Elliott Aviation STC ST04272CH is approved for use on ...

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Elliott Aviation Technical Products Development, Inc. Report No.: GTP-3832-560-1 6601 74th Ave Building A Revision: B Milan, IL 61264 Dated 09/28/2018 1 of 18

Ground Test Plan For Garmin ADS-B System Installation

Ground Test Plan

For

Garmin ADS-B Out System Installation

(Type Certificate A22CE)

© 2017 ELLIOTT AVIATION TECHNICAL PRODUCTS DEVELOPMENT, INC.

Elliott Aviation Technical Products Development, Inc. reserves the copyright of all information and illustrations in this publication which is provided in confidence and which may not be used for any purpose other than for which it was originally supplied. The publication may not be reproduced in part or in whole without the consent in writing of Elliott Aviation Technical Products Development, Inc.

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REVISIONS PAGE

Rev Description Page (S) Date Approved By

IR Initial Release ALL 11/15/2017 R. Woolums

A Added Section 3.7 11

07/31/2018 R. Woolums

Added Section 5.3 13

B Revised Section 3.7 11

09/28/18 Revised Section 5.3 13

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TABLE OF CONTENTS

COVER PAGE .......................................................................................................... 1 REVISIONS PAGE.................................................................................................... 2 TABLE OF CONTENTS ............................................................................................ 3 1 General: .............................................................................................................. 4

2 Preparation – Configuration Verification ............................................................. 8

3 ATC # 1 Mode S / Diversity ............................................................................... 10

4 Preparation – ATC # 2 ...................................................................................... 12

5 ATC # 2 Mode S / Diversity ............................................................................... 12

6 ADS-B Annunciators (RS-232 bus and GTX annunciator discrete) ................. 14

7 Preparation – ADS-B Out ATC # 2 ................................................................... 14

8 ATC # 2 ADS-B OUT / GDL 88 GPS / In Air ..................................................... 15

9 Preparation - ADS-B Out ATC # 1 .................................................................... 15

10 ATC # 1 ADS-B OUT / GDL 88 GPS / In Air ..................................................... 15

11 Preparation - UAT FIS-B IN / Bluetooth ............................................................ 16

12 UAT FIS-B IN / Bluetooth in air (If Flight Stream 110 is installed) .................... 16

13 Reversionary Modes ......................................................................................... 17

14 Circuit Breakers ................................................................................................. 17

15 Radio Altimeter .................................................................................................. 17 Test Conclusion ...................................................................................................... 18

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1 General: This Elliott Aviation Ground Test Plan (GTP) is intended for Model 560XL ADS-B Out transponder with FIS-B In installations modified in accordance with Elliott Aviation Master Data List MDL-3832-560.

14.CFR 91.215 Mode S Transponder and 91.227 ADS-B related functions and operations are evaluated.

EMC is evaluated.

14 CFR Part 43: 43.3 requires appropriately rated personnel and 43.9 require maintenance records.

Safe access to the top fuselage antennas is required. Mode S diversity isolation requires antenna blocking.

This GTP does not address RVSM aspects and assumes that the pitot / static system was not opened or modified in any way.

The ADS-B aspects of this test plan may be conducted in a hangar but clear view of the GPS constellation is required. Local airport Lat/Lon information is also required. Use either the Airport Reference Point (ARP) or the coordinates for the control tower.

No EMI/EMC included in this document. Use Repair Station procedures.

Information in (parenthesis) indicates aspect of installed system being evaluated, references to other document steps or variables for aircraft equipage. IFR 6000 Operators manual references are included.

1.1 Testing Prerequisites:

This GTP requires compliance with modifications described in the above Master Data List.

Notable specifics:

The previously installed and approved transponder antennas, coaxes and connectors are unmodified except where specifically indicated.

The GDL-88 to GTX3000 wiring connections must be is as indicated without deviation.

The GTX 3000 transponders and GDL 88 GPS must be configured in accordance with Elliott Aviation Configuration Instructions document CFG-3832-560.

Determine if the aircraft has Dynamic Flight ID. Refert to Honeywell RMU; ATC page.

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1.2 Required Test Equipment:

Equipment Description Comments

Cobham / Aeroflex ATC Tester with Standard accessories. (see manual for complete list)

IFR 6000 Used for Mode S and ADS-B testing. Ensure calibration covers options 2 (TCAS), 3 (ADS-B) and 5 (UAT). Operation Manual Issue 12 2014 or later required.

Apple I PAD or equivalent Blue Tooth PED

With Garmin Pilot or Foreflight app loaded. Used to verify the Flight Stream 110.

1.3 Required Air Traffic Control / Tower Coordination

Contact the local FAA to have a transponder code assigned for the duration of any testing.

1.4 Required Reference Documents

1) Elliott Aviation Configuration Instructions document CFG-3832-560.

2) FAA Advisory Circular AC43-6C dated 07/15/14 (or later revision).

3) Local tower Latitude / Longitude. Digital - Terminal Procedures Publication (d-TPP)/Airport Diagrams: https://www.faa.gov/air_traffic/flight_info/aeronav/digital_products/dtpp/

The GTX 3000 will not function properly until software setup and configuration is accomplished.

The GDL-88 will not function properly until software setup and configuration is accomplished.

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1.5 IFR 6000 setup an position notes:

1) The IFR 6000 installed options can be witnessed by pressing the “SETUP” hard-key repeatedly until the “SETUP-CONFIG INFO” screen appears.

2) Continue pressing the “SETUP” hard-key until “SETUP-GENERAL” appears. Set units to FEET and ERP to dBW.

3) When positioning and setting up the IFR 6000 Test Set, reasonably accurate values are to be used for “ANT RANGE” and “ANT HEIGHT”.

4) These values may be used as a starting point and must be addressed if the IFR 6000 needs to be repositioned. Note: Height is relative to the IFR 6000 ANTENNA, not ground.

NOTE: Do not exceed 50 ft from any ATC antenna when establishing test set position.

Multi-path reflections from other aircraft as well as hangar surfaces may severely impact this testing. Test set

position trial and error may be necessary.

5) The ideal testing condition is outside on the ramp away from other aircraft, vehicles and hangars. The most challenging transponder radio frequency testing environment in inside a closed cluttered hangar.

6) Keeping in mind the depiction above, the IFR 6000 test set may be hand held at different heights above the floor as well as moved along the arc representing the distances configured at set-up.

7) The above range settings are only a starting point for testing and may be changed to accommodate large deviations from the guide values. The IFR 6000 Ops Manual is recommended reading prior to testing.

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1.5.1 IFR 6000 Test Set quick start: The IFR 6000 XPDR – Auto Test runs several tests in sequence. The PASS / FAIL indication is based on the FAA requirements, of which Elementary and Enhanced Surveillance are not required. However, as they are required in Europe, they are included in the testing. The IFR 6000 test screen displays uses an arrow to highlight a failure:

When testing in a cluttered R/F reflective area, a common first-test failure is shown above. Select the “TEST LIST” to scroll through the tests that were run to find the individual test:

The above shows the FIRST page of the test list and an actual capture of Test 5. If the transponder coaxes are high confidence, failure as shown may be the impact of multi-path interference. Note that individual tests typically run until stopped. While running the above example test, move the test set, pause, watch for the error triangle(s) to change or clear. When clear, hold a moment to be sure.

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Item Procedure Pass Fail

2 Preparation – Configuration Verification

2.1 1) Aircraft may be positioned in a hangar or outdoors. 2) Ensure that the aircraft is properly grounded in accordance with AMM

procedures. 3) For the # 1 GTX 3000 Transponder, conduct Elliott Aviation

Configuration Instructions document CFG-3761-560; steps 4 through 4.1, check “NORMAL” box, then select the “Regions” tab to access the software part number and version number.

2.2 Verify # 1 GTX 3000 Transponder Software part number and Version is as indicated in document CFG-3832-560, paragraph 3.0.

2.3 Verify # 1 GTX 3000 Transponder configuration is as indicated in document CFG-3832-560, paragraph 4.4 through 4.6.2.

2.3.1 Select ATC # 1 Active. Verify that the GTX 3000 Install Tool “STATUS” XPDR State – Ident Active box indicates a check when either remote Ident switch is pressed.

2.3.2 Verify that the GTX 3000 Install Tool Diagnostics Tab / DAP Tab / Heading Data pane indicates Mag Heading value referenced to pilot display.

2.4 1) Confirm that the GTX 3000 Install Tool shows Normal and not CONFIG before disconnect.

2) Close Install Tool and disconnect from PC / Laptop. Properly stow cable. 3) For the # 2 GTX 3000 Transponder, conduct Elliott Aviation

Configuration Instructions document CFG-3832-560; steps 4 through 4.1, check “NORMAL” box, then select the “Product Data” tab to access the software part number and version number.

2.5 Verify # 2 GTX 3000 Transponder Software part number and Version is as indicated in document CFG-3832-560, paragraph 3.0.

2.6 Verify # 2 GTX 3000 Transponder configuration is as indicated in document CFG-3832-560, paragraph 4.4 through 4.6.2.

2.6.1 Select ATC # 2 Active Verify that the GTX 3000 Install Tool “STATUS” XPNDR State – Ident Active box indicates a check when either remote Ident switch is pressed.

2.6.2 Verify that the GTX 3000 Install Tool Diagnostics Tab / DAP Tab / Heading Data pane indicates Mag Heading referenced to co-pilot display.

2.7 1) Confirm that the GTX 3000 Install Tool shows Normal and not CONFIG before disconnect.

2) Close Install Tool and disconnect from PC / Laptop. Properly stow cable.

2.8 For the GDL 88 UAT/GPS, conduct Elliott Aviation Configuration Instructions document CFG-3832-560; step 5.1, then step 5.3.1 to gain access to the software part number and version number.

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2.9 Verify GDL 88 UAT/GPS System Software Version and System Software Part Number is as indicated in document CFG-3832-560, paragraph 3.0.

2.10 Verify GDL 88 UAT/GPS configuration is as indicated in document CFG-3832-560 paragraph 5.4 through 5.4.6.

2.11 1) Close Install Tool and disconnect from PC / Laptop. Properly stow cable. 2) Power down the aircraft in accordance with the AMM.

2.12 1) Aircraft may be positioned in a hangar or outdoors. GPS position is required. Be aware of hazards associated with transmitting RF signals inside an enclosed structure.

2) Ensure that the aircraft is properly grounded in accordance with AMM procedures.

3) Apply ground power and power up the avionics in accordance with the AMM.

4) Ensure that “Weight on Wheels”, (WOW) is in the ON GROUND state.

5) On the IFR 6000 Test Set configure the height and range for the ATC antenna per Operators Manual and set DIV TEST = ON. Refer to Section 1.5 of this document for initial height and range values.

6) Obtain the IFR 6000 Test Set antenna cover accessory.

7) Request a transponder code from ATC. ATC should be advised that the aircraft will be “squawking” on this code for the duration of the test. Advise ATC of the planned Flight ID if the aircraft is Flight ID capable. Testing inside a structure may block the aircraft transponder from ATC view but a code should be coordinated in any event.

8) Select ATC #1 Active, ALT, and set the transponder code as assigned by ATC. Set Flight ID to TEST 1 (if aircraft is elementary surveillance capable).

2.13 On the Honeywell RMU; select Test and confirm PASS. 2.14 Select EGPWS / TAWS test. Confirm PASS. 2.15 Using a properly equipped PED, configure for WiFi off and pair with Flight

Stream 110 (If installed). Start “Garmin Pilot” app (preferred) and monitor app for GPS position.

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3 ATC # 1 Mode S / Diversity 3.1 Locate the “ADS-B 1 / 2” Annunciators on the pilot’s instrument panel and press

master annunciator press to test. Verify that all segments illuminate.

3.2 Disable the #2 transponder by pulling the ATC 2 circuit breaker located in the pilots breaker panel.

3.3 Place the aircraft in AIR MODE, weight OFF wheels in accordance with AMM. 3.4 Install ATC antenna cover on BOTTOM ATC antenna.

3.5 IFR 6000 Test Set: XPDR – AUTO TEST screen; Select: CONFIG XPDR – CONFIG screen; Select MODE S CLASS A RETURN XPDR – AUTO TEST screen; Select Antenna: TOP Select: Run TEST: Verify the XPDR – AUTO TEST indicates the test as a PASS and screen fields results are as shown below:

A CODE = as assigned S CODE = as assigned TAIL = Correct N number Flight ID = TEST 1

Note for aircraft that do not have Elementary Surveillance, the Flight ID will match the aircraft N-number (US Aircraft only)

FS = 0, NO ALERT – NO SPI – IN AIR VS = IN AIR C ALT = QFE at QNE (*1, *2) S ALT = QFE at QNE (*1, *3)

Test stops automatically. *1 Air Data Test Set values if connected. *2 +/- 100 ft. *3 +/- 25 ft.

3.6 IFR 6000 Test Set: XPDR – AUTO TEST screen; Test List soft key: PRESS Verify the XPDR –TEST LIST screen fields results:

ELEMENTARY SURV 1 = PASS ELEMENTARY SURV 2 = PASS ENHANCED SURV = PASS

Note – Elementary Surv 2 will indicate FAIL if Flight ID is not enabled on the aircraft.

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3.7 If Enhanced Surveillance option is being installed, perform the following test On EFIS Control Panel set the selected altitude to 3000ft. Select the ENHANCED SURV test soft key. Select Run Test Verify the following parameters

o Verify Selected Altitude is 3000ft +/-50ft o Verify Vertical Rate matches what is displayed on the Pilots

EFIS o Verify Ground Speed is 0 (valid) o Verify Roll Angle matches what is displayed on the Pilots EFIS o Verify Magnetic Heading matches what is displayed on the

Pilots EFIS o Verify Indicated Airspeed matches what is displayed on the

Pilots EFIS

3.8 ANTENNA SHIELD: Remove from BOTTOM Antenna and install on TOP antenna. (Operators Manual app J, fig 2)

3.9 IFR 6000 Test Set: XPDR – AUTO TEST screen; Select: CONFIG XPDR – CONFIG screen; Select MODE S CLASS A RETURN XPDR – AUTO TEST screen; Select Antenna: BOTTOM Select: Run TEST: Verify the XPDR – AUTO TEST indicates the test as a PASS and screen fields results are as shown below:

A CODE = XXXX (ATC assigned) S CODE = XXXX (ATC assigned) TAIL = Correct N number

Test stops automatically.

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4 Preparation – ATC # 2 4.1 1) Maintain "Weight on Wheels", (WOW) in the IN AIR state.

2) On the IFR 6000 Test Set configure the height and range for the ATC antennas and maintain DIV TEST = ON. Refer to Section 1.5 of this document for initial height and range values.

3) Relocate the IFR 6000 Test Set antenna cover accessory the TOP ATC antenna.

4) Select ATC #2 Active, ALT, and set transponder code as assigned by ATC and Flight ID to 2 TEST (if aircraft is elementary surveillance capable).

5) Disable the # 1 transponder by pulling the ATC 1 circuit breaker and enable the #2 transponder by resetting the ATC 2 circuit breaker both are located in pilot circuit breaker panel.

5 ATC # 2 Mode S / Diversity

5.1 IFR 6000 Test Set: XPDR – AUTO TEST screen; Select: CONFIG XPDR – CONFIG screen; Select MODE S CLASS A RETURN XPDR – AUTO TEST screen; Select Antenna: BOTTOM Select: Run TEST: Verify the XPDR – AUTO TEST indicates the test as a PASS and screen fields results are as shown below:

A CODE = as assigned S CODE = as assigned TAIL = Correct N number Flight ID = 2 TEST

Note for aircraft that do not have Elementary Surveillance, the Flight ID will match the aircraft N-number (US Aircraft only)

FS = 0, NO ALERT – NO SPI – IN AIR VS = IN AIR C ALT = QFE at QNE (*1, *2) S ALT = QFE at QNE (*1, *3)


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5.2 IFR 6000 Test Set: XPDR – AUTO TEST screen; Test List soft key: PRESS Verify the XPDR –TEST LIST screen fields results:

ELEMENTARY SURV 1 = PASS ELEMENTARY SURV 2 = PASS ENHANCED SURV = PASS

Note – Elementary Surv 2 will indicate FAIL if Flight ID is not enabled on the aircraft.

5.3

If Enhanced Surveillance option is being installed, perform the following test

On EFIS Control Panel set the selected altitude to 3000ft. Select the ENHANCED SURV test soft key. Select Run Test Verify the following parameters

o Verify Selected Altitude is 3000ft +/-50ft o Verify Vertical Rate matches what is displayed on the Copilots

EFIS o Verify Ground Speed is 0 (valid) o Verify Roll Angle matches what is displayed on the Copilots

EFIS o Verify Magnetic Heading matches what is displayed on the

Copilots EFIS o Verify Indicated Airspeed matches what is displayed on the

Copilots EFIS

5.4 ANTENNA SHIELD: Remove from the TOP antenna and install on BOTTOM antenna.

5.5 IFR 6000 Test Set: XPDR – AUTO TEST screen; Select: CONFIG XPDR – CONFIG screen; Select MODE S CLASS A RETURN XPDR – AUTO TEST screen; Select Antenna: TOP Select: Run TEST: Verify the XPDR – AUTO TEST indicates the test as a PASS and screen fields results are as shown below:

A CODE = as assigned S CODE = as assigned TAIL = Correct N number


5.6 ANTENNA SHIELD: Remove and stow.

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6 ADS-B Annunciators (RS-232 bus and GTX annunciator discrete) 6.1 Ensure both transponders breakers are set. 6.2 Verify that the “ADS-B 1 / 2” Annunciator is not illuminated. 6.3 Select ATC 2 as the active transponder and set to ON 6.4 Disable ADS-B GPS signal source by pulling the GDL 88 circuit breaker and

verify that the “ADS-B 2” Annunciator segments on the instrument panel illuminate in amber.

6.5 Restore ADS-B GPS signal source by resetting the GDL 88 circuit breaker and verify that the "ADS-B 2" annunciator extinguishes within approximately 3 minutes.

6.6 Select ATC 1 as the active transponder and set to ON 6.7 Verify that the “ADS-B 1 / 2” Annunciator is not illuminated.. 6.8 Disable ADS-B GPS signal source by pulling the GDL 88 circuit breaker and

verify that the “ADS-B 1” Annunciator segments on the instrument panel illuminate in amber.

6.9 Restore ADS-B GPS signal source by resetting the GDL 88 circuit breaker and verify that the "ADS-B 1" annunciator extinguishes within approximately 3 minutes.

7 Preparation – ADS-B Out ATC # 2 PASS FAIL 7.1 1) Maintain "Weight on Wheels", (WOW) in the IN AIR state.

2) On the IFR 6000 Test Set maintain the height and range for the ATC antennas and configure DIV TEST = OFF.

3) Ensure IFR 6000 Test Set antenna cover accessory is removed.

4) Select ATC #2 Active, ALT, squawk code as assigned) and Flight ID 2 TEST. Note for aircraft that do not have Elementary Surveillance; the Flight ID will match the aircraft N-number (US Aircraft only).

5) Ensure both ATC circuit breakers are engaged.

7.2 IFR 6000 Test Set: SETUP – ADSB screen; Select and set parameters

POS DECODE: LOCAL LAT / LON: Manual Entry

(obtain from Collins PL4 CDU / GPS pages) BARO PRES ALT: Manual Entry ADSB GEN: DF17 ADSB MON DF17 GICB: DF20

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8 ATC # 2 ADS-B OUT / GDL 88 GPS / In Air 8.1 IFR 6000 Test Set:

ADVISORY CIRCULARS MAIN: Select AC20-165 AIR. ADV CIRC 20-165 AIR screen; select RUN. Verify the ADV CIRC 20-165 AIR test screen indicates the test as a PASS and screen fields results are as shown below:

NIC record: ADV CIRC 20-165 AIR screen; select NEXT PAGE:.

SDA = 2

9 Preparation - ADS-B Out ATC # 1

9.1 Maintain "Weight on Wheels", (WOW) in the IN AIR state.

On the IFR 6000 Test Set configure the height and range for the ATC antennas and maintain DIV TEST = OFF. Refer to section 1.5 of this document for initial height and range values.

Ensure IFR 6000 Test Set antenna cover accessory is removed.

Select ATC # 1 Active, ALT, squawk code as assigned and Flight ID TEST 1. Note for aircraft that do not have Elementary Surveillance, the Flight ID will match the aircraft N-number (US Aircraft only)

Ensure both ATC circuit breakers are engaged.

10 ATC # 1 ADS-B OUT / GDL 88 GPS / In Air PASS FAIL 10.1 IFR 6000 Test Set:

ADVISORY CIRCULARS MAIN: Select AC20-165 AIR. ADV CIRC 20-165 AIR screen; select RUN. Verify the ADV CIRC 20-165 AIR test screen indicates the test as a PASS and screen fields results are as shown below:

NIC record: ADV CIRC 20-165 AIR screen; select NEXT PAGE.

SDA = 2

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11 Preparation - UAT FIS-B IN / Bluetooth in air (UAT & antenna) (If Flight Stream 110 is installed) *Note If aircraft under test is within external UAT signal reception and expected function is witnessed (other than GPS position from the GDL-88), then step 11.1 may be considered passed.*

11.1 1) Maintain "Weight on Wheels", (WOW) in the IN AIR state. 2) IFR 6000 Test Set: Configure for UAT antenna range and height.

Reposition the test set and re-configure values as needed to ensure strong UAT antenna R/F link. 15 to 25 feet should be sufficient.

3) Allow the IFR 6000 time for its GPS to sync to live GPS signal. (Could take up to about 10 minutes.

4) IFR 6000:Adjust date and time to current date and correct UTC/ZULU. 5) IFR 6000: Adjust time-out to 20 minutes.

11.2 PED device: Clear any residual METAR data by navigating to “Settings” / “Pilot App” and selecting “Erase Weather Data”, close “Settings”.

11.3 PED device: Select “Garmin Pilot” app as active; Select “Home”, Select “Map”. On map that appears, navigate to airport desired. (ie KMCI).

11.4 IFR 6000 Test Set: UAT MAIN screen; Select UAT GEN. UAT GEN LIST screen; Select 1. FIS-B UAT FIS-B GEN screen:

GPS: Confirm “GPS SYNC” indicated REPORT:Select “METAR” STN Select local airport ICAO ID (ie:KMCI) RUN TEST Soft Key SELECT.

12 UAT FIS-B IN / Bluetooth in air (If Flight Stream 110 is installed)

12.1 1) Navigate within “Garmin Pilot” map to desired airport and select. From circle that appears, navigate to “weather” info.

2) Within app, monitor METAR data. Due to transmit interval of the FIS-B standard and the refresh rate of the GDL-88 UAT the METAR may take as long as 15 minutes to appear.

3) Upon arrival of the simulated METAR, confirm PED content with that of the IFR 6000 Test Set simulated STN settings.

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13 Reversionary Modes

13.1 Aircraft: Set to weight ON wheels; ON GROUND state.

IFR 6000 test set may stand down at this stage.

Ensure both ATC circuit breakers are still engaged

13.2 Comm # 2 circuit breaker: PULL RMU # 2: Verify OFF (blank screen)

13.3 RMU #1 press the ATC LSK and then press the TEST key. Verify NO FAULTS 13.4 Select ATC # 2 Active, ALT, and set squawk code to 2121. 13.5 Verify 2121 remains active on the #1 RMU 13.6 Comm # 2 circuit breaker: Press (reset)

RMU # 2: Verify ON (normal condition)

13.7 Comm # 1 circuit breakers: PULL RMU # 1: Verify OFF (blank screen)

13.8 RMU #2 press the ATC LSK and then press the TEST key. Verify NO FAULTS 13.9 Select ATC # 1 Active, ALT, and set squawk code to 4343 13.10 Verify 4343 remains active on the #2 RMU 13.11 Comm # 1 circuit breaker: Press (reset)

RMU # 1: Verify ON (normal condition)

14 Circuit Breakers

14.1 GDL 88 circuit breaker: Verify label: ADS-B (over) GPS 14.2 Flight Stream circuit breaker: Verify label: FIS-B (over) BL TH

15 Radio Altimeter

15.1 Perform Radio Altimeter test in accordance with Citation 560 AMM 34-12-02.

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Aircraft “N” number: Serial Number CFR Part 43.3 Test Personnel: Date Location: (ICAO Airport ID and General location) Test equipment make and model Calibration date Aircraft Hobbs Time: Notes:

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Elliott Aviation Technical Products Development, Inc. Report No.: CFG-3832-560 6601 74th Ave Building A Revision: D Milan, IL 61264 Dated: 10/01/2018 1 of 14

Configuration Instruction For Garmin ADS-B System Installation

Configuration Instructions

For





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REVISIONS PAGE



A

Section 3.0 updated GDL 88 software level and corrected wording of note 2 3

01/12/2018 R. Woolums Section 4.5.2 corrected 429 input assignments and antenna loss readings. 8

Section 5.4.1 corrected antenna orientation from right to left 12

B Section 4.5.2 corrected ADC speed to LOW 8 02/27/2018 R. Woolums

C Section 4.5.2 added RX 6 for EFIS, Change RX2 for Off and RX4 to AHRS 8 07/31/2018 R. Woolums

D

Section 3 corrected software p/n typo 5

10/01/2018

Section 4.4.1 Removed AHRS QTY 6

Removed Section 4.6.2 10

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Table of Contents COVER PAGE ............................................................................................................ 1 LOG OF REVISIONS .................................................................................................. 2 TABLE OF CONTENTS .............................................................................................. 3 1 Introduction: ............................................................................................................. 4 2 Preliminary Operations: ........................................................................................... 4

3 Effectivity .................................................................................................................. 5 4 GTX 3000 Configuration .......................................................................................... 5 5 GDL 88 Configuration ............................................................................................ 12 6 Conclusion ............................................................................................................. 14

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1 Introduction: 1.1 Read and understand these instructions prior to beginning these procedures.

1.2 Required equipment:

Serial port equipped PC laptop computer; Win 7 is preferred. HyperTerminal and current familiarity of basic RS232 operations is advised. Quality serial cable not to exceed 15 feet. USB “A” to “B” cable for the GDL 88.

1.3 Garmin supplied “Install Tool” software for access to the GTX 3000 and GDL 88 is required. Details found in paragraph 3.0 of this document.

1.4 GPS activity can be witnessed during these procedures. GPS/WAAS signal access may be beneficial for configuration troubleshooting and testing.

1.5 Qualified personnel familiar with Citation 560 Excel/XLS weight on wheels manipulation, with current PC/laptop configuration software activities and with the Honeywell SPZ 8000 cockpit.

1.6 Have available Garmin Transponder Installation Manual 190-00926-01 rev P for reference.

2 Preliminary Operations: 2.1 Establish PC laptop operations and familiarity with Garmin programming procedures:

2.1.1 Address the PC computer serial port functionality first, a baud rate of 19,200 is proven. Then address the Garmin “Install Tool”. (pgph 3.0) installations. Both the GTX 3000 Install Tool and GDL 88 Install Tool can be extracted and installed on the PC computer and operated without interface to the LRU’s. If either Install Tool ultimately fails to load, try another, newer computer. Due to the high number of variables, Install Tool operation cannot be guaranteed across all operating systems / update status / hardware platform combinations.

Also note that the GTX 3000 Install Tool, when not connected to a LRU, allows some configuration settings manipulation. An off-line configuration CANNOT be compiled for uploading later. However a previously SAVED configuration may be uploaded.

2.1.2 Take the off-line time to become familiar with each Install Tool. The GTX 3000 Install Tool has a lower “STATUS” window with real-time status information. Take particular note of the lower left area: OPERATING MODE; Normal and Config. Ensure that the Config box is checked prior to making configuration changes. Also the Install Tool Info tab opens windows that show real time data from other sources feeding into the GTX 3000.

For the GDL 88 install tool, note there is a Demo Mode available. Similar the GTX 3000 Install Tool, real time data is displayed, simple config changes can be made, etc.

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3 Effectivity GTX 3000 Transponder

L.R.U. P/N (1) Catalog P/N Software P/N Version Install Tool

011-01997-00 010-00736-00 006-B0912-16 3.30 006-a0271-23.zip GDL 88

L.R.U. P/N (1) Catalog P/N Software P/N Version Install Tool

011-02370-00 010-0000860-30 006-B0684-16 3.34 (2) 006-a0248-12.zip (1) Located on L.R.U. data plate. (2) Software P/N 006-B0684-12 Version 3.20 or later is REQUIRED for use with GTX3000 systems. Refer to Service Bulletin 1501 rev A for information on updating software. Later approved software Part Number (P/N), Version and Install Tool may be used only if supported by Garmin Service Bulletin release that specifically includes Garmin GTX3000 transponders.

4 GTX 3000 Configuration Once the aircraft is properly secured, take the following steps:

Confirm that the GTX 3000 transponders and the GDL 88 are properly installed Before applying power to the units, confirm that the antenna coaxes are connected and providing loads to the

transmitters De-energize the GTX 3000 transponders by pulling the associated circuit breakers. Connect the RS 232 config

cable between the GTX 3000 involved and PC. Conduct normal aircraft power turn-on including avionics. On the PC, start the GTX 3000 Install Tool, then apply

power to the GTX 3000 in use. In the very lower left corner “GTX CONNECTED” should be displayed highlighted in green. Confirm that the OPERATING MODE Config box is checked. Configuration can now begin.

4.1 First Configuration (This step is not applicable to subsequent configuration or ICA activities.)

4.1.1 Confirm config module status: Observe Install Tool: STATUS tab; Status OK panel:

4.1.1.1 Confirm that “Info: Config Module Absent” box is UN-checked.

4.1.1.2 Confirm that “Warn: No Config Module Data” box is UN-checked

4.1.2 If the previous step shows a checked box:

4.1.2.1 Install Tool; Regions tab: SELECT.

4.1.2.2 Status pane; Operating Mode. Check Config.

4.1.2.3 Large button “Initialize Configuration Module”: Press. (Resets to factory defaults)

4.1.2.4 Status pane; Operating Mode. Check Normal.

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4.1.3 Confirm Serial interface:

4.1.3.1 Install Tool; Wiring Tab; Serial sub tab: Select.

4.1.3.2 Status Tab; Operating Mode. Check Config.

4.1.3.3 RS232 - #1; Standard Periodic: Enabled

4.1.3.4 STATUS tab; Status OK Section: Confirm that “Err:NVM” is unchecked.

4.1.3.5 Status Tab; Operating Mode. Check Normal.

4.1.3.6 STATUS tab; Status OK Section: Confirm that “Err:NVM” is still unchecked

Note: Periodic checks of the STATUS tab; Status OK Section; Err:NVM, while selected to Status Tab; Operating Mode; Normal mode, is recommended. Always confirm Status Tab; Operating Mode; Config mode is checked PRIOR to making any desired configuration changes.

4.2 GTX 3000 Software Confirmation:

4.2.1 Confirm Software details shown in paragraph 3.0:

4.2.2 Install Tool; Regions tab: SELECT.

4.2.3 Observe: System; Part Number and Version Number. Confirm matches software p/n and version number in paragraph 3.0.

4.2.4 If yes, continue with config. If not, refer to paragraph 3.0 for Garmin Service bulletin information. Config cannot continue until this is rectified.

4.3 If aircraft is not currently configured for Flight ID in the Status Tab input the aircrafts registration number (example N123AB) into the Flight ID section and press enter.

4.4 Aircraft

4.4.1 Set and confirm the following:

Main Tab: Aircraft Sub Tab: none

Aircraft Configuration:

Aircraft Registration: As required IATA Airline Designator As required VFR Code 1200 ICAO Address (hex) Not Configurable when country = United States. Set ICAO Address from Registration country United States.

Press “Set Active” button to save to config module.

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4.5 Wiring:


Main Tab: Wiring Sub Tab: Serial

RS232 - #1: (Used for PC interface)

In Format Not Configurable Out Format Not Configurable Speed 19,200 Standard Periodic Enabled Datalog Periodic Disabled

RS232 - #2: (Used for GDL 88 interface)

In Format Transponder Format 1 Out Format Transponder Format 1 Speed 38,400 Standard Periodic Enabled Datalog Periodic Disabled

RS422: (Not Used)

In Format any Out Format any Speed any Standard Periodic Disabled Datalog Periodic Disabled


Main Tab: Wiring Sub Tab: Installation

Installation Options:

Install ID GTX #1 (or 2 as required) Standby None Squat Switch Low Air Data Select Switch None Altitude Data Select Switch None

Altitude Source:

Primary None Secondary None Supplemental None

Flight ID Sources

Flight ID Entry Unrestricted A429 Mode S Control Panel Options

Altitude/Air Data Select Off


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Main Tab: Wiring Sub Tab: A429

Input:

Channel 1 Speed: High Format: Mode S Control Panel Channel 2 Speed: Low Format: Off Channel 3 Speed: High Format: AHRS Channel 4 Speed: High Format: AHRS Channel 5 Speed: Low Format: ADC Channel 6 Speed: Low Format: EFIS Channel 7 Speed: Low Format: Off Channel 8 Speed: High Format: ARINC 735 TCAS Format 1

Output:

Channel 1 Speed: High Format: Mode S Control Panel Channel 2 Speed: Low Format: Off Channel 3 Speed: Low Format: Off Channel 4 Speed: High Format: ARINC 735 TCAS Format 1


Main Tab: Wiring Sub Tab: Antenna

Cable Specifications:

Top Antenna Loss (dB) 2.50 dB Top Antenna Delay (ns) 50 ns Bottom Antenna Loss (dB) 1.50 dB Bottom Antenna Delay (ns) 25 ns Antenna Switch None

Note: These values are general and may vary depending on model. Refer to Garmin Transponder Installation Manual 190-00926-01 rev P or later approved revision section 2.4 for information on coax cable lengths. Set delays to closest increment.

GPS Antenna Offset:

Position Offset Applied No Lateral Offset From Center (M) 0 Towards Field disappears when 0 entered above. Longitudinal Offset From Nose (M) 2


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Main Tab: Wiring Sub Tab: Discretes

Discrete Inputs:

Gillham Altitude Disabled Ident Unassigned Standby Unassigned Squat Switch J1-17 / J5-40 ADSB 1090 Out Disable Unassigned UAT ADSB Out Disable J1-47 / J5-22 Control Panel Select S0 J2-54 / J5-09 Air Data Select Unassigned Transponder Active J1-46 / J5-32 Altitude Data Select Unassigned

Discrete Outputs:

Fail 1 J1-61 / J5-06 Fail 2 J2-20 / J5-05 Reply Indicator Unassigned ADS-B Fail J1-19 / J5-07 XPDR Active Unassigned Antenna Select Unassigned Altitude Valid Unassigned


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4.6 Airframe:


Main Tab: Airframe Sub Tab: Airframe Configuration

ICAO Model C56X ICAO Aircraft Type Landplane ICAO Engine Type Jet ICAO Wake Medium (15,500lbs - 300,000lbs) Aircraft Length <=25 M Aircraft Width <=23 M Engine Quantity 2 Max Airspeed <=600 knots Aircraft Type A: Small (15,500 – 75,000 lbs)


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Main Tab: Airframe Sub Tab: Operational Options

Enhanced Surveillance Enabled ADS-B Transmit Always Enabled UAT In Disabled 1090 In Disabled Source Integrity Level (3)10˄-7th (AC20-165B; 3.3.3.3) SIL Data Measured Per Hour System Design Assurance (2)Level C (AC20-165B; App A, 3.1.2.1.1 Table A-6) Auto Moding Disabled Gillham Cross-Compare Failure Disabled


4.7 Configuration related aspects of interface settings may be checked:

4.7.1 GTX 3000 unit being configured; Install Tool; Status pane; Operating Mode. Check Normal.

4.7.2 Aircraft cockpit; Honeywell RMU: Confirm NO FAULTS.

4.7.3 Honeywell RMU and Yoke IDENT: Operate ATC functions ON/ALT/STDBY, change Mode “C” code, Select Reversionary Mode: Confirm normal operations.

4.7.4 GTX 3000 Install Tool: Monitor Status pane for correlation of ATC operations listed in previous step. .

4.8 Upon satisfactory configuration:

4.8.1 Confirm that each GTX 3000 units show Normal and not CONFIG before disconnecting.

4.8.2 Install Tool; Regions tab: SELECT

4.8.3 Install Tool; Regions Pane; “View Configuration” button: SELECT.

4.8.4 Close Install Tool and disconnect from PC / Laptop.

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5 GDL 88 Configuration 5.1 Once the aircraft is properly secured, ground power available, take the following steps:

When the GDL 88 is to be configured, pull the GDL 88 circuit breaker, connect using USB the GDL 88 to the PC. Apply power to the GDL 88 then start the GDL 88 install tool.

The USB drivers may take a moment, then the GDL 88 install tool lower left hand corner should indicate GDL 88 CONNECTED highlighted in green. Configuration can now begin. Note that upon making changes to a setting, a pop-up along the bottom of the tool page will appear. This allows either the change to be saved or cancelled.

5.2 Confirm Config module status:

5.2.1 Review Introduction 1.3 and Preliminary Operations 2.2.4 and 2.2.5.

5.2.2 Install Tool; Diagnostics; Faults: Select.

5.2.3 Confirm that Configuration Module Fault is green / inactive.

5.3 Confirm Software status:

5.3.1 Install Tool; Diagnostics; Unit Information: Select

5.3.2 Observe: System Software Version and System Software Part Number matches software p/n and version number in paragraph 3.0.

5.3.3 If yes, continue with config. If not, refer to paragraph 3.0 for Garmin Service bulletin information. Config cannot continue until this is rectified.

5.3.4 When accomplishing GDL 88 software update per the service bulletin, take particular note that the upload must be accomplished twice in order to satisfy the CRC Fault.

5.4 Configuration

(Note that the UAT transmit function is NOT used, however use of accurate data is required)

5.4.1 Antenna:

Top Antenna Not Present Top Antenna Self Test Not Present Bottom Antenna Self Test Enable for self test, disable prior to release. Internal GPS Antenna Lon. Offset 10 (Feet from nose) Internal GPS Antenna Lateral Offset 1 (Feet) Left External GPS/SBAS Source Antenna 0 (Not Applicable)

5.4.2 ARINC 429

Not used, set all to Disabled.

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5.4.3 Aircraft:

Aircraft ICAO Address (Octal) Manual entry. Aircraft Call Sign As required Mode 3/A VFR Code 1200 Aircraft Category Small Aircraft Length 52 feet Aircraft Width 56 Feet Stall Speed 95 Knots ADS-D Transmit Disable FIS-B Processing Enable Internal GPS/SBAS Enable Transponder Interrogation Disable UAT Call Sign ID Logic Enable Equipment Status Annunciators Dual Air/Ground Discrete Not Installed Pressure Alt Broadcast Inhib Switch Not Installed UAT Anonymous Mode Unavailable

5.4.4 Audio

Not used, take defaults.

5.4.5 Ethernet

Not used, set all to Not Present / None.

5.4.6 RS-232/RS-422

RS-232 In Out

Port 1 Disabled Disabled


Port 3 GTX 3000 Format 1 #1 GTX 3000 Format 1 #1


Port 5 GTX 3000 Format 1 #2 GTX 3000 Format 1 #2

RS-422

Port 1 Connext Format 1 Connext Format 1


5.5 Upon satisfactory configuration:

5.5.1 GDL 84/88 Install Tool: Confirm that the GDL 88 has no settings to save by observing the Install Tool lower edge.

5.5.2 Close Install Tool and disconnect from PC / Laptop

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6 Conclusion 6.1 Properly secure all connectors and cables.

6.2 Confirm normal Weight On Wheels status.

6.3 Conduct normal aircraft power down sequence.

6.4 Accomplish maintenance record in accordance with 14 CFR Part 43.9 for both the GTX 3000 transponders as well as the GDL 88 UAT. Be sure to include: Software part number and Version number visually confirmed within the Install Tool applications.

Signature:

Completed date:

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SINGLE WIRE M22759 / 16-XX-9 (XX = WIRE GAUGE)

SINGLE SHIELDED WIRE M27500-XXTG1T14 (XX = WIRE GAUGE)

2-WIRE SHIELDED M27500-XXTG2T14 (XX = WIRE GAUGE)


WIRE SPLICE

DIODE

CIRCUIT BREAKER

CAP & STOW WIRE

XX PARTS LIST PARTS BUBBLE

COAX

AMPS

NAMENAME

(REW) = REMOVE EXISTING WIRE

XXX -XXX X XX N451 -100 A 22 N (EXAMPLE ONLY)

REFERENCE DESIGNATOR

EXISTING

NEW WIRE

SYSTEMWIRE GAUGE

SEGMENT

GROUND

PARALLEL CONNECTIONP.C.

LEGEND:

B

W

O

W

B

SPLICE TO EXISTING SHIELDS

NOTES:

1. REFERENCE THE FOLLOWING GARMIN INTERNATIONAL MANUALS:GTX 3000 TRANSPONDER INSTALLATION MANUAL; 190-00926-01, REV L, OCT 2015GDL 84/88 TSO INSTALLATION MANUAL; 190-01122-00; REV H, DEC 2014.FLIGHT STREAM 110/210 TSO INSTALLATION MANUAL; 190-01700-00; REV E; DEC2015.

2. EXISTING TRANSPONDER MODULE INTERNAL TO THE RCZ IS DISABLED. THEEXISTING SOURCES TO THE TRANSPONDER ARE REWIRED.

3. NOT USED

4. ALL WIRING AND COMPONENT ASSEMBLY, INSTALLATION, ROUTING, SLEEVINGAND SECURING SHALL COMPLY WITH CESSNA CITATION 560XL - CHAPTER 20STANDARD PRACTICES - AIRFRAME

5. ALL TERMINAL AND SPLICE CRIMPING ARE TO BE IN ACCORDANCE WITHVENDOR SPECIFICATIONS AND PROCEDURES.

6. ASTERISK (*) NEXT TO A LETTER INDICATES A LOWER CASE LETTER.

7. IF OPTIONAL FLIGHT STREAM 110 IS NOT INSTALLED CAP AND STOW ALL WIRESINDIVIDUALLY NEAR COPILOTS JEP CHART HOLDER. ADDITIONALLY CAP ANDSTOW CIRCUIT BREAKER WIRE AND DO NOT INSTALL CIRCUIT BREAKER.

8. LABEL MARKER BAND (PARTS LIST ITEM 21) WITH INDELIBLE INK. LABEL SHALLCONTAIN THE CONNECTOR NUMBER AND UNIT OR CONNECTOR IT MATES WITH.

9. INSTALL ENOUGH TAPE TILL THE STRAIN RELIEF CLAMPS ONTO THE TAPE.

10. USE PAGE 8 TO ASSEMBLE CONNECTOR.

11. REFERENCE ECS/CARLISLE DRAWING NUMBER 322402 REV F DATED JUNE 10,2005.

12. SPECIAL RSB WIRING NOTES: IMPORTANT!

* USE 125OHM TWISTED-PAIR SHIELDED CABLE PER NOTE #11

* THE WIRE LENGTH BETWEEN UNITS AND TO THE TERMINATOR (RESISTOR 120+- 10% OHMS ) MUST BE GREATER THAN 23IN (>23IN)

* THE SHIELD CONNECTION AT EACH STUB MUST BE DONE WITH A SPLICETHAT PROVIDES A MAXIMUM SHIELD-TO-SHIELD CONNECTION OF 0.3IN (PG #8RSB WIRING EXAMPLE)

* ALL STUB WIRING SHOULD CONSIST OF WIRE, PER NOTE #11, WITH THEMAXIMUM LENGTH OF THE STUB WIRES 10IN OR LESS. THE UNSHIELDEDSTUB SECTION SHOULD BE TWISTED TOGETHER (PG #8 RSB WIRINGEXAMPLE)

* BUS SHIELDS SHOULD BE KEPT TO MINIMUM LENGTH. PERMISSIBLE TOSUBSTITUTE SHIELDED BRAID WITH 22 AWG WIRE.

* WHEN SPLICING RSB WIRING USE RED SPLICE TO SPLICE THE WIRESTOGETHER AND THE YELLOW ENVIRONMENTAL COVER.

WIRE CODE:

UNSHIELDED STUB WIRE TWISTED TOGETHER

DESCRIPTIONREV DATE APPROVED BY

REVISIONS

IR INITIAL RELEASE 01/08/18 R. WOOLUMS

.0 ± .1.00 ± .03

.000 ± .005

TOLERANCES IN INCHESUNLESS OTHERWISESPECIFIED

PAGE NUMBERDRAWING NUMBERDRAWING DESCRIPTIONA/C MAKE, MODEL

INITIAL RELEASE DATE A/C S/N

SCALEDRAWN BY

CHECKED BY

THIS DRAWING INCLUDING THE DESIGN AND PRINCIPLES OF CONSTRUCTION DISCLOSED IS THE PROPERTY OFELLIOTT AVIATION AND IS SUBMITTED WITH THE UNDERSTANDING THAT IT IS NOT TO BE REPRODUCED NORCOPIED IN WHOLE OR IN PART NOR LOANED OR OTHERWISE COMMUNICATED TO ANY THIRD PARTY NOR USEDIN ANY MANNER DETRIMENTAL TO THE INTEREST OF ELLIOTT AVIATION WITHOUT ITS EXPRESS CONSENT.ACCEPTANCE OF THIS DRAWING WILL BE CONSTRUED AS AN AGREEMENT TO THE ABOVE.

ELLIOTTMOLINE, IL 61266TECH PRODUCTS

SIZE

Bof 8237-3832-E0560-000GARMIN ADS-B OUT SYSTEMELECTRICAL INSTALLATION560-5501 THRU 560-600001/08/18TB

CITATION 560XLRLW1

NTS

A CHANGED GDL 88 COAX CONNECTOR TO 90°CORRECTED VARIOUS TYPOS 01/15/18 R. WOOLUMS

B ADDED NOTE 12 TO CLARIFY RSB WIRING 02/12/18 R. WOOLUMS

C 07/31/18 R. WOOLUMSCORRECTED VARIOUS TYPOS & ADDED EHS

D 12/11/18 R. WOOLUMSCHANGED SHADIN CONV P/N TO 833520-01

1/3/2019 8:53:33 AM

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AutoCAD SHX Text

AVIATION

PARTS LIST

ITEM NO. QTY DESCRIPTION MANUFACTURER PART NUMBER

1 1 ANNUNCIATOR EATON 582-10A0B0C1F4L9N12A (ADS-B 1/2)

2 1 UAT ANTENNA COMANT CI 110-40-30

3 2 GTX 3000 PROCESSOR GARMIN 011-01997-00

4 1 GDL 88 PROCESSOR GARMIN 011-02370-00

5 1 FLIGHT STREAM 110 (OPTIONAL) GARMIN 011-03257-00

6 1 GA 36 GPS ANTENNAGARMIN 013-00244-00

AERO ANTENNA AT575-126G-TNCF-000-RG-27-NM

7 2 SHADIN CONVERTER SHADIN 833520-01

8 31 SPLICE MIL-STD M81824/1-2


10 6 DIODE N/A 1N4001

11 19 SOLDER SLEEVE MIL-STD M835192/2-8

12 2 GTX3000 INSTALLATION KIT GARMIN INTERNATIONAL 011-02019-00

13 A/R SILICONE RUBBER INSULATION TAPE TE CONNECTIVITY 608036-1

14 A/R HEAT SHRINK MIL-SPEC M23053/5-104-9

15 2 GTX 3000 CONFIGURATION MODULE GARMIN INTERNATIONAL 011-00979-20

16 66 SOLDER SLEEVE (NO WIRE) MIL-SPEC M83519/1-4

17 330" 1/16" FLAT BRAID SEA WIRE & CABLE COMPANY AA59569F36T0062

18 26 #8 RING TERMINAL AMP 320554

19 2 9 PIN FEMALE SUB"D" CONNECTOR AMP 205203-1

20 18 SOCKET AMP 205090-1

21 13 MARKER BAND TEXTRON 13171-3

22 1 TNC BULKHEAD ADAPTER KINGS ELECTRONICS KA-91-02

23 A/R COAX N/A RG-142

24 3 COAX BNC PLUG; STRAIGHT; RG-142 (UAT) AMPHENOL RF 031-4427

25 3 BNC TO C ADAPTER PASTERNEK PE9087


27 1 GDL 88 INSTALLATION KIT GARMIN 010-00860-30

28 1 GDL 88 CONFIGURATION MODULE GARMIN 011-00979-03

29 8 COAX TNC PLUG; STRAIGHT; RG-142 TE CONNECTIVITY 5225555-6

30 1 COAX BNC PLUG; RIGHT ANGLE; RG-142 (UAT) TE CONNECTIVITY 5225554-6

31 2 COAX TNC PLUG; RIGHT ANGLE; RG-142 AMPHENOL RF 31-2381

32 1 FLIGHT STREAM 110 INSTALLATION KIT (OPTIONAL) GARMIN 011-03258-00

33 1 CIRCUIT BREAKER 1 AMP KLIXON 7274-67-1

34 1 CIRCUIT BREAKER 1/2 AMP KLIXON 7274-67-1/2


36 8 RESISTOR NTE ELECTRONICS HW112

37 2 25 SUB"D" CONNECTOR FEMALE AMP 5205207-1

38 50 SUB"D" SOCKETS NA M39029/63-368

39 2 44 PIN SUB"D" CONNECTOR FEMALE W/SOCKETS TE CONNECTIVITY 204516-2

40 4 BACKSHELL POSITRONICS D25000GE0

41 5 #4 RING TERMINAL AMP 52273-1

42 A/R DATA BUS WIRE CARLISLE/ECS 32240211DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-E0560-000 8 D21/3/2019 8:53:34 AM

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AutoCAD SHX Text

AVIATION

# 1 TRANSPONDER1J3301GTX3000

-28VDC POWER INPUT-28VDC POWER INPUT-POWER GROUND-POWER GROUND

GROUND 50

1J3302

53

4244-

51GROUND58GROUND

--

37ARINC 429 TX 1 (A)34ARINC 429 TX 1 (B)

32ARINC 429 RX 1 (A)35ARINC 429 RX 1 (B)

-(ADC) ARINC 429 RX 5 (A) 30-(ADC) ARINC 429 RX 5 (B) 31

--

2629

-

(TCAS) ARINC 429 RX 8 H/S (A) 36

-

37-

14

-

15

(#1 AHRS) ARINC 429 RX 3 (A)(#1 AHRS) ARINC 429 RX 3 (B)

(TCAS) ARINC 429 RX 8 H/S (B)

(TCAS) ARINC 429 TX 4 H/S (A)(TCAS) ARINC 429 TX 4 H/S (B)

B

W

B

W

B

W

B

W

B

W

B

W

31 -SUPPRESSION

17 -(GND = GND) WEIGHT ON WHEELS

LEFT NOSE AVIONICS BAY

560-104A22

560-110A22

560-105A22

560-106A22

560-108A22

560-100A20

560-101A20N

560-102A20N

A

FWD B/H

C

CB PANEL DISCPF920

20

HNDC11 GND BLOCK

R

-REMOTE ON 58

B

W

19ADS-B ANNUN -

1112

23

1269

1132 ADS-B

1 2

560-113A22

J560-302

RS-232 #2 RXRS-232 #2 TX

-24-25

RS-232 #2 GND -43O

W

B

560-109A22O

W

B

6J881 GDL88 (PG 5)25

44

47CONFIG DISCRETE INPUT -

B

W

B

W 23

6

-- B

W

B

W

B

W560-114A22

560-115A22-- B

W

40

1J1 #1 SHADIN AMC CONVERTER (PG 6)41

2510

(22AWG)

(22AWG)

560-107ACX

B

W 2848

12 O

W

B

O

W

B 3

560-109B22

560-107BCX

11TYPICAL

J1 #1 SHADIN AMC CONVERTER (PG 6)2560-100B20P.C.

46 -EXTERNAL STBY (GND=STBY)

PI601 #1 RMU 850*KB

PB831 JB831

NOSE CTR WEBPN525 JN525

PN381 NOSE AVIONICS J-BOX6360

PN384 NOSE J-BOX27

1718

1516

147

B

W

B

W

PN819 RMP TCAS 200014J14H

B

W

B

W

14B14A (REF CESSNA W/D 8608138 PG 2)

1231 2J3301 #2 GTX 3000 (PG 4)

42 PN611 #1 NAV UNIT

560-107CCX


N

FWD B/HPB526 JB526

4

PN900 NOSE AVIONICS J-BOX

2012

PG 4 859283242

M

PT

(REF CESSNA W/D 8600202 PG 6)

560-103A22

560-120A22560-121A22

560-119A22560-118A22

560-120B22560-121B22

560-119B22560-118B22

28VDC LEFT HAND

RH CB PANEL

AVIONICS BUS

A

(22AWG)

(22AWG)

(22AWG)

(22AWG)

(22AWG)

(22AWG)

(22AWG)

4849

-B

W560-116A22

(#2 AHRS) ARINC 429 RX 4 (A)(#2 AHRS) ARINC 429 RX 4 (B) B

W

3 8 10

18

-

PN311 AHRS(REF CESSNA W/D 8617119 PG 1)

P.C.

3351 PN330 NOSE CTR WEB


P.C.

- 1GROUND 1- 21POWER 4- 40DATA 3- 60CLOCK 2

CONFIG MODULE

22 -RS-232 #1 RX 323 -RS-232 #1 TX 227 -RS-232 #1 GND 5

O

W

B

O

W

B

LOC: BACKSHELL

560-117A22 CONFIG PORTCOVER AND STOWWHEN NOT IN USE.

PB843A

EXISTING #1 LOWER XPDR ANT

TOP ANTENNA

BOTTOM ANTENNA

(LOC: TIED IN HARNESS BEHIND GTX 3000 CONNECTORS)

15

1XPDR

5

8 TYPICAL

9

12

16 TYPICAL17

18 TYPICAL

19 20

10

29

29

23

23 25 24

29

18

J560-3039

(REF CESSNA W/D 8603113)

PN818 RMP TCAS 2000(REF CESSNA W/D 8608138 PG 2)



LOC: CENTER INSTRUMENT PANEL

PB843BFWD B/H

EXISTING #1 UPPER XPDR ANT




(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

560-113B22

560-123A22B

W 3952 PN367 J2A IC-615

P.C.--

32B

W(EFIS) ARINC 429 RX 6 (A)(EFIS) ARINC 429 RX 6 (B) 33 (REF CESSNA W/D 8612159 PG 2)

DRAWING NUMBER


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AVIATION



GROUND 50

2J3302

53

4244-

51GROUND58GROUND

--




--

2629

-


-

37-

14

-

15




B

W

B

W

B

W

B

W

2XPDR

5

31 -SUPPRESSION


RIGHT NOSE AVIONICS BAY

560-204A22

560-208A22

560-209A22

560-210A22

560-205A22

560-200A20

560-201A20N

560-202A20N

28VDC RIGHT HAND

RH CB PANEL

F

FWD B/H

C

CB PANEL DISCPF921

JNDC21 GND BLOCK

M

-REMOTE ON 58

B

W

19ADS-B ANNUN - 560-207A22

RS-232 #2 RXRS-232 #2 TX

-24-25

RS-232 #2 GND -43O

W

B

560-206A22O

W

B

2J881 GDL88 (PG 5)21

40


AVIONICS BUS

-- B

W

B

W

B

W560-212A22

560-213A22-- B

W

40


2510

(22AWG)

(22AWG)

560-107DCX

560-107ECX

11TYPICAL

J1 #2 SHADIN CONVERTER (PG 7)2560-200B20P.C.


PI602 #2 RMU 850*KE

PB832 JB832



PN384 NOSE J-BOX10

A

B

W

14G14F

B

W

15K15J

B

WPN381 NOSE AVIONICS J-BOX51

70


31 1J3301 #1 GTX 3000 (PG 3)


560-107CCX

560-203A22

PG 3

7

P.C.

4849

-- B

W560-211A22(#2 AHRS) ARINC 429 RX 4 (A)

(#2 AHRS) ARINC 429 RX 4 (B)

(22AWG)

(22AWG)

B


70


P.C.


CONFIG MODULE

22 -RS-232 #1 RX 323 -RS-232 #1 TX 227 -RS-232 #1 GND 5

O

W

B

O

W

B

LOC: BACKSHELL

560-214A22 CONFIG PORTCOVER AND STOWWHEN NOT IN USE.(LOC: TIED IN HARNESS BEHIND GTX 3000 CONNECTORS)

PB844A


TOP ANTENNA

BOTTOM ANTENNA

(22AWG)

(22AWG)

(22AWG)

(22AWG)

(22AWG)

3 8 TYPICAL

9

15

12

16 TYPICAL17

18 TYPICAL

19 20

29

29

23

23 25 24

29

J560-3049

8 10

PN819 RMP TCAS 2000(REF CESSNA W/D 8608138 PG 2)

PB844BFWD B/H








(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

560-223A22B

W 3952 PN367 J2A IC-615

P.C.--

32B

W(EFIS) ARINC 429 RX 6 (A)(EFIS) ARINC 429 RX 6 (B) 33 B

W

B

W45 560-223A22


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AVIATION

64GROUND65POWER62DATA63CLOCK

CONFIG

USB +USB -

USB POWERUSB JACK (PART OF CONNECTOR KIT)

USB GND

62544

O

W

B

RS-232 # 3 TXRS-232 # 3 RX

RS-232 # 3 GND

MODULE

1432

3214

61604241

GPS ANTENNA23

COVER AND STOWWHEN NOT IN USE.

UAT/WAAS RECIEVER

J881GDL88


POWER GROUNDPOWER GROUND

REMOTE ONREMOTE ON

77781718

22140

O

W

B

RS-232 # 5 TXRS-232 # 5 RX

RS-232 # 5 GND

501231

FAN GROUNDFAN SPEED

FAN POWER

RACK FAN

RACK FAN PIGTAIL

BLUETOOTH J301 FLIGHTSTREAM 11016

5 28VDC POWER INPUT15 POWER GROUND

B

W

B

W

13 ARINC 422 TX 1 (A)14 ARINC 422 TX 1 (B)

4 ARINC 422 RX 1 (A)10 ARINC 422 RX 1 (B)

28 VDC POWER IN28 VDC POWER IN

1920

GPSADS-B

1

BL THFIS-B

1/2

B

W

B

W

5776

5675

ARINC 422 TX 1 (A)ARINC 422 TX 1 (B)

ARINC 422 RX 1 (A)ARINC 422 RX 1 (B)

J884

GREENWHITEREDBLACKGRAY

BLACKREDYELLOWWHITE

O

W

B

560-300A22

560-301A22N560-302A22N

560-109B22

560-206A22

560-303A22

560-304A22

242543

2P3301 #2 GTX 3000 (PG 4)

24

UAT ANTENNA

UAT ANTENNA23J882

NDC21 GND BLOCKPN

560-305A22560-306A22N

GPS ANTENNA

33

34

7

BLACKYELLOWRED

123

BLACKYELLOWRED

35

35

8

4

5

6

2

RH CB PANEL

28

P/O 27

27

F

FWD B/H

E

CB PANEL DISCPF921PB525 JB525

G

B

W

B

W

GH

JK

B

W

B

W

O

W

B

242543

1P3301 #1 GTX 3000 (PG 3)192223

NOSE CTR WEBJN305 PN305

O

W

B

O

W

B

28VDC RIGHT HANDAVIONICS BUS

8 TYPICAL

16 TYPICAL17

18 TYPICAL

11TYPICAL 18

31

30

8

8 25

31

8

171832

10 8

8 10

22

LOC: BEHIND COPILOT JEP CHART CABINET

P560-30329 J560-303FWD B/H

29

LOC: BOTTOM AIRCRAFT, NOSE

LOC: UPPER FUSELAGE


23

560-109A22

560-300B22

560-303B22

560-304B22

560-300C22

560-305B22

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AVIATION

#1 SHADIN CONVERTER1J1#1 RSB CONVERTER

228VDC POWER INPUT

1POWER GROUND

25#1 GTX 3000 429 TX (A)10#1 GTX 3000 429 TX (B)

B

W

B

W

B

W

B

W

B

W

B

W560-402A24

37CHASSIS GROUND

21#1 PRIM RCZ (P)8#1 PRIM RCZ (N)

B

W560-403A24

B

W

1728VDC POWER INPUT

16POWER GROUND

40#1 GTX 3000 429 RX (A)41#1 GTX 3000 429 RX (B)

#1 RCZPN521 COM UNIT

RSB PRIMARY (P)11 RSB PRIMARY (N)B

W

B

W

B

W

B

W

25#1 PRIM RSB P12#1 PRIM RSB N

B

W560-403B24

B

WX

XX

XX

10

XX

XX

XX

X

XXXXXXXXXXXX

XXXXXXXXXXXXX

7

B

W

B

W 36B

W

B

W36

37 38 40

39 408

560-402B24 560-402C24

42

42

42

42


12 12

12

12

12

12

12

1J2

12

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

XX

XX

X

XX

XX

XX

X

XXXXXXXXXXXX

XXXXXXXXXXXXX

B

W

B

W 36B

W

B

W36

42

42

42

42

12 12

12

12

12

12

12

12

17#1 SEC RSB (P)4#1 SEC RSB (N)

14#1 SEC RCZ (P)1#1 SEC RCZ (N) 560-404A24

560-405A24

RSB SECONDARY (P)61 RSB SECONDARY (N)

560-405B24

74

560-404B24 560-404C24

16 TYPICAL41

8 TYPICAL

P.C.1J3302 #1 GTX3000 (PG 3)5560-100B20

560-400A20N

NDC11 GND BLOCKM

J

560-401A22N

560-406A16


1J3301 #1 GTX3000 (PG 3)

3235

560-114A22

560-115A22

3734

71(8615173 PG 1) PN612 #1 RNZ 81

1(86151173 PG 1) PN523 RESISTOR MODULE 34

88(8615173 PG 2) PN611 #1 RNZ 102

53(8615173 PG 2) PN369 #1 IC-600 54

P.C.PB526 FWD B/HW


26

17

23SDI #1

10

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AVIATION


228VDC POWER INPUTP.C.

2J3302 #2 GTX3000 (PG 4)5

1POWER GROUND

2J3301 #2 GTX3000 (PG 4)

25#2 GTX 3000 429 TX (A)10#2 GTX 3000 429 TX (B)

B

W

B

W 3235

B

W

B

W

B

W

B

W

560-200B20

560-502A24

560-500A20N

560-212A22

560-213A22

37CHASSIS GROUND


B

W560-503A24

B

W

NDC21 GND BLOCKR

P1728VDC POWER INPUT

16POWER GROUND 560-501A22N

40#2 GTX 3000 429 RX (A)41#2 GTX 3000 429 RX (B)

3734



W

B

W

B

W

B

W

19(8615173 PG 1) PN368 #2 IC-600 20


B

W560-503B24

B

W

XX

XX

X

10

XX

XX

XX

X

XXXXXXXXXXXX

XXXXXXXXXXXXX

71(8615173 PG 1) PN623 #2 RNZ 81

7

B

W

B

W 36B

W

B

W36

37 38 40

39 408

560-506A16P.C.

PB525 FWD B/HW(REF CESSNA W/D 8601177 PG 1)

560-502B24 560-502C24

42

42

42

42



12 12

12

12

12

12

12

2J2

12

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

XX

XX

X

XX

XX

XX

X

XXXXXXXXXXXX

XXXXXXXXXXXXX

B

W

B

W 36B

W

B

W36

42

42

42

42

12 12

12

12

12

12

12

12



560-505A24


560-505B24

7453(8615173 PG 2) PN370 #2 IC-600 54

88(8615173 PG 2) PN622 #2 RNZ 102

560-504B24 560-504C24

8 TYPICAL26

16 TYPICAL4117

10

DRAWING NUMBER


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AVIATION

14

16

17

13

18

GARMIN D-SUB CONNECTOR ASSEMBLY (TYPICAL)

9

ALL OTHER CONNECTOR PARTS ARE PART OF APPLICABLE INSTALLATION KIT

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AVIATION

SINGLE WIRE M22759 / 16-XX-9 (XX = WIRE GAUGE)

SINGLE SHIELDED WIRE M27500-XXTG1T14 (XX = WIRE GAUGE)



WIRE SPLICE

DIODE

CIRCUIT BREAKER

CAP & STOW WIRE

XX PARTS LIST PARTS BUBBLE

COAX

B.O.M. PARTS CALL OUTXX

AMPS

NAMENAME

(REW) = REMOVE EXISTING WIRE

XXX -XXX X XX N451 -100 A 22 N (EXAMPLE ONLY)

REFERENCE DESIGNATOR

EXISTING

NEW WIRE

SYSTEMWIRE GAUGE

SEGMENT

GROUND

PARALLEL CONNECTIONP.C.

WIRE CODE:

LEGEND:

B

W

O

W

B

SPLICE TO EXISTING SHIELDS

UNSHIELDED STUB WIRE TWISTED TOGETHER

NOTES:

1. REFERENCE THE FOLLOWING GARMIN INTERNATIONAL MANUALS:GTX 3000 TRANSPONDER INSTALLATION MANUAL; 190-00926-01, REV L, OCT 2015GDL 84/88 TSO INSTALLATION MANUAL; 190-01122-00; REV H, DEC 2014.FLIGHT STREAM 110/210 TSO INSTALLATION MANUAL; 190-01700-00; REV E; DEC2015.

2. EXISTING TRANSPONDER MODULE INTERNAL TO THE RCZ IS DISABLED. THEEXISTING SOURCES TO THE TRANSPONDER ARE REWIRED.

3. NOT USED

4. ALL WIRING AND COMPONENT ASSEMBLY, INSTALLATION, ROUTING, SLEEVINGAND SECURING SHALL COMPLY WITH CESSNA CITATION 560XL - CHAPTER 20STANDARD PRACTICES - AIRFRAME

5. ALL TERMINAL AND SPLICE CRIMPING ARE TO BE IN ACCORDANCE WITHVENDOR SPECIFICATIONS AND PROCEDURES.

6. ASTERISK (*) NEXT TO A LETTER INDICATES A LOWER CASE LETTER.

7. IF OPTIONAL FLIGHT STREAM 110 IS NOT INSTALLED CAP AND STOW ALL WIRESINDIVIDUALLY NEAR COPILOTS JEP CHART HOLDER. ADDITIONALLY CAP ANDSTOW CIRCUIT BREAKER WIRE AND DO NOT INSTALL CIRCUIT BREAKER.

8. LABEL MARKER BAND (PARTS LIST ITEM 21) WITH INDELIBLE INK. LABEL SHALLCONTAIN THE CONNECTOR NUMBER AND UNIT OR CONNECTOR IT MATES WITH.

9. INSTALL ENOUGH TAPE TILL THE STRAIN RELIEF CLAMPS ONTO THE TAPE.

10. USE PAGE 8 TO ASSEMBLE CONNECTOR.

11. REFERENCE ECS/CARLISLE DRAWING NUMBER 322402 REV F DATED JUNE 10,2005.

12. SPECIAL RSB WIRING NOTES: IMPORTANT!

* USE 125OHM TWISTED-PAIR SHIELDED CABLE PER NOTE #11

* THE WIRE LENGTH BETWEEN UNITS AND TO THE TERMINATOR (RESISTOR 120+- 10% OHMS ) MUST BE GREATER THAN 23IN (>23IN)

* THE SHIELD CONNECTION AT EACH STUB MUST BE DONE WITH A SPLICETHAT PROVIDES A MAXIMUM SHIELD-TO-SHIELD CONNECTION OF 0.3IN (PG #8RSB WIRING EXAMPLE)

* ALL STUB WIRING SHOULD CONSIST OF WIRE, PER NOTE #11, WITH THEMAXIMUM LENGTH OF THE STUB WIRES 10IN OR LESS. THE UNSHIELDEDSTUB SECTION SHOULD BE TWISTED TOGETHER (PG #8 RSB WIRINGEXAMPLE)

* BUS SHIELDS SHOULD BE KEPT TO MINIMUM LENGTH. PERMISSIBLE TOSUBSTITUTE SHIELDED BRAID WITH 22 AWG WIRE.

* WHEN SPLICING RSB WIRING USE RED SPLICE TO SPLICE THE WIRESTOGETHER AND THE YELLOW ENVIRONMENTAL COVER.

13. EXISTING SOURCES AND INTERFACE TO TRANSPONDER UNCHANGED. FULLDETAILS OMITTED FOR CLARITY. REFERENCE AIRCRAFT WIRING DIAGRAMMANUAL FOR COMPLETE DETAILS.


REVISIONS

IR INITIAL RELEASE 07/31/18 R. WOOLUMS

A CORRECTED TYPOS AND FEEDTHU PINOUTS 06/26/18 R. WOOLUMS

B CHANGED SHADIN CONV P/N TO 833520-01 12/11/18 R. WOOLUMS

.0 ± .1.00 ± .03

.000 ± .005




SCALEDRAWN BY

CHECKED BY

THIS DRAWING INCLUDING THE DESIGN AND PRINCIPLES OF CONSTRUCTION DISCLOSED IS THE PROPERTY OFELLIOTT AVIATION AND IS SUBMITTED WITH THE UNDERSTANDING THAT IT IS NOT TO BE REPRODUCED NORCOPIED IN WHOLE OR IN PART NOR LOANED OR OTHERWISE COMMUNICATED TO ANY THIRD PARTY NOR USEDIN ANY MANNER DETRIMENTAL TO THE INTEREST OF ELLIOTT AVIATION WITHOUT ITS EXPRESS CONSENT.ACCEPTANCE OF THIS DRAWING WILL BE CONSTRUED AS AN AGREEMENT TO THE ABOVE.


SIZE

Bof 8237-4071-E0560-000GARMIN GTX 3000 SYSTEMELECTRICAL INSTALLATION560-5001 THRU 560-550007/31/18TB

CITATION 560XLRLW1

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AVIATION

PARTS LIST

ITEM NO. QTY DESCRIPTION MANUFACTURER PART NUMBER

1 1 ANNUNCIATOR EATON 582-10A0B0C1F4L9N12A (ADS-B 1/2)

2 1 UAT ANTENNA COMANT CI 110-40-30

3 2 GTX 3000 PROCESSOR GARMIN 011-01997-00

4 1 GDL 88 PROCESSOR GARMIN 011-02370-00

5 1 FLIGHT STREAM 110 (OPTIONAL) GARMIN 011-03257-00

6 1 GA 36 GPS ANTENNAGARMIN 013-00244-00

AERO ANTENNA AT575-126G-TNCF-000-RG-27-NM

7 2 SHADIN CONVERTER SHADIN 833520-01



10 6 DIODE N/A 1N4001

11 59 SOLDER SLEEVE MIL-STD M835192/2-8

12 2 GTX3000 INSTALLATION KIT GARMIN INTERNATIONAL 011-02019-00

13 A/R SILICONE RUBBER INSULATION TAPE TE CONNECTIVITY 608036-1

14 A/R HEAT SHRINK MIL-SPEC M23053/5-104-9

15 2 GTX 3000 CONFIGURATION MODULE GARMIN INTERNATIONAL 011-00979-20

16 26 SOLDER SLEEVE (NO WIRE) MIL-SPEC M83519/1-4

17 130" 1/16" FLAT BRAID SEA WIRE & CABLE COMPANY AA59569F36T0062


19 2 9 PIN FEMALE SUB"D" CONNECTOR AMP 205203-1

20 18 SOCKET AMP 205090-1

21 13 MARKER BAND TEXTRON 131741-3

22 1 TNC BULKHEAD ADAPTER KINGS ELECTRONICS KA-91-02

23 A/R COAX N/A RG-142


25 3 BNC TO C ADAPTER PASTERNEK PE9087

26 - NOT USED - -

27 1 GDL 88 INSTALLATION KIT GARMIN 010-00860-30

28 1 GDL 88 CONFIGURATION MODULE GARMIN 011-00979-03

29 9 COAX TNC PLUG; STRAIGHT; RG-142 TE CONNECTIVITY 5225555-6


31 1 COAX TNC PLUG; RIGHT ANGLE; RG-142 AMPHENOL RF 31-2381

32 1 FLIGHT STREAM 110 INSTALLATION KIT (OPTIONAL) GARMIN 011-03258-00

33 1 CIRCUIT BREAKER 1 AMP KLIXON 7277-2-1

34 1 CIRCUIT BREAKER 1/2 AMP KLIXON 7277-2-1/2


36 8 RESISTOR NTE ELECTRONICS HW112

37 2 25 SUB"D" CONNECTOR FEMALE AMP 5205207-1

38 50 SUB"D" SOCKETS NA M39029/63-368

39 2 44 PIN SUB"D" CONNECTOR FEMALE W/SOCKETS TE CONNECTIVITY 204516-2

40 4 BACKSHELL POSITRONICS D25000GEO

41 5 #4 RING TERMINAL AMP 52273-1

42 A/R DATA BUS WIRE CARLISLE/ECS 32240211DRAWING NUMBER


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AVIATION



GROUND 50

1J3302

53

4244-

51GROUND58GROUND

--




--

2629

-


-

37-

14

-

15




B

W

B

W

B

W

B

W

B

W

B

W

31 -SUPPRESSION



560-104A22

560-110A22

560-105A22

560-106A22

560-108A22

560-100A20

560-101A20N

560-102A20N

A

FWD B/H

C

CB PANEL DISCPF908

20

MNDC11 GND BLOCK

R

-REMOTE ON 58

B

W

19ADS-B ANNUN -

1112

23

1269

1132 ADS-B

1 2

560-113A22

J560-302

RS-232 #2 RXRS-232 #2 TX

-24-25

RS-232 #2 GND -43O

W

B

560-109A22O

W

B

6J881 GDL88 (PG 5)25

44


B

W

B

W 23

6

-- B

W

B

W

B

W560-114A22

560-115A22-- B

W

40


2510

(22AWG)

(22AWG)

560-107ACX

B

W 2848

560-109B22

560-107BCX

11TYPICAL

J1 #1 SHADIN AMC CONVERTER (PG 6)2560-100B20P.C.


PI627 #1 RMU 850*KB

PB829 JB829



PN384 NOSE J-BOX27

1718

1516

147

B

W

B

W

PT809 LBP CAS 678180

B

W

B

W

6867

1331 2J3301 #2 GTX 3000 (PG 4)560-107CCX

M

FWD B/HPB512 JB512

PN900 NOSE AVIONICS J-BOX

2012

PG 4 1359333242

L

NP

560-103A22

560-120A22560-121A22

560-119A22560-118A22

560-120B22560-121B22

560-119B22560-118B22

28VDC LEFT HAND

RH CB PANEL

AVIONICS BUS

A

(22AWG)

(22AWG)

(22AWG)

(22AWG)

(22AWG)

(22AWG)

(22AWG)

4849

-B

W560-116A22

(#2 AHRS) ARINC 429 RX 4 (A)(#2 AHRS) ARINC 429 RX 4 (B) B

W

3 8 10

18

-

PN311 AHRS

P.C.

7051 PN382 J-BOX

P.C.


CONFIG MODULE

22 -RS-232 #1 RX 323 -RS-232 #1 TX 227 -RS-232 #1 GND 5

O

W

B

O

W

B

LOC: BACKSHELL

560-117A22 CONFIG PORTCOVER AND STOWWHEN NOT IN USE.

PB1004A


TOP ANTENNA

BOTTOM ANTENNA

(LOC: TIED IN HARNESS BEHIND GTX 3000 CONNECTORS)

15

1XPDR

5

8 TYPICAL

9

12

16 TYPICAL17

18 TYPICAL

19 20

10

29

29

23

23 25 24

29

18

J560-3039

PT808 RBP CAS 67

LOC: CENTER INSTRUMENT PANEL

PB1004BFWD B/H


BLKREDYELLOWWHITE

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

13

45 B

W

13


O

W

B

O

W

B

192021

22

B

W

(REW)

(REW)

560-116B22

560-123A22B

W 3952 PN367 J2A IC-600

P.C.--

32B

W(EFIS) ARINC 429 RX 6 (A)(EFIS) ARINC 429 RX 6 (B) 33

560-113B22












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AVIATION



GROUND 50

2J3302

53

4244-

51GROUND58GROUND

--




--

2629

-


-

37-

14

-

15




B

W

B

W

B

W

B

W

2XPDR

5

31 -SUPPRESSION



560-204A22

560-208A22

560-209A22

560-210A22

560-205A22

560-200A20

560-201A20N

560-202A20N

28VDC RIGHT HAND

RH CB PANEL

F

FWD B/H

C

CB PANEL DISCPF909

RNDC20 GND BLOCK

P

-REMOTE ON 58

B

W

19ADS-B ANNUN - 560-207A22

RS-232 #2 RXRS-232 #2 TX

-24-25

RS-232 #2 GND -43O

W

B

560-214B22O

W

B

2J881 GDL88 (PG 5)21

40


AVIONICS BUS

-- B

W

B

W

B

W560-212A22

560-213A22-- B

W

40


2510

(22AWG)

(22AWG)

560-107DCX

560-107ECX

11TYPICAL

J1 #2 SHADIN CONVERTER (PG 7)2560-200B20P.C.


PI628 #2 RMU 850*KE

PB830 JB830



PN384 NOSE J-BOX10

A

B

W

8382

B

W

5654

B


70

31 1J3301 #1 GTX 3000 (PG 3)


560-107CCX

560-203A22

PG 3

7

P.C.

4849

-- B

W560-211A22(#2 AHRS) ARINC 429 RX 4 (A)

(#2 AHRS) ARINC 429 RX 4 (B)

(22AWG)

(22AWG)

B


70P.C.


CONFIG MODULE

22 -RS-232 #1 RX 323 -RS-232 #1 TX 227 -RS-232 #1 GND 5

O

W

B

O

W

B

LOC: BACKSHELL

560-214A22 CONFIG PORTCOVER AND STOWWHEN NOT IN USE.(LOC: TIED IN HARNESS BEHIND GTX 3000 CONNECTORS)

PB1014A


TOP ANTENNA

BOTTOM ANTENNA

(22AWG)

(22AWG)

(22AWG)

(22AWG)

(22AWG)

3 8 TYPICAL

9

15

12

16 TYPICAL17

18 TYPICAL

19 20

29

29

23

23 25 24

29

J560-3049

8 10

PN809 LBP CAS 67

PB1014BFWD B/H


BLKREDYELLOWWHITE

(REW)

(REW)

(REW)

(REW)

B

W

B

W

FWD PRESS BHDPB822 JB822

B

W

B

W

1415

1213

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

(REW)

13








560-223A22B

W 3952 PN367 J2A IC-600

P.C.--

32B

W(EFIS) ARINC 429 RX 6 (A)(EFIS) ARINC 429 RX 6 (B) 33 B

W

B

W2223 560-223A22



11TYPICALNOSE CTR WEB

PN505 JN505

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AVIATION

64GROUND65POWER62DATA63CLOCK

CONFIG

USB +USB -

USB POWERUSB JACK (PART OF CONNECTOR KIT)

USB GND

62544

O

W

B

RS-232 # 3 TXRS-232 # 3 RX

RS-232 # 3 GND

MODULE

1432

3214

61604241

GPS ANTENNA23

COVER AND STOWWHEN NOT IN USE.

UAT/WAAS RECIEVER

J881GDL88


POWER GROUNDPOWER GROUND

REMOTE ONREMOTE ON

77781718

22140

O

W

B

RS-232 # 5 TXRS-232 # 5 RX

RS-232 # 5 GND

501231

FAN GROUNDFAN SPEED

FAN POWER

RACK FAN

RACK FAN PIGTAIL

BLUETOOTH J301 FLIGHTSTREAM 11016

5 28VDC POWER INPUT15 POWER GROUND

B

W

B

W

13 ARINC 422 TX 1 (A)14 ARINC 422 TX 1 (B)

4 ARINC 422 RX 1 (A)10 ARINC 422 RX 1 (B)

28 VDC POWER IN28 VDC POWER IN

1920

GPSADS-B

1

BL THFIS-B

1/2

B

W

B

W

5776

5675

ARINC 422 TX 1 (A)ARINC 422 TX 1 (B)

ARINC 422 RX 1 (A)ARINC 422 RX 1 (B)

J884

GREENWHITEREDBLACKGRAY

BLACKREDYELLOWWHITE

O

W

B

560-300A22

560-301A22N560-302A22N

560-109B22

560-214B22

560-303A22

560-304A22

242543

2P3301 #2 GTX 3000 (PG 4)

24

UAT ANTENNA

UAT ANTENNA23J882

NDC21 GND BLOCKNM

560-305A22560-306A22N

GPS ANTENNA

33

34

7

BLACKYELLOWRED

123

BLACKYELLOWRED

35

35

8

4

5

6

2

RH CB PANEL

28

P/O 27

27

F

FWD B/H

H

CB PANEL DISCPF909PB512 JB512

L

B

W

B

W

GH

JK

B

W

B

W

O

W

B

242543

1P3301 #1 GTX 3000 (PG 3)192021

NOSE CTR WEBJN505 PN505

O

W

B

O

W

B

28VDC RIGHT HANDAVIONICS BUS

8 TYPICAL

16 TYPICAL17

18 TYPICAL

11TYPICAL 18

29

30

8

8 25

31

8

171832

10 8

8 10

22

LOC: BEHIND COPILOT JEP CHART CABINET

P560-30329 J560-303FWD B/H 29

LOC: BOTTOM AIRCRAFT, NOSE

LOC: UPPER FUSELAGE

560-109A22

560-300B22

560-303B22

560-304B22

560-300C22

560-305B22(REF CESSNA W/D 8618103)

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AVIATION


228VDC POWER INPUT

1POWER GROUND

25#1 GTX 3000 429 TX (A)10#1 GTX 3000 429 TX (B)

B

W

B

W

B

W

B

W

B

W

B

W560-402A24

37CHASSIS GROUND


B

W560-403A24

B

W

1728VDC POWER INPUT

16POWER GROUND

40#1 GTX 3000 429 RX (A)41#1 GTX 3000 429 RX (B)



W

B

W

B

W

B

W


B

W560-403B24

B

W

XX

XX

X

10

XX

XX

XX

X

XXXXXXXXXXXX

XXXXXXXXXXXXX

7

B

W

B

W 36B

W

B

W36

37 38 40

39 408

560-402B24 560-402C24

42

42

42

42


12 12

12

12

12

12

12

1J2

12

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

XX

XX

X

XX

XX

XX

X

XXXXXXXXXXXX

XXXXXXXXXXXXX

B

W

B

W 36B

W

B

W36

42

42

42

42

12 12

12

12

12

12

12

#1 SEC RSB (N)

1

560-405B24

RSB SECONDARY (N)

12

8

41

1J3302 #1 GTX3000 (PG 3)560-100B20

560-400A20N

17#1 SEC RSB (P)

14

4

#1 SEC RCZ (N)#1 SEC RCZ (P)

RSB SECONDARY (P)

560-404A24

560-405A24

560-401A22N

61

11

74

560-404B24 560-404C24

TYPICAL

560-114A22

TYPICAL

P.C.5

34

71

NDC11 GND BLOCKP

PN612 #1 RNZ

J

560-406A16

81

34

321J3301 #1 GTX3000 (PG 3)

35560-115A22

37

102 PN611 #1 RNZ

5354

1

88

P.C.

PN523 RESISTOR MODULE

W

PN369 #1 IC-600

PB515 FWD B/H (28VDC COM 1)

23SDI #1

10







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AVIATION


228VDC POWER INPUTP.C.

2J3302 #2 GTX3000 (PG 4)5

1POWER GROUND

2J3301 #2 GTX3000 (PG 4)25#2 GTX 3000 429 TX (A)10#2 GTX 3000 429 TX (B)

B

W

B

W 3235

B

W

B

W

B

W

B

W

560-200B20

560-502A24

560-500A20N

560-212A22

560-213A22

37CHASSIS GROUND


B

W560-503A24

B

W

NDC20 GND BLOCKN

M1728VDC POWER INPUT

16POWER GROUND 560-501A22N

40#2 GTX 3000 429 RX (A)41#2 GTX 3000 429 RX (B)

3734



W

B

W

B

W

B

W

19PN368 #2 IC-600 20


B

W560-503B24

B

W

XX

XX

X

10

XX

XX

XX

X

XXXXXXXXXXXX

XXXXXXXXXXXXX

71PN623 #2 RNZ 81

7

B

W

B

W 36B

W

B

W36

37 38 40

39 408

560-506A16P.C.

PB512 FWD B/H (28VDC COM 2)W(REF CESSNA W/D 8601103)

560-502B24 560-502C24

42

42

42

42


12 12

12

12

12

12

12

2J2

12

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

B

W

XX

XX

X

XX

XX

XX

X

XXXXXXXXXXXX

XXXXXXXXXXXXX

B

W

B

W 36B

W

B

W36

42

42

42

42

12 12

12

12

12

12

12

12



560-505A24


560-505B24

7453PN370 #2 IC-600 54

88PN622 #2 RNZ 102

560-504B24 560-504C24

11 TYPICAL41

8 TYPICAL

10






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AVIATION

14

16

17

13

18

GARMIN D-SUB CONNECTOR ASSEMBLY (TYPICAL)

9

ALL OTHER CONNECTOR PARTS ARE PART OF APPLICABLE INSTALLATION KIT

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AVIATION


REVISIONS

IR INITIAL RELEASE 08/17/17 S. MCCORD

A UPDATED AIRCRAFT SKIN LAYUP 01/19/18 S. MCCORD

B ADDED OPTION FOR GPS ON RH OR LH 05/08/18 S. MCCORD

.0 ± .1.00 ± .03

.000 ± .005




SCALEDRAWN BY

CHECKED BY

THIS DRAWING INCLUDING THE DESIGN AND PRINCIPLES OF CONSTRUCTION DISCLOSED IS THE PROPERTYOF ELLIOTT AVIATION AND IS SUBMITTED WITH THE UNDERSTANDING THAT IT IS NOT TO BE REPRODUCEDNOR COPIED IN WHOLE OR IN PART NOR LOANED OR OTHERWISE COMMUNICATED TO ANY THIRD PARTY NORUSED IN ANY MANNER DETRIMENTAL TO THE INTEREST OF ELLIOTT AVIATION WITHOUT ITS EXPRESSCONSENT. ACCEPTANCE OF THIS DRAWING WILL BE CONSTRUED AS AN AGREEMENT TO THE ABOVE.


SIZE

Bof 3237-3832-M0560-010ANTENNAINSTALLATIONSN/A08/17/17GS

CESSNA 560XLSM1

NTS

FWD

UP

-501 P/N DESCRIPTION SIZE / WT SPECIFICATION ITEM

PARTS LISTQTY

. 1234567891011121314

. .. .... .

.. .

.#10 NUTPLATE MIL-STD

.. .

.UAT ANTENNA INSTL .

..

.RIVET

.RIVET

.#10-32 FH SCREW MIL-STD


.UAT ANTENNA DOUBLER ELLIOTT AVIATION

.GPS ANTENNA DOUBLER ELLIOTT AVIATION

..

NOT USED.

NAS1473A34

NOT USED.

-503.

..NAS1097AD4-425MS20426AD3-38MS24694S-574

MS24694S-51.

.121-3761-M0560-010-511

-501 GPS ANTENNA INSTL .

MIL-STDMIL-STD

.

237-3832-M0560-010-53

-503

.

.

.

4

.

.288.

4

1.

1. REFERENCE ELLIOTT AVIATION DWG. # 237-3832-E0560-000 OR 237-4071-E0560-000FOR ANTENNA PART NUMBERS.

2. ALL DIMENSIONS GIVEN IN INCHES.

3. CONTOUR PARTS TO MATCH AIRCRAFT CONTOUR.

4. VERIFY ANTENNA CLEARS NOSE LANDING GEAR DOOR.

5. REMOVE PAINT FROM AIRCRAFT SKIN AND PREP FOR PROPER BONDING INACCORDANCE WITH MAINTENANCE MANUAL 20-21-02. THE ELECTRICAL BONDSHALL ACHIEVE A DC RESISTANCE OF 2.5 MILLIOHMS OR LESS BETWEEN THEANTENNA METAL BASE AND AIRCRAFT STRUCTURE (WITH THE COAXDISCONNECTED). COMPLIANCE SHALL BE VERIFIED USING A CALIBRATEDMILLIOHMMETER.

6. MATCH DRILL FUSELAGE TO DOUBLERS.

7. BREAK ALL EDGES AND REMOVE ALL BURRS.

8. ATTACH NUTPLATES TO DOUBLERS ONLY.

9. APPLY FAYING SURFACE SEALANT OF PS890B1/2 TO DOUBLERS.

10. APPLY A FILLET SEAL OF P/S 890 B 1/2 AROUND PERIMETER OF ANTENNA ANDCONNECTOR HOLE AND COVER ALL NUTPLATES.

11. CONNECT ANTENNA TO HARNESS PER ELLIOTT AVIATION DWG. #237-3832-E0560-000.

NOTES:

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AVIATION

AutoCAD SHX Text

VIEW LOOKING INBD

AutoCAD SHX Text

%%U(-501, -503) ANTENNA INSTALLATIONS

AutoCAD SHX Text

PORTIONS REMOVED FOR CLARITY

AutoCAD SHX Text

VIEW LOOKING INBOARD FROM LH SIDE OF AIRCRAFT SHOWING -501, -503 INSTL LOCATIONS

AutoCAD SHX Text

DETAIL A

AutoCAD SHX Text

02

AutoCAD SHX Text

SH

AutoCAD SHX Text

DETAIL B

AutoCAD SHX Text

03

AutoCAD SHX Text

SH

CONNECTOR

1.1± 0.5

0.13

1.1± 0.5

0.13

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-010 3 B2

FWD

UP

39

4X

84X

AIRCRAFT SKIN0.040" THK. 2024T3

FWD

LH

(GPS ANTENNA) 1

(SKIN SPLICE)

EXISTING DOUBLER0.016" THK. 2024T3

OR

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AVIATION

AutoCAD SHX Text

VIEW LOOKING INBD

AutoCAD SHX Text

VIEW LOOKING UP FROM INSIDE OF AIRCRAFT SHOWING -501 INSTL

AutoCAD SHX Text

RH OR LH BAY INSTALLATION

AutoCAD SHX Text

0.0

AutoCAD SHX Text

BL

AutoCAD SHX Text

172.00

AutoCAD SHX Text

FS

AutoCAD SHX Text

%%U-501 GPS ANTENNA INSTL

AutoCAD SHX Text

11

AutoCAD SHX Text

25

AutoCAD SHX Text

3

AutoCAD SHX Text

REF

AutoCAD SHX Text

10

AutoCAD SHX Text

2

AutoCAD SHX Text

9

AutoCAD SHX Text

REF

AutoCAD SHX Text

11

AutoCAD SHX Text

REF

AutoCAD SHX Text

3

AutoCAD SHX Text

REF

AutoCAD SHX Text

8

AutoCAD SHX Text

REF

AutoCAD SHX Text

VIEW LOOKING UP

AutoCAD SHX Text

187.00

AutoCAD SHX Text

FS

AutoCAD SHX Text

VIEW LOOKING INBOARD FROM LH SIDE OF AIRCRAFT SHOWING -501 INSTL

AutoCAD SHX Text


AutoCAD SHX Text

%%U(-501) GPS ANTENNA INSTL

AutoCAD SHX Text

%%UDETAIL A

AutoCAD SHX Text

%%USECTION C-C

AutoCAD SHX Text

C

AutoCAD SHX Text

C

AutoCAD SHX Text

02

AutoCAD SHX Text

SH

AutoCAD SHX Text


2.4±0.2

CONNECTOR

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-010 3 B3

FWD

UP

4

7

4X

8

4X

AIRCRAFT SKIN0.050" THK. 2024 T42

FWD

RH

(UAT ANTENNA)

4

1

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AVIATION

AutoCAD SHX Text

VIEW LOOKING INBD

AutoCAD SHX Text

VIEW LOOKING DOWN FROM INSIDE OF NOSE AVIONICS COMPARTMENT SHOWING -503 INSTL

AutoCAD SHX Text


AutoCAD SHX Text

6.3

AutoCAD SHX Text

LBL

AutoCAD SHX Text

67.1

AutoCAD SHX Text

FS

AutoCAD SHX Text

%%U-503 UAT ANTENNA INSTL

AutoCAD SHX Text

11

AutoCAD SHX Text

28

AutoCAD SHX Text

4

AutoCAD SHX Text

REF

AutoCAD SHX Text

10

AutoCAD SHX Text

2

AutoCAD SHX Text

7

AutoCAD SHX Text

REF

AutoCAD SHX Text

11

AutoCAD SHX Text

REF

AutoCAD SHX Text

4

AutoCAD SHX Text

REF

AutoCAD SHX Text

8

AutoCAD SHX Text

REF

AutoCAD SHX Text

VIEW LOOKING DWN

AutoCAD SHX Text

75.80

AutoCAD SHX Text

FS

AutoCAD SHX Text


AutoCAD SHX Text


AutoCAD SHX Text

%%U(-503) UAT ANTENNA INSTL

AutoCAD SHX Text

%%UDETAIL B

AutoCAD SHX Text

%%USECTION D-D

AutoCAD SHX Text

D

AutoCAD SHX Text

D

AutoCAD SHX Text

03

AutoCAD SHX Text

SH


REVISIONS


.0 ± .1.00 ± .03

.000 ± .005




SCALEDRAWN BY

CHECKED BY



SIZE

Bof 2237-3832-M0560-020ANNUNCIATORINSTALLATIONN/A08/17/17GS

CESSNA 560XLSM1

NTS

FWD

UP

1. REFERENCE ELLIOTT AVIATION DWG. # 237-3832-E0560-000 FORANNUNCIATOR PART NUMBER.


3. LOCATE ANNUNCIATOR WITHIN REGION SHOWN. ENSUREANNUNCIATOR CLEARS PANEL STRUCTURE AND IS ALIGNED WITHEXISTING ANNUNCIATORS.

4. CONNECT ANNUNCIATOR TO HARNESS PER APPLICABLE WIRINGDIAGRAM OR PER MFG INSTRUCTIONS.

NOTES:

DESCRIPTION SIZE / WT SPECIFICATION ITEM

PARTS LIST

. 1234

789

10........ .

.. .

.. .ANNUNCIATOR INSTALLATION .

.

.

.

-501 P/N

QTY

..

..

..

..

.....

-501.

.

.

.

.

.

.

.

.

.

.

.

.5.

. .....

6.. ..

... . ..

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AVIATION

AutoCAD SHX Text

%%U(-501) ANNUNCIATOR INSTALLATION

AutoCAD SHX Text

VIEW LOOKING INBOARD FROM LH SIDE OF AIRCRAFT SHOWING -501 LOCATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING INBD

AutoCAD SHX Text

A

AutoCAD SHX Text

A

AutoCAD SHX Text

02

AutoCAD SHX Text

SH

0.70

0.70

PULL LENS CAPSULEFROM ANNUNCIATORBODY

MOUNTING SLEEVE

LOCKING PAW

INSTRUMENT PANEL

ONCE LENS CAPSULE IS REMOVED.USE SCREW DRIVER TO TIGHTENSCREWS INSIDE ANNUNCIATORBODY TO TIGHTEN LOCKING PAWINTO THE MOUNTING SLEEVE.

5.2

2.9

DRAWING NUMBER


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SIZE

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of237-3832-M0560-020 2 IR2

LH

UP 1(ANNUNCIATOR)

8/17/2017 3:32:13 PM

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AVIATION

AutoCAD SHX Text

%%U-501 ANNUNCIATOR INSTALLATION

AutoCAD SHX Text

VIEW SHOWING -501 LOCATION ON INSTRUMENT PANEL

AutoCAD SHX Text


AutoCAD SHX Text

%%USECTION A-A

AutoCAD SHX Text

VIEW LOOKING FWD

AutoCAD SHX Text

%%UDETAIL B

AutoCAD SHX Text

VIEW SHOWING CUTOUT DIMENSIONS

AutoCAD SHX Text

DETAIL B

AutoCAD SHX Text

02

AutoCAD SHX Text

SH

AutoCAD SHX Text

%%UDETAIL C

AutoCAD SHX Text

VIEW SHOWING INSTALLATION

AutoCAD SHX Text

DETAIL C

AutoCAD SHX Text

DETAIL C


REVISIONS


A ITEM 14 REVISION CHANGE, ADD NOTE 9 01/08/18 S. MCCORD

.0 ± .1.00 ± .03

.000 ± .005




SCALEDRAWN BY

CHECKED BY



SIZE

Bof 9237-3832-M0560-030NOSE EQUIPMENTINSTALLATIONN/A08/17/17RJ

CESSNA 560XLSM1

NTS

AFT

LH

1. REFERENCE ELLIOTT AVIATION DWG. # 237-3832-E0560-000 FOR LRU AND RACK PARTNUMBERS.


3. REMOVE EXISTING RADIO ALTIMETER FROM LOWER SHELF FORWARD POSITION (#1 GTX3000 INSTALLATION LOCATION) AND RELOCATE TO UPPER SHELF AS SHOWN.

4. MATCH DRILL EXISTING STRUCTURE TO LRU TRAYS AT TIME OF INSTALLATION. MAINTAINMIN 2D EDGE DISTANCE.

5. BREAK ALL EDGES, AND REMOVE ALL BURRS.

6. INSTALL ALL NUTPLATES USING MS20426AD3-X OR CR2662-3-X RIVETS.

7. BURNISH EQUIPMENT AND MOUNTING TRAYS MIN Ø0.5 AT EACH FASTENER LOCATION.

8. BOND EQUIPMENT IN ACCORDANCE WITH TEXTRON 560XL MAINTENANCE MANUAL 20-21-02.

9. REMOVE EXISTING STRAIGHT FITTING AND REPLACE WITH 45° BULKHEAD ELBOW(AN837-6D), NUT (AN924-6D), AND O-RING (NAS1612-6A). LEAK CHECK IN ACCORDANCEWITH AMM 34-11-09.

NOTES:


PARTS LIST

. 1234

789

10.ADS-B LABELS.ADS-B LABELS.#8 SELF LOCKING NUT.#8-32 FH SCREW MIL-STD

.#8-32 PH SCREW MIL-STD

.CONVERTER MOUNTING PLATE ELLIOTT AVIATIONEQUIPMENT INSTALLATION .

MIL-STDELLIOTT AVIATIONELLIOTT AVIATION

-501 P/N

QTY

160-3760-M0560-070 REV A "#2 GTX 3000"REF160-3760-M0560-070 REV A "#1 GTX 3000"1

MS21042L082MS24694S55

4MS27039-08098

237-3832-M0560-030-512-501

.

.

.

.

.

.

.

.

.

.

.

.

.5.

#8-32 PH SCREW MIL-STDMS27039-08188..

6.#8 WASHER MIL-STDNAS1149FN816P

12..

. 11ADS-B LABELS ELLIOTT AVIATION160-3760-M0560-070 REV A "GDL 88"REF..

#8 NUTPLATE MIL-STDMS21059L08

. 12ADS-B LABELS ELLIOTT AVIATION237-3832-M0560-070 "#1 AMC"1..

. 13ADS-B LABELS ELLIOTT AVIATION237-3832-M0560-070 "#2 AMC"REF..

. 14RADIO ALTIMETER MOUNTING PLATE ELLIOTT AVIATION237-3832-M0560-030-53 REV_A1..

. 15#10-32 PH SCREW MIL-STDMS27039-1-088..

. 16#10 NUTPLATE MIL-STDMS21059L38..

. 17#8-32 PH SCREW MIL-STDMS27039-08164..

2/26/2018 1:44:25 PM

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AVIATION

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%%U(-501) EQUIPMENT INSTALLATION

AutoCAD SHX Text

VIEW LOOKING DOWN FROM ABOVE AIRCRAFT SHOWING -501 LOCATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING DWN

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94.0

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FS

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A

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A

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02

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SH

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B

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B

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07

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SH

RNZ-850 NAV11.1 LB EST

RNZ-833 COM11.1 LB EST

LCR-935.6 LB

IC-61514 LB

J1J1

J2J2

BTM

J330

1

J330

2

AIR

TOP

GA

RM

IN

ADC3.7 LB RT-300 RADIO

ALTIMETER4.6 LB

EGPWS7.0 LB

DRAWING NUMBER


PAGE NUMBER REV

SIZE

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of237-3832-M0560-030 9 A2

FWD

UP

(GTX 3000) 1

(SHADIN COVERTER) 1 .3.9

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%%U-501 EQUIPMENT INSTL

AutoCAD SHX Text


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AutoCAD SHX Text

%%USECTION A-A

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VIEW LOOKING INBD

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87.0

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FS

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55.0

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FS

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C

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C

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03

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SH

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D

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D

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05

AutoCAD SHX Text

SH

CL

1.25± 0.5

ELECTRONICMODULEENCLOSURE ASSY7 LB EST

ADC3.7 LB

EGPWS7.0 LB

0.2

0.35

#1 AMC

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-030 9 A3

FWD

INBD

(0.14" THK ALUMINUM HONEYCOMB SHELF0.030" THK UPPER AND LOWER SKINS)

(SHADIN CONVERTER)1

12.3

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AVIATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING DOWN ABOVE LH UPPER SHELF SHOWING -501 INSTL

AutoCAD SHX Text


AutoCAD SHX Text

%%USECTION C-C

AutoCAD SHX Text

VIEW LOOKING DWN

AutoCAD SHX Text

04

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SH

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F

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E

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04

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SH

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E

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0.0

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BL

AutoCAD SHX Text

87.0

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FS

AutoCAD SHX Text

F

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-030 9 A4

INBD

UP

(SHADIN CONVERTER) 1

.3

FWD

UP

3X

2X

2X

2X

2X

3X

6

2X

5

2X

8

7

2

14

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AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING AFT (LH SIDE) OR FWD (RH SIDE) SHOWING SHADIN CONVERTER INSTL

AutoCAD SHX Text


AutoCAD SHX Text

%%USECTION E-E

AutoCAD SHX Text

VIEW LOOKING AFT/FWD

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING INBOARD SHOWING RADIO ALTIMETER RELOCATION

AutoCAD SHX Text


AutoCAD SHX Text

%%USECTION F-F

AutoCAD SHX Text

VIEW LOOKING INBD

AutoCAD SHX Text

3

AutoCAD SHX Text

2

AutoCAD SHX Text

5

AutoCAD SHX Text

2

AutoCAD SHX Text

6

AutoCAD SHX Text

2

AutoCAD SHX Text

7

AutoCAD SHX Text

2

AutoCAD SHX Text

4

AutoCAD SHX Text

2

AutoCAD SHX Text

5

AutoCAD SHX Text

2

#1 GTX 3000

IC-61514 LB

LCR-935.6 LB


3.2

1.6

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-030 9 A5

FWD

INBD 9

(GTX 3000) 1

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AVIATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING DOWN ABOVE LH LOWER SHELF SHOWING -501 INSTL

AutoCAD SHX Text


AutoCAD SHX Text

%%USECTION D-D

AutoCAD SHX Text

VIEW LOOKING DWN

AutoCAD SHX Text

G

AutoCAD SHX Text

06

AutoCAD SHX Text

SH

AutoCAD SHX Text

G

AutoCAD SHX Text

0.0

AutoCAD SHX Text

BL

AutoCAD SHX Text

87.0

AutoCAD SHX Text

FS

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-030 9 A6

RH

UP

RH

UP

(GTX 3000) 1

EXISTING EQUIPMENTTRAY

(GTX 3000 TRAY)1

(GTX 3000) 1

2X

2X

2X

2X

EXISTING EQUIPMENTSHELF

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AVIATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING AFT SHOWING #1 GTX 3000 INSTL

AutoCAD SHX Text


AutoCAD SHX Text

%%USECTION G-G

AutoCAD SHX Text

VIEW LOOKING AFT

AutoCAD SHX Text


AutoCAD SHX Text


AutoCAD SHX Text


AutoCAD SHX Text

%%USECTION I-I

AutoCAD SHX Text

VIEW LOOKING AFT

AutoCAD SHX Text

15

AutoCAD SHX Text

2

AutoCAD SHX Text

16

AutoCAD SHX Text

2

AutoCAD SHX Text

15

AutoCAD SHX Text

2

AutoCAD SHX Text

16

AutoCAD SHX Text

2


RCZ-833 COM11.1 LB EST

LCR-935.6 LB

IC-61514 LB

J1 J1

J2 J2

TCAS14.2 #

ADC3.7 LB

AOASTALL

WARNINGCOMP3.0 LB

PWR SUPPLY14 LB

BTM

J330

1

J330

2

AIR

TOP

GA

RM

IN

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-030 9 A7

AFT

UP

(GTX 3000) 1


(GDL 88) 1

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AVIATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING INBOARD FROM RH SIDE OF AIRCRAFT SHOWING -501 INSTL

AutoCAD SHX Text


AutoCAD SHX Text

%%USECTION B-B

AutoCAD SHX Text

VIEW LOOKING INBD

AutoCAD SHX Text

87.0

AutoCAD SHX Text

FS

AutoCAD SHX Text

55.0

AutoCAD SHX Text

FS

AutoCAD SHX Text

H

AutoCAD SHX Text

H

AutoCAD SHX Text

08

AutoCAD SHX Text

SH

1.25± 0.5

4.5

0.9

4.0

5.8

#2 GTX 3000 GDL 88

TCAS14.2 #

AOASTALL

WARNINGCOMP3.0 LB

ADC3.7 LB

#2 AMC

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-030 9 A8

AFT

INBD


(SHADIN CONVERTER)

1

(GTX 3000) 1

(GDL 88) 1

10 11

13

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AVIATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING DOWN ABOVE RH UPPER SHELF SHOWING -501 INSTL

AutoCAD SHX Text


AutoCAD SHX Text

%%USECTION H-H

AutoCAD SHX Text

VIEW LOOKING DWN

AutoCAD SHX Text

I

AutoCAD SHX Text

06

AutoCAD SHX Text

SH

AutoCAD SHX Text

I

AutoCAD SHX Text

0.0

AutoCAD SHX Text

BL

AutoCAD SHX Text

87.0

AutoCAD SHX Text

FS

AutoCAD SHX Text

J

AutoCAD SHX Text

09

AutoCAD SHX Text

SH

AutoCAD SHX Text

J

AutoCAD SHX Text

E

AutoCAD SHX Text

04

AutoCAD SHX Text

SH

AutoCAD SHX Text

E

FAN

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-030 9 A9

LH

UP

(GDL 88) 1

EXISTING SHELF

(GDL 88 TRAY)1

2X

2X

2X

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AVIATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING FWD SHOWING GDL 88 INSTL

AutoCAD SHX Text


AutoCAD SHX Text

%%USECTION J-J

AutoCAD SHX Text

VIEW LOOKING FWD

AutoCAD SHX Text

17

AutoCAD SHX Text

2

AutoCAD SHX Text

6

AutoCAD SHX Text

2

AutoCAD SHX Text

5

AutoCAD SHX Text

2


REVISIONS


.0 ± .1.00 ± .03

.000 ± .005




SCALEDRAWN BY

CHECKED BY



SIZE

Bof 2237-3832-M0560-040FLIGHT STREAM 110INSTALLATION (OPTIONAL)N/A08/17/17GS

CESSNA 560XLSM1

NTS

FWD

UP

1. REFERENCE ELLIOTT AVIATION DWG. # 237-3832-E0560-000 FORFLIGHTSTREAM PART NUMBER.


3. LOCATE FLIGHT STREAM 110 ON OUTBOARD SIDE OF COPILOTJEPPS CABINET. MATCH DRILL CABINET TO FLIGHT STREAM 110.

4. BOND ALL INSERTS IN PLACE USING 3M DP420, MAGNOLIA 121-146A/B, ATR 360, OR ATR 525 A/B EPOXY. DRILL INSTALLATION HOLE.RAKE OUT CORE 0.25 AROUND ENTIRE PERIMETER OFINSTALLATION HOLE. INSTALL TAB/INSERT ASSY IN INSTALLATIONHOLE AND INJECT EPOXY UNTIL IT APPEARS IN VENT HOLE. LETSET ACCORDING TO MANUFACTURER'S INSTRUCTIONS.

5. CONNECT LRU TO HARNESS PER ELLIOTT AVIATION DWG. #237-3832-E0560-000.

NOTES:


PARTS LIST

. 1234

789

10...ADS-B LABELS...#6 INSERT MIL-STD

.. .

.. .EQUIPMENT INSTALLATION .

.ELLIOTT AVIATION

.

-501 P/N

QTY

..160-3760-M0560-070 "FLIGHTSTREAM 110"1

NOT USED.NAS1836-06-74

.NOT USED.NOT USED.

-501.

.

.

.

.

.

.

.

.

.

.

.

.5.

. .NOT USED4..

6.#6-32 PH SCREW MIL-STDMS35206-228

4.. #6 WASHER MIL-STDNAS1149FN632P

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AVIATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING INBOARD FROM LH SIDE OF AIRCRAFT SHOWING -501 LOCATION (COPILOT SIDE)

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING INBD

AutoCAD SHX Text

157

AutoCAD SHX Text

FS

AutoCAD SHX Text

DETAIL A

AutoCAD SHX Text

02

AutoCAD SHX Text

SH

5.11.0

FLIGHTSTREAM 110

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-040 2 IR2

RH

UP 9

(FLIGHTSTREAM 110)1

1 (FLIGHTSTREAM 110)

(EXISTING JEPPS CABINET)

RH

UP

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AVIATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING AFT SHOWING -501 LOCATION ON COPILOT JEPPS CABINET

AutoCAD SHX Text

%%USECTION A-A

AutoCAD SHX Text

VIEW LOOKING AFT

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING AFT SHOWING -501 INSTL

AutoCAD SHX Text


AutoCAD SHX Text

%%UDETAIL B

AutoCAD SHX Text

157

AutoCAD SHX Text

FS

AutoCAD SHX Text

DETAIL B

AutoCAD SHX Text

02

AutoCAD SHX Text

SH

AutoCAD SHX Text

7

AutoCAD SHX Text

4

AutoCAD SHX Text

6

AutoCAD SHX Text

4

AutoCAD SHX Text

5

AutoCAD SHX Text

4

AutoCAD SHX Text

VIEW LOOKING AFT

AutoCAD SHX Text

VIEW LOOKING AFT


RCZ-833 COM11.1 LB EST

LCR-935.6 LB

IC-61514 LB

J1 J1

J2 J2

TCAS14.2 #

ADC3.7 LB

AOASTALL

WARNINGCOMP3.0 LB

PWR SUPPLY14 LB

BTM

J330

1

J330

2

AIR

TOP

GA

RM

IN

NOSEJ-BOX

NOSE WEB DISC


REVISIONS


.0 ± .1.00 ± .03

.000 ± .005




SCALEDRAWN BY

CHECKED BY



SIZE

Bof 4237-3832-M0560-050WIRE ROUTINGINSTALLATIONN/A01/08/18TB

CESSNA 560XLSM1

NTS

AFT

UP

NOTES

1. REFERENCE ELLIOTT ELECTRICAL WIRING DIAGRAMS237-3932-E0560-000 FOR REQUIRED PARTS.

2. MAINTAIN A MINIMUM BEND RADIUS OF 10 TIMES THE WIRE DIAMETERDURING HANDLING AND ROUTING. SEE SAMPLE "A" LAST PAGE.

3. TAKE CARE TO NOT CRUSH COAX. IF COAX GETS KINKED OR CRUSHEDDURING INSTALLATION, REPLACE WITH NEW. PERMISSIBLE TO ROUTENEW WIRING GROUP INCLUDING COAX OUTSIDE CLAMP IF PROPERLYSECURED WITHIN 2 INCHES ON EITHER SIDE OF CLAMP. DO NOTOVERTIGHTEN TIE WRAPS ON COAX.

4. ROUTE NEW WIRING WITH EXISTING WHERE POSSIBLE. SECURE ATREGULAR INTERVALS NOT TO EXCEED 12 INCHES. EXCEPT WIRING ATTHE ANNUNCIATOR WHERE IT IS IN CLOSE PROXIMITY TO THE ENGINEINDICATORS THESE WIRES MUST BE SECURED TO THE EXISTINGANNUNCIATOR WIRING AT A 2" INTERVAL.

5. HYDRAULIC, FUEL AND OXYGEN LINES: MAKE SURE A MINIMUM OF 0.4INCHES POSITIVE CONTROL SEPARATION EXIST BETWEEN NEW WIRES /COAXES. AND THESE LINES. ANY NEW WIRING / COAXES WITHIN 2.0INCHES OF THESE LINES MUST BE CLAMPED TO MAINTAIN SEPARATION.

6. SEE PAGE 3 FOR DETAILED WRITTEN WIRE ROUTING INSTRUCTIONS.

7. IDENTIFY NEW WIRES NOT TO EXCEED 24 INCHES BETWEEN TAGS.MARK AS FOLLOWS USING SUPPLIED (PARTS LIST ITEM #3) MARKERBANDS:

(GPS ANTENNA)

(#2 TRANSPONDER)

(ANNUNCIATOR)

(FWD PRESSURE BULKHEAD)

(GDL 88)

(FLIGHT STREAM 110 OPTIONAL)

-501WIRE ROUTING INSTL

P/N DESCRIPTION SIZE / WT SPECIFICATION ITEM

PARTS LISTQTY

.

.12345

.-501

TEXTRONMARKER BANDS13171-3

.

.30A/R

A/R

HELITUBESPIRAL WRAPHT1/4N

.

(#2 AMC)

(CIRCUIT BREAKER PANEL)

(EXISTING #2 XPDR ANT)

AR 4" CABLE TIEBT1M-M PANDUIT

(NOSE WEB DISC)

(NOSE J-BOX)

(TCAS PROCESSOR)

(#2 RCZ)

ADS-B

6.A/R7.A/R

PANDUITPANDUITAVERY

6.125" CABLE TIEBT1.5I-M8" CABLE TIEBT2S-M15" CABLE TIE10036

1/30/2018 12:23:17 PM

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AVIATION

AutoCAD SHX Text

%%U(-501) WIRE ROUTING INSTALLATION

AutoCAD SHX Text


AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING INBD



LCR-935.6 LB

IC-61514 LB

J1J1

J2J2

BTM

J330

1

J330

2

AIR

TOP

GA

RM

IN

ADC3.7 LB RT-300 RADIO

ALTIMETER4.6 LB

EGPWS7.0 LB

NOSE WEB DISC

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-050 4 IR3

AFT

UP

(#1 AMC)

(EXISTING #1 XPDR ANT)(UAT ANT)

(#1 TRANSPONDER) (#1 RCZ)

(#1 NOSE WEB DISC)

1/30/2018 12:23:18 PM

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AutoCAD SHX Text

VIEW LOOKING INBD

AutoCAD SHX Text


AutoCAD SHX Text


AutoCAD SHX Text


3X

BULKHEAD- 7.5

CL

#2 GTX 3000 GDL 88

#2 SHADIN CONVERTER

3X

BULKHEAD- 7.5

CL

#1 SHADIN CONVERTER

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-050 4 IR2

AFT

LH

(GDL 88)

(ANNUNCIATOR)

(FLIGHT STREAM 110 OPTIONAL)


(UAT ANTENNA)

(GPS ANTENNA)

(#1 TRANSPONDER)(#1 AMC)

(#2 TRANSPONDER)

(#2 AMC)



(CIRCUIT BREAKER PANEL)

2

1/30/2018 12:23:18 PM

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AVIATION

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING DOWN FROM ABOVE AIRCRAFT SHOWING -501 INSTL

AutoCAD SHX Text


AutoCAD SHX Text

VIEW LOOKING DWN

(TYPICAL INSTALLATION)

SAMPLE A

TIE WRAPNYLON

MINIMUM BEND RADIUS: MUST NOT BE LESS THAN 10 TIMESTHE OUTSIDE DIAMETER OF THE LARGEST WIRE OR CABLE,EXCEPT WHERE WIRES BREAK OUT AT TERMINATIONS.WHERE WIRE IS SUITABLY SUPPORTED, THE RADIUS MAY BE6 TIMES THE DIAMETER OF THE WIRE. COAX BEND RADIUSSHOULD NEVER EXCEED 10 TIMES IT'S DIAMETER.

USED FOR ALL BENDS UNLESS OTHERWISE SHOWN

DRAWING NUMBER


PAGE NUMBER REV

SIZE

B

of237-3832-M0560-050 4 IR4

Wire Routing Instructions

1. Wiring from the #1 GTX 3000 and #1 AMC is is routed from the forward side of the left nose avionics bay. The #1 GTX3000 is on the lower shelf and the AMCis located on the upper shelf. The wiring follows the existing aircraft wire some wires go to the nose center web disconnects while the remaing cable bundle isrouted aft towards the forward bulkhead. At that point some of the wiring follows the existing AHRS wiring bundle to the AHRS connector, and some of otherfollows the existing wiring bundle to the #1 RCZ connector. The rest of the wiring is routed aft to the forward bulkhead. At this point the wiring keeps followingthe existing avionics wiring outboard to the forward pressure bulkhead connectors. The existing avionics wiring bundles also contain the same type of low level28vdc and discrete wiring along with ARINC 429 and RSB databus wiring. All wiring is secured using tie straps in accordance with Textron Aviation 560XLstandard wiring practices as shown in Chapter 20, Section 21.

2. Wiring from the #2 GTX3000 and GDL 88 are in the middle of the upper shelf and the #2 AMC is located forward on the upper shelf. The wiring follows theexisting aircraft wire bundles along the lower avionics bay center wall to the nose center web disconnects. From there it follows along the center web afttowards the forward bulkhead and at that point some wiring follows the existing wiring bundle to the #2 RCZ connector. The rest of the wiring is routed aft tothe forward bulkhead. At this point the wiring keeps following the existing avionics wiring outboard to existing forward pressure bulkhead connectors. Somewiring breaks out and follows the existing wiring the Nose J-box the remaining wiring goes to existing forward pressure bulkhead connectors. The existingavionics wiring bundles in the nose also contain the same type of low level 28 VDC and discrete wiring along with ARINC 429 and RSB databus wiring. Allwiring is secured using tie straps in accordance with Textron Aviation 560XL standard wiring practices as shown in Chapter 20, Section 21.

3. Wiring from the existing forward bulkhead connectors is routed from the existing forward bulkhead connectors following existing like avionics wiring bundles.The annunciator wiring breaks out and follows like avionics bundles to behind the center instruments panel. FQIS wiring is present behind the centerinstrument panel. It is likely that a six (6) inch separation margin between the FQIS wiring and new cable cannot be ensured. Therefore, the new annunciatorwiring will be zip tied to the existing aircraft annunciator wiring. The zip ties in this area only will be spaced at no greater than every 2” in order to maintainrequired separation from the FQIS wiring such that a broken wire plus a broken zip tie will not result in any physical contact with adjacent FQIS wiring. Theremaining wires follow along the right cockpit side wall to the circuit breaker panel. If the Flight Stream 110 is installed the remaining wires continue aft to thechart holder to the Flight Stream 110 location. Except where noted for the annunciator wiring, the existing avionics wiring bundles in the cockpit also containthe same type of low level 28 VDC and discrete wiring along with databus wiring. All wiring is secured using tie straps in accordance with Textron Aviation560XL standard wiring practices as shown in Chapter 20, Section 21.

4. The UAT antenna cable is routed from the GDL 88 located in the middle of the upper right avionics shelf in nose following and tie wrapped to existing coaxes.The new cable is routed inboard to the nose center web, then aft to the forward pressure bulkhead where it routes to the left side of the aircraft. It then routesdown to the bottom of the nose avionics bay to the UAT antenna. All wiring is secured using tie straps in accordance with Textron Aviation 560XL standardwiring practices as shown in Chapter 20, Section 21.

5. The GPS antenna cable is routed from the GDL 88 located in the middle of the upper right avionics shelf in the following the existing TCAS cables to a newlyinstalled forward bulkhead TNC connector. On the cabin side of the forward bulkhead it continues to follow the TCAS antenna coaxes down the RH cockpitsidewall to the middle of the right hand side circuit breaker panel. At this point the GPS coax remains in its own wire bundle down the right hand sidewall, it issecured using tie wraps to existing tie down blocks to the aircraft frame. At the right forward cockpit partition, the coax goes up the aircraft sidewall to the topof the aircraft. The coax is also wrapped with spiral wrap from this point to the antenna. Once at the top of the aircraft it follows the #2 GPS coax through ahole in the frame. The coax then goes through an existing lightning hole in the aircraft to the left bay where the GPS antenna is located. All wiring is securedusing tie straps in accordance with Textron Aviation 560XL standard wiring practices as shown in Chapter 20, Section 21.

6. The lower #1 lower transponder antenna cable is routed from the #2 GTX 3000 located on the lower left avionics shelf following and tie wrapped to existingcoax. The new cable is routed inboard to the nose center web, then aft following existing com and nav coaxes to the forward pressure bulkhead. At this pointthe coax routes outboard and then down to the bottom of the nose avionics bay to the existing #1 lower transponder antenna. All wiring is secured using tiestraps in accordance with Textron Aviation 560XL standard wiring practices as shown in Chapter 20, Section 21.

7. The #2 lower transponder antenna cable is routed from the #2 GTX 3000 located in the middle of the upper right avionics shelf in nose following and tiewrapped to existing coaxes. The new cable is routed inboard to the nose center web, then aft following the existing TCAS antenna coaxes to the forwardpressure bulkhead where it routes to the left side of the aircraft. It then routes down to the bottom of the nose avionics bay to the lower transponder antenna.All wiring is secured using tie straps in accordance with Textron Aviation 560XL standard wiring practices as shown in Chapter 20, Section 21.

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1.0MIN

(#8-32 FASTENERS TYP)

Ø0.50


REVISIONS


A CHANGED TNC P/N 02/27/18 R. WOOLUMS

.0 ± .1.00 ± .03

.000 ± .005




SCALEDRAWN BY

CHECKED BY



SIZE

Bof 1237-3832-M0560-060FWD BULKHEAD FEEDTHROUGHINSTALLATIONN/A08/17/17RJ

CESSNA 560XLSM1

NTS

-501BULKHEAD INSTALLATION

P/N DESCRIPTION SIZE / WT SPECIFICATION.

.

ITEM

PARTS LISTQTY

.

.

.

12345

.

..-501

NOT USED.

.

.

6.

.

.

.. . .NOT USED .

122340 TNC BULKHEAD ADAPTER F-F (HERM) SEALED AMPHENOL CONNEX1 7

RH

UP


2. INSTALL BULKHEAD CONNECTOR IN APPROPRIATE SIZEHOLE AS SHOWN.


4. SEAL AROUND THE CONNECTOR ON BOTH SIDES WITH PS890 B1/2.

5. WEB 0.063" THK. ALUM.

6. DIMENSION SHOWN IS TO CLOSEST SURROUNDINGCONNECTOR/FEEDTHROUGH HOLE. CENTER AT TIME OFINSTALLATION.

7. ITEM #7 CONSISTS OF CONNECTOR, WASHER, AND NUT.

NOTES:

.. NOT USED ... .

.. NOT USED ... .

.. NOT USED ... .

5

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VIEW LOOKING AFT AT FS 94.0 SHOWING -501 INSTL

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REVISIONS


A UPDATED NOTE 3 FOR ALTERNATE P/N, 09/24/18 S. MCCORD

ADDED NOTE 4 (PG 6)

.0 ± .1.00 ± .03

.000 ± .005




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Bof 10237-4071-M0560-080NOSE EQUIPMENTINSTALLATIONN/A05/08/18GS

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NTS

AFT

LH

1. REFERENCE ELLIOTT AVIATION DWG. # 237-4071-E0560-000 FOR LRU AND RACK PARTNUMBERS.

2. RELOCATE #2 RNZ-850 FROM TOP OF SHELF TO BOTTOM OF SHELF USING BRACKETRY ASSHOWN.

3. REMOVE EXISTING STATIC LINE AND REPLACE WITH NEW STATIC LINE SHOWN. CLAMPSECURELY AS REQUIRED AND ENSURE ADEQUATE CHAFE PROTECTION. PERMISSIBLE TOSUBSTITUTE TEXTRON P/N 6614130-10 IN LIEU OF HOSE AND FITTINGS. LEAK CHECK INACCORDANCE WITH AMM 34-11-09.

4. MAINTAIN MIN SPACING AS SHOWN.


6. MATCH DRILL EXISTING STRUCTURE TO LRU TRAYS AT TIME OF INSTALLATION. MAINTAINMIN 2D EDGE DISTANCE.


8. INSTALL ALL NUTPLATES USING MS20426AD3-X OR CR2662-3-X RIVETS.

9. BURNISH EQUIPMENT SHELVES AND MATING SURFACE OF -001 SHELF ASSY MIN Ø0.5 ATEACH FASTENER LOCATION. BOND EQUIPMENT IN ACCORDANCE WITH TEXTRON 560XLMAINTENANCE MANUAL 20-21-02. TREAT PER MIL-C-5541, CLASS 1A.

NOTES:

94.0FS


PARTS LIST

. 1234

789

10

.ADS-B LABELS

.ADS-B LABELS

.#8 NUTPLATE


.#8-32 PH SCREW MIL-STDCONVERTER MOUNTING PLATE ELLIOTT AVIATION

EQUIPMENT INSTALLATION .

MIL-STDELLIOTT AVIATIONELLIOTT AVIATION

-501 P/N

QTY

160-3760-M0560-070 REV A "#2 GTS 3000"REF160-3760-M0560-070 REV A "#1 GTS 3000"1

MS21061L08.MS24694S512

18MS27039-08098

237-3832-M0560-030-512

-501-001

.

.4.

.

.

.

.

.

.

.

.

5

.RIVET MIL-STDMS20470AD4-4

11..

6

.#8 WASHER MIL-STDNAS1149FN816P

13..

.

11

ADS-B LABELS ELLIOTT AVIATION160-3760-M0560-070 REV A "GDL 88"REF..

#8 NUTPLATE MIL-STDMS21059L08

.

12

ADS-B LABELS ELLIOTT AVIATION237-3832-M0560-070 "#1 AMC"1...

13

ADS-B LABELS ELLIOTT AVIATION237-3832-M0560-070 "#2 AMC"REF...

14

TUBE ASSY PITOT STATIC TEXTRON6614130-101...

15

#10-32 PH SCREW MIL-STDMS27039-1-088...

16

#10 NUTPLATE MIL-STDMS21059L38...

17

#8-32 PH SCREW MIL-STDMS27039-08154..

.

1819202122232425

....

.RIVET MIL-STDNAS1097AD4-428..

.#8-32 PH SCREW MIL-STDMS27039-08075..

.MOUNTING PLATE ELLIOTT AVIATION237-4071-M0560-080-591..

.STIFFENER ELLIOTT AVIATION237-4071-M0560-080-57.2.

.FWD SUPPORT ELLIOTT AVIATION237-4071-M0560-080-55.1.

.AFT SUPPORT ELLIOTT AVIATION237-4071-M0560-080-53.1.

.SHELF ELLIOTT AVIATION237-4071-M0560-080-51.11 .SHELF ASSY .-001

16.0" ± 0.5"STRATOFLEX HOSE AIRCRAFT SPRUCE193-6 (LP-MIL-H-5593-6)1.. 26.HOSE FITTING AIRCRAFT SPRUCE311-6D2.. 27.. ..... 28

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RNZ-850 NAV11.9 LB

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(0.071)EXISTING CHANNELS

2 PLCS

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VIEW LOOKING AFT (LH SIDE) OR FWD (RH SIDE) SHOWING SHADIN CONVERTER INSTL

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VIEW LOOKING AFT/FWD

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VIEW LOOKING AFT SHOWING GTX 3000 INSTL

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RCZ-833 COM11.1 LB

LCR-935.6 LB

IC-61514 LB

J1 J1

J2 J2

ADC3.7 LB

AOASTALL

WARNINGCOMP3.0 LB

PWR SUPPLY14 LB

BTM

J330

1

J330

2

AIR

TOP

GA

RM

IN

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MIN

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H

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08

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3X

BULKHEAD- 7.5

CL

1.75± 0.5

3.8

6.2± 0.5

0.5

4.0

#2 GTX 3000

AOASTALL

WARNINGCOMP3.0 LB

ADC3.7 LB

#2 AMC

1.50GDL 88

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Elliott Aviation Technical Products Development, Inc. Report No.: ICA-3832-560 6601 74th Ave Building A Revision: A Milan, IL 61264 Dated 12/11/2018 1 of 21

Instructions for Continued Airworthiness For Garmin ADS-B System Installation

Instructions for Continued Airworthiness

For





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REVISIONS PAGE



A Updated Appendix A A1 12/11/2018

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TABLE OF CONTENTS COVER PAGE .......................................................................................................... 1 REVISIONS PAGE.................................................................................................... 2 TABLE OF CONTENTS ............................................................................................ 3 Chapter 1 Introduction .............................................................................................. 4 Chapter 2 Maintenance Instructions and Shedules .................................................. 6 Chapter 3 Access .................................................................................................... 13 Chapter 4 Lifting and Shoring ................................................................................. 14

Chapter 5 Leving and Weighing .............................................................................. 14 Chapter 6 Towing and Taxing ................................................................................. 15 Chapter 7 Parking and Moring ................................................................................ 15 Chapter 8 Placards and Markings ........................................................................... 15 Chapter 9 Servicing................................................................................................. 15 Chapter 10 Airworthiness Limitations ..................................................................... 16 Appendix A .............................................................................................................. A1

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Chapter 1 INTRODUCTION

1.1 Scope/Purpose/Applicability/Distribution

The Instructions for Continued Airworthiness (ICA) described herein are applicable only to those aircraft modified by FAA STC . These ICA describe the recommended and required maintenance procedures for the installation of Garmin ADS-B System.

The maintenance information provided by this document must be included in the operator’s Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance Program. All documents listed in the required documents section must be maintained with this document. FAA accepted revisions to this document will be distributed by mail to the applicable certifying authorities and operators of legally modified aircraft.

1.2 System Description

The features of this modification include the installation of Garmin GTX 3000 transponders, reusing existing aircraft wiring, and two installed Shadin AMC Converters connecting the transponders to the RCZ Com units and the remaining RSB bus. This modification also includes a Garmin GDL 88 GPS / UAT and optional Flight Stream 110 Bluetooth FIS-B installation. A GPS and UAT-SBS antenna is installed. Annunciation is added for ADS-B status. New circuit breakers are installed in the copilot’s circuit breaker panel. New wiring is added to supply the GTX 3000 transponders with GPS position for the GDL 88. The Flight Stream 110 (if installed) supports properly equipped FIS-B capable Bluetooth devices

1.3 Required Data

All requited data is located in Appendix A of this document.

1.4 Referenced Garmin/Shadin documents:

Nomenclature Drawing Number Rev Date

GTX 3000 Transponder Installation Manual 190-00926-01 P Apr 2017

GDL 84/88 TSO Installation Manual 190-01122-00 L Nov 2017

Flight Stream 110/210 TSO Installation Manual 190-01700-00 F Aug 2017

ARINC to Manchester Converter M833520-00 A Dec 2017 1.5 Systems Control:

1.5.1 The GTX 3000 transponders replace the Honeywell transponder modules. All control is via the existing Honeywell RMU. No changes to operational control are imposed by this STC.

1.5.2 The Shadin AMC Converters convert RSB databus into ARINC 429. The AMC has no external control.

1.5.3 The GDL 88 is a GPS sensor and FIS-B UAT receiver. The GDL 88 has no external control.

1.5.4 The Flight Stream 110 is a Bluetooth repeater for the GDL 88 FIS-B products and has no external control.

1.6 Document administration:

1.6.1 This document will be revised by Elliott Aviation Engineering when revisions to descriptive or approval data warrant.

1.6.2 When this document is revised, all pages will be revised to indicate the current level. Chapter 10 will have its own revision status embedded. FAA approved revisions to the document will be distributed by mail to the applicable certifying authorities and operations of legally modified aircraft.

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1.7 Abbreviations and Definitions:

1090ES A transponder distinction. 1090 is the classic frequency of Secondary Surveillance Radar (SSR) transponders. The addition of “ES” at the end signifies that the transponder is equipped with Extended Squitter used by the ADS-B aircraft segment. Note that this class of transponder supports Class “A” airspace (altitudes above 18,000 feet) operations. Typically, no FIS-B or TIS-B functionality is included, compared to UAT.

AMM Aircraft Maintenance Manual DAH Design Approval Holder. The FAA term that includes STC holders such as Elliott Aviation. FIS-B Flight Information System broadcast. A radio frequency service that transmits weather and

aeronautical products, either by satellite or ground based systems. Refer to FAA Advisory Circular 20-149A for thorough explanation.

Latency The total time between when the position is measured and when the position is transmitted by the aircraft. A 14 CFR §91.227 performance requirement for ADS-B broadcast systems. The collection of specific equipment, interface and testing represented by this STC comprises an approved Latency

OEM Original Equipment Manufacturer. SBS Surveillance and Broadcast Service. Provided by the FAA. Ground based transmission at a

frequency of 978 MHz. SDA System Design Assurance. A 14 CFR §91.227 performance requirement for ADS-B broadcast

systems. The collection of specific equipment, interface and testing represented by this STC comprises an approved SDA.

UAT Universal Access Transceiver. A new device that supports the ADS-B aircraft segment at lower altitudes (below 18,000 feet) Allows smaller aircraft that operate below Class “A” airspace a more

AMC ARINC to Manchester Converter. Converts RSB databus to ARINC 429 and vice versa. 1.8 Precautions

Typical precautions are to be taken when accessing, removing, replacing, testing or inspecting these STC modifications. Specific precautions will be addressed in context throughout this document.

1.9 Units of measurement:

Non- metric. English units including Inches, feet, etc..

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Chapter 2 MAINTENANCE INSTRUCTIONS AND SCHEDULES:

2.1 Mandatory Replacements:

The GTX 3000 1090ES Transponder, GDL 88 GPS / UAT and optional Flight Stream 110 systems’ electrical components and installation is "On Condition" as determined by routine surveillance and there is no mandatory replacement time for any aspect of this system.

Refer to 560XL OEM WDM, Wiring – Maintenance Practices - chapter 20-10-01, for comprehensive wiring harness surveillance concerns.

See Chapter 10 Airworthiness Limitations for antenna installation inspections.

2.2 Recurring Maintenance:

2.2.1 Antenna Installations

Antenna installations require special inspection requirements and shall be maintained using Chapter 10 of this document.

2.2.2 Bulkhead Connector Installation

The bulkhead connector installation requires no special inspections requirements and shall be maintained using normal OEM maintenance manual procedures

2.2.3 Basic Mode S Transponder functions:

The installation of the GTX 3000 transponders must continue to meet the operational requirements of 14 CFR §§ 91.413, 91.215, and 91.217 and comply with the transponder system tests and inspections called out in 14 CFR § 43, appendix F.

The Honeywell SPZ 8000 altitude reporting equipment connected to the Garmin ADS-B transponders must comply with all applicable 14 CFR §§ 91.217, 91.411, and part 43 appendix E test and inspection requirements. If the altimetry system is compliant with the Reduced Vertical Separation Minimum (RVSM) standards, the requirements and tolerances stated in the approved RVSM maintenance program must be met. ADS-B installation does not alter these requirements.

2.2.4 ADS-B functions:

Compliance with aircraft equipage requirements imposed by the operational requirements of 14 CFR §§ 91.225 and 91.227 is achieved by these STC modifications. ADS-B Maintenance is "On Condition" as determined by routine surveillance during Mode S maintenance, by the flight crew as well the FAA Air Traffic Control system.

2.2.5 FIS-B functions:

This modification has an optional installation that supports ground based SBS FIS-B reception. UAT/FIS-B Maintenance is "On Condition”.

2.3 Setup and Configuration in Service

Note: There is NO Shadin AMC Converter Setup or Configuration required.

2.3.1 Garmin GDL 88 (Removal & Installation Only)

2.3.1.1 Confirm Garmin GDL 88 line replaceable unit part number from the Elliott Aviation wiring diagram 121-3832-E0560-000 located in Appendix A.

2.3.1.2 Obtain Elliott Configuration Instructions located in Appendix A. Read Section 5 of Configuration Instructions before proceeding with reconfiguration of the GDL 88. Take special note of the specific instructions for laptop computer interface, software effectivity and maintenance record details.

The GDL-88 will not function properly until software setup and configuration is accomplished.

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PRECAUTION:

Part number, configuration and electrical interface has been evaluated and approved for ADS-B Latency and SDA requirements. Any deviations

will require additional approval.

2.3.1.3 While using the Elliott Configuration Instructions Section 5, access to the GDL 88 Diagnostics

section is available. Real time GPS information is presented.

2.3.1.4 For setup and configuration, GPS reception must be confirmed using the diagnostic page. Use known GPS position to validate the GDL 88 diagnostic position readout such as the aircrafts navigation GPS. This information is presented on the Pro Line 4 cockpit control display unit under the IDX pages. Sample page below show typical GDL 88 GPS data.

2.3.1.5 After GPS reception is verified aircraft maybe returned to service.

2.3.1.6 For troubleshooting an in-service system, GPS activity may be confirmed using this diagnostic page. Lack of GPS position may be due to disconnect antenna coax, faulty antenna or faulty GDL 88. Neither the GDL 88 nor GPS antenna is field serviceable. If faulty, the GDL 88 line replaceable unit may only be repaired by Garmin. Replace a faulty GPS antenna with new.

Sample page:

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2.3.2 GTX 3000 Transponder (Removal & Installation Only)

2.3.2.1 Confirm Garmin GTX 3000 line replaceable unit part number from the Elliott Aviation wiring diagram 237-3832-E0560-000 located in Appendix A.

2.3.2.2 Obtain Elliott Configuration Instructions located in Appendix A. Read sections 2 and 4 of this document before proceeding with reconfiguring of the GTX 3000. Take special note of the requirements for laptop computer interface and software effectivity details.

The GTX 3000 will not function properly until software setup and configuration is accomplished.

PRECAUTION:

Part number, configuration and electrical interface has been evaluated and approved for ADS-B Latency and SDA requirements. Any deviations

will require additional approval.

2.3.2.3 While using the Elliott Configuration Instructions, access to the GTX 3000 status is available. Real

time information is presented.

2.3.2.4 For setup and configuration, the following items must be verified:

GPS Position Magnetic Weight on wheels is operating correctly. ADS-B mode indicated. 4096 code agrees with RMU ATC settings. Flight ID agrees with RMU ATC settings.(note: Dynamic (pilot set) Flight ID not available

on aircraft all.) TCAS status correct for aircraft. Most aircraft will have TCAS installed.

2.3.2.5 GPS position is confirmed using the “Info / ADS-B Out” page. Confirm GPS position from the GDL 88. Sample page follows to show typical GTX 3000 GPS source information.

2.3.2.6 Heading is confirmed using “Info / EHS” page. Confirm heading from the Pro Line 4 system. Sample page follows to show typical GTX 3000 Heading source information.

2.3.2.7 WOW, ADS-B mode, 4096 Code, Flight ID, and TCAS status is confirmed using the “Status” page in the GTX 3000 configuration tool. Sample page follows to show typical GTX 3000 “Status” page information.

2.3.2.8 After these have been verified perform 14 CFR 43 App F ¶ A-J.

2.3.2.9 The aircraft may now be returned to service.

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GTX 3000 Configuration GPS Sample page:

GTX 3000 Configuration Heading Sample page:

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GTX 3000 Configuration Status Sample Page:

2.3.2.10 For troubleshooting an in-service system, GPS activity may be confirmed using this “Info / ADS-B

Out” page. Lack of GPS position may be due to GDL 88 issues such as disconnect antenna coax, faulty antenna or faulty GDL 88. See 2.5 above. If the GDL 88 is not suspect, suspect RS 232 interface, configuration or GTX 3000 transponder. The GTX 3000 is not field serviceable. If faulty, the GTX 3000 line replaceable unit may only be repaired by Garmin.

2.3.2.11 For troubleshooting an in-service system, heading activity may be confirmed using this “Info / EHS” page. Lack of heading may be due to suspect 429 interface or configuration. The GTX 3000 heading source is the same as is used for the Flight Crew presentations The GTX 3000 is not field serviceable. If faulty, the GTX 3000 line replaceable unit may only be repaired by Garmin.

2.3.2.12 For troubleshooting an in-service system, the above may be confirmed using this “Status” page:

Weight on wheels is operating correctly. (squat switch, wiring and config). ADS-B mode indicated. (GDL 88, valid 429 data, wiring and config). 4096 code agrees with RMU ATC settings. Access the Pro Line control display unit and

exercise the squawk codes, the GTX 3000 should indicate correctly almost immediately. (wiring and config).

Flight ID agrees with RMU ATC settings. Select reversionary mode on the associated instrument panel to enable off-side control display unit GTX 3000 control. (RMU, wiring and config).

TCAS status correct for aircraft. Most aircraft will have TCAS installed. Confirm TCAS by visual observation of directional antennas and / or Pro Line control display unit TCAS page. Confirm no faults if TCAS installed and the ADS-B system is interfaced properly. (wiring and config).

2.3.2.13 The GTX 3000 is not field serviceable. If faulty, the GTX 3000 line replaceable unit may only be repaired by Garmin.

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2.3.3 GTX 3000 “N” number Registration change.

2.3.3.1 Obtain Elliott Configuration Instructions located in Appendix A. Using sections 2 and 4 of the Configuration Instructions Access the “Aircraft” tab on the GTX 3000 configuration tool. Modify the registration as needed and press enter to set the configuration. Shutdown the configuration tool and verify registration number change using IFR 6000 or similar transponder test set.

Sample page:

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2.4 GTX 3000 / GDL 88 / Shadin AMC Troubleshooting

Reported Issue Steps Transponder reporting:

Altitude

Observe or determine Honeywell flight displays for air data indications.

If present and correct, GTX 3000 suspect wiring or configuration.

Transponder reporting:

Heading

Observe or determine Honeywell flight displays for heading indications.

If present and correct, GTX 3000 suspect wiring or configuration.


ADS-B - Air

Observe or determine the ADS-B annunciator status.

If ADS-B annunciation OFF, suspect GTX 3000 in use.

If ADS-B annunciation ON, suspect GDL 88 LRU, wiring or configuration.


ADS-B - Surface

Not seen by flight crew, report will come from ATC Ground.

Same as above for ADS-B annunciation status.


Mode C

Observe or determine the Honeywell RMU annunciations.

If alternate GTX 3000 can be controlled using Honeywell RMU, suspect the GTX 3000 LRU.

TCAS Honeywell MFD: Observe status. Use the Test button on the front of the TCAS processor and verify errors displayed on the LED lights.

RMU display is dashed, in COMM & Transponder Segments

Swap #1 & #2 AMC IF fault follows LRU swap, replace AMC Unit. If fault does not follow check Wiring.

Commercial Off The Shelf ADS-B receiver devices are suitable for GO / NO GO confirmation that the GTX 3000 transponders are transmitting GPS position. HOWEVER, only approved calibrated test devices, such as the IFR 6000, may be used to confirm transponder output power and minimum trigger levels as well as diversity isolation.

To conduct an in-depth as-installed complete functional check including UAT, qualified test equipment such as the IFR 6000 will be required. Refer to specific test set instructions for operation and testing.

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Chapter 3 ACCESS:

3.1 Overview:

The information contained herein supplements the basic Maintenance Manuals only in those areas listed, when the aircraft is modified in accordance with Elliott Aviation drawings and diagrams specified in Section 1.3 of this document.

3.1.1 GTX 3000s are located in the forward right avionics bay upper equipment shelf. A configuration module is also located inside the J3302 connectors.

3.1.2 GDL 88 is located in the forward right avionics bay upper equipment shelf. A configuration module is also located inside the J811 connector.

3.1.3 AMCs are located in the forward right and left avionics bays upper equipment shelf.

3.1.4 Flight Stream 110 (if installed) is located on the outboard side of the Co-Pilot’s chart holder cabinet.

3.1.5 ADS-B 1/2 annunciator is located in the cockpit panel

3.1.6 GA 36 GPS Antenna is located on top of the aircraft fuselage above the cabin headliner FS 172.00-187.00 left of center line

3.1.7 UAT Antenna is located on the belly of the aircraft fuselage below the left forward avionics bay FS 67.10-75.80

3.1.8 Wiring follows existing aircraft wire routes in the nose and cockpit area.

3.2 Equipment and wiring access:

No new access is required from the installation of this modification. Access to all equipment and wiring is gained using existing aircraft maintenance manual techniques.

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3.2.1 GDL 88 and GTX 3000 rack mounted Line Replaceable Units (LRU):

3.2.1.1 No hand tools are required. The coax and wire harness connectors knurled and are intended to be removed and tightened by hand. Should assistance in the form of pliers be used, take care to not distort or over tighten.

3.2.1.2 Observe typical avionics systems precautions including:

Coax connectors. Do not bend or kink the coax, avoid bending the center pin, inspect for debris prior to reinstallation.

Wire harness connectors. Disengage associated circuit breakers first. Use care when handling connectors to ensure shield drain integrity, alternate locking screw tightening sequence and ensure proper alignment during re-installation.

3.2.1.3 Each LRU rack uses a lock down mechanism to secure the LRU in the rack.

To remove, pull while twisting counter clockwise until the LRU hook is clear. The LRU should now be free.

To install, align the LRU in the rack. Slide the LRU until the foot is firmly engaged in the rack. Lift the lockdown mechanism over the LRU hook. Tighten firmly until secure.

Conduct necessary checkout procedures described elsewhere in this document.

3.2.1.4 Configuration Modules are located inside the J881 GDL 88 connector and inside each J3302 GTX 3000 connector. Hand tools are required to gain access inside the backshell. Retain hardware after removal. To install secure retained hardware and Reconnect to applicable unit. Conduct necessary checkout procedure described elsewhere in this document.

3.2.2 Flight Stream 110 (if installed) Line Replaceable Unit (LRU), AMC, GPS and UAT antennas:

Hand tools are required. These components are secured with screws and nuts. To remove, remove this hardware and retain. Disconnect the electrical / coax connector. To install, secure with the retained hardware. Reconnect electrical / coax connector.

3.2.3 ADS-B 1/2 Annunciator:

Hand tools are required. This component is secured with locking paws. To gain access to these locking paws gently pull the annunciator lens out. Screws located inside loosen the upper and lower screw. Once locking paw has been loosened pull annunciator body out of the annunciator housing and instrument panel. To install insert annunciator body back through the instrument panel and annunciator housing. Tighten locking paws until annunciator body and housing are tight against the instrument panel, then press annunciator lens firmly into the annunciator body. Conduct necessary checkout procedures described elsewhere in this document.

Chapter 4 LIFTING AND SHORING: Not applicable this modification.

Chapter 5 LEVELING AND WEIGHING:

Not applicable this modification.

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Chapter 6 TOWING AND TAXIING:


Chapter 7 PARKING AND MOORING: Not applicable this modification.

Chapter 8 PLACARDS AND MARKINGS:


Chapter 9 SERVICING:


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Elliott Aviation Technical Products Development, Inc. Report No.: ICA-3832-560 6601 74th Ave Building A Revision: A Milan, IL 61264 Dated 12/11/2018 A1


APPENDIX A ATTACHMENTS

All documents listed in the table below must be attached to this document and maintained in accordance with Chapter one.

ATTACHMENTS

DOCUMENT NO. TITLE REV PAGES

CFG-3832-560 Configuration Instructions for Garmin ADS-B Out System Installation D 14

237-3832-E0560-000 Garmin ADS-B Out System Electrical Installation D 8

237-3832-M0560-050 Wire Routing Installation IR 4

237-4071-E0560-000 Garmin GTX 3000 System Electrical Installation B 8

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Elliott Aviation Technical Products Development, Inc. Report No.: WBE-3832-560 6601 74

th Ave Building A Revision: A

Milan, IL 61264 Dated 01/15/2018 1 of 4

Weight and Balance Effects For Garmin ADS-B System Installation

Weight and Balance Effects

For




Elliott Aviation Technical Products Development, Inc. reserves the copyright of all information and illustrations in this publication which is

provided in confidence and which may not be used for any purpose other than for which it was originally supplied. The publication may not

be reproduced in part or in whole without the consent in writing of Elliott Aviation Technical Products Development, Inc.

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Milan, IL 61264 Dated 01/15/2018 2 of 4


REVISIONS PAGE



A Incorporated ODA comments 2, 4 01/15/2018

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Milan, IL 61264 Dated 01/15/2018 3 of 4


TABLE OF CONTENTS

COVER PAGE ....................................................................................................... 1

REVISIONS PAGE ................................................................................................ 2

TABLE OF CONTENTS ......................................................................................... 3

1 Purpose .......................................................................................................... 4

2 Removed Equipment ....................................................................................... 4

3 Added Equipment ............................................................................................ 4

4 Optional Added Equipment .............................................................................. 4

5 Weight and Balance Effects ............................................................................. 4

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Milan, IL 61264 Dated 01/15/2018 4 of 4


1 Purpose

The purpose of this document is to illustrate the changes in the weight and balance after modification installing Garmin ADS-B system. This data is supplied to support updating the aircraft’s actual weight and balance records.

2 Removed Equipment

QTY Part Number Description Unit Weight

(lbs) Total Weight

(lbs) Arm (in) Moment

1 7001840-936 RT-300 Radalt 4.6 -4.6 68 -312.8 Total -4.6 -312.8

None

3 Installed/Relocated Equipment


(lbs) Total Weight


1 011-01997-00 #1 GTX3000 6 6 68 408 1 7001840-936 RT-300 Radalt 4.6 4.6 81.89 376.7 1 011-01997-00 #2 GTX3000 6 6 84.26 505.56 1 011-02370-00 GDL88 4.1 4.1 81.83 201.72 1 833520-00 #1 AMC .9 .9 66.9 60.21 1 833520-00 #2 AMC .9 .9 67.17 60.54 1 013-00244-00 GA36 GPS Antenna .47 .47 177.57 83.46 1 CI 110-40-30 UAT Antenna .25 .25 78.61 19.65

Total 23.22 1715.84

4 Optional Added Equipment


(lbs) Total Weight


1 011-03257-00 Flight Stream 110 .27 .27 177.68 47.97 Total .27 47.97

5 Weight and Balance Effects

Part numbers of removed equipment to be verified with actual aircraft equipment list during modification.

Weight (lbs)

Moment

Removed Equipment -4.6 -312.8

Added / Relocated Equipment without options

23.22 1715.84

Added / Relocated Equipment

with options 23.49 1763.81

Total without options 18.62 1403.04

Total with options 18.89 1451.01

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Elliott Aviation Technical Products Development, Inc. Report No.: ELA-3832-560 6601 74th Ave Building A Revision: IR Milan, IL 61264 Dated 01/08/2018 1 of 6

Electrical Load Analysis For Garmin ADS-B System Installation

Electrical Load Analysis

For





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REVISIONS PAGE


IR Initial Release ALL 01/08/2018

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TABLE OF CONTENTS COVER PAGE .......................................................................................................... 1 REVISIONS PAGE.................................................................................................... 2 TABLE OF CONTENTS ............................................................................................ 3 1 Purpose and scope: ............................................................................................. 4

2 Electrical System Capacity Analysis: ................................................................... 4

3 Conclusion:........................................................................................................... 6

A1 Textron AMM 560XL ELA .................................................................................. A1

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1 Purpose and scope: This document will provide the electrical load change of all the removed equipment and all the installed equipment associated with the Garmin ADS-B System installation in support of MDL-3832-560 for Textron Aviation Model 560XL. This is based off the Textron Aviation AMM ELA and made current for 560-5628.

Due to the nature of ADS-B, all phases of flight as well surface operations are assumed. Since the ADS-B requirements involve use of the transponder during surface operations, no idle (quiescent) values are used.

The GTX 3000 switched output DC is not used in this installation.

2 Electrical System Capacity Analysis: 2.1 Equipment details:

Avionics Emergency Bus Load Change (amps)

Circuit Breaker Size

Removed Equipment

None Installed Equipment:

Shadin #1 AMC [+] .2 A NA*

Total Avionics Emergency Bus Change [+] .2 A

*When powered by the Avionics Emergency Bus, Shadin #1 AMC is protected by the existing #1 COMM 1 circuit breaker (10A).

Left Avionics Bus Load Change (amps)


Removed Equipment

Honeywell #1 XPDR [-] .95 A 5A* Installed Equipment:

Garmin GTX 3000 # 1 [+] 1.6 A 5A*

Shadin #1 AMC [+] .2 A NA**

Total Left Avionics Bus Change [+] 0.4 A

*The existing Honeywell #1 XPDR circuit breaker (5A) is retained and re-purposed for the Garmin GTX 3000 #1 circuit breaker (5A).

**When powered by the Left Avionics Bus, Shadin #1 AMC wiring is protected by the Garmin GTX 3000 #1 circuit breaker (5A).

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Right Avionics Bus Load Change (amps)


Removed Equipment

Honeywell #2 XPDR [-] .95 A 5A Installed Equipment:

Garmin GTX 3000 # 2 [+] 1.6 A 5A*

Garmin GDL 88 [+] 0.71 A 1A

Shadin #2 AMC [+] 0.2 A NA**

Garmin Flight Stream 110 (optional) [+] 0.06 A 1/2A

Total Right Avionics Bus Change (w/ Flight Stream 110 installed) [+] 1.17 A

Total Aircraft Load Change (w/ Flight Stream 110 installed) [+] 2.67 A

Total Right Avionics Bus Change (w/o Flight Stream 110 installed) [+] 1.11 A

Total Aircraft Load Change (w/o Flight Stream 110 installed) [+] 2.61 A

*The existing Honeywell #1 XPDR circuit breaker (5A) is retained and re-purposed for the Garmin GTX 3000 #1 circuit breaker (5A).

**When powered by the Left Avionics Bus, Shadin #1 AMC wiring is protected by the Garmin GTX 3000 #1 circuit breaker (5A).

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3 Conclusion: The result of the Garmin ADS-B System installation is a total net gain of 2.67 Amp to the aircraft generation system. In accordance with the Textron Aviation 560XL AMM the worst case amperage draw is 567.88 amps which occurs during night takeoff in non-icing conditions. The new total aircraft load is 570.55 amps during a night takeoff in non-icing conditions. This total is still less than the total rated maximum load capacity of 600 amps the aircraft is capable of and within electrical load safety margins. During single generator icing operation the new total maximum load went from 356.92 amps to 359.59 amps. This has no effect on the existing aircraft procedure during single generator operation, to turn the interiors master switch off. This shed 135.19 amps and brings the aircraft total to 224.4 amps which is below the 300 amp aircraft single generator capacity and within the electrical load safety margin.

The result of the Garmin ADS-B system installation is a total net gain of .2 Amps to the Emergency bus. In accordance with the Textron Aviation 560XL AMM the original Emergency Bus total is 29.94 amps. The new total Emergency Bus load is 30.14 amps. Using the calculations below the total Emergency Bus Operating time is now 51.30 minutes which is above the required 30 minutes.

40 Amp / hour Battery Capacity

Average Demand ................................ =Battery total load ............................ (29.94)

Amp Minutes in 30 Minutes ................. =Average demand x 30 minutes ...... (29.94 x 30=898.2)

Amp Hour Required ............................. =Amp Minutes in 30 Minutes ÷ 60 .... (898.2÷60=14.97)

Battery Rated Capacity ....................... =Amp Hour Required÷0.8................. (14.97÷0.8=18.71)

Time on Emergency Bus Operation .... =Battery Capacity ÷Battery Rated Capacity x 30 51.30

(40 amp-hr x 0.8 ÷18.71) x 30=51.30 minutes.

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Elliott Aviation Technical Products Development, Inc. Report No.: ELA-3832-560 6601 74th Ave Building A Revision: IR Milan, IL 61264 Dated 01/08/2018 A1 of A14


Textron Aviation

Aircraft Maintenance Manual

Electrical Load Analysis

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