chapter 34 flight & navigation instruments - … ack a-30 altitude encoder ... removal and...

FBA-2C1, FBA-2C2, FBA-2C3 Found Aircraft Canada FBA-2C4, FBA-2C3T, FBA-2C4T Maintenance Program FAC2-M200

34-Title January 23, 2012

Chapter 34

FLIGHT & NAVIGATION

INSTRUMENTS


34-Title January 23, 2012

INTENTIONALLY LEFT BLANK


34-LOEP Page 1 January 23, 2012

LIST OF EFFECTIVE PAGES

Chapter Section Page No. Date

34 34-Title 1 January 23, 2012

2 January 23, 2012

34 -LOEP 1 January 23, 2012

2 January 23, 2012

3 January 23, 2012

4 January 23, 2012

34 -TOC 1 January 23, 2012

2 January 23, 2012

34-00 1 August 5, 2010

2 July 28, 2008

3 July 28, 2008

4 July 28, 2008

5 August 5, 2010

6 August 5, 2010

7 August 5, 2010

34-11 1 July 28, 2008

2 July 28, 2008

3 July 28, 2008

4 July 28, 2008

5 July 28, 2008

6 July 28, 2008

7 July 28, 2008

8 July 28, 2008

9 August 5, 2010

10 August 5, 2010

11 August 5, 2010

12 July 28, 2008

13 July 28, 2008

14 July 28, 2008

15 July 28, 2008

16 July 28, 2008

34-12 1 July 28, 2008

2 July 28, 2008

34-13 1 July 28, 2008

2 July 28, 2008





34 34-14 1 July 28, 2008

2 July 28, 2008

34-15 1 July 28, 2008

2 July 28, 2008

34-18 1 July 28, 2008

2 July 28, 2008

3 July 28, 2008

4 July 28, 2008

5 July 28, 2008

6 July 28, 2008

7 July 28, 2008

8 July 28, 2008

34-21 1 July 28, 2008

2 July 28, 2008

34-22 1 July 28, 2008

2 July 28, 2008

3 July 28, 2008

4 July 28, 2008

5 July 28, 2008

6 July 28, 2008

7 July 28, 2008

8 July 28, 2008

34-23 1 July 28, 2008

2 July 28, 2008

3 July 28, 2008

4 July 28, 2008

5 July 28, 2008

6 July 28, 2008

34-24 1 July 28, 2008

2 July 28, 2008

34-45 1 January 23, 2012

2 January 23, 2012

3 January 23, 2012

4 January 23, 2012

5 January 23, 2012

6 January 23, 2012





34 23-46 1 January 23, 2012

2 January 23, 2012

34-51 1 July 28, 2008

2 July 28, 2008

3 July 28, 2008

4 July 28, 2008

5 July 28, 2008

6 July 28, 2008

34-52 1 January 23, 2012

2 July 28, 2008

3 January 23, 2012

4 July 28, 2008

5 July 28, 2008

6 July 28, 2008

7 July 28, 2008

8 January 23, 2012

9 January 23, 2012

10 January 23, 2012

11 July 28, 2008

12 July 28, 2008

13 January 23, 2012

14 July 28, 2008

15 July 28, 2008

16 July 28, 2008

17 January 23, 2012

18 January 23, 2012

19 January 23, 2012

20 January 23, 2012

21 January 23, 2012

22 January 23, 2012

34-54 1 July 28, 2008

2 July 28, 2008

34-55 1 July 28, 2008

2 July 28, 2008

3 July 28, 2008

4 July 28, 2008





34 34-56 1 July 28, 2008

2 July 28, 2008

34-59 1 July 28, 2008

2 July 28, 2008

34-70 1 August 5, 2010

2 August 5, 2010

3 August 5, 2010

4 August 5, 2010

5 August 5, 2010

6 August 5, 2010

7 August 5, 2010

8 August 5, 2010

9 August 5, 2010

10 August 5, 2010

11 August 5, 2010

12 August 5, 2010

34-70 13 August 5, 2010

14 August 5, 2010

15 August 5, 2010

16 August 5, 2010

17 August 5, 2010

18 August 5, 2010

19 August 5, 2010

20 August 5, 2010

21 August 5, 2010

22 August 5, 2010

23 August 5, 2010

24 August 5, 2010


34-TOC Page 1 January 23, 2012

TABLE OF CONTENTS

Chapter Section Title 34 Flight & Navigation Instruments 34-Title Title Page 34 -LOEP List of Effective Pages 34 -TOC Table of Contents 34-00 General 34-11 Pitot Static 34-11-05 Pitot Head-Static System (2C3 & 2C4) 34-11-10 Head, Mast & System (2C1 & 2C2) 34-11-11 System Maintenance 34-11-12 Pitot/Static Test Set 34-11-13 Pitot Leak Check 34-11-14 Static Leak Check 34-11-15 Pitot & Static Line Purging 34-11-20 Alternate Static Port 34-12 OAT 34-13 Vertical Speed Indicator 34-14 Airspeed Indicator 34-15 Barometric Altimeter 34-18 Stall Warning 34-21 Attitude Gyro 34-22 Directional Gyros 34-22-01 Vacuum Directional Gyro 34-22-02 Pictorial Navigation System 34-23 Standby Compasses 34-23-01 Airpath Compass 34-23-02 SIRS Navigation Compass 34-24 Turn and Bank or Turn Coordinator Indicator 34-45 Traffic System-Garmin GTS 8XX (2C3 & 2C4) 34-46 Garmin GDL 69/69XM Satellite Radio(2C3 & 2C4) 34-51 Distance Measuring Equipment 34-52 ATC Transponder Systems 34-52-05 Garmin GTX 330 Digital Transponder 34-52-06 Garmin GTX 33 Digital Transponder (2C3 & 2C4) 34-52-01 ACK A-30 Altitude Encoder 34-52-02 GTX 327A Garmin Digital Transponder 34-52-03 Bendix/King KT-76A Transponder 34-52-04 Bendix/King KT-76C Digital Transponder 34-54 VHF Omni-Directional Range Finding Equipment 34-55 Bendix/King KR 87 Automatic Direction Finding Equipment 34-56 Global Positioning Systems


34-TOC Page 2 January 23, 2012

TABLE OF CONTENTS

Chapter Section Title 34-59 TIB 2000 Tracking System 34-70 Garmin G500 or G 600 Electronic Flight Information System


34-00 Page 1 August 5, 2010

34 FLIGHT & NAVIGATION INSTRUMENTS

34-00-00 GENERAL This chapter describes the navigation systems, units, and components which provide aircraft navigational information. All the navigational instruments are located on the instrument panel. The instrument panel is installed in modular sections to permit easy access to instruments and switches without the need to remove the entire instrument panel. Refer to Chapter 31 for panel removal and installation. During the manufacture of the different models there have been several different instrument panel layouts. Refer to the following figures for the applicable layout:

FBA-2C1 Figure 34-00-01 FBA-2C1 (with Mod 1043) Figure 34-00-02 FBA-2C2 Figure 34-00-03 FBA-2C3/2C4 (Analog instruments) Figure 34-00-04 FBA-2C3/2C4 (EFIS Panel) Figure 34-00-05


34-00 Page 2 July 28, 2008

R

OFF

L BOTH

START

RED

FOR FLOAT EQUIPPED AIRCRAFTWATER RUDDER ALWAYS UP

EXCEPT FOR TAXIING

34

The markings and placards installed in this airplanecontain operating limitations which must be compliedwith when operating this airplane in the Normal Category.Other operating limitations which must be complied with when operating this airplane in this category are contained in the Airplane Flight Manual.

Normal Category: No acrobatic maneuvers, including spins, approved.

Flight into known icing conditions prohibited.This airplane is certified for the following flight operations: DAY-VFRMANEUVER SPEED = 119 KIAS

MASTERON

OFF

ALTERNATORENABLE

OFF

NAUX.FUEL

EGT

OIL TEMP.OIL PRESS.

CYL. TEMP.

OFF

NAV.LTS

OFF

AUX.FUEL

STROBELIGHT

OFF OFF

PITOTHEAT

OFF

AVIONICSMASTER

LAND.LTS

OFF

TAXI LIGHT

OFF OFF

BACKUPPOWER

DO NOT RELY ON FUEL FLOW INSTRUMENTTO DETERMINE FUEL LEVEL IN TANKS

LEFT FUEL RIGHT FUEL

FOUNDAIRCRAFTCANADA

AMPS

BUSH HAWK

LAND.LTS

STROBELIGHT

NAV.LTS

TAXILTS

PITOTHEAT

VOLT.REG.

IGN. STALLWARN.

ALT.

FOR AVIATION EMERGENCY USE ONLYUNAUTHORIZED OPERATION PROHIBITED

INTERCOM

RADIO

VOLTAGE

UNDEROVER

RED RED

AUX HD PHONE

INTERCOM

TACH.

RADIO

INSTR.CLUSTER

To apply parking brakedepress brake pedals

and pull parking brake handleTo release parking brake

depress brake pedalsand push parking brake handle

Parking Brake Handle

TURN &BANK

MAN.PRESS.

FUELFLOW

NO SMOKINGFASTEN SEATBELTS

FIRE EXTINGUISHER LOCATED UNDER PILOT SEAT

Figure 34-00-01 Instrument Panel (FBA-2C1)


34-00 Page 3 July 28, 2008

Figure 34-00-02 Instrument Panel (FBA-2C1 / MOD-1043)


34-00 Page 4 July 28, 2008

2325

Figure 34-00-03 Instrument Panel (S/N 40 +)


34-00 Page 5 August 5, 2010

1. Airspeed Indicator2. Attitute indicator3. Altimeter4. Turn & Bank Indicator5. Directional Gyro6. Vertical Speed Indicator7. Blanking Plate8. Stall Warning Light19. Flap Position Indicator10. Flap Switch11. Blanking Plate12. Throttle Control Knob13. Propeller Pitch Control Knob14. Mixture Control Knob15. Cabin Heat Control16. Trim Indicator Dimmer Switch17. Defrost Control18. Trim Indicator

Figure 34-00-04 Instrument Panel (2C3 & 2C4)


34-00 Page 6 August 5, 2010

MVP-50:

A. TachometerB. C.H.T.C. E.G.T.D. Manifold PressureE. Fuel FlowF. Oil TemperatureG. Oil PressureH. Fuel QuantityI. Instrument VaccumJ. VoltsK. AmpsL. O.A.T.

353334

32

22

22

2120

26 31

30

29

282726

24

23

17

15

1412 13

MVP-50

1098

1111

7

1

Absence of light during first3 seconds of test indicatespossible G switch failure

FOR AVIATION EMERGENCYUSE ONLYUNAUTHORIZED OPERATION PROHIBITED

X2117

CAUTION:

36

19

18

DOWN6

UP4 0

ELEV. TRIM

2

3

PFD MFD

19. ELT Remote Switch20. Check Engine Light21. Engine Monitor Voice Alarm Switch22. Eye Ball Vent23. DC Outlet24. Circuit Brakers25. Dimmer Switches26. Toggle Switches27. Magnetic Compass28. Post Light29. Over/Under Voltage Indicator Light30. Ignition Switch31. Parking Brake Handle32. Alternate Air Control33. Electric Rudder Trim Switch34. Electric Rudder Trim Indicator35. Electric Cowl Flap Indicator36. Alternate Static Port Switch

1. Stby Airspeed Indicator2. Stby Attitute indicator3. Stby Altimeter4. Turn & Bank Indicator (PFD)5. H.S.I. (PFD)6. Vertical Speed Indicator (PFD)7. Blanking Plate (T.C. For A.P.)8. Stall Warning Light9. Flap Position Indicator10. Flap Switch11. Blanking Plate12. Throttle Control Knob13. Propeller Pitch Control Knob14. Mixture Control Knob15. Cabin Heat Control16. Indicator Dimmer Switch17. Defrost Control18. Trim Indicator

Figure 34-00-05 EFIS Panel (2C3 & 2C4)


34-11 Page 1 July 28, 2008

34-11 PITOT STATIC The 2C1 and 2C2 aircraft utilize a heated pitot/static head and mast installed in the Port wing. Pitot/static flexible lines then route through the wing and fuselage to the various instruments. Pitot ram air is routed to the airspeed indicator and atmospheric pressure is routed to the airspeed, altitude and vertical speed indicators. The 2C3 and 2C4 aircraft utilize a heated L-type pitot head mounted on the underside of the “starboard” wing just inboard of rib #9 at wing station 115. There are 2 static ports, one on either side of the aft fuselage at fuselage station 189. In addition, there is an alternate static port located in the cabin directly above the trim indicator. Note: Anytime a Pitot/Static system is disrupted a Pitot/Static leak check is required.

34-11-05 Pitot-Static System (2C3 & 2C4)

A. Pitot Head Removal and Installation:

Refer to Figure 34-11-02 Note: Ensure power to the pitot static head heater is turned off. Step 1 Remove access panel just aft of the pitot head (optional). Step 2 Remove screws securing pitot head to the base. Step 3 Carefully pull down the pitot head to gain access to the pitot line and electric

wires. Step 4 Disconnect pitot line and wires. Cap open pitot lines to prevent contamination. Step 5 Pitot head is now free. To install Pitot head reverse above steps and carry out pitot/static system leak test as outlined in this chapter and check operation of pitot heater.

B. Static Port Removal and Installation:

Refer to Figure 34-11-02 Step 1 Gain access to inside of aft fuselage through the rear baggage compartment. Step 2 Remove tie-wraps securing the tubing to the static port spigot. Tie-wraps are

scrap and must be replaced on installation. Step 3 Gently remove the tube off the spigot. Step 4 Remove the nut and lock washer securing the static port to the skin. Step 5 The static port is now free. To install static port, reverse above steps and carry out pitot/static system leak test as outlined in this chapter.


34-11 Page 2 July 28, 2008

34-11-10 Head, Mast & System (2C1 & 2C2)

The pitot/static head located in the Port wing at Station 128 is heated with 28VDC. The aluminium tubing which is connected to the pitot/static head runs through the pitot/static mast into the wing where it is routed behind the fuel tank and into the fuselage. The tygon flexible line runs over the left hand side door and behind the instrument panel where the pitot line connects to the airspeed indicator, and the static line connects to the airspeed indicator, altimeter and the vertical speed indicator. See Figure 34-11-01. Pitot/Static Head Removal and Installation (2C1 & 2C2) Note: Ensure power to the pitot static head heater is turned off.

Step 1. Remove screws which hold the head to the mast. Step 2. Gently pull head out of the mast until the lines are exposed. Do not pull the head

out of the mast to far as damage to the pitot/static lines may occur. Step 3. Remove the lines from the head one at a time and label lines for reinstallation.

Cap lines and fittings. The lines may have to be secured or they may slip back inside the mast.

Step 4. Remove electrical leads from head, label the leads, cap connections. Head is now

free. To install Pitot head reverse above steps and carry out pitot/static system leak test as outlined in this chapter and check operation of pitot heater.

34-11-11 System Maintenance

Cleanliness of the system is critical as deterioration of the system may result in erroneous reading of the Airspeed, Altitude and Vertical Speed. When the system is disrupted, for any reason, a leak check must be carried out. Note: When doing maintenance on pitot/static system, cap all line openings to prevent

contamination. Any installation of pitot/static ports covers must be marked, or identified, by a high visibility colour, and that warning flag has been securely attached.


34-11 Page 3 July 28, 2008

34-11-12 Pitot/Static Test Set

It is recommended to use a pitot/static test set to carry out any instrument checks or leak checks on the pitot static system. Follow the test set manufacturers instructions to carry out any tests. If a test set is not available, carry out checks per 34-11-13 & 14. Precautions in testing; Observe the following precautions in all pitot-static system leak testing:

Perform all other work and inspections before leak testing. Be certain that no leaks exist in the test equipment. Run full range tests only if you are thoroughly familiar with the aircraft instrument

system and the test equipment. Pressure in the pitot system must always be equal to or greater than that in the static

system. A negative differential pressure across an airspeed indicator can damage it. The rate of change of the pressure applied should not exceed the design limit of any pitot

or static instrument connected to the system. After the conclusion of the leak test, be certain that the system is returned to its normal

flying configuration, such as removing tape from static ports and pitot tube drain holes, etc. Note: It is advisable to clearly mark all static ports and pitot tubes with contrasting

colour streamer or “Remove Before Flight” tag to avoid inadvertently leaving areas covered up before the next flight.


34-11 Page 4 July 28, 2008

1. shock−mounted instrument panel2. altimeter3. vertical speed indicator4. airspeed indicator5. static pressure line6. Pitot pressure line7. static line (altimeter to vsi)8. static line (airspeed ind. to altimeter)9. tee fitting10. nipple11. rubber grommet12. coupling13. pitot static tube an5816−214. pitot mast15. pitot mast bracket16. switch & circuit braker panel17. pitot heat circuit breaker18. pitot heat switch19. pitot heat wiring

Figure 34-11-01 Pitot-Static System Installation (2C1 & 2C2)


34-11 Page 5 July 28, 2008

Pitot line

ElectricalWires



34-11 Page 6 July 28, 2008

Bolt

Static Line



34-11 Page 7 July 28, 2008

Altimeter

V.S.I.

Static Source

PitotSource



34-11 Page 8 July 28, 2008

Figure 34-11-05 Pitot-Static System Schematic (2C3 & 2C4)


34-11 Page 9 August 5, 2010

Figure 34-11-06 EFIS Pitot-Static System Installation (2C3 & 2C4)


34-11 Page 10 August 5, 2010

Figure 34-11-07 EFIS Pitot-Static System Installation (2C3 & 2C4)


34-11 Page 11 August 5, 2010

Figure 34-11-08 EFIS Pitot-Static System Schematic (2C3 & 2C4)


34-11 Page 12 July 28, 2008

Figure 34-11-09 Pitot-Static System Electrical Schematic (2C3 & 2C4)


34-11 Page 13 July 28, 2008

34-11-13 Pitot Leak Check

Apply pressure to cause the airspeed indicator to indicate 150 knots (differential pressure 1.1 inches of mercury or 14.9 inches of water), hold at this point and clamp off source of pressure. After 1 minute, the leakage should not exceed 10 knots (differential pressure of approximately 0.15 inches of mercury or 2.04 inches of water).

34-11-14 Static Leak Check

Apply a vacuum equivalent to 1,000 feet altitude above the field elevation, (differential pressure of approximately 1.07 inches of mercury or 14.5 inches of water) and hold. After one minute, check to see that the leakage has not exceeded the equivalent of 100 feet of altitude (decrease in differential pressure of approximately 0.105 inches of mercury or 1.43 inches of water). NOTE: FBA-2C3 and FBA-2C4 type aircraft are Factory tested at 18500 feet for a leak rate of< 100 feet/min.

34-11-15 Pitot & Static Line Purging

It may be necessary from time to time to clear the pitot/static lines using pressure. CAUTION: Never leave instruments connected to the system when purging lines. CAUTION: Never blow air through the line toward the instruments as it will damage the

instrument. Blow clean air from the disconnected line at the instrument towards the Pitot/Static head. Either dry air or nitrogen is recommended. Shop air is acceptable. Note: Shop air contains moisture. Check drains after use.


34-11 Page 14 July 28, 2008

34-11-20 Alternate Static Port

The alternate static switch, if installed, is located on the console just above the trim position indicator. Refer to Figure 34-11-07. It provides an alternate atmospheric pressure source to the airspeed indicator, altimeter, and vertical speed indicator in case of failure of the main atmospheric pressure source. The alternate source is activated by lifting the switch leaver. Note: For 2C3 & 2C4 aircraft, the outlet of the alternate static port has been provisioned with a

¼” barbed fitting. The alternate static port outlet is located on the port side of the control console. (See Figure 34-11-10).

Alternate Static Port Removal Step 1. To remove the alternate static port switch, set the switch to the open position, lift the

switch handle up. Step 2. Remove the 11/16” panel nut and the handle positioner to free the switch. Step 3. Push the switch back into the panel. Reaching up under the flight panel locate the

connected ¼” “Tygon” tube and use it to pull the switch up out of the control consol. Step 4. The “Tygon” tube is fastened to the switch with tie wraps. Cut these tie wraps to free

the switch for removal.


34-11 Page 15 July 28, 2008

Alternate Static Port Installation

Step 1. To install the alternate static switch port, remove the fourteen (12) AN525 screws holding the trim wheel cover. (Note the position of the trim indicator so that it may be correctly repositioned when reinstalling the trim wheel cover).

Step 2. Install the ¼” “Tygon” tube to the static port and secure with 3 tie wraps. After the ¼” “Tygon” tube is secured to the static port switch, route the switch as indicated on diagram.

Step 3. Attach the switch to the trim wheel cover with the panel nut. Be certain to relocate the handle positioner at this time.

Step 4. Reinstall the trim wheel cover. Step 5. Confirm the correct position of the trim indicator by moving the trim wheel from full

nose up to full nose down positions. Check for correct direction of travel, correct range of travel, and any binding or other noises from system.

Step 6. The aircraft will now require a static leak check per Maintenance Manual Chapter 34-11-14.

Continued Airworthiness Once per calendar year, perform a static leak check per MM CH 34-11-14. Cycle the alternate static port switch and again perform the static leak check.


34-11 Page 16 July 28, 2008

1

To Tee

Figure 34-11-10 Alternate Static Port


34-12 Page 1 July 28, 2008

34-12 OAT The outside air temperature gauge in 2C1 and 2C2 aircraft is located on the co-pilot side window, see Figure 34-12-01. The outside air temperature gauge in 2C3 and 2C4 is part of the MVP-50 monitoring system. It includes a temperature probe mounted on the bottom of starboard wing just outboard of Rib #1 and wire harness connecting the probe and MVP-50 encoder (EDC-33P), see Figure 34-12-02. Removal and Installation (2C1 and 2C2) Step 1. Remove the black hex shaped probe shroud by unscrewing it counter clockwise. Step 2. The OAT may now be removed from the window. To install the OAT reverse the above steps. Note the gasket and washer installations. Hand tight pressure is adequate.

Figure 34-12-01 OAT Installation (2C1 &2C2)


34-12 Page 2 July 28, 2008

MVP-50P Temperature Probe Removal and Installation (2C3 and 2C4) Step 1. Remove access panel WS15. Reference Figure 06-30-02. Step 2. Remove jam nut and crush washer securing the temperature probe. Step 3. Reach in through the access cut-out and pull the probe to clear the skin. Step 4. Disconnect wire harness at the connector. Step 5. The temperature probe is now free. To install the OAT reverse the above steps. Replace crush washer.

YELLOW WIRE

RED WIRE

Connector

OAT Probe

NutCrush Washer

Wing SkinTo

Remove

Connetor

Fire Wall

EDC−33P

OAT Wire

OAT Probe

EDC−33

Figure 34-12-02 OAT Installation (2C3 &2C4)


34-13 Page 1 July 28, 2008

34-13 Vertical Speed Indicator The Vertical Speed Indicator is located on the flight instrument panel assembly. Removal and Installation Step 1. Remove the screws securing the flight panel. Refer to 31-11. Gently pull panel away

from structure taking care of lines and wires behind. Step 2. Remove the screws which hold the instrument to the panel. Step 3. Pull instrument from the panel. Step 4. Remove the static line from the instrument. The instrument is now free. Cap all lines

and fittings. To install Vertical Speed Indicator reverse above steps and carry out system leak check


34-13 Page 2 July 28, 2008

Figure 34-13-01 VSI Installation


34-14 Page 1 July 28, 2008

34-14 AIRSPEED INDICATOR The Airspeed Indicator is located on the flight instrument panel. Removal and Installation Step 1. Remove the screws securing the flight panel. Gently pull panel away from structure

taking care of lines and wires behind. Step 2. Remove the screws which hold the instrument to the panel. Step 3. Pull instrument from the panel. Step 4. Remove the Pitot and Static lines from the instrument. The instrument is now free.

Label lines for installation. Cap all lines and fittings. To install Airspeed Indicator reverse above steps and carry out system leak check

Figure 34-14-01 Airspeed Indicator Installation


34-14 Page 2 July 28, 2008



34-15 Page 1 July 28, 2008

34-15 BAROMETRIC ALTIMETER The Altimeter is located on the flight instrument panel.

Removal and Installation

Step 1. Remove the screws securing the flight panel. Gently pull panel away from structure taking care of lines and wires behind.

Step 2. Remove the screws which hold the instrument to the panel. Step 3. Pull instrument from the panel. Step 4. Remove the static line from the instrument. The instrument is now free. Cap all lines

and fittings.

To install Altimeter reverse above steps and carry out system leak check.


34-15 Page 2 July 28, 2008

Figure 34-15-01 Altimeter Installation


34-18 Page 1 July 28, 2008

34-18 STALL WARNING The stall warning system is made up of a lift detector, warning horn, and red warning light. This chapter describes removal, installation, and function check of the stall warning system. 2C1 and 2C2 Aircraft S/N 29-44

The stall warning horn and light are located on the flight instrument panel. The lift detector is located on the leading edge of the starboard wing, between Rib #9 and Rib #11. Function Check Step 1. Ensure master switch is turned ‘ON’.

Step 2. Ensure stall warning circuit breaker is pushed in.

Step 3. Slowly raise the stall warning vane, located on the starboard wing, until the horn

sounds and the light illuminates. Release the stall warning vane. Stall Warning Horn & Light Removal and Installation

Step 1. Remove the screws which hold the panel to the vibration isolators. Gently pull panel away from structure taking care of lines and wires behind.

Step 2. Remove the screws which hold the instrument to the panel.

Step 3. Pull instrument from the panel.

Step 4. Remove the electrical connections from the instrument. The instrument is now free.

To install stall warning horn and light reverse above steps and carry out operational check.

2C1 and 2C2 Aircraft S/N 40 and on.

The stall warning horn is located on the interior panel just above pilot’s door. The warning light is located on the upper left hand corner of the instrument panel. See Figure 34-00-01, 34-18-01, 34-18-02, 34-18-03 & 34-18-04. Warning Horn Removal Reference Figure 34-18-01


34-18 Page 2 July 28, 2008

Step 1. Ensure electrical power is turned off.

Step 2. Locate the warning horn and unscrew the cover from the top of the horn assembly. This will free the horn assembly from the attachment bracket.

Step 3. Identify the two wires attached to the horn assembly. Remove the two screws which attach the wires to the horn assembly. The unit is now free.

Warning Horn Installation

Step 1. Attach the two wires to the horn assembly in the correct position.

Step 2. Place the horn assembly in location on the attachment bracket.

Step 3. Screw the cover onto the horn assembly.

Step 4. Carry out an operational check to confirm the horn is working.

2C3 and 2C4 Aircraft.

The stall warning horn is located on the interior upper console between pilot’s and co-pilot’s head. The warning light is located on the upper left hand corner of the instrument panel. See Figure 34-00-04, 34-18-01, 34-18-02, 34-18-03 & 34-18-04. Warning Horn Removal Reference Figure 34-18-01 Step 1. Ensure electrical power is turned off.

Step 2. Locate the warning horn and unscrew the cover from the top of the horn

assembly. This will free the horn assembly from the attachment bracket.

Step 3. Identify the two wires attached to the horn assembly. Remove the two screws which attach the wires to the horn assembly. The unit is now free.

Warning Horn Installation

Step 5. Attach the two wires to the horn assembly in the correct position.

Step 6. Place the horn assembly in location on the attachment bracket.

Step 7. Screw the cover onto the horn assembly.

Step 8. Carry out an operational check to confirm the horn is working.


34-18 Page 3 July 28, 2008

All Aircraft Warning Light Removal Reference Figure 34-18-02 Step 1. Ensure electrical power is turned off. Step 2. Unscrew the cover from the light assembly, and remove the bulb. Step 3. Remove the four attachment screws from the flight instrument panel. Carefully move

the flight instrument panel aft. CAUTION: Support the flight instrument panel so that there is no tension on any of the

instrument wires, lines, hoses, or fittings. Step 4. Identify the two wires attached to the light assembly. Step 5. There is heat shrink over the connections which must be removed. Using a soldering

iron, de-solder the two wires from the light assembly. Step 6. Remove one of the jam nuts from the light assembly. The light is now free. Warning Light Installation Step 1. Slide a 1” piece of heat shrink over each of the two wires, and slide them away from

the end of each wire. Step 2. Place the light assembly in the flight instrument panel and reinstall the jam nut. Step 3. Using a soldering iron, solder the wires to the correct terminals. Step 4. Slide the heat shrink over the soldered connections and shrink it. Step 5. Reinstall the bulb, and replace the cover. Step 6. Carry out an operational check to confirm the light assembly is working. Step 7. Place the flight instrument panel in position and reinstall the four attachment screws. Warning Light - Bulb Replacement The bulb can be replaced by unscrewing the cover from the light assembly. The 327 bulb will stay in the cover and can be pulled straight out of the cover. Install a new bulb and reinstall the cover.


34-18 Page 4 July 28, 2008

Carry out an operational check to confirm the bulb is working. Lift Detector Removal Reference Figure 34-18-03 Step 1. Ensure electrical power is turned off. Step 2. IMPORTANT -Mark the location of the lift detector before loosening any

attachment screws. Step 3. Remove the two attachment screws. Step 4. Carefully pull the lift detector away from the wing. Step 5. Identify the two wires attached to the lift detector. Remove the two screws which

attach the wires to the lift detector. The unit is now free. Lift Detector Installation Step 1. Attach the two wires to the lift detector in the correct location. Step 2. Place the lift detector in position and use the location marks to position the lift

detector in the correct location. Step 3. Install the attachment screws. Step 4. Carry out an operational check of the stall warning system. Step 5. Carry out a test flight to determine that the stall warning system activates between 5

and 10 knots above the indicated stall speed. Stall Warning Adjustment Before carrying out any adjustment to the lift detector, the position of the lift transducer must be identified with a piece of tape, or a non permanent marker. This provides a point of reference during adjustments. To carry out an adjustment, loosen off the two lift detector attachment screws and move the lift detector up or down. Moving the lift detector up will increase the stall warning speed. Moving the lift detector down will decrease the stall warning speed.


34-18 Page 5 July 28, 2008

The lift detector should only be moved by a small amount, usually about 1/32” (1mm) to 1/16” (2mm).

WARNING THE STALL WARNING MUST ACTIVATE BETWEEN 5 KNOTS

AND 10 KNOTS ABOVE AIRCRAFT STALL SPEED. Operational Check To carry out an operational check of the stall system the aircraft power must be turned ‘ON’. Move the lift detector vane upwards. The stall warning horn and the stall warning light must both activate. Turn aircraft power ‘OFF’. Continued Airworthiness This system does not require routine periodic maintenance.


34-18 Page 6 July 28, 2008

Figure 34-18-01 Stall Horn

Figure 34-18-02 Stall Warning Light


34-18 Page 7 July 28, 2008

Figure 34-18-03 Lift Detector

Figure 34-18-04 Stall Warning System, Schematic


34-18 Page 8 July 28, 2008



34-21 Page 1 July 28, 2008

34-21 ATTITUDE GYRO The artificial horizon is located on the flight instrument panel. Removal and Installation Step 1 Remove the screws securing the flight panel. Gently pull panel away from structure

taking care of lines and wires behind. Step 2 Remove the screws which hold the instrument to the panel. Step 3 Pull instrument from the panel. Step 4 Remove the vacuum lines from the instrument. The instrument is now free. Label

lines for installation. Cap all lines and fittings. To install Artificial Horizon reverse above steps and carry out a function check (Ref. 05-00)

Figure 34-21-01 Attitude Gyro Installation


34-21 Page 2 July 28, 2008



34-22 Page 1 July 28, 2008

34-22 DIRECTIONAL GYROS

34-22-01 Vacuum Directional Gyro

The directional gyro is located on the flight instrument panel. See Figure 34-22-01 Removal and Installation Step 1. Remove the screws securing the flight panel. Gently pull panel away from structure

taking care of lines and wires behind. Step 2. Remove the screws which hold the instrument to the adapter plate. Step 3. Pull instrument from the panel. Step 4. Remove the vacuum lines from the instrument. The instrument is now free. To install directional gyro reverse above steps and carry out a function check (Ref. 05-00)

Figure 34-22-01 Directional Gyro


34-22 Page 2 July 28, 2008

34-22-02 Pictorial Navigation System

General The Bendix/King KCS 55A pictorial navigation system is composed of four units: The KI 525A pictorial navigation indicator, KG 102A directional gyro, KMT 112 magnetic azimuth transmitter, and the KA 51B slaving accessory. The KI 525A pictorial navigation indicator provides a pictorial display of the horizontal navigation situation. The KI 525A also provides manual controls for course and heading datum selections. Outputs from the KI 525A are for automatic pilot or flight director, VOR receivers and additional compass loads like the synchronized compass card of the KI 227-01 ADF indicator. The KI 525A pictorial navigation indicator is located in the center of the flight panel per Figure 34-00-01. The KG 102A directional gyro is a remote mounted unit, which, in conjunction with the KMT 112 magnetic azimuth transmitter, provides a gyro stabilized magnetic heading to the KI 525A indicator. In addition to the slaving circuitry this unit contains an internal power supply, which provides excitation voltages for the magnetic azimuth transmitter and positive and negative D.C. voltages for the pictorial navigation indicator and the slaving accessory. The KMT 112 magnetic azimuth transmitter (Flux Valve) senses the direction of the earth’s magnetic field and transmits this information to the pictorial navigation indicator. The KA 51B slaving accessory is a panel mounted unit which contains the slaving meter, slaving switches and corrector circuitry which compensates for the effect of local magnetic disturbances on the magnetic azimuth transmitter. Compass Verification If the KI 525A Indicator, or the KG 102A Directional Gyro, or the KMT 112 Magnetic Azimuth Transmitter, or the KA 51B Slaving Accessory are replaced, carry out the applicable sections of KCS55A installation manual, P/N 006-00111-0007, section 2.8. This must be accomplished to verify correct operation of each unit, and the system. KI 525A Indicator Removal Step 1. Disconnect the two “D” connectors at the aft of the unit. This will require loosening

the two slot head screws on either side of each “D” connector and gently pulling the connectors away from the unit.

Step 2. Remove the four instrument screws from the face of the unit securing it to the panel.

The unit is now free to remove. (Note, ensure to support the unit when removing the attachment screws from the face of the unit).


34-22 Page 3 July 28, 2008

KI525A Indicator Installation Step 1. To install the KI525A Indicator reverse the above steps. Step 2. Carry out a compass verification. KG 102A Directional Gyro Removal The KG 102A directional gyro is located in the aft fuselage. Step 1. Disconnect the “D” connector by loosening the two slot screws on either side of the

connector. Step 2. Gently pull the connector from the unit. Step 3. Remove the two screws securing the gyro to its shock isolation base. Step 4. Pull the unit forward about 1” to release it from the aft catches and carefully removed

from the aircraft. KG 102A Directional Gyro Installation Step 1. To install the KG 102A Directional Gyro reverse the above steps. Note: Ensure that the ground bonding strap is properly connected. Step 2. Carry out compass verification. KMT 112 Magnetic Azimuth Transmitter (Flux Valve) This unit is located in the port wing between ribs 13 and 14 and accessed through a cover on the underside of the wing. KMT 112 Removal Step 1. Remove the ten stainless steel screws securing the cover. Step 2. Remove the three #6 screws securing the unit to its mounting bracket. This will allow

the unit to drop down enough to allow access to the connector. Step 3. Disengage the connector by rotating the locking mechanism 90 counter-clockwise. Step 4. Gently pull the connector from the unit. The unit is now free for removal.


34-22 Page 4 July 28, 2008

KMT 112 Installation Step 1. To Install the KMT 112 reverse the above steps. Be certain to correctly orient the

unit. Step 2. Carry out compass verification. KA 51B Slaving Accessory Removal This unit is located on the instrument panel just below the throttle control. Step 1. To remove the unit reach behind the panel and disengage the two connectors by

rotating their locking mechanisms 90 counter-clockwise and gently pull them apart. Step 2. Remove the four screws, which secure the unit to the panel. Step 3. Pull the unit from the panel. Be certain to secure the retaining ring as the unit is

removed. KA 51B Slaving Accessory Installation Step 1. To install the KA 51B Slaving Accessory, reverse the above steps. Step 2. Carry out a compass verification. Installation Guide Consult the installation guide (P/N 006-00111-0007) supplied with the appliance for additional information. Continued Airworthiness This system does not require routine periodic maintenance.


34-22 Page 5 July 28, 2008

Figure 34-22-02 H.S.I. Schematic (2C1 & 2C2)


34-22 Page 6 July 28, 2008

The markings and placards installed in this airplane contain operating limitations which must be complied with when

operating this airplane in the Normal Category. Other operatinglimitations which must be complied with when operating this

airplane in this category are contained in the Airplane Flight Manual.

To apply parking brake depress brake pedals and pull parking brake handle To release parking brake depress brake pedals and push parking brake handle

Parking Brake Handle

NO SMOKING FIRE EXTINGUISHER FASTEN SEATBELTS LOCATED UNDER PILOT SEAT

AUDIOINT

BLINDENC.

115 VacINVRTR

A PALERT

DME AUTOPILOT

AVNFAN

12 VAUX

HSI

ENGMONITOR

PANELLTS

PULSELT

STALLWARNING

MANEUVER SPEED = 114 KIAS

Normal Category: No acrobatic maneuversincluding spins, approved.Flight into knownicing conditions prohibited. This airplane iscertified for the following flight operations:

I.F.R.

FOR FLOAT EQUIPPED AIRCRAFTWATER RUDDER ALWAYS UP

EXCEPT FOR TAXIING

Figure 34-22-03 H.S.I. Mechanical Installation (2C1 & 2C2)


34-22 Page 7 July 28, 2008

NOTES:

1) INSTALLATION OF KCS 55A HSI PER BENDIX/KING MANUAL 006-00111-0010, THE NOTES WITHIN THIS DOCUMENT AND OTHER DOCUMENTS AS MAY BE APPLICABLE. BE CERTAIN TO READ AND UNDERSTAND THESE DOCUMENTS.

2) UNLESS OTHERWISE SPECIFIED ALL ELECTRICAL WIRE HARNESS AND EQUIPMENT INSTALLATIONS SHALL BE IN ACCORDANCE WITH AC 43.13-1B CHAPTER 11.

3) WIRES ARE IDENTIFIED BY A NUMBER AND ARE PREFACED BY A ZERO. THE BASE # IS FOLLOWED BY A DASH # REPRESENTING THE WIRE GAUGE.

Figure 34-22-04 H.S.I. Schematic (2C3 & 2C4)


34-22 Page 8 July 28, 2008



34-22 Page 1 July 28, 2008

34-23 STANDBY COMPASSES The standby compass is located on top of the instrument panel deck in front of the pilot. Continued Airworthiness The compass swing must be performed every 12 months.

34-23-01 Airpath Compass

Removal and Installation Step 1. Remove the four instrument screws securing the compass to its’ mounting bracket Step 2. Disconnect the wires for the integral compass lighting. The compass may now be

removed from the aircraft. To install the compass reverse the aforementioned steps. Carryout compass swing.

COMPASSMOUNTING BRACKET

OFF

LAND.LTS

BRACKETMOUNTINGSCREWS




0°

10°

30°

20°

AVIONICSMASTER

OFF OFF

AUX.FUEL

OFF OFF

NAV.LTS

TAXI LIGHT

OFF

COMPASSMOUNTINGSCREWS

Figure 34-23-01 Airpath Compass Installation


34-22 Page 2 July 28, 2008

34-23-02 SIRS Navigation Compass

Removal and Installation Step 1. Remove the three instrument screws securing the compass to instrument panel deck. Step 2. Disconnect the wires for the integral compass lighting. The compass may now be

removed from the aircraft. To install the compass reverse the aforementioned steps. Carryout compass swing.




OFF

NAUX.FUEL

30°0°

10°

OFFOFF OFF

20°

OFFOFF

NAV.LTS

AVIONICSMASTER

TAXI LIGHT

LAND.LTS

COMPASS

COMPASSMOUNTINGSCREWS

Figure 34-23-02 SIRS Compass Installation


34-23 Page 3 July 28, 2008

Compass Adjustments CAUTION: Non-ferrous tools must be used not to affect compass adjustment. Before the compass can be adjusted the aircraft must be capable of being aligned to both the East/West axis and the North/South axis. The use of another land compass outside the aircraft to determine the cardinal points is advised. Through out the body of this text references to various screws, adjustments, etc are made, see Fig 34-23-04 for clarifications. Note also that if the technician wishes to return the compass compensation magnets to a zero condition Fig 34-23-04 shows the requirements.

Levelling the Compass

1. The level of the compass – Fore to Aft – can be adjusted by loosening the rear screw and rotating the compass about the swivel. The screw should be re-tightened after adjustment.

Correction East/West (‘B’ Coefficient)

1. Align the aircraft facing East. Insert the Corrector Key provided into the Left hand hole at the front of the compass. Rotate the key in either direction so that the East point is directly under the index line, (a.k.a. Lubber Line).

2. Align the aircraft facing west and check that the West Point is under the Index line. Any error may be corrected by readjusting to remove HALF the error shown.

Correction North/South (‘C’ Coefficient)

1. Align your aircraft facing North, insert the Corrector Key into the Right hand hole at the front of the compass, rotate the key in either direction so that the North point is directly under the Index line.

2. Align your aircraft facing South and check that the South point is under the Index line. Any error may be corrected by readjusting to remove HALF the error shown.

The above procedure can be repeated until the errors are minimised. If the adjustments detailed above result in consistent errors on each of the Cardinal points the compass may not be aligned correctly on the Fore and Aft line of the aircraft. To correct this misalignment proceed as follows: Correction for Misalignment (‘A’ Coefficient) Note, the following instructions are with reference to Table 34-23-01

1. Align the aircraft facing North; record the compass error in Box A.


34-23 Page 4 July 28, 2008

2. Align the aircraft facing South; record the compass error in Box B. 3. Align the aircraft facing East; record the compass error in Box C. 4. Align the aircraft facing West; record the compass error in Box D.

Note: Errors to the Left of the true heading should be prefixed with a plus sign (+). Fig 34-23-03 A Errors to the Right of the true heading should be prefixed with a minus sign (+) Fig 34-23-03 B

5. Add the readings in Boxes A to D enter the result in Box E. Divide the figure in Box E by 4, record the result in Box F. This figure is the error due to misalignment and may be corrected as follows.

6. Note the current magnetic heading, carefully loosen the two cross headed screws which secure the compass to the bracket, rotate the compass body in the opposite direction to the error shown in Box F. i.e. If the error in Box F is +5 degrees, rotate the compass body by -5 degrees and vice versa. Carefully tighten the two cross-headed screws without moving the compass body.

7. Note that for the example given in Table 34-23-01 the compass would need to be rotated by -5 degrees.

CORRECTION TABLE 34-23-01

Box Sample Error Box Actual Error A (North) +15 A B (South) +5 B C (East) -10 C D (West) +10 D E (Total) +20 E F (“E”/4) +5 F

A B

Figure 34-23-03 SIRS Compass samples of +/- corrections


34-23 Page 5 July 28, 2008

Figure 34-23-04 SIRS Compass Details


34-23 Page 6 July 28, 2008



34-24 Page 1 July 28, 2008

34-24 TURN AND BANK OR TURN COORDINATOR INDICATOR The aircraft may be equipped with either a turn and bank or turn coordinator indicator. Either instrument will be located on the flight instrument panel. See Figure 34-24-01. Removal and Installation Step 1. Remove the screws securing the flight panel. Gently pull panel away from structure

taking care of lines and wires behind. Step 2. Remove the screws which hold the instrument to the panel. Step 3. Pull instrument from the panel. Step 4. Remove the electrical connection from the instrument. The instrument is now free. To install either instrument reverse the above steps and carry out a function check (Ref. 05-00). Ensure that the “ball” is level when the aircraft is level in the roll axis. Note, serial number 40 and up the mounting holes for this instrument are oval shaped to ease the “ball” levelling adjustment.

Figure 34-24-01 Turn & Bank or Turn Coordinator Installation


34-24 Page 2 July 28, 2008



34- 45 Page 1 January 23, 2012

34-45 TRAFFIC SYSTEM - GARMIN GTS 8XX (2C3 & 2C4) The GTS 8XX is a microprocessor-based Line Replaceable Unit (LRU) that uses active interrogations of Mode S (GTS 820 and GTS 850 only) and Mode C transponders to provide Traffic Advisories to the pilot. When installed with a 1090 MHz ADS-B transmit class of equipment the GTS 8XX also utilizes passive surveillance. Traffic is displayed on an external MFD via ARINC 429 and/or Ethernet High Speed Data Bus (HSDB). An aural alert is also provided to inform the crew a traffic advisory (TA) will be displayed. A top-mounted directional antenna is used to derive bearing of the intruder aircraft, which is displayed with relative altitude to own aircraft. Top antenna transmitted interrogations are directional, reducing the number of transponders that receive the interrogation thus reducing potential garble on the 1090 MHz band. The bottom antenna transmit interrogations are omni directional, using a monopole antenna. A bottom antenna installation gives the benefit of intruder visibility for targets that are shaded from the top directional antenna. There are a series of Garmin manuals describing the installation of the GTS 8xx series of traffic systems.

190-00587-00 GTS 8XX/GA 65 Installation Manual 190-00993-00 Part 1: Overview and Limitations 190-00993-04 Part 2: Mechanical Installation 190-00993-05 Part 3: Electrical Installation 190-00993-03 Part 4 Configuration, Checkout and Maintenance

GTS 800 Removal Step 1. Remove the co-pilot floor cover, (See Figure 34-45-01a/b).

Step 2. Disconnect three D-Sub connectors, (Jack Screw Type).

Step 3. Disconnect the cooling hose.

Step 4. Disconnect the antenna cables

Step 5. Finally, loosen the thumb screw and carefully remove the LRU, (See Figure 34-45-02)

GTS 800 Installation Step 1. Remove the co-pilot floor access cover, (See Figure 34-45-01 and -02.

Step 2. Install LRU and secure with Thumb Screw, (See Figure 34-45-03).

Step 3. Connect three D-Sub connectors, (Jack Screw Type)


34- 45 Page 2 January 23, 2012

Step 4. Connect the cooling hose.

Step 5. Connect the antenna cables. Note the color bands and ensure they match the connections.

Step 6. Carry out a test flight per 190-00993-03 Part 4 Configuration, Checkout and Maintenance.

Bottom Antenna Removal, (See Figure 34-45-04). Step 1. Gain access to the bottom monopole traffic antenna by removal of the center main

gear access cover, (See Section 32-20-10 and Figure 32-10-03 for additional details) Step 2. Locate and remove the antenna connector, (BNC). Step 3. Remove the two nuts securing the antenna and bond wires. Carefully separate the

antenna from the aircraft by breaking the seal at the base of the antenna and pulling straight away from the panel.

Bottom Antenna Installation, (See Figure 34-45-04). Step 1. Reinstall the antenna giving due consideration to the notes. Step 2. Carry out a test flight per 190-00993-03 Part 4 Configuration, Checkout and

Maintenance. Upper Antenna Removal,. Step 1. Remove "Center Overhead Console" per Section 25-80-20. Step 2. Locate and remove the four antenna connectors, (QMA). Step 3. Remove the four screws securing the antenna base and carefully separate the antenna

from the aircraft by breaking the seal at the base of the antenna and pulling straight away from the aircraft skin.

Upper Antenna Installation, . Step 1. Remove "Center Overhead Console" per Section 25-80-20. Step 2. Install four screws to secure antenna. Note, at least one nut must provide a positive

bond to aircraft skin; a bond brush may be required. Corrosion protection shall be applied to any exposed metal after screws are tightened.


34- 45 Page 3 January 23, 2012

Step 3. Attach four QMA antenna cables. Note the color bands and ensure they match the associated connection.

Step 4. Carry out a test flight per 190-00993-03 Part 4 Configuration, Checkout and Maintenance.

Continued Airworthiness This system does not require routine periodic maintenance.

Figure 34-45-01 GTS 800 LRU Access Cover Removal Co-Pilot Floor


34- 45 Page 4 January 23, 2012

Figure 34-45-02 GTS 800 LRU Access

Figure 34-45-03 GTS 800 Thumb Screw (Removal)


34- 45 Page 5 January 23, 2012

FWD

BOND WIRE

2 PLACES

ACCEPTABLE TOINSTALL AT EITHERFWD OR AFT ANTENNASTUD

REAPPLY CORROSIONPROTECTION AFTER

INSTALLING GROUND STUD.

REMOVE PAINT BEFOREATTACHING BOND WIRE. REAPPLY

EPOXY PAINT TO ANY EXPOSEDMETAL POST INSTALLATION.

BoltWasherNut

2 PLACES

Figure 34-45-04 Bottom Traffic Antenna Installation


34- 45 Page 6 January 23, 2012

QMA Connector Insertion and Removal

To engage the QMA connectors, use the outer sleeve of the QMA plug to align the connectors and insert the plug onto the jack until it snaps into place. There will be an audible “snap” when the connectors are fully engaged, refer to Figure 34-45-05. No tools are required for the insertion of a QMA plug onto a QMA jack. CAUTION: Side-loading of the QMA connectors should be avoided during both the insertion

and removal of the connectors. Excessive side-loading may result in damage or premature failure of the QMA connectors. Do not pull on cable when removing the QMA plug from jack.

Figure 34-45-05 Engaging QMA Connectors

To disengage the QMA connectors, pull back firmly on the outer sleeve of the QMA plug away from the jack connector (refer to Figure 34-45-06). This will disengage the locking mechanism that secures the plug connector to the jack connector. Pulling on or disengaging the QMA connectors in any other way is not recommended and may cause damage to both the connectors and coaxial cable.

Figure 34-45-06 Disengaging QMA Connectors


34- 46 Page 1 January 23, 2012

34-46 GARMIN GDL 69/69A XM SATELLITE RADIO (2C3 & 2C4) The GDL 69/69A is an XM Satellite Radio data link receiver. The XM Satellite Radio antenna receives the XM satellite signal and passes it to the GDL 69/69A. The GDL 69 is a weather data receiver and the GDL 69A is a weather receiver with the addition of XM Satellite Radio audio entertainment. To display weather information and control the audio channel and volume, the GDL69/69A can be interfaced with the GDU 620 via an Ethernet link. Audio volume The GDL 69A may also be interfaced to a Garmin audio panel for amplification and distribution of the audio signal Removal Step 1. Using a Phillips screw loosen the screw shown in Figure 34-46-01 and release the

lever securing the LRU. Step 2. Gently slide the unit straight out from its rack. Installation Step 1. The unit is installed in the rack by gently sliding it straight in until it rests against the

back of the rack. Step 2. Depress the lock lever until the captive Phillips screw is at its' mating hole. Using a

Phillips Screwdriver secure the LRU into position. For post installation check out procedure, consult the installation manuals, TSO Installation Manual, Garmin p/n 190-00355-07 and STC Installation Manual Garmin p/n 190-00355-02. Antenna Locations For information on antenna location and installation details on Figures 34-46-02. Continued Airworthiness No schedule servicing tasks or internal manual adjustments are required on the GDL 69/69A, GRT 10 Transceiver or GRC 10 Remote Control.


34- 46 Page 2 January 23, 2012

GDL 69 LRU

Phillips Screw,Lock Lever

ControlsConsole

Figure 34-46-01 GDL69 Data Link Install

10-32 ScrewsTorque 20-25 inch lbs

A/C FWD

Starboard Location

Isometeric View Forward FuselageData Link Antenna Cable Routing

Typical

GPS/XM Cable RoutesPort Side Only

Blue Band GPS Yellow Band XM

A/C FWD

View Looking Down At Cabin RoofGA 37 Antenna Installation

(Either Port or Starboard location Acceptable)

Figure 34-46-02 GDL 69 Antenna Installation


34-51 Page 1 July 28, 2008

34-51 DISTANCE MEASURING EQUIPMENT The KN 62A Digital DME is interconnected to the navigation section of the #1 GNS 430 for parallel tuning or may be manually tuned from the units’ front controls. The DME is interconnected to the audio panel for station identification. Allied Signal/Bendix King KN 62A Installation Manual Consult the KN 62A Installation manual (P/N 006-00144-0006) supplied with the appliance for additional information on removal, installation, and post installation testing. KN 62A Digital DME Removal Step 1. Insert a 3/32” hex drive tool into the access hole on the unit face and rotate counter-

clockwise until the unit is forced out about 3/8” and can be freely pulled from the rack.

KN 62A Digital DME Installation Step 1. Install the KN 62A unit in the rack by sliding it straight in until it stops, about 1”

short of the final position.

CAUTION: Be sure not to over tighten the unit into the rack. The application of the hex driver tool torque exceeding 15 in/lbs can damage the locking mechanism.

Step 2. A 3/32” hex drive tool is then inserted into the access hole in the face of the unit.

Rotate the hex tool clockwise while pressing on the left side of the bezel until the unit is firmly seated in the rack.

Note: It may be necessary to insert the hex drive tool into the access hole and rotate the

mechanism 90 counter clockwise to insure correct position prior to placing the unit in the rack.

Step 3. Carry out a test flight to confirm correct display of DME distance and ground speed. Antenna Removal Step 1. Remove the pilot’s seat and floor per section 53-20 of the maintenance manual. Step 2. Locate and remove the antenna connector.


34-51 Page 2 July 28, 2008

Step 3. Remove the two nuts securing the antenna. Carefully separate the antenna from the

aircraft by breaking the seal at the base of the antenna and pulling straight away from the aircraft.

Antenna Installation Step 1. Reinstall the antenna giving due consideration to the notes. Step 2. Carry out a test flight to confirm correct display of DME distance and ground speed. Continued Airworthiness This system does not require routine periodic maintenance.


34-51 Page 3 July 28, 2008

Figure 34-51-01 DME Schematic (2C1 & 2C2)


34-51 Page 4 July 28, 2008

Figure 34-51-02 DME Antenna Installation (2C1 & 2C2)


34-51 Page 5 July 28, 2008

NOTES:

1) INSTALLATION OF KN 62A DME PER BENDIX/KING

MANUAL 006-00144-0006, THE NOTES WITHIN THIS DOCUMENT

AND OTHER DOCUMENTS AS MAY BE APPLICABLE. BE CERTAIN

TO READ AND UNDERSTAND THESE DOCUMENTS.

2) UNLESS OTHERWISE SPECIFIED ALL ELECTRICAL WIRE HARNESS

AND EQUIPMENT INSTALLATIONS SHALL

BE IN ACCORDANCE WITH AC 43.13-1B CHAPTER 11.

3) WIRES ARE IDENTIFIED BY A NUMBER AND ARE PREFACED BY A ZERO.

THE BASE # IS FOLLOWED BY A DASH # REPRESENTING THE

WIRE GAUGE.

BEFORE INSTALLING THIS EQUIPMENT BE SURRE TO READ AND

UNDERSTAND THE CURRENT REVISION INSTALLATION MANUAL

BENDIX/KING P/N 006-00144-0006.

Figure 34-51-03 DME Schematic (2C3 & 2C4)


34-51 Page 6 July 28, 2008



34-52 Page 1 January 23, 2012

34-52 ATC TRANSPONDER SYSTEMS The aircraft may be equipped with “Mode C Transponder” equipment. If so the main unit will be located on the right panel, usually at the bottom of the avionics stack.

34-52-01 ACK A-30 Altitude Encoder

The ACK A-30 Altitude Encoder is located on the upper port side of the control consol behind the flight panel. The unit provides altitude data to the ATCRBS transponder. The operation of the unit is independent of any user controls save for turning on the avionics master. It is useful to note that the unit has a warm-up time. Warm-Up Time:

From 70 degrees Fahrenheit ambient temperature 6 minutes From 0 Fahrenheit ambient temperature 10 minutes

Removal Step 1. To remove the unit turn the thumbwheel nut counter clockwise until loose. Step 2. Pull the unit aft and upward to release the unit. Step 3. Disconnect the static line from the encoder and cap both the unit and the static line. Step 4. Disconnect the 15 pin D-sub connector. To install, reverse the above steps. Carry out a leak check. Note: Depending on the reasons for removal it may be necessary to complete the steps outlined

in the “Continued Airworthiness” section of this supplement.

34-52-02 GTX 327A Garmin Digital Transponder

The GTX 327A Digital Transponder is interfaced to the ACK model A-30 blind encoder to provide “mode C” capability. In addition the unit can be connected to a GPS to provide the transponder with ground speed data to allow it to automatically go into and out of standby mode. The unit also provides serial altitude data to the GPS. This unit may also use the Garmin ADC, GDC 74A, for an altitude source, (RS-232 #8 from GDU620). Installation Guide Consult the Garmin GTX 327A Installation Manual (P/N 190-00187-02) supplied with the appliance for additional information on removal, installation, and post installation testing.


34-52 Page 2 July 28, 2008

GTX 327A Removal Step 1. Insert a 3/32” hex drive tool into the access hole on the unit face and rotate counter-

clockwise until the unit moves out about 3/8”. Step 2. Pull the unit from the rack. GTX 327A Installation Step 1. Install the GTX 327A unit in the rack by sliding it straight in until it stops, about 1”

short of the final position. Step 2. A 3/32” hex drive tool is then inserted into the access hole at the bottom of the unit

face.

CAUTION: Be sure not to over tighten the unit into the rack. The application of the hex drive tool torque exceeding 15 in/lbs can damage the locking mechanism.

Step 3. Rotate the hex tool clockwise while pressing on the left side of the bezel until the unit

is firmly seated in the rack. Note: It may be necessary to insert the hex drive tool into the access hole and rotate the

mechanism 90 counter-clockwise to insure correct position prior to placing the unit in the rack.

Step 4. Carry out an operational check per Section 3 of the Installation Manual P/N 190-00187-02. Note: Depending upon the reasons for removal it may be necessary to complete the steps

outlined in the “Continued Airworthiness” section of this supplement. Antenna Removal Note, two locations are available for the transponder antenna on the 2C1 and 2C2 aircraft. The first location is illustrated in Figure 34-52-02. The second location, illustrated in Figure 34-52-03, is employed when the transponder is installed in conjunction with a DME. Step 1. Locate and remove the antenna giving due consideration to the notes. Step 2. Carry out an operational check per the installation manual P/N 190-00187-02. Note: Depending on the reasons for removal it may be necessary to complete the steps outlined

in the “Continued Airworthiness” section of this supplement.


34-52 Page 3 January 23, 2012

Antenna Installation Note, two locations are available for the transponder antenna on the 2C1 and 2C2 aircraft. The first location is illustrated in Figure 34-52-02. The second location, illustrated in Figure 34-52-03, is employed when the transponder is installed in conjunction with a DME. Similarly, Figure 34-52-04 shows the forward antenna location on a 2C3 or 2C4. Step 1. Install the antenna giving due consideration to the notes. Step 2. Carry out an operational check per the installation manual P/N 190-00187-02. Note, depending on the reasons for removal it may be necessary to complete the steps outlined in the “Continued Airworthiness” section of this supplement. Step 3. Carry out an operational check per the installation manual P/N 190-00187-02. Note: Depending on the reasons for removal it may be necessary to complete the steps outlined

in the “Continued Airworthiness” section of this supplement. Continued Airworthiness The GTX 327A Digital Transponder system does not require routine periodic maintenance. Replacement of transponder requires Mode C certification. Consult governing aviation regulations regarding Mode C certification.


34-52 Page 4 July 28, 2008



34-52 Page 5 July 28, 2008

Figure 34-52-01 GTX 327A Transponder Sample Schematic (2C1 & 2C2)


34-52 Page 6 July 28, 2008

Figure 34-52-02 Transponder Antenna Location 1 (DME Not Installed) – 2C1 & 2C2


34-52 Page 7 July 28, 2008

Figure 34-52-03 Transponder Antenna Location 2 (DME Installed) – 2C1 & 2C2


34-52 Page 8 January 23, 2012

VIEW ON ARROW ALOOKING DOWN AT FLOOR STRUCTURE

F343-326

(Ø0.191)DRILL #11

CENTERED IN BOTTOMFLANGE OF F343-326

NOTE: REMOVE PAINT AFTER DRILLING #11 HOLE WITHBONDING BRUSH BEFORE ATTACHING BOND WIRE

WITH INDICATED HARDWARE. REAPPLY EPOXYPAINT TO ANY EXPOSED METAL POST INSTALLATION

ARROW "A"

Washer

Washer

Nut

BoltF343-326

Split Washer

Jam Nut

Jam Nut

Split Washer

Washer

Remove Epoxy PrimerUsing Bonding Brush.Reapply AlodineBefore InstallingGround Stud.Reapply Primer ToExposed AluminumAfter Ground Stud Installed

Screw

Bonding WireMinimum 1

Figure 34-52-04 Transponder Antenna Location – 2C3 & 2C4


34-52 Page 9 January 23, 2012

NOTES:

1) INSTALLATION OF GTX 327 TRANSPONDER PER GARMIN









WIRE GAUGE.



GARMIN P/N 010-00188-03.

Figure 34-52-05 GTX 327A Transponder Sample Schematic


34-52 Page 10 January 23, 2012



34-52 Page 11 July 28, 2008

34-52-03 Bendix/King KT-76A Transponder

The Bendix/King KT-76A Transponder is located on the instrument panel. The unit is an ATCRBS. It receives altitude data from the ACK A-30 altitude encoder. The operation of the unit is described in the Bendix/King Installation Manual number 006-00143-0006 Removal Step 1. Insert a 3/32” hex drive tool into the access hole on the unit face and rotate counter-

clockwise until the unit protrudes about 3/8” from the panel Step 2. Gently slide the unit straight out from its rack. Installation Step 1. The unit is installed in the rack by gently sliding it straight in until it rests against the

back of the rack. Step 2. A 3/32” hex drive tool is then inserted into the access hole at the bottom of the unit

face. Rotate the hex tool clockwise while pressing on the left side of the Bezel until is firmly seated in the rack

CAUTION: Be sure not to over tighten the unit into the rack. The application of hex drive tool

torque exceeding 15 in lbs can damage the locking mechanism. For post installation check out procedure, consult the Bendix/King Installation Manual number 006-00143-0006 Antenna Locations For information on antenna location and installation details on the 2C1 and 2C2 aircraft refer to Figures 34-52-02 and 34-52-03. Continued Airworthiness Replacement of transponder requires Mode C certification. Consult governing aviation regulations regarding Mode C certification.


34-52 Page 12 July 28, 2008



34-52 Page 13 January 23, 2012

Figure 34-52-06 Bendix/King KT 76A Transponder Schematic


34-52 Page 14 July 28, 2008



34-52 Page 15 July 28, 2008

34-52-04 Bendix/King KT-76C Digital Transponder

The Bendix/King KMA- KT-76C Transponder is located on the instrument panel. The unit is an ATCRBS. It receives altitude data from the ACK A-30 altitude encoder. The operation of the unit is described in the Bendix/King Installation Manual number 006-10545-0000 Removal Step 1. Insert a 3/32” hex drive tool into the access hole on the unit face and rotate counter-





torque exceeding 15 in lbs can damage the locking mechanism. For post installation check out procedure, consult the Bendix/King Installation Manual number 006-10545-0000 Antenna Locations For information on antenna location and installation details on the 2C1 and 2C3 aircraft refer to Figures 34-52-02 and 34-52-03. Continued Airworthiness Replacement of transponder requires Mode C certification. Consult governing aviation regulations regarding Mode C certification.


34-52 Page 16 July 28, 2008



34-52 Page 17 January 23, 2012

Figure 34-52-07 Bendix/King KT 76C Transponder Schematic


34-52 Page 18 January 23, 2012



34-52 Page 19 January 23, 2012

34-52-05 Garmin GTX 330 Digital Transponder

The Garmin GTX 330 Digital Transponder is typically located on the right hand instrument panel. It receives altitude data from the Garmin GDC 74A Air Data Computer (2C3 & 2C4) or from a blind encoder (2C1 & 2C2). See the installation manual, (Garmin p/n 190-00207-02), for additional information. Typically, a non diversity, enhanced squitter type LRU will be installed, although these instructions apply equally to all types. Removal Step 1. Insert a 3/32” hex drive tool into the access hole on the unit face and rotate counter-





torque exceeding 15 in lbs can damage the locking mechanism. For post installation check out procedure, consult the installation manual, Garmin p/n 190-00207-02. Antenna Locations For information on antenna location and installation details on the 2C1, 2C2, 2C3 and 2C4 aircraft refer to Figures 34-52-02 thru 34-52-04. Continued Airworthiness Replacement of transponder requires Mode S certification. Consult governing aviation regulations regarding Mode S certification.


34-52 Page 20 January 23, 2012

34-52-06 Garmin GTX 33 Digital Transponder (2C3 and 2C4)

The Garmin GTX 33 Remote Digital Transponder is located on the equipment shelf in front of the flight instrument panel above the pilot's rudder controls. It receives altitude data from the Garmin GDC 74A Air Data Computer. See the TSO Installation Manual, Garmin p/n 190-00906-00 and STC Installation Manual Garmin p/n 190-00303-61 for additional information. Typically, a non diversity, enhanced squitter type LRU will be installed, although these instructions apply equally to all types. Removal Step 3. Using a Phillips screw loosen the screw shown in Figure 34-52-08 and release the

lever securing the LRU. Step 4. Gently slide the unit straight out from its rack. Installation Step 3. The unit is installed in the rack by gently sliding it straight in until it rests against the

back of the rack. Step 4. Depress the lock lever until the captive Phillips screw is at its' mating hole. Using a

Phillips Screwdriver secure the LRU into position. For post installation check out procedure, consult the installation manuals, TSO Installation Manual, Garmin p/n 190-00906-00 and STC Installation Manual Garmin p/n 190-00303-61 Antenna Locations For information on antenna location and installation details on the 2C1, 2C2, 2C3 & 2C4 aircraft refer to Figures 34-52-02 thru 34-52-04. Continued Airworthiness Replacement of transponder requires Mode S certification. Consult governing aviation regulations regarding Mode S certification.


34-52 Page 21 January 23, 2012

GTX 33 LRU

Phillips Screw,Lock Lever

ControlsConsole

Figure 34-52-08 GTX 33 Installation


34-52 Page 22 January 23, 2012



34-54 Page 23 July 28, 2008

34-54 VHF OMNI-DIRECTIONAL RANGE FINDING EQUIPMENT For information on the VOR see section 23-12-40 and 23-12-45.


34-54 Page 24 July 28, 2008



34-55 Page 1 July 28, 2008

34-55 BENDIX/KING KR 87 AUTOMATIC DIRECTION FINDING EQUIPMENT

The KR 87 Digital ADF is a stand alone system except for interconnecting with the audio panel to provide station identification. Installation Guide Consult the Installation Manual (P/N 006-00184-0005) supplied with the appliance for additional information on removal, installation, and post installation testing. KR 87 Digital ADF Removal Step 1. Remove the unit from the rack, insert the 3/32” hex drive tool into the access hole on

the unit face and rotate counter-clockwise until the unit is moved out about 3/8” and can be freely pulled from the rack.

KR 87 Digital ADF Installation Step 1. The KR 87 unit is installed in the rack by sliding it straight in until it stops, about 1”

short of the final position.

CAUTION: Be sure not to over tighten the unit into the rack. The application of the hex driver tool torque exceeding 15 in/lbs can damage the locking mechanism.

Step 2. Rotate the hex tool clockwise while pressing on the left side of the bezel until the unit

is firmly seated in the rack. It may be necessary to insert the hex drive tool into the access hole and rotate the mechanism 90 counter-clockwise to insure correct position prior to placing the unit in the rack.

Step 3. Carry out operational checks per Section 2.4, and Section 3 of the Installation Manual P/N 006-00184-0005.

Antenna Removal

Step 1. Disconnect the antenna cable ‘D’ connector Step 2. Remove the sealant used to fill the screw holes that secure the antenna. Step 3. Remove the two screws securing the antenna. Step 4. Carefully break the sealant at the base of the antenna and remove the antenna.


34-55 Page 2 July 28, 2008

Antenna Installation

Step 1. Insert the antenna into its’ mounting hole. Step 2. Install the two mounting screws and refill the screw holes with a quality silicon

sealant. Step 3. Fillet seal the base of the antenna with silicone, or a suitable PRC product. Step 4. Reconnect the antenna cables connector. Step 5. Carry out operational checks per Section 2.4, and Section 3 of the Installation Manual

P/N 006-00184-0005.

Continued Airworthiness This system does not require routine periodic maintenance.

Figure 34-55-01 ADF Antenna Mounting Details


34-55 Page 3 July 28, 2008

Figure 34-55-02 KR 87 Bendix/King ADF Schematic (2C1 & 2C2)


34-55 Page 4 July 28, 2008

NOTES:

1) INSTALLATION OF KR 87 ADF PER BENDIX/KING









WIRE GAUGE.



BENDIX/KING P/N 006-00184-0005.

Figure 34-55-03 KR 87 Bendix/King ADF Schematic (2C3 & 2C4)


34-56 Page 1 July 28, 2008

34-56 GLOBAL POSITIONING SYSTEMS For information on GPS installations see sections 23-12-20, 30, 40 & 45.


34-56 Page 2 July 28, 2008



34-59 Page 1 July 28, 2008

34-59 TIB 2000 TRACKING SYSTEM If installed, the Telonics tracking system consists of several components. There is a switch located on the lower right hand quarter of the avionics panel, a control box located under the avionics panel mounted on the fuselage structure, 4 hardpoints in each wing to allow antenna mounting, and an antenna lead running from each wing mount to the switch. The switch is a single pole double throw that allows port, starboard, or both to be selected. Control Box Removal Step 1. Remove the 6 screws that attach the cover to the box. Step 2. Remove one bolt from the forward and aft ends of the box. Step 3. Remove the 2 quick disconnect ‘BNC’ connectors from the forward end of the box,

and 1 quick disconnect ‘BNC’ connectors from the aft end of the box. Step 4. Remove 2 screws that secure the 15 pin ‘D’ connector to the aft end of the box.

Control box is now free. Control Box Installation Step 1. Reverse the above steps to install the control box. Step 2. Carry out an operational check of the system. Switch Removal Step 1. By reaching behind the avionics panel gain access to the rear of the switch. Loosen

and remove the retaining nut from the front of the switch. Pull the switch through the mounting hole.

Step 2. Identify the 3 wires. Remove 3 screws that attach ring tongue terminals to the rear of

the switch. Switch Installation Step 1. Install the 3 ring tongue terminals in the correct location with 3 screws on the rear of

the switch. Note: Ensure the retaining nut is over the wires before securing.


34-59 Page 2 July 28, 2008

Step 2. The mounting hole has a ‘key’ which must align with a slot on the body of the switch.

Tighten the retaining nut. This installation is ‘ON CONDITION’. There are no other specific inspections or checks to be carried out on the Telonics tracking system.


34-70 Page 1 August 5, 2010

34-70 GARMIN G500 OR G600 ELECTRONIC FLIGHT INFORMATION SYSTEM

1. Description This section provides an overview of the Garmin G500 and G600 Electronic Flight Information System (EFIS). The G500/G600 system is an integrated display system that presents primary flight instrumentation, navigation, and a moving map to the pilot through large format displays. In normal operating mode, the Primary Flight Display (PFD) presents graphical flight instrumentation (attitude, heading, airspeed, altitude, vertical speed), replacing the traditional flight instrument cluster. The Multi-Function Display (MFD) normally displays a full-color moving map with navigation information. The G500/G600 system is composed of sub-units or Line Replaceable Units (LRUs). LRUs have a modular design. This design greatly eases troubleshooting and maintenance of the G500/G600 system. A failure or problem can be isolated to a particular LRU, which can be replaced quickly and easily. Each LRU has a particular function, or set of functions, that contributes to the system’s operation. The following table illustrates the differences between the G500 and G600. It should be noted that both systems utilize the same hardware. The various optional features are enabled using specific SD cards. Each SD enablement card can only be used once and, once used, the card will only work with that particular aircraft installation.

How the units compare: G500 G600

Approved for Class 2 Aircraft (typically piston twins and turbine aircraft under 6,000 lbs.)

Yes Yes

Approved for Class 3 Aircraft (typically piston or turbine aircraft between 6,000 lbs. and 12,500 lbs)

No Yes

Software design assurance level Level C Level B

Garmin SVT Synthetic Vision Technology Optional Standard

GAD 43 replaces select A/P gyro attitude with AHRS references and provides bootstrap heading, yaw information, and baro corrections

Optional1 Standard

GWX 68 Radar interface (radar LRU sold separately) Optional Standard

Internal TAWS-B terrain alerting No Optional

1 Not required for the rate based autopilots


34-70 Page 2 August 5, 2010

Figure 34-70-00 G500/G600 EFIS Block Diagram


34-70 Page 3 August 5, 2010

GDU 620

The GDU 620 has dual VGA (640 x 480 pixels) 6.5 inch LCD displays. The left side of the GDU is a PFD and the right side is the MFD. The MFD shows a moving map, flight plan, weather, and more. The PFD shows primary flight information, in place of traditional pitot-static and gyroscopic systems and also provides an HSI for navigation.

CAUTION

The GDU 620 uses a lens coated with a special anti-reflective coating that is very sensitive to skin oils, waxes and abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI-REFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free cloth and an eyeglass lens cleaner that is specified as safe for anti-reflective coatings.


34-70 Page 4 August 5, 2010

GDC 74A

The GDC 74A Air Data Computer (ADC) compiles information from the pitot/static system and an Outside Air Temperature (OAT) sensor. The GDC 74A provides pressure altitude, airspeed, vertical speed, and OAT information to the system. The GDC 74A communicates with the GDU 620 and GRS 77 using an ARINC 429 digital interface.

GTP 59

A temperature probe provides Outside Air Temperature (OAT) data to the GDC 74A. The GTP 59 is the temperature probe installed with the system.


34-70 Page 5 August 5, 2010

GRS 77

The GRS 77 is an Attitude and Heading Reference System (AHRS) unit that provides aircraft attitude information to the system. The unit contains advanced tilt sensors, accelerometers, and rate sensors. In addition, the GRS 77 interfaces with both the GDC 74A Air Data Computer and the GMU 44 magnetometer. The GRS 77 also utilizes GPS data forwarded from the GDU 620. Actual attitude and heading information is sent to the GDU 620 using an ARINC 429 digital interface.

The IGRF (International Geomagnetic Reference Field) model is contained in the GRS 77 and is only updated once every five years. The IGRF model is part of the Navigation Database. At system power-up, the IGRF models in the GRS 77 and in the Navigation Database are compared, and if the IGRF model in the GRS 77 is out of date, the user is prompted to update the IGRF model in the GRS 77. The prompt will appear after the G500 splash screen is acknowledged on the MFD.


34-70 Page 6 August 5, 2010

GMU 44

The GMU 44 magnetometer senses the earth’s magnetic field. Data is sent to the GRS 77 AHRS for processing to determine aircraft magnetic heading. This unit receives power directly from the GRS 77 and communicates with the GRS 77 using a RS-485 digital interface.

GPS Navigator

In addition to the aforementioned LRUs, (line replaceable units) the G500/G600 system requires at least one of the following: GNS 480, CNX80, GNS 400W series, or GNS 500W series GPS Navigator.

GTX 330/330D (Optional)

The GTX 330/330D is a solid-state transponder that provides Modes A, C, and S functions. The transponder provides traffic information to the display through an ARINC 429 digital interface.


34-70 Page 7 August 5, 2010

GDL 69/69A (Optional)

The GDL 69/69A is an XM Satellite Radio Data Link Receiver that receives broadcast weather data. The GDL 69A is the same as the GDL 69 with the addition of an XM Satellite Radio audio entertainment receiver. Weather data and control of audio channel and volume is displayed on the MFD, via a High- Speed Data Bus (HSDB) Ethernet connection. The GDL 69A is also interfaced to an audio panel for distribution of the audio signal. A subscription to the XM Satellite Radio service is required to enable the GDL 69/69A capability.

For additional hardware and software options; see the manufactures installation manual: G500 p/n 190-01102-06 & G600 p/n 190-00601-06


34-70 Page 8 August 5, 2010

Figure 34-70-01 G500/G600 System Architecture


34-70 Page 9 August 5, 2010

2. Troubleshooting The G500/G600 system is composed of sub-units or Line Replaceable Units (LRUs). This design greatly eases troubleshooting and maintenance of the G500/G600 system. A failure or problem can be isolated to a particular LRU, which can be replaced quickly and easily. Each LRU has a particular function, or set of functions, that contributes to the system’s operation. Figure 34-70-01 provides a generalized system arrangement including optional equipment. Figure 37-70-08 provides a typical electrical schematic. For information on trouble shooting the G500/G600 system refer to Section 6 of the applicable Garmin installation manual.

G500 Manual p/n 190-01102-06 G600 Manual p/n 190-00601-06

Figure 34-70-02 G500/G600 AHRS Fault Tree (Simplified)


34-70 Page 10 August 5, 2010

Figure 34-70-02 shows a simple fault tree and the resultant effect on the primary flight display. The green arrows signify the device is available and the red arrows denote a device is unavailable. Attitude and heading information is displayed on the PFD when the AHRS receives appropriate combinations of information from the external sensor inputs. Loss of GPS, magnetometer, or air data inputs is communicated to the pilot by message advisory alerts (refer to Section 6 for specific AHRS alert information). Any failure of the internal AHRS inertial sensors results in loss of attitude and heading information (indicated by red “X” flags over the corresponding flight instruments). A maximum of two GPS inputs are provided to the AHRS. If GPS information from one of the inputs fails, the AHRS uses the remaining GPS input and an alert message is issued to inform the pilot. If both GPS inputs fail, the AHRS will continue to provide attitude and heading information to the PFD as long as magnetometer and airspeed data are available and valid. If the magnetometer input fails, the AHRS continues to output valid attitude information and GPS Track information is used; however, the heading output on the PFD is flagged as invalid with a red “X,” “TRK” in magenta is annunciated to the right of the Track value, and the Track value color is changed from white to magenta. NOTE: In this case the magnetic standby compass and GPS ground track can be used to keep the aircraft on the desired heading. Failure of the air data input has no effect on the AHRS output while AHRS is receiving valid GPS information. Invalid or unavailable airspeed data in addition to complete GPS failure results in loss of all attitude and heading information.


34-70 Page 11 August 5, 2010

3. Maintenance Practices Maintenance of all G500/G600 LRUs is “on condition” only, with the exception of the air data computer (GDC 74A). The air data computer (GDC 74A) is “on condition” other than for regulatory testing pertaining to Part 43 Appendix E and F, (Pitot/Static leak test as described in Part 91.411). Per Part 43 Appendix E, paragraph (b)(2), the GDC 74A must be checked using a test procedure equivalent to Part 43 Appendix E, paragraph (b)(1) with two exceptions. The tests of sub-paragraphs (iv) (Friction) and (vi) (Barometric Scale Error) are not applicable because the digital outputs of the GDC 74A are not susceptible to these types of errors. Garmin Manuals In order to perform the maintenance tasks detailed in the following sections the technician will require access to the following Garmin installation manuals:

G500 Manual p/n 190-01102-06 G600 Manual p/n 190-00601-06

References to specific sections in the Garmin manuals are shown in green text.

Unit Replacement

Whenever removing or replacing units, remove power from the LRU by removing aircraft power or opening the LRU circuit breaker.

A. GDU 620 Display Unit Replacement (Reference Figure 34-70-03)

Removal Step 1. Remove the six mounting screws from the bezel of the GDU 620. Step 2. Pull the GDU 620 far enough out from the instrument panel to access the three rear

connectors. Step 3. Disconnect the rear connectors. Step 4. Remove the GDU 620. Replacement Step 1. Visually inspect the connectors to ensure that there are no bent or damaged pins.

Repair any damage. Step 2. Connect the rear connectors, ensuring that each slidelock is secured on both sides. Step 3. Set the GDU 620 into place. Step 4. Install the six mounting screws into the bezel of the GDU 620.


34-70 Page 12 August 5, 2010

Note: The installation configuration settings are stored in the configuration module and will be

retained when the GDU 620 is replaced with a new unit. User settings, such as map orientation preferences, are stored internally and will be lost when the GDU 620 is replaced with a new unit.

Original GDU 620 is Reinstalled If the original GDU 620 is reinstalled, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair process. No configuration is required. Verify that the configuration is correct using the previously completed checkout log in the aircraft technical log. New, Repaired or Exchange GDU 620 is Installed If the GDU 620 is replaced with a new, repaired, or exchange unit then software must be loaded. No configuration is required. Note: Upon first power-up after installing a new GDU 620, it is normal to see a series of

“LOADING…” messages appear on the screen. These messages indicate that the GDU 620 is updating its configuration settings from the configuration module. Continue to the GDU 620 Software Loading procedure in Section 5.4.1 followed by the Manifest Configuration in Section 5.5.4, and the Configuration Module Update in Section 5.5.11.

GDU 620 Configuration Module is Replaced If the GDU 620 Configuration Module is replaced, the GDU 620 will update the configuration module from its internally-stored settings when the UPDT CFG soft key is pressed as described in Section 5.5.11. Verify that the configuration is correct using the previously completed checkout log in the aircraft technical log. If the GDU 620 is replaced at the same time as the Configuration Module, then the System Setup will need to be performed per Section 5.5. To replace the configuration module, reference Section 3.4.2.2. G500 AML STC Installation Manual Page 3-119 190-01102-06 or G600 AML STC Installation Manual Page 3-113 190-00601-06 Return to Service After removing and reinstalling the GDU 620 per the instructions above, a simple return-to-service check should be performed. Step 1. Power up the GDU 620 in configuration mode. Verify that the configuration settings

match those recorded in the checkout log in the aircraft technical log Step 2. Power up the GDU 620 in normal mode. Verify that there are no red-Xs and that no

alerts are present. If red Xs or alerts are present, troubleshoot using Sections 6.2 and 6.3 of the applicable manufactures manual.


34-70 Page 13 August 5, 2010

B. GRS 77 AHRS Unit Replacement (Reference Figure 34-70-04)

The AHRS is located beneath the flight panel and is accessible from the pilot’s foot well without removing any access panels. Removal Step 1. Disconnect the GRS 77 connector. Step 2. Loosen the four Phillips thumbscrews with a screwdriver. Step 3. Gently lift the GRS 77 from the mounting plate (if the supports for the mounting plate

are removed, the GRS 77 must be recalibrated. See Section 5.6) Replacement Step 1. Place the GRS 77 on the mounting plate, ensuring the orientation is correct. Step 2. Fasten the unit to the plate using the Phillips thumbscrews. Recommended torque is

22-25 inch pounds. Step 3. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair

any damage. Step 4. Connect the connector to the GRS 77, ensuring that each slidelock is secured on both

sides. Original GRS 77 is Reinstalled If the original GRS 77 is reinstalled, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Reference Table 34-70-10 to determine whether recalibration is required. New, Repaired or Exchange GRS 77 is Installed If the GRS 77 is replaced with a new, repaired, or exchange unit, then software must be loaded per Section 5.4.2. Reference Table 34-70-10 to determine whether re-calibration is required. GRS 77 Configuration Module is Replaced If the GRS 77 Configuration Module is replaced, the GRS 77 must be re-calibrated refer to Table 34-70-01. To replace the configuration module, reference Section 3.4.2.2.


34-70 Page 14 August 5, 2010

Return to Service After removing and reinstalling the GRS 77, the following return-to-service checks should be performed. Step 1. Power up the system with the GDU 620 in normal mode. Step 2. Verify that the GDU displays valid heading and attitude within approximately one

minute. Note that heading can remain invalid if the magnetometer is near a large metal structure such as a hangar wall or if the magnetometer is close to a large ground power cart.

Step 3. Verify that no unexpected alerts are present. If alerts are present, troubleshoot using Sections 6.2 and 6.3.

Calibrations Required

Condition GRS 77

Pitch/Roll Offset

Section 5.6.1

GRS/GMU Magnetic

Calibration Section 5.6.2

Engine Run-up Vibration

Test Section 5.6.5

GRS 77 AHRS was removed and/or replaced. The mounting tray was NOT removed and the mounting tray bolts were NOT loosened.

None Required.

GRS 77 AHRS was removed and/or replaced. The mounting tray WAS removed and/or mounting tray bolts WERE loosened.

X X X

GRS 77 AHRS Configuration Module was replaced.

X X X

Table 34-70-01 GRS 77 AHRS Calibration Requirements


34-70 Page 15 August 5, 2010

C. GDC 74A ADC Unit Replacement (Reference Figure 34-70-05)

The ADC is located beneath the flight panel and is accessible from the pilot’s foot well without removing any access panels. Removal Step 1 Disconnect the pitot/static plumbing from the rear of the unit. Disconnect the single

connector. Step 2 Loosen each thumbscrew on the hold-down clamp and remove the clamp. Step 3 Carefully remove the unit from its mount. Replacement Step 1 Place the unit in the mounting tray. Step 2 Position the locking clamp and fasten using the thumbscrews. Step 3 Connect the pitot/static plumbing. Step 4 Inspect the connector and pins for damage. Repair any damage. Step 5 Connect the connector to the unit, ensuring that each slidelock is secured on both

sides. Original GDC 74A is Reinstalled If the original GDC 74A is re-installed, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. New, Repaired or Exchange GDC 74A is Installed If the GDC 74A is replaced with a new, repaired, or exchange unit, then software must be loaded to the unit. Continue to the GDC 74A Software Loading procedure in Section 5.4.4. GDC 74A Configuration Module is Replaced If the GDC 74A Configuration Module is replaced, the GDC 74A must be configured. Continue to Section 5.5.7. To replace the configuration module, reference Section 3.4.2.2. Return to Service After removing and reinstalling the GDC 74A, the following return-to-service checks should be performed. Step 1 Power up the G500 system with the GDU 620 in normal mode. Step 2 Verify that the GDU displays valid air data within approximately one minute.


34-70 Page 16 August 5, 2010

Step 3 Verify that no unexpected alerts are present. If alerts are present, troubleshoot using

Sections 6.2 and 6.3. Step 4 Perform a leak check of the pitot-static system and observe the airspeed, altitude, and

vertical speed for proper operation.

D. GMU 44 Unit Replacement (Reference Figure 34-70-06)

Removal Step 1 Gain access to the GMU 44 magnetometer located in the outboard port wing by

removing the access panel on the bottom of the wing.. Step 2 Unscrew the three screws that hold the GMU 44 to its mounting rack. Step 3 Carefully drop the GMU 44 from the rack. Step 4 Disconnect the wiring harness. Replacement Step 1 Visually inspect the connectors to ensure there are no bent or damaged pins. Repair

any damage. Step 2 Connect the wiring harness to the GMU 44. Step 3 Install the GMU 44 into the rack and secure the plate with the three Phillips screws. Original GMU 44 is Reinstalled If the original GMU 44 was reinstalled, then software loading is not required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Recalibration is required only if the mount for the magnetometer was changed. If the magnetometer mount was changed, continue to Section 5.6.2 for the GRS 77/GMU 44 Magnetic Calibration. After the GRS 77/GMU 44 Magnetic Calibration is performed, the criteria in Sections 5.6.3 and 5.6.4 should be used to determine whether the Heading Offset Compensation is necessary. New, Repaired or Exchange GMU 44 is Installed If the GMU 44 was replaced with a new, repaired, or exchanged unit, then software must be loaded and the GRS 77/GMU 44 Magnetic Calibration must be performed. Continue to Section 5.4.3 for software loading and Section 5.6.2 for the GRS 77/GMU 44 Magnetic Calibration. After the GRS 77/GMU 44 Magnetic Calibration is performed, the criteria in Sections 5.6.3 and 5.6.4 should be used to determine whether the Heading Offset Compensation is necessary.


34-70 Page 17 August 5, 2010

Return to Service After removing and reinstalling the GMU 44, the following return-to-service checks should be performed. Step 1 Power up the G500/G600 system with the GDU 620 in normal mode. Step 2 Verify that the GDU displays valid heading within approximately one minute. Note

that heading can remain invalid if the magnetometer is near a large metal structure such as a hangar wall or if the magnetometer is close to a large ground power cart.

Step 3 Verify that no unexpected alerts are present. If alerts are present, troubleshoot using Sections 6.2 and 6.3.

E. GTP 59 Unit Replacement (Reference Figure 34-70-07)

Removal Step 1 Remove the six retaining screws securing the inboard port side flap track cover on the

bottom of the wing. Step 2 Remove the “skirted” 5/16” hex nut. Step 3 Remove the associated pins on connector P741 of the GDC 74A, (pins 2, 3 and 4)

The temperature probe may now be removed. (Additional wire clamps and tie wraps may still need to be removed).

Installation Reverse the above steps Return to Service After removing and reinstalling the GTP 59, the following return-to-service checks should be performed. Step 1 Power up the G500/G600 system with the GDU 620 in normal mode. Step 2 Verify that the GDU displays valid OAT within approximately one minute. Step 3 Verify that no unexpected alerts are present. If alerts are present, troubleshoot using

Sections 6.2 and 6.3.


34-70 Page 18 August 5, 2010

Figure 34-70-03 GDU 620 Installation


34-70 Page 19 August 5, 2010

Figure 34-70-04 GRS 77 AHRS Installation


34-70 Page 20 August 5, 2010

Figure 34-70-05 GDC 74A Air Data Computer Installation


34-70 Page 21 August 5, 2010

MAGNETOMETERMOUNTINGRING

3 PLACESBRASS SCREWS WITH INTEGRAL LOCK FEATURE

(IF REMOVING AND REINSTALLING THESE SCREWSREAPPLY "BLUE LOCTITE" TO THE THREADS. IT IS

ACCEPTABLE TO REPLACE THESE SCREWS WITHMS35214−23 SECURED WITH "BLUE LOCTITE".

(OR ANY PAN−HEAD 6−32X1/4" LONG BRASS SCREW))

Figure 34-70-06 GMU 44 Magnetometer Installation


34-70 Page 22 August 5, 2010

Scuff Area Around Hole To Allow Electrical Bond

With OAT Probe. ApplyA small Amount Of DC4

Compound For Corrosion Protection

Figure 34-70-07 G500/G600 GTP-59 OAT Installation


34-70 Page 23 August 5, 2010

GDU 620G500 EFIS Display Unit

134

235

49503233

1516

421

102744

3047

AIRCRAFT POWERAIRCRAFT POWER

AIRCRAFT GROUNDAIRCRAFT GROUND

CONFIGURATION MODULE POWERCONFIGURATION MODULE GND

CONFIGURATION MODULE DATACONFIGURATION MODULE CLOCK

0605-200604-20

0606-200607-20

RED (0608)BLACK (0609)YELLOW (0610)

0612-220613-22

WHITE (0611)

GRS 77G600 EFIS AHRS Unit

1820

2224

171

1631

2539

10940

1530

AIRCRAFT POWER1AIRCRAFT POWER2

AIRCRAFT GROUND1AIRCRAFT GROUND2



RS-485 IN 1ARS-485 IN 1B

RS-232 OUT 2MAGNETOMETER PWR OUT

MAGNETONETOMETER GROUND

ARINC 429 IN 1AARINC 429 IN 1B

P771

0615-220614-22

0616-220617-22

RED (0619)BLACK (0620)YELLOW (0621)

0601-22 BLU0601-22 WHT

WHITE (0622)

GDC 74AG600 EFIS ADC Unit

4241

55

17

211

4060

234

ARINC 429 OUT 1BARINC 429 OUT 1A

AIRCRAFT POWER 1

AIRCRAFT GROUND 1



OAT POWEROAT PROBE IN HI

OAT PROBE IN LO

P741

0623-22 WHT0623-22 BLU

0625-22

0626-22

0603-22 WHT0603-22 BLU

0602-22 BLU0602-22 WHT

0602-22 ORG

0603-22 ORN

2627

111012

6717

ARINC 429 OUT 1AARINC 429 OUT 1B

GPS1 RS-232 OUTGPS1 RS-232 INSIGNAL GND

GPS2 RS-232 INSIGNAL GND

AHRS SYSTEM ID PGM* 1AHRS SYSTEM ID PGM* 2SIGNAL GROUND

1429

261141

635

23

37


RS-232 OUT 1RS-232 IN 1SIGNAL GND

ADC SYSTEM ID PGM* 1ADC SYSTEM ID PGM* 2SIGNAL GROUND

GTP 59OAT Probe

GMU 44Magnetometer

4218963

P771

P741

4132

ConfigurationModule

4132

ConfigurationModule

4132

ConfigurationModule

5

F45

5

F46

5

F44

A/P HEADING ERROR HIA/P HEADING ERROR LO

A/P COURSE ERROR HIA/P COURSE ERROR LO

LATERAL +FLAG OUTLATERAL -FLAG OUT

LATERAL +LEFT OUTLATERAL +RIGHT OUT

VERTICAL +FLAG OUTVERTICAL -FLAG OUT

VERTICAL +UP OUTVERTICAL +DOWN OUT

GPS SELECTRS-232 OUT 8RS-232 GND 8

ILS/GPS APPROACH


RS-485 3ARS-485 3B

1840

1941

5455

5253

5859

5657

453051

46

123

1133

P6203

2

2

S

S

S

S

S

S

S S

SS

S S

S S

LIGHTING BUS HILIGHTING BUS LO


RS-232 IN 1RS-232 OUT 1 RS-232 GND 1

RS-232 OUT 4RS-232 GND 4

n/cn/cn/c

n/cn/cn/c


RS-232 IN 2RS-232 OUT 2 RS-232 GND 2

Ground At ProbeInstallation Point(See N2389)

RS-232 IN 3RS-232 GND 3

TIME MARK IN 1ATIME MARK IN 1B



S

S

S

S

522

112845

1246

4041

623

320

A

A

B

C

D

E

F

G

H

I

J

X

Y

Z

JN218-216 CRIMP NUT

SILVER SOLDER

60/40 RESIN CORE

PDIG22-1

SOLDER SLEEVE

VENDOR SUPPLIED

PN14-6R

PN14-8R

PN14-10R

P6-8R

P6-10R

P6-56R

PN18-56R

PN14-14R

P2-14R

PN18-10R

PN18-8R

PN18-6R

P6-14R

K P2-56R

*

ARINC VOR/ILS 429 IN 4A ARINC VOR/ILS 429 IN 4B

S

724

P6202SYSTEM 55XAUTO PILOT

2829

1112

1314

3130

49

32

HDG DATUM HIHDG DATUM LO

CRS DATUM HICRS DATUM LO

LAT DEV FLAG+LAT DEV FLAG-

LAT DEV +LTLAT DEV +RT

GS DEV FLAG+GS DEV FLAG-

GS DEV+UPGS DEV +DOWN

GPSS STEERING

GPS TRACK GAIN

LOC SWITCH

AB

AB

ALT SEL JUMPERGROUND

P2

12

1819

38

3637

2120

2342

P1

n/cn/c

S

S

S

S

S

S

S

S

429 GPSS DATA IN {

{ALT SEL/BARO ALTRS-485

4

1229

1330

101144

27

P6201

9

3534

1516

2829

26n/cn/cn/c

FD LOGIC

ROLL FD STEERINGSIG REF (ROLL FD)

PITCH FD STEERINGSIGNAL REF (PITCH FD)

10 VDC PARALLAX POTPITCH STR CENTERING

FD POT GROUND

AUDIO OUT

OPTIONAL - REFERENCE ONLY - SEE L2073 FOR ADDITIONAL DETAILS

TO TB3-5 (FLIGHT PANEL LIGHTS, SEE L2007 FOR ADDITIONAL DETAILS)

RED (0627)BLACK (0628)YELLOW (0629)WHITE (0630)

0650-20 SH

0637-22

0638-22

0639-22

0642-22

0631-22 BLU0631-22 WHT

0632-22 BLU0632-22 WHT

0633-22 BLU0633-22 WHT

0634-22 BLU0634-22 WHT

0635-22 BLU0635-22 WHT

0636-22 BLU0636-22 WHT

0640-22 BLU0640-22 WHT

0641-22 BLU0641-22 WHT

0643-22 BLU0643-22 WHT

0644-22 BLU

0644-22 WHT

S

S

FD ENABLE IN

FD ROLL RIGHT FD ROLL LEFT

FD PITCH UPFD PITCH DOWN

AUDIO OUT HIAUDIO OUT LO

TIS/TAS STANDBY

0646-22 BLU0646-22 WHT

0646-22 ORG

0648-22 BLU0648-22 WHT

0648-22 ORG

0647-22 BLU0647-22 WHT

0645-22 BLU0645-22 WHT

0649-22 BLU0649-22 WHT

0651-22 BLU0651-22 WHT

0652-22 BLU0652-22 WHT

0653-22 BLU0653-22 WHT

5

5

5

4x - 390 1/4 W

S

2

2

GENERAL NOTES:

1. Ground Designations: Shield Block Ground Airframe Ground

2. Unless otherwise specified by PMS or drawing notes, all electrical wire harness and equipment installations shall be in accordance with ac 43.13-1B chapter 11.3. FBA-2C3 and FBA-2C4 aircraft wires are, in general, sequentially numbered and are prefaced by a zero. The base # is followed by a dash # representing the wire gauge. 4. Wires with colour or other designations, implied or otherwise noted, are vendor supplied and do not require additional labels. Number designators are for reference and compliance use.

7

It Is AcceptableTo Extend Cable.(Keep Splice CompactAs Practical).

S S

RS-232 IN 4

TIME MARK IN 2A


S

S

13

42

825

ARINC VOR/ILS 429 IN 6A ARINC VOR/ILS 429 IN 6B

S

926

0655-22

0654-22

0656-22 BLU0656-22 WHT

0657-22 BLU0657-22 WHT

S

AIRCRAFT POWER 1AIRCRAFT POWER 2

POWER GROUNDPOWER GROUND

SIGNAL GROUNDTxDRxDSIGNAL GROUND

ETHERNET OUT AETHERNET OUT BETHERNET IN AETHERNET IN B

AUDIO SUPRESSION IN (HI)AUDIO SUPRESSION IN (LO) _____AUDIO MUTE ___CHANNEL UP ______CHANNEL DOWN ___ VOLUME UP ______VOLUME DOWN

SIGNAL GROUND

AUDIO OUT LOAUDIO OUT RIGHTAUDIO OUT LEFT

3537

2078

425

39

25242322

6164

70

71

72

73

74

75

171819

GDL 69AXM WX Satellite Weather

XM Satellite Radio011-00987-00

P691

5

F47

0662-22

0663-22

0667-22 WH0667-22 BL0667-22 OR

Terminate Shields At Screws Located On Back Of Mounting Tray

123

255

242389

10111213141516172046

181972122

RESERVEDRESERVEDRESERVEDRESERVED

INTERCOM MIC HIRESERVEDRESERVEDRESERVEDRESERVEDRESERVED


RESERVEDTRANSMIT INTERLOCK

COM REMOTE TRANSFERSPARE

INTERCOM MIC LORESERVED

COM MIC KEYCOM MIC AUDIO HI

COM MIC AUDIO LO500 OHM COM AUDIO LO500 OHM COM AUDIO HI


60616263646566676869707215637312

7187459

14167546474849505110114344451718751213373852537476

0752-22 WH0753-22 BL

0749-22 WH0750-22 BL

0817-180816-18

0798-22

VOR ILS ARINC 429 OUT BVOR ILS ARINC 429 OUT A

VOR OBI CLOCKVOR OBI SYNCVOR OBI DATA

VLOC REMOTE TRANSFERILS ENERGIZE

GLIDESLOPE +FLAGGLIDESLOPE +DOWN -FLAG GS COM.

GLIDESLOPE +UPPARALLEL DME 1MHz

RESERVEDVOR ILS ARINC 429 IN BVOR ILS ARINC 429 IN APARALLEL DME 800KHz

GLIDESLOPE SUPERFLAGPARALLEL DME 400KHzPARALLEL DME 200KHzPARALLEL DME 100KHzPARALLEL DME 50KHz

19

18

20

22

1617

4441

123456789

101112131415212324252627282930313233343536373839404243

VOR/LOCANT.

ALTITUDE COMMONALTITUDE C4ALTITUDE C2ALTITUDE C1ALTITUDE B4ALTITUDE B2ALTITUDE B1ALTITUDE A4ALTITUDE A2ALTITUDE A1ALTITUDE D4

GLIDESLOPEANT.

P4007

MAIN +UPMAIN +DOWN

MAIN OBS STATOR DMAIN OBS STATOR EMAIN OBS STATOR FMAIN OBS STATOR GMAIN OBS ROTOR HMAIN OBS ROTOR C

1920

7778

3940

5756

5859

4241

5554




GPS RS 232 IN 1GPS RS 232 OUT 1

GPS RS 232 OUT 2GPS RS 232 IN 2



0805-22

0799-22

0804-22

0802-220803-22

5

0797-220796-22

0794-220795-22

2728

333435363231

P4005

P4003

GPSANT.

COMMANT.

P4004

0751-22 OR

0815-22

0814-22

0813-180812-18

5

RG400

RG400

RG400

RG400COMMANT.

CI 121

GNS 430WCOMM/GPS/VOR

011-01060-00

MAIN UNIT (NAV 1)

MAIN +LEFTMAIN +RIGHT

MAIN +TOMAIN +FROM

MAIN LATERAL +FLAGMAIN LATERAL -FLAG

MAIN VERTICAL -FLAGMAIN VERTICAL +FLAG

2122

2526

2324

3029

P4001 P4006

0740-22 WH

0811-22

0741-22 BL

123255242389

10111213141516172046

181972122

RESERVEDRESERVEDRESERVEDRESERVEDINTERCOM MIC HIRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDAIRCRAFT POWERAIRCRAFT POWERRESERVEDTRANSMIT INTERLOCKCOM REMOTE TRANSFERSPAREINTERCOM MIC LORESERVEDCOM MIC KEYCOM MIC AUDIO HICOM MIC AUDIO LO500 OHM COM AUDIO LO500 OHM COM AUDIO HIAIRCRAFT GROUNDAIRCRAFT GROUND

Belden

8490

ICS MUTE INHIBITICS MUTE INHIBIT RETURN

SWAPSWAP RETURN

PA MUTE8 OHM SELECTTONE ENABLERESERVED DO NOT USE


PILOT MIC RETURNPILOT MIC IN

PILOT MIC KEY

PASS HEADSET RETURNPASS HEADSET RPASS HEADSET L

EXT WHITE LAMP AEXT BLUE LAMP O

EXT AMBER LAMP M

13116

243

343233

3635

3837

4039

4241

252423

282726

4443

1314

2021

12171918

89

1011

567

15222930

2526

910

1112

2728

1314

1530

2324

3456

1718

1920

2122

78

3132

4443

353334

424140

363738

39

12

1629

Terminate Shields At Screws Located On Back Of Mounting Tray

AIRCRAFT GNDAIRCRAFT GND

14V LGT LO - 28V LGT LO14V LGT HI - 28V LGT LO28V LGT HI

NCNCNCCOM TX MUTE

0736-22

0734-22

0733-22 0732-22

5

0735-22

MIDDLE MKR SENS

MKR ANTMKR ANT RETURN

MASQ INHNC

0171-22 WH

0171-22 BL

159-22

GP-A

162-22

X

BLKGRN

094-22 BL

PILOT HEADSET RETURNPILOT HEADSET RPILOT HEADSET L

COPILOT HEADSET RETURNCOPILOT HEADSET RCOPILOT HEADSET L

COPILOT MIC RETURNCOPILOT MIC INCOPILOT MIC KEY

PASS 1 MIC RETURNPASS 1 MIC




MUSIC 1 RETURNMUSIC 1 RMUSIC 1 L

MUSIC 2 RETURNMUSIC 2 RMUSIC 2 L

SPKR OUTSPKR RETURN

0177-22 BL0177-22 WH

098-22 BL098-22 WH

097-22 BL097-22 WH

099-22 OR

099-22 BL099-22 WH

0162-22

NAV 1 INNAV 1 RETURN

NAV 2 INNAV 2 RETURN

DME INDME RETURN

ADF INADF RETURN

ALTWARN INALTWARN RETURN

TELRINGER INTELRINGER RETURN

COM 3 SPKRLOADCOM 3 SPKRLOAD RETURN

COM 2 SPKRLOADCOM 2 SPKRLOAD RETURN

COM 3 INCOM 3 RETURN

COM 3 MICCOM 3 KEY


COM 2 MICCOM 2 KEY

094-22 WH

095-22 BL

095-22 WH

J2COM 1 SPKRLOAD

COM 1 SPKRLOAD RETURN


COM 1 MICCOM 1 KEY

J1

0100-22 OR

0100-22 BL0100-22 WH

0160-22

0743-22 BL0742-22 WH

0741-22 BL0740-22 WH

0748-22 BL0747-22 WH

0746-22 OR0745-22 BL0744-22 WH

160-22 WHT

07

52-2

2 W

H0

753

-22

BL

07

49-2

2 W

H0

750

-22

BL

07

51-2

2 O

R

0747-22 WH0748-22 BL

0744-22 WH0745-22 BL

0862-180858-18

164-22 WH

SW21, P.T.T., CO-PILOT

165-22 WH

BLKGRN

163-22 BL

WHT

161-22 BLSW13, P.T.T., PILOT

SERIAL DME DATA

SERIAL DME DATA

SER DME-CHAN REQ PAR DME-4MHz

DME COMMON

500 OHM VOR-ILS AUDIO HI500 OHM VOR-ILS AUDIO LO

AIRCRAFT POWERAIRCRAFT GROUND

GNS 430WCOMM/GPS/VOR

011-01060-00

BACKUP UNIT (NAV 2)

19

18

20

22

1617

4441

123456789

101112131415212324252627282930313233343536373839404243

RG400GLIDESLOPE

ANT. 1GLIDESLOPE

ANT. 2

MODEL CI 1125TWO-WAY VOR/LOC/GS

DIPLEXER

RG400

RG400

ANTENNAINPUT

RG400

VOR/LOCANT. 1

VOR/LOCANT. 2

CI 159C

VOR/LOC/GSANT.

RG400VOR/LOC

ANT.

814-22

0746-22 OR

5 0860-180859-18

0815-22

P4007RG400

GLIDESLOPEANT.

013-00244-00

CI 121

GPS ANT.GA 36

COMMANT.

P4005

P4003

P4004

RG400

RG400

RG400

GPS ANT.

COMMANT.

0742-22 WH0743-22 BL

0861-22

P4006

MAIN +LEFTMAIN +RIGHT

MAIN +TOMAIN+FROM

MAIN LATERAL +FLAGMAIN LATERAL -FLAG

MAIN +UPMAIN +DOWN

MAIN VERTICAL +FLAGMAIN VERTICAL -FLAG

MAIN OBS ROTOR HMAIN OBS ROTOR C

MAIN OBS STATOR DMAIN OBS STATOR E

MAIN OBS STATOR FMAIN OBS STATOR G

GPS ANNUNCIATOR

VLOC ANNUNCIATOR

2122

2526

2324

2728

2930

3231

3334

3536

2

1

6061626364656667686970721563

73

7187459

14167546474849505110114344451718751213373852537476

AIRCRAFT POWER 2AIRCRAFT POWER 2

MESSAGE ANNUNCIATEWAYPOINT ANNUNCIATE

CDI SOURCE SELECT

OBS MODE SELECTAUTO ANNUNCIATE

OBS ANNUNCIATETERMINAL ANNUNCIATE

APPROACH ANNUNCIATEINTEGRITY ANNUNCIATE

ILS-GPS APPROACHTIME MARK OUT

DEMO MODE SELECTGPS ARINC 429 OUT 1 AGPS ARINC 429 OUT 1 B

GPS ARINC 429 IN 1 AGPS ARINC 429 IN 1 BGPS ARINC 429 IN 2 AGPS ARINC 429 IN 2 B

ANNUNCIATE DANNUNCIATE E

MAIN OBI CLOCKMAIN OBI DATAMAIN OBI SYNC

MAIN LATERAL SUPERFLAGMAIN VERTICAL SUPERFLAG

DEMO MODE SELECTALTITUDE ALARM ANNUNCIATE

ANNUNCIATE FALTITUDE ALARM AUDIO HI

ALTITUDE ALARM AUDIO LORESERVEDRESERVEDRESERVEDRESERVED

0856-22

0804-22

0805-22

0855-22

0854-22

0853-22

0849-22

0848-221920

7778

3940

5756

5958

4241

5554








ALTITUDE COMMONALTITUDE C4ALTITUDE C2ALTITUDE C1ALTITUDE B4ALTITUDE B2ALTITUDE B1ALTITUDE A4ALTITUDE A2ALTITUDE A1ALTITUDE D4

5

P4001

11121314

ETHERNET IN 1AETHERNET IN 1B

ETHERNET OUT 1AETHERNET OUT 1B

0658-22 Brn0658-22 Brn/Wht0658-22 Org

0658-22 Org/Wht

ADF X/COS INADF Y/SIN INADF DC REF IN

171836

SERIAL DME DATA

SERIAL DME DATA

SER DME-CHAN REQ PAR DME-4MHz

DME COMMON

500 OHM VOR-ILS AUDIO HI500 OHM VOR-ILS AUDIO LO

AIRCRAFT POWERAIRCRAFT GROUND

VOR-LOC +TOVOR-LOC +FROM VOR-LOC COMMON

VOR-LOC +FLAGVOR-LOC -FLAG VOR-LOC COMMON

VOR-LOC +LEFTVOR +RIGHT VOR-LOC COMMON

RESERVEDVOR-LOC COMPOSITE OUT

VOR OBS ROTOR CVOR OBS ROTOR H GROUND

VOR OBS STATOR EG VOR-LOC COM.VOR OBS STATOR FVOR OBS STATOR D

PARALLEL DME - 8MHzVOR-LOC SUPERFLAG

SER DME RNAV MODE PARDME-2MHz

P4002 P4002

TIME MARK OUTDEMO MODE SELECTGPS ARINC 429 OUT AGPS ARINC 429 OUT BGPS ARINC 429 IN 1 AGPS ARINC 429 IN 1 BGPS ARINC 429 IN 2 AGPS ARINC 429 IN 2 BANNUNCIATE DANNUNCIATE EMAIN OBI CLOCKMAIN OBI DATAMAIN OBI SYNCMAIN LATERAL SUPERFLAGMAIN VERTICAL SUPERFLAGDEMO MODE SELECTALTITUDE ALARM ANNUNCIATEANNUNCIATE FALTITUDE ALARM AUDIO HIALTITUDE ALARM AUDIO LORESERVEDRESERVEDRESERVEDRESERVED

AIRCRAFT POWER 2AIRCRAFT POWER 2MESSAGE ANNUNCIATEWAYPOINT ANNUNCIATECDI SOURCE SELECTVLOC ANNUNCIATEGPS ANNUNCIATEOBS MODE SELECTAUTO ANNUNCIATEOBS ANNUNCIATETERMINAL ANNUNCIATEAPPROACH ANNUNCIATEINTEGRITY ANNUNCIATEILS-GPS APPROACH

VOR ILS ARINC 429 OUT BVOR ILS ARINC 429 OUT AVOR OBI CLOCKVOR OBI SYNCVOR OBI DATAVLOC REMOTE TRANSFERILS ENERGIZEGLIDESLOPE +FLAGGLIDESLOPE +DOWN -FLAG GS COM.GLIDESLOPE +UPPARALLEL DME 1MHzRESERVEDVOR ILS ARINC 429 IN BVOR ILS ARINC 429 IN APARALLEL DME 800KHzGLIDESLOPE SUPERFLAGPARALLEL DME 400KHzPARALLEL DME 200KHzPARALLEL DME 100KHzPARALLEL DME 50KHz

VOR-LOC +TOVOR-LOC +FROM VOR-LOC COMMONVOR-LOC +FLAGVOR-LOC -FLAG VOR-LOC COMMONVOR-LOC +LEFTVOR +RIGHT VOR-LOC COMMONRESERVEDVOR-LOC COMPOSITE OUTVOR OBS ROTOR CVOR OBS ROTOR H GROUNDVOR OBS STATOR EG VOR-LOC COM.VOR OBS STATOR FVOR OBS STATOR DPARALLEL DME - 8MHzVOR-LOC SUPERFLAGSER DME RNAV MODE PARDME-2MHz

S

MVP-50P-6ENGINE MONITOR

(See L2003)

RS232 RxD (8)RS232 TxD (7)

VOICE WARNING OUT+ (23)VOICE WARNING OUT- (24)

4

Connector AtWing RouteSee L2331

06B-22 Z

ZZ

09-22

08C-22

GP-Wing

X

Lift DetectorP/N 164

5

08D-22

Stall Warning HornMallory Sonalert

P/N SC628MN

Z Z

Z

0658-22 Brn0658-22 Brn/Wht0658-22 Org

0658-22 Org/Wht

0659-22 BLU

0659-22 WHT

0660-22 BLU

0660-22 WHT

0661-22 BLU0661-22 WHT

n/c

n/c

n/c

n/c

n/c

n/c

n/c

L2017 SchematicReference

06

60-

22 W

HT

06

60

-22

BL

U

06

49-2

2 B

LU

06

49-2

2 W

HT

0649-22 BLU

0802-220803-22

0649-22 WHT

Ground All 430W ShieldsAt Grounding Block,

(Back Plate).

0668-22*It is acceptable to splice 0668 into

wire 08D or 08C with solder sleeveor use a RTT as indicated.

XMANT.

013-00245-00

GPS ANT.GA 37

Ground All 430W ShieldsAt Grounding Block,(Back Plate).

0655-22

Ground All 430W ShieldsAt Grounding Block,

(Back Plate).

Ground All 430W ShieldsAt Grounding Block,(Back Plate).

0654-22

0656-22 BLU0656-22 WHT

0657-22 WHT

0657-22 BLU

0669-22 BLU0669-22 WHT

0669-22 BLU0669-22 WHT

0650-20 SH

0651-22 BLU0651-22 WHT0652-22 BLU

0652-22 WHT

0653-22 BLU0653-22 WHT

GRNWHT

WHT/BLU

WHT/GRY 0680-22 WHT0680-22 BLU

11-33 Vdc AIRCRAFT POWER 111-33 Vdc AIRCRAFT POWER 1

11-33 Vdc AIRCRAFT POWER 211-33 Vdc AIRCRAFT POWER 2


SWITCHED POWER OUT

AVIONICS MASTER ON SELECT

28V LIGHTING BUS HI

2142

5660

2743

62

1

14

010-10160-00

BOTTOMXPNDR ANT.

P3302

GTX 330DTRANSPONDER

011-00455-70

0678-220676-22

P3301



_______TIS CONNECT SELECT

3235

3028

46

0675-22

0674-225

n/cn/c

010-10160-00

TOPXPNDR ANT.

P3303

ALTITIUDE D4ALTITIUDE A1ALTITIUDE A2ALTITIUDE A4ALTITIUDE B1ALTITIUDE B2ALTITIUDE B4ALTITIUDE C1ALTITIUDE C2ALTITIUDE C4

ALTITUDE COMMON (GROUND)_______

AUDIO MUTE SELECT

AUDIO OUT HIAUDIO OUT LO

_______EXTERNAL IDENT SELECT

SQWAT SWITCH IN

EXTERNAL SUPPRESSION I/O_______

EXTERNAL STANDBY SELECT___________

ALTITUDE ALERT ANNUNCIATE

1124579

10836

50

47

1516

12

17

31

13

19

RS 232 IN 1RS 232 OUT 1

SIGNAL GROUND

RS 232 IN 2RS 232 OUT 2





CURRENT TEMPERATURE PROBE INCURRENT TEMPERATURE PROBE OUT

222351

2425

3734

3336

2629

4849

4441

0679-22


426

0670-22 WHT0670-22 BLU

INDICATES 'CAP & STOW' (HEAT SHRINK PREFERRED)

0670-22 BLU0670-22 WHT

0671-22 WHT0671-22 BLU

0672-22

0671-22 BLU0671-22 WHT

0672-22

Cables Must Be Equal Length(< 4" Difference Finished Length)

0673-22 BLU0673-22 WHT

06

73-2

2 B

LU

06

73

-22

WH

T

06

80-2

2 B

LU

06

80

-22

WH

T

0681-22

06

81-2

2 0

661

-22

BLU

06

61

-22

WH

T

NOTES:

1. The G500 System Shall Be Installed Per The AML STC Installation Manual 190-01102-06. Additional Guidance Shall Be Provided On N300/N400 And Other Drawings As May Be Applicable.2. The GNS 430W Systems Shall Be Installed Per The AML STC Installation Manual 190-00356-02. Additional Guidance Shall Be Provided On N300/N400 And Other Drawings As May Be Applicable. 3. The GTX 330D System Shall Be Installed Per The AML STC Installation Manual 190-00207-02. Additional Guidance Shall Be Provided On N300/N400 And Other Drawings As May Be Applicable. 4. The PMA8000-MP3 System Shall Be Installed Per The AML STC Installation Manual 200-890-0600. Additional Guidance Shall Be Provided On N300/N400 And Other Drawings As May Be Applicable. 5. The GDL 69A System Shall Be Installed Per The AML STC Installation Manual 190-00355-02. Additional Guidance Shall Be Provided On N300/N400 And Other Drawings As May Be Applicable. 6. The S-Tec System 55X Connections Are Provided For Reference Only. The Associated Wires Shall Be Routed For A Top Center Stack Location With An Additional 6" Length. Stub Off And Label These Wires.

REFERENCE - SEE L2003 FOR ADDITIONAL DETAILS

PMA8000B-MP3ICS/AUDIO PANEL/MARKER RECEIVER

050-890-0602

0171-22 OR

095-22 OR

094-22 OR

0667-22 WH0667-22 BL0667-22 OR

01

72-22

BL

01

72

-22 W

H0

17

2-22 O

R

09

6-2

2 BL

09

6-2

2 W

H0

96

-22

OR

Figure 34-70-08 G500/G600 Typical Electrical Schematic


34-70 Page 24 August 5, 2010


chapter 34 flight & navigation instruments - … ack a-30 altitude encoder ... removal and...

Documents