEN. 'I *4 0ON V.C.CTNICAL OUGOVAII WS riCalige4 TRANSPONECR TOR440 NO.2 (TOP WTI Poi MICIONCAL INSTALIAEOR SO 1105 1.3 rW NICIPICIA WRING PAGAN& WI 0G4. .2 ANNUNCIATOR. NO. I TRANSPONDER FON P.NOWKA‘ NISTN.LATICH, WE HOAR At PON UACTRIOA VSINCOACIAIN SLR/Aloft Si TRANSPONDER CONTROL (C1.420) /OA lEONNICAL INST NU L, ION Sit HONK A4 row .C.INCAL NIRPO PANAMA x LxtI LA srl NOW ANNUNCIATOR. NO. 2 TRANSPONDER at ut ONANCAL 145•AltATKPI Ut Naas A4  ACtacT u NOM WAWA. Mt NCASIIII.2 FIGURE A-1, TOP VIEW SINGLE OR DUAL ROCKWELL COLLINS TDR-94D ATCINIODE-S (ADS-B) TRANSPONDER(S) RR El. 00 PET swims, NO. 2 TRMISPONDUC (TOP) FOR IROSIKAL MSTAILATION SCA 1,004 MI FOR E1ECTNGL1 RAMS OLICALAN YC 'GAR Si ANTENNA, NO.1 TRANSPONDER (TOP) ICR PECAMSCAI NI/ALIATEN SEE NOSE FOR ELECTACM. WANG MORAY SITE FIGURE AI 11,141.14C1-0091 REVISMAY la fobsoryR MU APPENNY A EFTA01329552

SDNY_GM_02757768 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244690 EFTA01329553

ve, co ‘_ H n -O O n rn O C rn 70 70 N(0 CM 00 0 P I- 11O u-i r a_ g l-a PM. ht EMI SE Etuarrinr Thnravy , -04kner lu MAI 0110120C too ANTONIA. NO. 1 TRIJIIIPONDER ANTENNA. NO 2 TRANSPONDER ON NO TRANSPONDER CON1ROL 1CTLA2E) ANNUNClATON. 110.1 TRANSPONDER (olio ANNINCIAT011.. SD. S 111.41111110NOINI 0.111, MAY MOUNT. NO. 2 TRANSPONDER (RIS) rot utowec.N. riStAL LAMM MC /MUM Al 004UAC19Y.M WPKNCMIM SIN 'WS 84 111.11/41.13NO01 MIND NO. 2 (TOP Inn ‘1 01101 41. , 1 TRANSPONOIN TORSO NO., (BOTTOM ONO) RELAY MOUNT. NO.1 TRANSPONDER MINN — cON mtaumedy. Halµ1AIIOR SEE rq.AtE FOR MC TRIM WSW) OACSA MC F SI STf Ref AM ON NO. 2 TRANSPONDER 0101TOIN FOR liperuNICAL NEtµtMG11 Mt IlOa 44 SOP EIECTACAL RaG DuCcull SEE FIGURE 04 SINGLE OR DUAL ROCKWELL COLLINS TDR-94D ATC/MODE-S (ADS-11) TRANSPONDER(S) RE A-1, LEFT SIDE VIEW ANTENNANO.I 111ANSPONOER (WITCO' FOR ima0WIlat HST& LAI10µ St; MUM A4 POP MCCOOK/at ISM WC t•Al 'Kt nos • I FIGURE A-1, BOTTOM VIEW Al PlllS744C4 &MON IR fans°. 4. 2014 AMEATIIN A EFTA01329554

SDNY_GM_02757770 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244692 EFTA01329555

PHI Inc. 2001 SE Ems:cline Thnstray Lafayette. La. 70508 P11I-576-/CA-0005 Revision A February 21, 2014 Appends's A FIGURE A-2 TDR-94O Single Transponder Installation, Mechanical ITEM I QT I Part Number Nomenclature i 4 M527039-0806 SCREW 2 4 NAS620-8 WASHER 3 4 NASI832-08-3 INSERT 4 AR EA9309.3NA ADHESIVE 5 I PHID-1757 DECAL 6 I 622-9672-104 TDR-94D MOUNTING TRAY 7 4 MS35338.42 LOCK WASHER 8 2 DMNI50-6-2 ANTENNA 9 2 AO247000-01 ANTENNA GASKET 10 2 PHI.050.60948.01 ANTENNA RETAINER ASSEMBLY (1 ea. / antenna installation) 1 1 12 MS24693-538 SCREWS (6 ca. / antenna installation) 12 AR AMS-S-8802 SEALANT 13 AR MIL-PRE-16173 CORROSION PREVENTITIVE COMPOUND 14 I PHID-1913 DECAL 15 I MI2883-52-001 RELAY MOUNT 16 2 MS24693-•• (8-32) SCREW 17 2 NASI149DN816.1 WASHER IS 2 MS21042L08 NUT 19 I PH1D-1915 DECAL 20 I 95-XX-17-III-E I BKK ANNUNCIATOR CAP (Number I) 21 I 95.40.17 ANNUNCIATOR BODY 22 I 17-043 LAMP QT —Quantity AR —As Required ** — Double asterisks at the end of a pan number indicates, installer must determine length of hardware. A4 0070120A SDNY_GM_02757771 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244693 EFTA01329556

SONY_GM 02757772 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241694 EFTA01329557

C co H 0 -0 os 0 n os C oo -0 os oo -0 Co i-a In o 2 • O 0.1 r„4 CD_ Z; I-a Pill tar :WI St Elleagetwe rArte.v• 14.neme WM RAI SIDE VIEW SINGLE TOR•940 INSTALLATION FIGURE A-2 SINGLE TDR-94D TRANSPONDER INSTALLATION 00,01300049 AS TOP VIEW PIIISMICLOOPS untlav Alinun• ION AMENOLV A NOTE: THE RESISTANCE a TRANSPONDER TO THE MOUNTING RACK MIST NOT E/OCEILO G0025 OHMS, THE RESISTANCE OF MOUNTING RICK TO THE SHELF MUST NOT EXCEE0 ROM OHMS EFTA01329558

SDNY_GM02757774 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241696 EFTA01329559

co H H n -O 0 n H H 0 7J 70 C.) 7J Co .514 O I-1 o Ul r-4 O- PH( IA- :on SI ,,,,,, 0070ITOCHAH NQ 1 TRMI G(DER TOR 94D TOR-940 HETRITING TRAY FIGURE A-2 (Contd.) DETAIL A-A SINGLE TDR-94D TRANSPONDER INSTALLATION PIIINISIC64901 REVISION IR PAP MI APIKIVINE SECURE TDR-94D ICUNT DIG TRAY@ TO EXISTING SKIS WIND O O 0 SCREW PL) I. WASHER (4 PO RASHER (4 PI.) INSERT (4 VW C) ADHESIVE AS EFTA01329560

SDNYGNI02757776 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241698 EFTA01329561

CM C ozi H n -O 0 C n C -O Gl -O (f) CO 40 2 VT 3 U m IJ net lAv Nal SC CiusirtAne irntli I WC 14, Fon SEALANT SCREWS (6 PER ANTENNA INSTALLATIDN) DHESIVE ANTENNA RETAINER ASSEMBLY FIGURE A-2 (Contd.) ANTEnNA GASKET SINGLE TDR-94D TRANSPONDER INSTALLATION DMNI50.6-2 TRANSPONDER ANTENNA INSTALLATION NOTE: BOTH UPPER AND LOWER ANTENNA INSTALLATIONS ARE TYPICAL Dona 12oca.4 NOTE: 1. THE RESISTANCE FROM THE ANTENNA TO THE ANTENNA GROUND PLANE MUST NOT EXCEED 0.0025 OHMS. 2. THE RESISTANCE FROM THE ANTENNA TO THE AIRFRAME MUST NOT EXCEED 0.005 OHMS. CERROSIEN PREvENTAI5E COMPOUND OVER HEADS or ALL SCREWS SEALANT ANTENNA RETAINER ASSEMBLY APTESIVE SCREWS 6 PER ANTENNA INSTALLATION) Al RI-YAWN IN )(Mn 4. 2014 APPENDIV A c os M ION PREVENTATIVE COPIPOuND OVER HEADS Or ALL@ SCREWS GASKET ANTENNA EFTA01329562

SDNY_GM_02757778 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA _00244700 EFTA01329563

co 0 73 0 0 73 0 73 73 P z) .93 No P 0 • IM Al • U-4 0_ af I-s PM PA INN .SELNAmTAr 1100PY Lamm fa. AMOS INSTRU€NT PANEL A CENTER SECTION EO7O12OC4m INSTRUI.ENT PANEL CAP LAMP TYPICAL ANNUNCIATOR INSTALLATION FIGURE A-2 (Contd.) ANNUNCIATOR AND RELAY MOUNT MOUNTING SLEEVE LUCKING TAB BODY PlIASICAICAMO RAYLUCAV A Fnlertv APPENPLI f A Q EXACT LOCATION IS au mato ON NUM INVALLATVN BUT MUST REMAIN WITHIN SIMOEO AREA SHOW. IMICATED MCA,. TO BE ADMCENT TO ANM.R.CATOR APPROMMTELY M %OMNI (LEFT. RIGHT. MOVE OR BELOW) Q FOR MCI C TRANSPONDER (AD. I SYSTEDNEANCTRICP4 PARTSANDOM& SEE APPENDix B FIGURE St PLUG CONNECTER EFTA01329564

SDNY_GM_02757780 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244702 EFTA01329565

PHI Inc. 2001 SE Evangeline Thruway Lafayette. La. 70508 PH1476-1CA-0005 Revision A February 2!. 2014 Appendix A FIGURE A 3 TDR-941) Dual Installation, Mechanical ITEM I QT Part Number Nomenclature I 2 MS27039-0809 SCREW 2 8 MS35338-42 LOCK WASHER 3 8 NAS620.8 WASHER 4 2 MS27039-0805 SCREW 5 4 MS27039-0807 SCREW 6 AR LOCTITE 222MS THREAD LOCK 7 4 NAS1832.08.3 INSERT a AR EA9309.3NA ADHESIVE 9 I PHID-1757 DECAL 10 I PHID-1756 DECAL II 2 622.9672.104 TDR-94D MOUNTING TRAY 12 2 PHI-050-60913-01 TANDEM ADAPTER ASSEMBLY 13 4 DMNI50-6-2 ANTENNA 14 4 A6247000.01 ANTENNA GASKET IS 4 P111-050-60948-01 ANTENNA RETAINER ASSEMBLY (I ea. / antenna installation) 16 24 MS24693.538 SCREWS (6 ea. / antenna installation) 17 AR AMS-S-8802 SEALANT III AR MIL-PRE-16173 CORROSION PREVENTITIVE COMPOUND 19 I PHID-I914 DECAL 20 I PHID-1913 DECAL 21 2 M12883-52-001 RELAY MOUNT 22 4 MS24693-n (8-32) SCREW 23 4 NASI149DN8161 WASHER 24 4 MS21042L08 NUT 25 I PHID-1915 DECAL 26 I PHID-1916 DECAL 27 I 95-XX-17-HI-El 5KB ANNUNCIATOR CAP (Number 2) 28 I 95.40.17 ANNUNCIATOR BODY 29 AR 17-043 LAMP 30 I 95-XX-17-HI-E15KK ANNUNCIATOR CAP (Number I) OT - Quantity AR - As Required — Double asterisks at the end of a part number indicates, installer must determine length of hardware. A9 0070120A SDNY_GM_02757781 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_OO2447O3 EFTA01329566

SDNY_GM_02757782 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244704 EFTA01329567

cr) n H 0 -0 0 H rn H n 33 0 -o 7u (J ro .5) nW P 3 I-, 10 Lri Al -4 0_ 5 1—k PHI. Ax. ION SC tkompOur newsy L•letwe. la MIRY WM WOE VIEW DUAL TDR44D INSTALLATION FIGURE A-3 DUAL TDR-94D TRANSPONDER INSTALLATION 0070120CAND MS76 HASH RE11OOII lR FiAnnut t 20II API/AVIV A A10 NOTE: THE RESISTANCE OF TRANSPONDER TO THE CAL MOUNTING RACX MUST NOT MEW ROOM CORM THE RESISTANCE OF PADUPITPC RACK TO THE SHELF MUST POT INCING0402$ ONE. TOP VIEW EFTA01329568

SDNY_GM_02757784 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244706 EFTA01329569

n H 0 -o 0 n H H 7c; -0 UI 23 -o 00 ) of •• l" 0 • IE • 4.4 SECURE TDR-91D RACK To EXISTING SHELF vSING. SOW+ (2 Pia LOO( wASI-ER (2 RL) WASHER (2 RE) INSERT (2 PI.) ACNESIKE 00,101200049 SEEIRC IDR -94D WANTING TRAY TO TAMEN ADAPTER ASSEMBLIES USING, I SCREW (2 PL) LOCK WASHER (2 PL) $ WASTER (2 PL) THREAD LEEK FIGURE A-3 (Contd.) DETAIL B-B DUAL TOR-94D TRANSPONDER INSTALLATION TM-94D HOUNTING TRAY Al( RAYAVION Ix fetnepr ION APPENDIX A TOR-910 MOUNTING TRAY SCORE TOR-940 WONTING TRAY TO TANDEM ADAPTER ASSEMBLIES USURP SCREW (2 in.) LOCK WASHER (2 PL) WASTER (2 PL) THREAD LOCK SECURE TER-94D MOUNTING TRAY AND TANK), ADAPTER ASSEHILYS TO EXISTING SHELF USING. SCREW (2 PL) LOCK WAS)ER (2 PL) WASHER (Z PL) INSERT (2 PL) AEmESIvE EFTA01329570

SDNY_GM 02757786 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244708 EFTA01329571

C Co 0 -o 73 0 0 73 0 73 734 73 cm Pc) lO g P F-1 io ()IF V V cu IA m 8 AN pall SE Evnellee MHHIP '4— 70503 SEALANT 46 PER ANTENNA I TILLATIONT ANTENNA RETAINER ASSENT?. ANTOBM CASKET NOTE: 1. THE RESISTANCE FROM THE ANTENNA TO THE ANTENNA GROUND PLANE MUST NOT EXCEED 0.0025 OHMS. 2. THE RESISTANCE FROM THE ANTENNA TO THE AIRFRAME MUST NOT EXCEED 0.005 OHMS. CORROSIO4 PREVENTAgVE CCOPOUND OVER /CADS CF ALL I6 SCREWS SEALANT FIGURE A-3 (Contd.) DUAL TDR-94D TRANSPONDER INSTALLATION DMNI50-6-2 TRANSPONDER ANTENNA INSTALLATION NOTE: ALL FOUR ANTENNA INSTALLATIONS ARE TYPICAL 037012CC AN MAN RETAINER ASSEMBLY ADHESIVE scp stEDH C6 PER µTEMM I TALLATI0NT iii2 PIIISHLICASEH REVIVING, Ix TrIvnery 4. ZOI4 APPFARIN A COMOSION PREVENTATIVE C75/3 OVER WADS OF ALL SCREWS CASICET ANTENNA EFTA01329572

SDNY_GM_02757788 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244710 EFTA01329573

co 0 73 0 0 73 0 -12 73 73 cm .93 .93 g P I-- 0 w 0_ et PM At MN SE Esmatlee Rowe Law. la NM A ANNUNCIATOR 3451D3 I I L\ DECAL 0070120C.Ong INSTRUMENT PANEL CENTER SECTICH ADS-1 I FAIL FIGURE A-3 (Contd.) ANNUNCIATORS AND RELAY MOUNTS A P lAVAICI-000 MOAN* A PgArvan 2/. 2N4 APIINDI% A A EXACT LOCATION IS CRTERMINE0 ON MINH VISTALLAIION BUT FAUST REMAIN WITHIN SHADED AREA SHOWN. hs MCCATED DECAL TOSE ADJACENT TOANNUNCIATOR APPROXIMATELY AS SHOWN (LEFT. RIGHT. ABOVE OR BELOW). A FOR SPICA t TRANSPONDER (HO. L SYSTEM) ELECTRICAL PARTS AHD DATA. SEE APPENDIX S FIGURE 6, INSTRUMENT PANEL CAP LAW MAT NOWT SCREW (2 PL) RASHER (2 Pt) MIT (2 Pt) DECAL PCLAT MOUNT SCREW La PL) WASTER L2 PL) MIT (2 PL) DECAL TYPICAL ANNUNCIATOR INSTALLATION MUNI 'NG SLEEVE LOCKING TAB EIJOY PLUG CONNECTOR AN EFTA01329574

SONY_GM 02757790 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244712 EFTA01329575

VI CO ATO/StasoloIewOlowoo H Lamm. La 70/01 0 -0 0 n 0 rn -0 INSTRuPoi PAWL ,Z3 UI -0 V) CENTER CONSOLE TRANSPONDER CONTREL C -92D , 00 FIGURE A-4 .93 TRANSPONDER CONTROL (CTL-92E) cn INSTALLATION :c:' 2lc) O 00/0i70C ZA4 CL 6`888 88.88° PIII316-1C.4.000 ReIVION IR FAratas).4. 2014 AMINIPIN A NOTES: &COOT LOCATION IS DETERMINED CR 110114 INS TALMO, ba MUST REMAIN WORM 5100(0 PASS S, MN &FOR ELECTRICAL PARTS AND DATA. SEE APPENDU 3. %HEN INSTALLING TRANSPOsOER CONTROL. MARE CERTAII UMT ODES NOT INTERTERE MIN EXISTING COMPONENTS AND HARNESSES A. nit RESISTANCE FROM THE TRANSPONDER CONTROL TO LOCAL AinRfralt MUST NOT EXCEED OHO OHMS CIL -92E CUTOUT 70 ENSURE ELECTRICAL IONDOC. LC NOT PAINT OR PRIME SHADED ISSAS ON THE RACK SIDE or TIC INSTRUMENT PMCL. APPLY AUDI IC OLT AM EFTA01329576

SDNY_GM 02757792 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244714 EFTA01329577

PHI Inc. IH1-S76.1C4.0005 2001 SE Evangeline Thruway Revision 11? Lafayette, La. 70508 Febnany 4. 2014 Appendix APPENDIX B. ELECTRICAL INSTALLATION INFORMATION Anuendix B Table of Contents Title Page/Contents BI General Electrical System Notes BI TDR-94D Transponder System I FIGURE B-I Parts List B2 FIGURE B-I Electrical Drawing Notes B4 FIGURE B-I Decals B4 FIGURE B-I B5 FIGURE B-I Component Locations B9 TDR-94D Transponder System 2 FIGURE B-2 Parts List BI0 FIGURE B-2 Electrical Drawing Notes B12 FIGURE 8-2 Decals 812 FIGURE B-2 B13 FIGURE B-2 Component Locations BI7 Electrical System General Notes: I. Abbreviations per MIL-STD-I2D. 2. Unless noted otherwise, all unshielded wire per M1L-W-22759/43-**-9. 3. Unless noted otherwise, all shielded wire per MIL-C -27500-••SP-•S23. 4. As a minimum standard for workmanship, prepare, perform, and inspect electrical installations per AC 43.13-I B, Chapter II: a General inspection and care for electrical systems per Section I. b. Select electrical wire and materials per Sections 6, 7, & 12. c. Install and inspect wire and cable installations per Sections 8, 9, & 10. d. Clamp wire and cable installations per Section I I. e. Prepare, install, & inspect splices for wire & cable installations per Section 13. 1 Prepare, install, & inspect electrical bonding for mounting and components per Section IS. g. Marking wiring and cables per Section 16. h. Prepare unused connectors and unused wiring per Section 19. 5. Use shield terminations manufactured to military specification NASI745, or M83519/l or /2. 6. Install MS25274 caps to terminate and stow unused wires. 7. Install MIL-I-23053/13 Heat Shrinkable Tubing when required. 8. All installed materials are required to meet flammability per 14 CFR 29.853. 9. Wire Legend: EXISTING NEW WIRE REROUTE -o-o-o-o-o •• Double asterisks correspond to wire size. • Single asterisk corresponds to number of wires in the cable. BI 0070 I 20A SDNY_GM_02757793 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002447I5 EFTA01329578

SDNY_GM02757794 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244716 EFTA01329579

PHI Inc. 2001 SE Evangeline Thruway Lafayette. La. 70508 PHAS76-ICA-0005 Revision A February 21.2014 Appendix B Figure B-I TDR-940 Single System, Electrical ITEM QT Part Number Nomenclature 1 1 628-8660.001 CONNECTOR KIT 2 2 MS25036-149 TERMINAL LUG, CRIMP 3 AR 628-8664-001 BLOCK MOUNTING 4 AR 343-0133.000 SCREW 5 AR 17-043 LAMP 6 AR 372-2514-110 CONTACT 7 AR MS25036-103 TERMINAL LUG, CRIMP 8 6 8660-202 CONTACT 9 AR M39029/5-115 CONTACT 10 1 M85049/524.20W STRAIN RELIEF 11 AR 0-436-82 WIRE SPLICE 12 AR 372-2514-110 CONTACT 13 I 030-1975407 CONTACT 14 AR M39029/22-191 CONTACT 15 AR M39029132-259 CONTACT 16 AR M39029/5-115 CONTACT 17 AR M39029/22-192 CONTACT 18 I 622-9672-104 MOUNTING TRAY 19 I PHID-1740 DECAL 20 I 95-XX-17-H 1 -El BKK ANNUNCIATOR CAP (number 1) 21 .2 AG247000-0I • . GASKET 22 I 95-40-17 ANNUNCIATOR BODY 23 I PHID-1757 DECAL 24 I PHID-1913 DECAL 25 AR M23053/13412-0 HEAT-SHRINKABLE TUBING 26 AR 311601 COAXIAL CABLE 27 AR M39029/22-I92 CONTACT 28 AR 18-215 SEALING PLUG 29 I MI 2883/53-00I MOUNTING TRACK 30 I PHID-1915 DECAL 31 AR M39029-101.553 CONTACT 32 I M39029/63-368 CONTACT 33 I PHID-1827 DECAL 34 I PH1S76-683 DECAL 35 AR M17/113-R0316 COAXIAL CABLE 3451CB1 I MS3320-3 CIRCUIT BREAKER 345 ICT1 I 822-1807-004 TRANSPONDER CONTROL 3451051 I 95-40-17-H 1 -El BKK ANNUNCIATOR ASSEMBLY (cap & body) 3451E1 I DMNI504-2 ANTENNA 82 0070I20A SDNY_GM_02757795 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002447 17 EFTA01329580

SONY_GM 02757796 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002447 I 8 EFTA01329581

PHI Inc. 2001 SE Evangeline Thruway Lafayette. La. 70508 PH1-S76.1CA-0005 Revision A February 21, 2014 Appendix B Figure B-I TDR-940 Single System Electrical ITEM QT Part Number i Nomenclature 3451E2 I DMN150.6.2 ANTENNA 3451K1 I M83536/2-028M RELAY 345IRVI AR 714-3258-020 VARISTOR 345ITRI 1 622-9210-550 TRANSPONDER 3451W I I P111.576-13204.01 CABLE ASSEMBLY 3451XDSI I 18-200 CONNECTOR MODULE 345 IXKI I M12883.52.00I RELAY SOCKET PI73R AR 634.1112.001 CONNECTOR PI882R AR 634.1112.001 CONNECTOR P1883R I CTR922 _ TNC CONNECTOR P1884R 1 CTR922 TNC CONNECTOR P I 889R I CNS922 TYPE N CONNECTOR P1891R I CNS922 TYPE N CONNECTOR P792R I MS3476W20-4 I SY CONNECTOR, CRIMP CONTACTS P792RS 1 MS3126F8-45 CONNECTOR T1534-V AR CT.1122EOIC TERMINAL JUNCTION MODULE QT— Quantity AR— As Required ALT — This part is an alternate to the preceding part. B3 0070120A SDNY_GM_02757797 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241719 EFTA01329582

SDNY_GM02757798 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244720 EFTA01329583

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SDNYGM_ 02757800 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244722 EFTA01329585

H 0 0 n H rn C rn —O xp -O Co lD l-a cn P 2 = CD_ I-a PHI St 1 notselue Thrwavp LAIneue. 'WU 00/012(XWING 00<el Ansa moc IC sats „ MOW SCONIMEEELD 001Et criza 0-4 B>+ 00 =WWI O WI i• @01 xual I..—IIAal.TIJ I 1 " o l- et MO IGO- i 1-14". 1-1=11 a lr ,= Z War rra , WOWSICIUS li>t>{}— lar 0—tn O ..arEM ta>.4°7111.c fil>DIrl00 DI> FIGURE B-1 Transponder System 1 SHEET 1 of 5 a CAILL .atan /WI IMP Ram , OW IRI MAWS.. WIT. 44/55 pad. =1M rtr" WW W0 MOW WWI WWW a I WNW WWI PIIISASHIADONS AMWAY A Airmen. ll. 2814 APPNIVIAPC EFTA01329586

SDNY_GM 02757802 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244724 EFTA01329587

Cr co n rn -0 70 0 rn n H rn H 70 0 rn 7a -o -0 (r) -Co lD cn O z ul io CU co CL. 8 GO 701X18 ONG FIGURE B-1 Transponder System 1 ADS-B Fail Annunciator SHEET 2 of 5 PHISISICA-000 REPANTV m 1014 APPIRM.V EFTA01329588

SDNY_GM_02757804 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244726 EFTA01329589

m IS IpJ IJ to co H T O 0 n rn os C oo -0 os ul oo -0 CM > I Co Y) ,p 2 1-a 0 U1 3 N 3,1 CD- 8 I-a Hit Air ZOO St nokrOkar Peanntr taws , Ia NOUS I 345ICII Cit•St IRMSPONDIR I Pna I@ @ -, r c > 21 'PDC 16 '"Cl [3, CAMPO LIDOS CONNITN ANL SELECT 5V LTG LIGHTS GIN CTRL IN IA CTRL IN II iszooiszt—t CgallifttriV5O S -S500142214 SLIM SX002A221/ tl -SX001APPIN A l>O1 maxi I MIEFENI Et:13) tl -SX004Ar ILJ CTRL OUT IA T CTRL OUT II 0 .t2) Cri.tel KW egg : MIS CO70120ROWG CONSOLE <ANTS OMNI HE' 0-5 YS OUT CL IGIIT ITC) nv,COPILOT AIR - 77777 'AYR- COINIBIR -IFAI74028 -44 - RATA LIADDIAta.--{lala.ch...@ .. ,,,..9., ...,,... EDE] paws I Th t2 svG tom h D@ VG <V iSx0atin WI ISX0391.22 IST010422N-I WF kl• 000 Op Plow I •VG fV -AVG IV 2AVG (V 22-AvG IN0NP2 INg30 333S (>"' Walt /IX n >O Ea] [ji=ca LIINC FIGURE B-1 ANTENN e A Transponder System 1 CTL-92E Control Interface SHEET 3 of 5 03)\ 11.7002A-131,60l) <25 Pt ISVIOIP,I311101/ CV IT @ 7 Plait PIIISYNICIONT REVISION A &Naar 70I RVIENINV Tftn'; 707, <I .12) ALT Trim Aso MX Att AIRSPEED Ft A M NAX AIRSPEED ARSPEED SDI INPUT A SDI INPUT 3 STRAP CERRO, DISABLE CPS INTEGRITY LIMIT CIPII/A411 CONDO. 919 PM IN A 429 ALT IN gat E 2 4 : 12; 41 I N a ISO UPPER mama LAID MIDes 87 EFTA01329590

SDNY_GM02757806 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244728 EFTA01329591

In CO rn H H n 73 0 H rn n H rn 0 0 rn -o -o Ib :D I_a to '0 VI 3 O 0.) 0- I p p O IJ lw ?VISE ImmoVac Thmov, Wm*, I. Mot AM-s 00$11ail IOUlet MUIC 4rt °Awe KM, {gra: MOWS 114 0 en. am faros 0 1* entassim—I>Msta 1-.C)e<1 L FIGURE B-1 Transponder System 1 UNS-1Fw Interface SHEET 4 of 5 tible•I24,1/ IT10412- 6.2=r111. 7 PHISISICA-01,05 RE iltION A Arauri 21.1014 APIIWOIN oar Anterf moat 000 mum Is. I nee-me mina< a artlitifil 00701206.CMG tla EFTA01329592

SDNY GM 02757808 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244730 EFTA01329593

SDNY_GM_02757809 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024473 I EFTA01329594

SDNY_GM02757810 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00244732 EFTA01329595

Pill 2001 SE Evangeline Thruway Lafayette. La. 70308 PH/-S76-!Cd.00B, Revision A February 21. 2014 .4ppendir B Figure B-2 TDR-94D Dual System, Electrical ITEM I QT I Part Number Nomenclature I I 6284660.001 MATING CONNECTOR KIT 2 2 MS25036-149 TERMINAL LUG, CRIMP 3 AR 628-8664-001 BLOCK, MOUNTING 4 AR 343-0133.000 SCREW 5 AR 17443 LAMP 6 AR 372-2514-110 CONTACT 7 10 MS25036-103 TERMINAL LUG, CRIMP 8 I PHID-1828 DECAL 9 AR M39029/5.115 CONTACT 10 I M39029/63-368 CONTACT II IS D-436-82 WIRE SPLICE 12 I 0-434-83 WIRE SPLICE 13 1 030-1975-007 CONTACT 14 AR M39029/22-191 CONTACT IS AR M39029-101453 CONTACT 16 I M39029/5-115 CONTACT 17 I PHID-1916 DECAL IS I 622-9672-104 MOUNTING TRAY 19 I PH1D-1741 DECAL 20 1 95-XX-I 7-HI-El BKL ANNUNCIATOR CAP (number 2) 21 2 AG247000-01 GASKET 22 I 95-40-17 ANNUNCIATOR BODY 23 I PHID-1756 DECAL 24 I PH1D-1914 DECAL 25 AR M23053/I3-012-0 HEAT-SHRINKABLE TUBING 26 AR 311601 COAXIAL CABLE 27 AR M39029/22-192 CONTACT 28 AR 18-215 SEALING PLUG 29 I M12883/53-00I MOUNTING TRACK 30 AR MI7/I I3-RG316 COAXIAL CABLE 3451 CB2 I MS3320-3 CIRCUIT BREAKER 345 ICTI AR 822-1807-004 TRANSPONDER CONTROL 3451DS2 I 95-40- 1 7-H 1-EI BKL ANNUNCIATOR ASSEMBLY (cap & body) 3451 E3 I DMN150-64 ANTENNA 3451 EA I DMNI50-6-2 ANTENNA 3451K2 I M83536/2-028M RELAY 345IRV2 AR 714-3258-020 VARISTOR 345 ITR2 1 622-9210-550 TRANSPONDER 345 IW2 I PH1476-1320541 CABLE ASSEMBLY 3451XDS2 I 18-200 CONNECTOR MODULE 345 I XK2 I M12883-52-001 RELAY SOCKET RIO 0070120A SDNY_GIv102757811 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244733 EFTA01329596

SDNY GM 02757812 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244734 EFTA01329597

PHI Inc. 200! SE Evangeline thruway Lafayette. La. 70508 PlitS76-1CA-0005 Revision A February 21. 2014 Appendix B FigUre 8-2 -.; , c•-!' :' p .: ;: .1,Waicijit:tilt ,-.4.:Ci•,31r4ti - ri . .4. ..4 ',. :::::reicC; :: /TDR-94D Dual System, Electrical . 't ;:, 4 k ITEM : QT • :.•:. Part Nisiiiliei-a. 14S1. 4 " &N0ITIellelaillier, e r .. PI7IR AR ; 634.1I I 2-00 I -, ^=r ".V8444,, '41 CONNECTORI1/2,ii:k. a , .8>514A.1- -''2r"c--; PIDSR I - CTR922, I- .' O-NC.CONNECTOR14 ` . . -- P11386R ' , AR 634-1112-001 CONNECTOR.. , ., . P I 887R I CTR922 . TNC CONNECTOR :-.._7,- i- P I D0R I CNS922 TYPE N CONNECTOR P1892R I 4 CNS922 TYPE N, CONNECTOR.. ')n- P792R AR MS3476W20-4 I SY CONNECTOR; CRIMP CONTACTS ' 11534-X AR CTJI22E0IC TERMINAL JUNCTION MODULE QT — Quantity AR- As Required ALT — This part is an alternate to the preceding pan Et I I 0070120A SDNY_GM_02757813 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244735 EFTA01329598

SDNY_GM 02757814 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244736 EFTA01329599

t .0 LL 1. 2 ; Sc.! As Ks x1242 agh5l 4.428 al!! ilApe IPsY1 roll o ; ! il e:! orIg 4se ;1 Xli ke Y g i!5° ! !pig ! ggqi g -6 Egigl irt! op 2' Ex 6 43 4i 21 tr - ;Ii;1 4O0 rem W w PX 0 D I' A - 4pg Z 0 it 0 1 4= Fi.b i§ I EV:P YR AIEEY =AAA OA • •v; • 4 •vi ;ft 2.4 !PI -.4 grt elt; iSi !!! tr: !gt-f ZEE a imwormilm i nt 416444 M2R ;;; ) i I A 2 2 ! W I .1! i yy M i i IP 2 I is 11; V I '; ! 4 1 p glI f 4 e E s II 1 i li i i ! e s li I g i k 'kE v g . ! ie3! i g i d I I 1 1 ! 1 2 1 t i yr* 1 I I IX; I I i 6 i I I i b I i 1 EF1 ; 4 i i i 3 lani 2 ; ..ee; 1 i 4 a . . 4 ? M; i H / / ! I NI; I ! 1 . - : st. g g ; v m ; i I ha g I i i 5 AAA AAAA AAA I tl I 8 SDNY_GM_02757815 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244737 EFTA01329600

SDNY_GM02757816 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244738 EFTA01329601

6ELtrZOO- V.U3 to 0 H 7Z, -0 0 rn rn C 7Z, rn -O 7S -O to My Oz Ul Im 0 0.) Zji CD_ r, i-a L.- 209Ill:e.erder Moir, Lnine.v. 00701200 DWG yi:tigartt—h CliEB3ITED 13)- f t>=7600 C mi nitcl ona l untsferbilig FIGURE B-2 Transponder System 2 SHEET 1 of 5 044 00[>ilat 0 000 vac awe KIES. I.E4 I Ma, MI ID bit MAD a SI CIO SOJI OM @L,2 i• 14 Itri•CA I 264Srlittt UNA at3 164000 a AVG IV li lt' Aparennonas mei Loweertare • LSO AW ON6 O kleelftellal. evict C e2 4.6 c. 'CH tt : TgekirofitIsuligsrstrw' 1. Linrjr;Itg.c =tar r' r-el An in- it Wtsta i ," 22 Waal rot ▪ I 0 OJC•8 lastla Pram I I M e. aj NAM OM Iivilt>{r====.- anxix— AMMO 'tea IAD -eSzin•ee O \-0 tci =Mg ligra" 3 guns. • latrt ObM 00.00, It Ii St a S MOM Can all PIII.SAWCA.0003 REVINION A rt.e..7rn NI I AKtVPI%S EFTA01329602

SDNYGAL02757818 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244740 EFTA01329603

I fLtti0O-VIda to CO L_ H -O rn n rn O C rn -O xp Gl -O Co Y) I_am Oz FR IG) C0 Z31 CD- al i-a tilt Ave 1001 SL LSsvicreior Tbrwer, LaAnnie la 7056.1 ANNUNCIATOR 343IDS2 ;glee I 345IXDSE le@ 2-PAIG (6•/—, Z-AWG 32 132022 2-4G (V CAILE ASSOTILTI 345112 el P14922 2-ANN CPl)-3 73) 22-ANN C6')--, I . 2 WON OA/VAIN @@el 34511(2 I I 3451Xx2 ICI ESX 15RAW1 2SX-1nA22 2SX 133422 INTIGRATID INSTRIANNT MILO Slit 11 KNOT( DATA AWNINTION WIT! LOW TEST OUTPUT 2S2 131Ata 212 136A2211 @Ina-RI PILOT ANNUNCIATOR OWNER VT 5 WC DM CIO VOC 000 (i)l P1712 j 3431182 1 No, 2 TOR-540 TRANSPONDER (Al 31 PALLT POSITOR OUTPUT P 17 P6D9 I 745 24 -L121A22- — — --WARMS-D-22- —A— -L121122- — —A— -.PPRP745-27-22- — — - 27 - — 0•11006 FIGURE B-2 Transponder System 2 ADS-B Fail Annunciator SHEET 2 of 5 00701706.0WO 1114 RE ItS74ICA.04.$ REVAIOPI IN &two" 4. 20Il AMAMI. EFTA01329604

SDNY_GM 02757820 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244742 EFTA01329605

EtLitZ00-VIi3 to co H H n -0 0 rn H 0 rn 3D -0 3D 3D -0 Co cO to Oz '0 O V CL 1-1 PHIAL' :iv), SC C•wyeeme Anon) LAntnr. la 7O,A, CO/Ol200 ONG 345ICTI cn.-92E TRANSPRNDER r pm,* 10 canna v¢ IN MaIN. 2 G ▪ 2SECOIDe2-4 Calriro R> ccgana iZ t G.._ CONTROL WT PA N pi-- COMM WI 21 Dr• I Pala-% 18 Eat annul 312132 000 345'112 IN. 2 TC41-940 TRANSPONDER 01 PISA I ca, I>. PUT -ermanat—r as ts 42,429 ALT p 144 Am DATA t_ _erstottaa GONPUTER 'm aul 2SP361•224-1 GG44 I—NO 252030422 at 255031.22 12.0 -251O32A22 WI 251033•22 RU ecc 0.1 GG4le J-2510063•2204 AMEN LIPPER NA Ci 4 IEDI 3451(4 FIGURE B-2 Transponder System 2 CTL-92E Control Interface SHEET 3 of 5 AVG ES• - t3 GIRL Guy • 24 CTRL WT I 13 QV Wal k 14 429 TIM IN AwG 22 Un— 4I ALT TYPE ASO _Aut (6. )__ 42 ALT TYPE ASI z_AvG "e t__ 43 Nix AIRSPEED 22-AvG (6')— 44 MAX AIRSPEED 45 MAX AIRSPEED 22-AvG (6•/— 46 501 Dan A 47 SRI Dan D e-ANG WY-- 52 STRAP gap 53 DISABLE GPS INTEGRITY LIMIT % CtinfrA421 Wan - I pin I ja, 1511020 311601 (25 ED- 0=OUPPER NOrin LOME ANTENNA PINPOR N>01 351E3>=3=11-2SX101A-3DEOI CI' ay =GIN C —.• DKR ANTDom als PIII4764CIAlb31 IttnIJON A filwifflrr:I.2011 APPENDIV EFTA01329606

SDNY GM 02757822 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244744 EFTA01329607

5fLtti0O- V.Li3 co n H H rn -0 0 rn n H rn H 31 rn 3D -0 7s 3D -0 to So .90 NIn SD 2 'O O CD_ t,' PM Mt NOW NE EBBywiine risnawar Lalunor. Ls AUK COI 0070 I 20, OWG a. PM. - NAL AtIONCII WPC no 1014-1. • SPAYS sono. MILICIECCOME nos aeon Al Y {on DATA A 1011•C 743A DATA On ATA $ IOC /*INC W OJTIUT PCill 3 VMS TIMMIOX KO* 0 I Ida/ 1CAll AINICILY SS@ 04 041 FIGURE B-2 Transponder System 2 UNS-1Fw Interface SHEET 4 of 5 016 fIllaNICANNO5 E£YAWWN A Amin. 11 . 70" APPENDIX a EFTA01329608

SDNYGM02757824 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244746 EFTA01329609

H H 0 rn n rn H rn -0 -o Co cn .9 F-1 '0 to 3 2 = ;34, m I8 IpJ PH(. few M0I St tavaaohur Ana.) Loiarrut La 711,05 cocun MAME O(C4110) BLOCK G02 MONO ACC( TERMIAL AACIOA a a KAY 345122 NOM IA 2 1M-110 TRANISPONDER C0701200.0.220 3431052 I W. 2 POWItIt 0101140 (OMIN) -42 low-4 mansttra( TRANSPONOCI =alba FIGURE B-2 Transponder System 2 SHEET 5 of 5 uv PIII4744CA.MIPS RICYLVON A &Nueva?). MU APPENDIX A EFTA01329610

SDNY_GM_02757826 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244748 EFTA01329611

PRO STAR Federal Aviation Administration Aircraft Registration Branch, AFS-750 P.O. Box 25504 Oklahoma City, OK 73125 Attn: Please find enclosed FAA Form 337 for the following aircraft: Registration: N722JE Make: Keystone Helicopters Model: S-76C Serial No.: 760750 Thank You, John Driscoll Pro Star Aviation Manchester Airport 5 Industrial Drive Londonderry, NH 03053 E-mail: 603 627-7827 Voice ax Pro Sky AvioHon. LIC.. 5 IndusIdol Drive. Londonderry, NH 03053 U.S.A. CRS RP6UR0067 Bus: 0031 627.7827 I Fax: (603) 627.7801 I gRostaoTlalion.com STC 0DA •O0A-R3fl3.NE SDNY_GM_02757827 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244749 EFTA01329612

SDNY_GM_02757828 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00244750 EFTA01329613