C LDaRL. RVIRTIDl'"l TECHnDLDCIES INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FOR THE

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1 . J C LDaRL RVIRTIDl'"l TECHnDLDCIES INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FOR THE COLLINS 850 FMS TO UNIVERSAL AVIONICS 1 Ew FMS UPGRADE LEARJET MODEL 60 AIRCRAFT SIN oa9 REG. NO. Nlftf D THIS DOCUMENT CONTAINS INFORMA non OF A PROPRIETARY NATURE AND SHALL NOT BE TRANSMITTED, REVEALED, OR DISCLOSED TO ANYONE WITHOUT THE EXPRESS WRITTEN PERMISSION OF GLOBAL AVIAnON TECHNOLOGIES. ADDITIONALLY, USE OF THE INFORMA non JS PROHIBITED EXCEPT WHEN EXPRESSL y AUTHORIZED IN WRITING BY GLOBAL AVIA non TECHNOLOGIES.

2 RECORD OF REVISIONS: Approved Date Rev Description ~ 2/19/2009 {IR) Original Release ICA Page2 of25 "

3 ICM Page 3 of26 Table of Contents RECORD OF REVISIONS: ~ TABLE OF CONTENTS INTRODUCTION PURPOSE... _ ABBREVIATIONS AND OEFINlTIONS GENERAL GENERAL (CONTINUED)... _ APPLICABILrTY REFERENCED DOCUMENTS... _.. & 7.0 EQUIPMENT AND FACILITIES NEEDED... & 8.0 TIME LIMITS/MAINTENANCE CHECKS UNS-1EW FMS EQUIPMENT - REMOVAL AND INSTALLATION FMS EQUIPMENT - TROUBLESHOOTING REPAJR OF UNS-1EW FMS COMPONENTS CONTROL AND OPERATION DIAGRA.MS _...;io SPECIAL INSPECTION REQUIREMENTS APPLICATION OF SPECIAL TREATMENTS DATA RELATIVE TO STRUCTURAL FASTENERS SPECIAL TOOLS COMMUTER CATEGORY AIRCRAFT OVERHAUL PERIOD AIRWORTHINESS LIMITATIONS REVISION ASSISTANCE IMPLEMENTATION ANO RECORD KEEPING APPENDIX A... A 1 APPENDIX B APPENDIX C C1 APPENDIX D... D1

4 1.0 INTRODUCTION ICA Page 4 of26 The information presented in this document supplements or supersedes the existing maintenance requirements only in those areas specified. Refer to the manufacturer's requirements and procedures for maintenance procedures pertaining to the airplane's systems and specific avionics equipment not covered in these instructions. 2.0 PURPOSE This document identifies the Instructions for Continued Airworthiness for the installation of the Universal Avionics UNS-1 Ew FMS System installed per Global Aviation Technologies Design data outlined in Section 6.0. These Instructions for continued airworthiness comply with the requirements of part and part 25 Appendix H of the Federal Aviation Regulations. 3.0 ABBREVIATIONS AND DEFINITIONS 3.1 Abbreviations: A ADC 8. ADF C. AP D. ATC E. CDU F. COM G. DME H. DTU I. FAA J. FAR K. FD L. FMS M. FSDO N. GPS 0. IAS P. ICA Q. ILS R. MFD S. NAV T. NCU U. SAT V. SIDS Air Data Computer Automatic Direction Finder Autopilot Air Traffic Controller Control Display Unit Communication Distance Measuring Equipment Data Transfer Unit Federal Aviation Administration Federal Aviation Regulation Flight Director Flight Management System Flight Standards District Office Global Positioning System Indicated Airspeed Instructions for Continued Airworthiness Instrument Landing System Multifunction Display Navigation Navigation Control Unit Static Air Temperature Standard Instrument Departures

5 , W. STARS X. TAS Y. TSO ICAA Page 5 of26 Standard Terminal Automation Replacement System True Air Speed Technical Standard Order 3.2 Definitions: NIA

6 Instruction for Continued Aiiworthiness 4.0 GENERAL 4.1 Description of the Alteration ICA Page6of26 The Universal Dual UNS-1 Ew FMS system replaces the existing Dual Collins 851 FMS System installation. The Universal Avionics Systems Corporation UNS-1 Ew Flight Management (FMS) installation consists of the following new units: Dual UNS-1 Ew Control Display Unit (CDU) located in the FWD Pedestal Dual FMS Configuration Module. Dual GPS Antenna. The Dual UNS-1 Ew FMS system contains software, which provides capability for point-to-point navigation, as well as SIOs, STARs. Holding patterns. and GPS approaches. The software complies with requirements oftsos C115b and C129a Class A1 when interfaces to the internal GPS sensor which is TSO C129a Class A1/B1 /C1 certified. The Dual UNS-1 Ew FMS system contains an internal GPS sensor that incorporates Receiver Autonomous Integrity Monitoring (RAIM) to provide position data. The FMS also uses VOR and OME for short range position data. Each UNS-1 Ew system receives air data information from the aircraft's respective air data computer (AOC). Air data inputs include: barocorrected and pressure altitude, TAS, IAS, SAT. and Mach. Fuel Management is available through automatic fuel flow inputs. A Solid State Data Transfer Unit (SSOTU) is used to load the FAA Approved Jeppesen Data Base into the FMS's. The FMS provides a radio tuning function capable of tuning the COM. NAV, ADF, and ATC avionics.

7 Instruction for Contmued Airworthiness AvionlCS 1 Ew FMS 4.0 GENERAL (CONTINUED) 4.1 Description of the Alteration (Continued) ICAA Page 7 of26 The Dual UNS-1 Ew system provides lateral navigation and steering data to the pilot's and copilot's flight instruments and to the flight director/autopilot (FD/AP). The system also provides enroute VNAV data to the pilot's and the copilot's flight instruments which can be coupled to the FD/AP. Remote annunciators are also provided to indicate the status of certain FMS functions as explained in Section II, Normal Procedures. The Dual UNS-1 Ew software contains software, which provides capability for point-to-point navigation and approaches. Lateral steering is provided for enroute, terminal area and approach operation. The Dual UNS-1 Ew systems provide lateral and vertical steering data to the Collins Proline-4 EFIS and Autopilot 4.2 Precautions : NIA 4.3 Units of Measurement: NIA

8 For the Collins 650 FMS to Universal Lea~et Model 60 Aircraft ICA ~01 Page 6 of APPLICABILITY The requirements and information contained within this document apply to the Learjet Model 60 aircraft altered by the installation of the Universal Avionics UNS-1Ew FMS System per Global Aviation Technologies design data outlined in Section Distribution This document should be a permanent aircraft record. 6.0 REFERENCED DOCUMENTS Global Aviation Technologies ID GPS Antenna Installation Drawing (Drawing included in Appendix A). Global Aviation Technologies ID UNS-1Ew FMS Installation (Drawing included in Appendix A). Global Aviation Technologies. WD Wiring Diagram - UNS 1 E 0N) FMS lnstl LR60 (Drawing included in Appendix A). Universal Avionics Systems UNS-1Ew FMS Technical Manual dated 27 August EQUIPMENT AND FACILITIES NEEDED Depending on the type of maintenance being performed, the following equipment may be required: Test Set for Air Data System Test Set for ILS System Test Set for DME System Multimeter No special facilities are required to perform maintenance on the FMS installation.

9 8.0 TIME LIMITS/MAJNTENANCE CHECKS 8.1 Inspection Intervals ICA Page 9 of26 A. 600 HOURS OR 12 CALENDER MONTH INSPECTION At intervals of not greater than 600 flight hours or 12 calendar months, whichever occurs first, following the installation of the UNS-1Ew FMS system accomplish the UNS-1Ew FMS 600 HOUR/12 MONTH INSPECTION Form in Appendix B. This inspection is to be repeated at intervals of not greater than 600 flight hours or 12 calendar months, whichever comes first, as a recurring inspection. B. 18 CALENDAR MONTH INSPECTION At intervals of not greater than 18 calendar months following the installation of the Dual UNS-1 Ew FMS system, accomplish the Dual UNS-1Ew FMS 18 MONTH INSPECTION Form in Appendix B. This inspection is to be repeated at intervals not to exceed 18 calendar months as a recurring inspection. 8.2 Database Updates A Use of the UNS-1Ew as an IFR approved navigation system is predicated on the navigation database being maintained at a current revision level. The navigation database must be updated at intervals not to exceed the effectivity of the database (28 day cycle). B. At intervals not to exceed the effectivity of the database (28 days) update the navigation database per the UNS-1 Ew 28 DAY NAVIGATION DATABASE UPDATE Form in Appendix B. A lapse in the navigation database updates will be evident by a message appearing during FMS initialization stating that the navigation database is not current 8.3 Cleaning, Lubrication, and Adjustments None

10 For the Collins 850 FMS to UniversaJ 9.0 UNS-1 Ew FMS EQUIPMENT INSTALLATION 9.1 Access to Equipment A. UNIVERSAL AVIONICS UNS-1Ew FMS CDU ICA Page 10 of26 REMOVAL AND 1. The UNS-1 Ew FMS Control Display Unit (CDU) is located in the FWD Pedestal as shown in Figure 1. It can be removed by loosening the four (4) quarter turn fasteners on the face of the unit and pulling the unit out of the pedestal. FIGURE 1 TOP DOWN VIEW OF PEDESTAL SHOWING FMS

11 Instruction for Continued Alrworthiness Learjet Model 60 Aircrart ICM Page 11 of26 B. UNIVERSALAVlONICS FMS CONFIGURATION MODULE 1. The FMS Configuration Module is located on the COU Connector backshell on the aft side of the UNS-1 Ew COU as shown in Figure 3. The Configuration module can be accessed from the aft end of the COU connector with the COU removed from the pedestal.,.. "' ' J J,.. "'... '.. I I --- _,_... "' 'J..._,..,. A A....( ' STRAIN RELIEF 1 SCREW & WASHER / ~/ CONFIGURATION I, MODULE...:~ \ '-- THREADED SIDE OF WIRE CLAMP \ "- CONNECTOR FIGURE 3 VIEW OF CONFIGURATION MODULE ON UNS-1 Ew COU CONNECTOR C. FMS CIRCUIT BREAKER (existing) 1. The FMS circuit breakers are located in the Pilot's & Copilot's circuit breaker panel. They can be reset, or pulled to deactivate the FMS, from the Pilot's & Copilot's seat position. Replacement of the circuit breaker will require the Pilot's circuit breaker panel to be removed.

12 D. PORTABLE DATA LOADER CONNECTORS ICA Page 12 of The Solid State Data Transfer Unit (SSDTU) is located at the aft end of the pedestal as shown in Figure 4. SSDTIJ FIGURE 4 VIEW OF AFT END OF THE COCKPIT PEDESTAL SHOWING SSDTU E. FMS SSDTU CIRCUIT BREAKER 1. The FMS SSDTU circuit breaker is located in the Pilot's circuit breaker panel. It can be reset, or pulled to deactivate the FMS SSDTU from the Pilot's seat position. Replacement of the circuit breaker will require the Pilot circuit breaker panel to be removed.

13 AVIOOICS 1 Ew FMS F. FMS ANNUNCIATORS (existing) ICA Page 13 of26 TffiE PAGE RIGHTS APPLY 1. The UNS-1 Ew FMS annunciators are integrated in the Collins Pro Line 4 System. They are displayed on the PFD & MFD. Refer to the Collins Learjet 60 Avionics System Manual PIN A dated 20 January There are two (2) dedicated LOS annunciators (one for each pilot) installed in the pilot and copilots instrument panel. G. FMS GPS ANTENNA (existing) FIGURE 5 PILOTS LOS ANNUNCIATOR 1. The existing GPS antenna is mounted to the top of the outside of the aircraft on the aircraft centerline. It is typically mounted AFT of the Main Entry Door between the First and Second Window Area on the Learjet 60 aircraft as shown in Figure 5.

14 ICA Page 14 of26 OPS ANT FIGURE 6 TYPICAL LOCATION OF GPS ANTENNA

15 lnstructjon for Continued Airworthiness 9.2 Removal and Replacement of FMS Equipment CAUTION: ICA Page 15 of 26 Prior to removing or installing any FMS Components, ensure aircraft power is selected OFF and that external ground power is disconnected. A. UNIVERSAL AVIONICS UNS-1Ew FMS CONTROL DISPLAY UNIT (CDU) 1. Removala. The Dual UNS-1 Ew FMS Control Display Units (CDU) is located in the FWD Pedestal as shown in Figure 1. It can be removed by accomplishing the following: (1) Disengage the four (4) 1/4 turn fasteners on the face of the FMS. (2) Pull the FMS CDU out of the Pedestal. (3) Disconnect the FMS electrical connectors on the bottom (back) side of the FMS COU. (4) Remove the UNS-1Ew FMS Control Display Unit (CDU) from the aircraft. 2. Installation - a. Installation of the UNS-1Ew FMS Control Display Unit (COU) is done in reverse order of the removal. The FMS can be installed by accomplishing the following: (1) With the FMS loose, connect the electrical connectors. (2) Set the FMS in place in the Dzus rails of the instrument panel and tighten the fasteners until tight (approximately 1/4 turn). (3) Functional Test the FMS per UASC UNS-1Ew Flight Management System Installation Manual (Ref. Appendix C).

16 Lea~e t Model 60 Aircraft ICM104.J Page 16 of UNIVERSAL AVIONICS UNS-1Ew FMS CONFIGURATION MODULE 1. Removal - a. The FMS Configuration Module Is located on the CDU Connector backshell on the aft side of the UNS-1 Ew CDU. The configuration module can be removed by accomplishing the following: (1) Remove the UNS 1 Ew from the pedestal following the CDU removal instructions outlined in Section 9.2 A 1, Universal Avionics UNS-1 Ew FMS Control Display Unit (CDU). (2) Unscrew the configuration module from the CDU backshell (see Figure 3 for installed view of module). (3) Extract the configuration module wires from P1 CDU connector. Configuration module is now removed. 2. Installation - a. Installation of the FMS Configuration Module is done in reverse order of the removal. The module can be installed by accomplishing the following: (1) If not already accomplished, remove the FMS CDU from the pedestal, as outlined in Section 9.2 A 1 Universal Avionics UNS-1 Ew FMS Control Display Unit (CDU). (2) Insert the pins from the configuration module into the rack connector using the Wiring Diagram WD for pin assignments. (3) Reattach the configuration module to the CDU backshell (Ref Figure 3). (4) Reinstall the FMS CDU and secure in the pedestal as outlined in Section 9.2 A2 Universal Avionics UNS-1 Ew FMS Control Display Unit {COU). (5) Apply power to the aircraft and ensure that the inverters and avionics/radio master switches are selected ON.

17 Avionics 1Ew FMS ICM Page 17 of 26 (6) Using the values shown on the FMS Configuration Table on Sheet 3 of the Global Aviation Technologies. Wiring Diagram WD , program the configuration module. (7) Functional Test the FMS per UASC UNS-1Ew Flight Management System Installation Manual (Ref. Appendix C). C. CIRCUIT BREAKERS 1. FMS DTU Circuit Breaker Removala. To access the Pilot's circuit breaker panel, follow procedures outlined in the lea~et Model 60 Maintenance Manual. CAUTION: Prior to loosening the circuit breaker panel, ensure that no external power is connected to the aircraft. the aircraft master power switches are selected OFF, and that the aircraft batteries are disconnected. (1) Remove the circuit breaker from the circuit breaker panel assembly. 2. FMS SSDTU CIRCUIT BREAKER INSTALLATION - a. To access the Pilofs circuit breaker panel, follow procedures outlined in the Learjet Model 60 Majntenance Manual. (1) If not already done, accomplish steps 1 of the removal process. (2) Insert the new circuit breaker in the circuit breaker panel paying special attention to the orientation of the circuit breaker. (3) Tighten the circuit breaker in place with the supplied nut and lock washer. (4) Connect the circuit breaker to the appropriate wiring as shown in the Global Aviation Technologies. Wiring diagram WD located in Appendix A.

18 ICA Page 18 of26 (5) Reconnect the circuit breaker panel connectors if previously disconnected. (6) Place the circuit breaker panel in place. Install the Pilot's circuit breaker panel, following procedures outlined in the Learjet Model 60 Maintenance Manual. (7) Reconnect the aircraft's batteries and apply power to the aircraft. Use external power as necessary. (8) Functional Test the FMS per UASC UNS-1Ew Flight Management System Installation Manual (Ref. Appendix C). 3. FMS CIRCUIT BREAKER REMOVAL a. To access the Pilot's or Copilots circuit breaker panel, follow procedures outlined in the Learjet Model 60 Maintenance Manual. CAUTION: Prior to loosening the circuit breaker panel, ensure that no external power is connected to the aircraft, the aircraft master power switches are selected OFF, and that the aircraft batteries are disconnected. 4. FMS CIRCUIT BREAKER INSTALLATIONa. To install the Pilot's or Copilots circuit breaker panel, follow procedures outlined in the Learjet Model 60 Maintenance Manual (1) Functional Test the FMS per UASC UNS-1Ew Flight Management System Installation Manual (Ref. Appendix C). D. FMS ANNUNCIATORS 1. RemovaVlnstallation - a. The FMS UNS 1 Ew annunciation is integrated in the Collins Pro line-4 Avionics Suite. Annunciation is displayed on the Pilot's and Copilot's PFD & MFO. Removal of the PFD & MFD shall be accomplished following instructions contained in the Learjet Model 60 Maintenance Manual.

19 Instruction for Contmued Airworthiness For the Coflms 850 FMS to Universal Leaf"jet Model 60 Aircraft ICA Page 19 of26 mle PAGE RIGHTS APPLY E. FMS GPS ANTENNA 1. Removala. The GPS Antenna is mounted to the top of the aircraft in locations shown in Figure 5. The Antenna can be removed by accomplishing the following: ( 1) Locate the antenna on the top of the aircraft (2) Remove the 4 screws attaching the antenna to the aircraft. (3) Pull the antenna off the aircraft far enough to gain access to the coaxial connector on the bottom side of the antenna. NOTE: It may be necessary to use a plastic scraper to remove the edge sealant around the antenna. This would be necessary if the antenna is firmly sealed In place. CAUTION: Never use a metal scraper to remove sealant around the GPS antenna. Damage to the aircraft could result NOTE: If the antenna coax does not allow the coaxial connector to be removed while outside the aircrafts it may be necessary to remove the appropriate headliner piece to gain access to the antenna coaxral connector from inside the aircraft (4) Remove the antenna coaxial connector. If this is being accomplished from the outside of the aircraft, it is advisable to temporarily secure a piece of string to the connector to keep it from falling inside the aircraft (5) Antenna should be free of the aircraft. 2. Installation - a. Installation of the GPS Antenna is done in reverse order of the removal. The Antenna can be installed by accomplishing the following: (1) Using a plastic scraper, remove the excess sealant from the GPS antenna mounting area. CAUTION: Never use a metal scraper to remove sealant around the GPS antenna. Damage to the aircraft could result

20 For the Collins 650 FMS to Universal leariet Model 60 Aircraft ICA Page20 of26 (2) Connect the GPS antenna coaxial connector to the antenna. (3) With the GPS antenna in place secure the antenna with the four (4) antenna mounting screws. (4) Fillet seal the antenna with Pro-Seal 890 (Class B 1/2) sealant at the edge of antenna. (5) Reinstall the aircraft interior if removed. (6) Reposition the aircraft outside in an area that is capable of receiving GPS signals. (7) Apply power to the aircraft and ensure that the inverters and avionics/radio master switches are selected ON. (8) Tum on the FMS and verify that it acquires enough satellites to navigate in IFR airspace. (9) AJlow the sealant to cure for a minimum of 24 hours before flying the aircraft.

21 10.0 FMS EQUIPMENT - TROUBLESHOOTING ICA Page 21 of26 Due to the complexity of the FMS installation, only installation specific faults will be discussed in this section. For faults not listed below refer to the Universal Avionics UNS-1Ew Technical Manual for troubleshooting faults and corrective action information, refer to the troubleshooting excerpts from UNS-1Ew installation manual located in Appendix D of this document Troubleshooting Faults A. FMS INOPERA TlVE (NO POWER} - 1. If either UNS-1Ew FMS is inoperative and it has been determined that no power exists at the FMS connectors, verify the 28VDC FMS circuit breaker is pushed in. 2. If the FMS circuit breaker is pushed in, ensure that the other systems operating off of the same electrical bus are functioning. If the bus is not being powered, refer to the appropriate section of the Learjet Maintenance Manual for aircraft electrical systems troubleshooting information. 3. If other systems operating on the electrical bus are functioning, power down the aircraft, disconnect any external power if applied, and disconnect the main batteries. 4. To access the Pilot's or Copilots circuit breaker panel, follow procedures outlined in the Learjet Model 60 Maintenance Manual. 5. Disconnect the wire from the load side of the FMS circuit breaker. and with the circuit breaker pushed in. check for continuity across the two posts at the back of the circuit breaker with a multimeter. If the meter shows an open, replace the circuit breaker per procedure in the Removal and Installation section of this document. 6. If the circuit breaker meters good, meter from the f MS circuit breaker to the electrical bus. If open replace/repair the connection. 7. If the circuit breaker meters good to the 28VDC Bus, use a multimeter and the Global Aviation Technologies UNS-1 Ew Wiring Diagram WD in Appendix A to meter the wiring from the circuit breaker to the UNS-1Ew FMS connectors. Repair the damaged wiring between the components.

22 For the Col6ns 850 FMS to Universal Av1ontes 1 Ew FMS ICA41 ~ Page 22 of26 B. FMS INOPERATIVE {No Ground/sat the UNS-1Ew)- 1. Use a multimeter and the Global Aviation Technologies Wiring Diagram WD in Appendix A to meter the wiring from the UNS-1Ew FMS CDU to the aircraft ground point. Repair the damaged area. C. FMS ANNUNCIATOR INOPERATIVE - (annunciation displayed on Collins Pro Line 4 displays) 1. If an annunciator is inoperative, swap CDUs to determine if the problem transfers to other side. 2. If the problem does not transfer to other side, refer to Collins Learjet 60 Avionics System Manual PIN A for troubleshooting assistance with Collins Pro Line 4 system. 3. If the problem does transfer from side to side, replace defective CDU and perform Functional Test the FMS per UASC UNS- 1 Ew Flight Management System Installation Manual (Ref. Appendix C). 0. FMS LOS ANNUNCIATORS INOPERATIVE - (Dedicated LOS annunciators) 1. Using WD wiring diagram, verify 28 VDC power and grounds are present at the suspected annunciator. (Pin 7 28 VDC; Pins 6, 8, 9 Gnd) Power has to be verified using the press to test button. 2. If power is not present check continuity between RP1228 and RP760 (Pilot) 2RP1228 and RP761 (Copilot). If open (no continuity) repair or replace faulty wiring. 3. If power is present, and ground power has been verified, replace faulty wiring between RP760 (Pilot) RP761 (Copilot) and faulty annunciator. 4. If the problem still exists replace defective COU and perform Functional Test the FMS per UASC UNS-1Ew Flight Management System Installation Manual (Ref. Appendix C).

23 lnstrucbon for Continued Airworthiness Lea 11et Model 60 Aircraft ICA Page23of26 TlnE PAGE RIGHTS APPLY E. FMS INOPERATIVE (No Satellites Received)- 1. Verify the aircraft is positioned in an area that is capable of receiving a GPS signal. Reposition aircraft if necessary. 2. Turn off aircraft Power and remove the FMS CDU per Section Gain Access to the GPS coaxial connector above the aircraft headliner. 4. Meter the coaxial cable between the GPS antenna and GPS receiver. Check for both shorts and opens in the cable. Also perform a visual inspection of the exposed cable and connectors to check for condition. 5. If the Coaxial cable checks good, reinstall the FMS CDU per Section 9.2. Using an extension cable and a known good compatible GPS antenna, temporarily connect these to the GPS antenna connector in the headliner. Place the temporary GPS antenna outside the aircraft in view of the GPS satellites. 6. Apply power to the aircraft and ensure that the inverters and avionics/radio master switches are selected ON. 7. Turn the FMS ON and allow the UNS-1Ew FMS to acquire the satellites. 8. If The FMS is still unable to receive any GPS data, the most likely cause is a failed UNS-1 Ew FMS component. Contact Universal Avionics to locate a repair facility for the component. 9. If the FMS does acquire a strong GPS signal remove power from the aircraft. Remove the temporary GPS antenna and extender cable and replace the GPS antenna per Section 9.2.

24 F0< the Collins 850 FMS to Universal Aviomcs 1 Ew FMS Rev IR ICA Page24 of REPAIR OF UNS-1 Ew FMS COMPONENTS If a defective FMS component is found and requires repair, return it to the following venders for repair. A UNIVERSAL AVIONICS UNS-1 Ew FMS CDU. NCU, GPS ANTENNA, OR FMS CONFIGURATION MODULE. 1. Contact Universal Avionics for return information and qualified repair facilities at the below address: Universal Avionics Systems Corporation 3260 E. Universal Way Tucson, Arizona USA Tel: (520) or (800) Fax: (520) CONTROL AND OPERATION Control and operation for the UNS-1Ew FMS System is described in the Approved Flight Manual Supplement FMS The FMS undergoes a Self Test (Built-In-Test) during power-up. This test verifies that the FMS Computer is operating properly. The test, as well as the desired results, is listed in the Functional Test Report in Appendix C DIAGRAMS The UNS-1 Ew FMS Wiring diagram is included in Appendix A for troubleshooting reference. Refer to the Global Aviation Technologies design data as stated in Section 6.0 of this report for the appropriate mechanical drawing/report when performing maintenance on the aircraft SPECIAL INSPECTION REQUIREMENTS NIA

25 ICA4104~ Page25 of APPLICATION OF SPECIAL TREATMENTS NIA 16.0 DATA RELATIVE TO STRUCTURAL FASTENERS Refer to Global Aviation Technologies design data as stated in Section 6.0 of this report for the appropriate installation drawings. Torque fasteners in accordance with procedures and torque values shown in Learjet 60 Maintenance Manual SPECIAL TOOLS NIA 18.0 COMMUTER CATEGORY AIRCRAFT NIA 19.0 OVERHAUL PERIOD Components installed per this installation have no mandatory replacement/overhaul schedule. Replace all components "on condition". Refer to Section 11.0 for contact information of FMS component vender information AIRWORTHINESS LIMITATIONS The airworthiness limitations section is FAA Approved and specifies maintenance required under FAR and unless an alternative program has been FAA Approved. There are no airworthiness limitations for the installation of the Dual UNS- 1 Ew FMS system installed in the Learjet Model 60.

26 Fof the Collins 850 FMS to Universal Avionics 1Ew FMS ICA Page26 of REVISION 21.1 REVlSIONS TO ICA BY GLOBAL AVIATION TECHNOLOGIES All revisions to the Instructions for Continued Airworthiness document will be controlled and distributed according to the guidelines established in Global Aviation Technologies' AS9100 Quality System Manual and Procedures ASSISTANCE Global Aviation Technologies will provide assistance and respond to questions addressing the Instructions for Continued Airworthiness for the UNS-1Ew FMS STC. A. Contact information for Global Aviation Technologies. is listed below: GLOBAL AVIATION TECHNOLOGIES 2629WMay Wichita, KS Phone: (316) Fax: (316) IMPLEMENTATION AND RECORD KEEPING For major alterations performed in accordance with FAA Field Approval policy, the owner/operator operating under part 91 is responsible for ensuring that the ICA is made part of the applicable section inspection program for their aircraft. This is accomplished when a maintenance entry is made in the aircraft's maintenance record in accordance with section This entry records the major alteration and identifies the original ICA location (e.g., Block 8 of FAA Fonn 337, dated,) along with a statement that the ICA is now part of the aircraft's inspection/maintenance. After initial airworthiness has been granted, the airplane must be maintained in accordance with the continued airworthiness requirements presented in of this document

27 Av1on1cs 1 Ew FMS ICA Pa,ge A1 t APPENDIX A DIAGRAMS UNS-1Ew FMS WIRING DIAGRAM WD41Q GPS ANTENNA INSTL UNS-1Ew FMS INSTL

28 ICA PageA2 Drawing Number Drawing Title No.Of Pgs W WO - UNS 1 E(W) FMS INSTL LR WR W IRE ROUTING UNS-1 Ew FMS INSTL GPS ANTENNA INSTL UNS-1 Ew FMS INSTL 3

29 ICA Page 81 APPENDIX B INSPECTION FORMS UNS-1 Ew FMS 600 HOUR/12 MONTH INSPECTION UNS-1Ew FMS 18 MONTH INSPECTION UNS-1 Ew FMS 28 DAY NAVIGATION DAT ABASE UPDATE

30 ICA Page 82 Inspection TiUe No.Of Pgs UNS-1 Ew FMS 600 HOUR/12 MONTH INSPECTION 1 UNS-1Ew FMS 18 MONTH INSPECTION 1 UNS-1Ew FMS 28 DAY NAVIGATION DATABASE UPDATE 1

31 . ICA Page BJ UNS-1Ew FMS 600HOUR/12 MONTH INSPECTION CSHT. 1OF1) MODEL SERIAL NO. REGISTRATION NO. INSP. DUE TIME/DATE INSP. START TIME/DATE INSP. FINISH TIME/DATE INSPECTION MECH INSP DATE 1 GPS ANTENNA '- I ~ a. Visually inspect the GPS Antenna from the outside of the aircraft checking for./ Security and condition of the attaching screws.i Condition of the antenna, paying special attention to look for cracks or severe erosion of the antenna. If cracks or erosion of the antenna exist, contact Universal Avionics (ref Instructions For Continued Airworthiness Section 11) to determine if antenna replacement is necessary..i Condition of the sealant around the antenna. It the sealant is missing or if evidence of a pressurization leak is found, remove and reseal the antenna per Section 9.2 of the Instructions For Continued Airworthiness Reoort. 2 COCKPIT a. In the Pedestal, remove the UNS.1Ew Control Display Unlt to the extent necessary to gain visual access to the FMS connectors and FMS wiring harness in this area. b. Inspect the FMS connectors for condition and securitv. Reinstall the UNS-1 Ew Control Display Unit in the panel. Verify that all four (4) 1/4 fasteners engage and lock and that the FMS is secure.

32 ICA Page B4 UNS-1Ew FMS 18 MONTH INSPECTION MODEL INSP. DUE TIME/DATE SERIAL NO. INSP. START TIME/DATE REGISTRATION NO. INSP. FINISH TIME/DATE INSPECTION MECH INSP DATE 1 UNS-1Ew FMS FUNCTIONAL TEST a. Perform a Functional Test the FMS per UASC UNS-1 Ew Flight Management System Installation Manual (Ref. Aooendix C). b. Visually inspect the FMS Display, checking for condition If cracks or deep scratches that Impede reading of display data, or distortion of the text or graphics are found. remove the UNS-1 Ew Control Q15plav Unit/Comouter for reoair/reolacement c. Visually inspect the FMS Keypad checking for condition. If the keys are missing or no longer readable due to wear, abuse, or damage, remove the UNS-1 Ew Control Display Unit/Computer for repa1r/reolacement,., ~~~~ : rt~

33 For the Colhns 850 FMS to Universal Rev lr ICA Page BS UNS-1Ew FMS 28 DAY NAVIGATION DATABASE UPDATE MODEL - INSP. DUE TIME/DATE SERIAL NO. INSP. START TIME/DATE REGISTRATION NO. INSP. FINISH TIME/DATE INSPECTION MECH INSP DATE ", 1 UNS-1 Ew FMS FUNCTIONAL TEST i."t :~ ).;i,. a. Using the appropriately effective Universal Avionics navigation database, Load the navigation database per UNS 1 Ew Installation Manual dated 27 August b Note: Prior to accomplishing this item, apply power to the aircraft and turn the UNS-1 Ew FMS on. Power down aircraft systems. Ensure Nav. database disc is removed from aircraft. Record nav1gabon database information below from newly Installed discs: Database Number: Database Expiration Date:

34 ICA Page C1 APPENDIX C MAINTENANCE, CHECKOUT UNS FMS 1Ew

35 ~ ICM Page C2 Report Number Drawing Title No. Of Pgs UNS FMS 1 Ew Installation Manual (Maintenance, Checkout Procedures) FUNCTIONAL TEST PROCEDURES DUAL FT UNIVERSAL AVIONICS FMS 1 Ew UPGRADE 25 LEARJET MODEL 60 AIRCRAFT - STC 14

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