21-10-04 mass flow controller - extra aircraft · 2015-05-27 · maintenance manual extra 500 page...

Maintenance Manual EXTRA 500

Page Date: 30. March 2012 21 5

21-10-04 Mass Flow Controller

Removal/Installation Detail Steps/Work Items Key Items

1 Remove left side armrest paneling. Refer to Chapter 25-20-21.

2 Disconnect the electrical connector from the mass flow controller.

2 Remove mass flow controller. 4 attachment nuts

5 Install in reverse sequence of removal.

21-10-05 Muffler The muffler is directly mounted to a flange providing a holding fixture for the mass flow sensor.


1 Remove LH engine cowling. Refer to Chapter 71-10-01.

2 Remove mass flow sensor. Remove 4 screws.

3 Disconnect SCEET hoses from muffler and flange.

4 Remove attachment bolts of hose clip and hose clamp carrying muffler and flange.

5 Remove muffler with flange.


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Page 16 21 Page Date: 30. March 2012

21-20-00 DISTRIBUTION

Description Refer to Figure 21-1.

The system consists of a valve box, SCEET hoses, a distribution valve, a Bowden cable with a handle on the center console panel and the panel vent fans.

Ram air or bleed air is ducted into the cabin (refer to Section 21-10 for the bleed air system).

Ram air is taken from the oil cooler inlet on the right engine side and routed through SCEET hoses to a valve box on the firewall. 2 check valves are mounted to the valve box (ram air and bleed air side). Additionally the valve box has a holding fixture for the duct temperature sensor. The cabin inflow check valve is mounted between the valve box and the firewall.

Inside the cabin a valvular operated air distributor guides the air stream to the windshield and/or legroom dispensers. The air distributor has also a holding fixture for the temperature switch.

For better ventilation in the forward cabin section two vent fans are installed in the LH and RH side of the instrument panel. Each vent fan sucks air from behind the panel. On the discharge side each vent fan is connected to an eyeball vent, which can be adjusted to direct or shut off the airflow. Two switches, placed on the instrument panel near the resp. air outlet, control the vent fans. The electric fan motors are protected by a 2 A - fuse. The evaporators (refer to Section 21-50) also work as cabin fans. Both evaporator blowers work with different power settings in low or high mode.

21-20-01 Panel Vent Fans Removal/Installation

Detail Steps/Work Items Key Items

1 a (RH vent fan) Remove right main panel. Refer to Chapter 31-10-03

1 b (LH vent fan) Remove IFD-1 and IFD-2 and engine indicator.

Refer to Chapter 31-60-01 and Chapter 77-40-01

2 Loosen worm drive hose clamp on vent fan casing.

3 Disconnect electrical wiring.

4 Remove vent fan with casing.

5 Disassemble vent fan and casing if applicable.

4 bolts

6 Remove eyeball vent. 1 nut

7 Reverse procedure for installation.

Page Date: 12. December 2013 TEMPORARY REVISION N° 0B702-TR-03-20131212


Page Date: 30. March 2012 21 Page 17


8 Perform pitot/static test. According to FAR 43, Appendix E and AC 43.13-1B CHG1 (or later) § 12-59

TEMPORARY REVISION N° 0B702-TR-03-20131212

Page Date: 12. December 2013



21-30-00 PRESSURIZATION CONTROL

Description Refer to Figure 21-1.

The system consists of the engine compressor, two sonic venturi (flow limiters), a cabin control outflow valve, an unregulated safety valve, the cabin pressurization/dump switch, the cabin pressure controller, the landing gear squat switch, and two indicators, one for cabin altitude and differential pressure and one for cabin rate-of-climb.

Pressurized air is supplied from the engine bleed air through the sonic venturi and then through a check valve into the cabin. Adequate flow to maintain pressurization up to the maximum differential pressure of 5.5 PSI is provided by the engine at normal power setting. Power changes should be made smoothly to prevent sudden changes in pressurization air inflow resulting in cabin pressure transients.

Operation The airplane may be operated in either the pressurized or depressurized mode. The mode selection is made with the cabin pressurization switch, which either activates the cabin control outflow valve or leaves it open. Mode operation should be selected prior to takeoff. If a change from pressurized to depressurized mode must be made while airborne, depressurize the cabin following the procedure given below before turning the dump switch as otherwise a rapid decompression occurs, which would cause discomfort to the passengers. When changing from unpressurized to pressurized mode, the cabin altitude rate of change will be limited by the pressurization controller. The valves are also opened by the landing gear squat switch assuring depressurized mode when aircraft is on ground to avoid bursting the cabin door due to cabin pressure when opening.

In the pressurized mode cabin pressure is regulated by the cabin control outflow valve allowing air to exhaust either to the pressure level preselected by the cabin pressure controller or to maximum differential pressure level. Setting the center dial (identified as “Flight Level”) of the cabin pressure controller will suggest the system being at a certain flight altitude. So the system will maintain the corresponding cabin altitude (about 5.5 PSI above static pressure of flight level) or reach it with the rate set by the rate control knob located on the lower left corner of the pressurization controller. Only in case of maximum differential pressure is reached or flight level is below the selected cabin altitude, cabin altitude changes with the same rate the flight altitude does.

In case of failure of the cabin outflow control valve the safety valve will open at a differential pressure of slightly above 5.5 PSI to avoid structure damage.

Handling Use the cabin pressure controller as follows. Also refer to the sample chart (Figure 21-1).

1 Activate the pressurization controller by turning on the cabin pressurization switch. Make sure the ENV AIR switch is ON.

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Selected and held in COOL or WARM position activates the temperature modulating valve manually (overrides the controller) causing warm up or cool down of incoming bleed air.

21-60-01 Temperature Switch


1 Ensure BATT switch is OFF and no external power connected.

2 Remove right main panel. Refer to Chapter 31-10-03

3 Remove attachment bolts of distribution valve.

To allow moving the distribution valve.

4 Move the distribution valve up some centimeters.

5 Cut the electrical wiring from the temperature switch

Reconnect later by splicing.

6 Remove temperature switch from the distribution valve.


Function Test Detail Steps/Work Items Key Items


2 Remove front SCEET hose from cabin inflow box.

3 Carefully induct a 10 mm Ø tube through the two check valves in the cabin inflow box up to the temperature switch.

4 Place BATT switch to ON position.

5 Place NIGHT/DAY switch to TEST position. To ensure annunciator lights are OK.

6 Apply hot air through the tube to the temperature switch.

More than 85 °C. Use a blow dryer.

7 Check BLEED OVERTEMP illuminates. Replace temperature switch if necessary.

8 Place BATT switch to OFF position.






9 Carefully remove the tube from the cabin inflow box.

10 Reinstall front SCEET hose.

21-60-02 Duct Temperature Sensor

Removal/Installation The duct temperature sensor is attached to the valve box on the RH upper firewall with 4 bolts and nuts. To make the nuts accessible the forward hose and the flange have to be removed.



2 Remove LH and RH engine cowling. Refer to Ch. 71-10-01/02

3 Disconnect the forward SCEET hose from the valve box.

Worm drive hose clamp, safety wire

4 Remove flange from the valve box. 4 nuts

5 Disconnect electrical connector from the temperature sensor.

Bayonet nut

6 Remove temperature sensor. 4 bolts and nuts

7 Install in reverse sequence of removal. Observe the following step.

WARNING Refer to Product Label and Material Safety Data Sheet for health and safety information before using PR812.

8 Seal flange with PR812.

21-60-03 Cabin Temperature Sensor



2 Remove paneling above pilot seat. Refer to Chapter 25

3 Disconnect electrical wiring from the cabin temperature sensor.






4 Remove sensor. 4 nuts


21-60-04 Temperature Controller



2 Remove left side cabin paneling. Refer to Chapter 25.

3 Disconnect the electrical wiring from the temperature controller.

4 Remove temperature controller. 4 attachment screws






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22-00-00 GENERAL

This chapter describes the features and functions of the System 55X Two and a half Axis Autopilot and gives information on basically required maintenance practices as well as related system components.



22-10-00 AUTOPILOT

Description Refer to Figure 22-1. The S-TEC System 55X autopilot system is a rate based autopilot. Internal signal processing for regulating purposes is mainly analog, whereas digital electronics is used for the pilot interface and for controlling the mode of operation.

Pitch and Roll Axis The signal for the roll servo is generated using the following inputs:

1 Rate of turn information heading bug determined by the Turn Coordinator.

2 Navigation avionics (VOR / LOC, GPS; via IFD).

The signal for the pitch servo is generated using the following inputs: 1 Static pressure (via remote mounted Absolute Pressure Transducer).

2 Sensitive Accelerometer (contained in the Programmer / Computer unit).

3 Altitude Selector (via IFD, key pad or vertical speed knob on A/P computer).

4 Glide Slope Receiver (via IFD).

The autopilot can be activated by means of the 3-position AUTOPILOT MASTER/FD switch located in the right lower side of the pilot's instrument panel.

Switching it from the OFF-position to the first stage (FD) energizes the autopilot system. The autopilot will start its self-test routine ending up in a ready mode if performed successfully. This allows the pilot to select the different operating modes. If appropriate modes are activated set-point steering commands are shown by the Flight Director symbol displayed in the IFD-1. The pitch and roll servos are not engaged. Pitch and roll still have to be controlled by normal steering, using the data provided by the IFD as a set-actual comparison.

In the second stage (MASTER) the servos are energized and the autopilot controls pitch and roll axis according to the operating mode(s) selected (refer to POH).

One possibility to engage the autopilot (both axis) is given by the CWS switch (control wheel steering) located on top of the right horn of the pilot's control yoke. This mode engages the autopilot in a way which maintains the actual pitch and roll attitude (refer to POH).

NOTE Operation in a pitch mode is possible only if a roll mode is activated. As a safety device an autopilot quick disconnect switch (AP DISC, red) is also located in the left horn of the pilot's control wheel to enable the pilot to disengage the autopilot quickly. Additionally, servo transmissions are designed as slip clutches, which can be overpowered in any case of failure or malfunction. The operation mode selection is done via the autopilot main unit and the IFD or the related keyboard. Indication is made on the autopilot main unit and the upper IFD-1.




Page Date: 30. March 2012 22

Troubleshooting Complaint Possible Cause Remedy

Autopilot has no power Check AUTOPILOT MASTER switch FD or MASTER.

Autopilot has no power Check AVIONICS switch ON.

No valid signals from turn coordinator

Check turn coordinator no flag.

AP disconnect switch struck/defective

Check AP disconnect switch continuity.

Pitch trim switch stuck/defective

Check pitch trim switch stuck.

Autopilot will not engage in any mode

Computer defective Replace computer.

No roll mode engaged A roll mode MUST be selected first


Will not engage in any altitude mode

No valid signal from absolute pressure transducer

Replace absolute pressure transducer.

Autopilot not coupled in both axes

An altitude and roll mode must be engaged previously.

Switch defective Replace CWS switch.

CWS does not work


Switch defective Replace AP disconnect switch.AP disconnect switch does not work Computer defective Replace computer.

AP in FD mode Check AUTOPILOT MASTER switch in MASTER position (not FD)

Mode engages, but servo does not couple

Servo defective Replace servo.

Pitch system has no power Check battery bus power.

Pitch system has no power Check pitch trim switch ON.

Pitch trim switch defective Replace pitch trim switch.


Electrical Pitch trim does not work

Pitch trim servo defective Replace pitch trim servo.


22 Page Date: 30. March 2012

Complaint Possible Cause Remedy

No power to yaw amplifier Check battery bus power

YAW DAMPER switch OFF. YAW DAMPER switch ON.

Yaw damper switch defective Replace yaw damper switch.

No roll mode enabled Engage roll mode first.

Yaw amplifier defective Replace yaw amplifier.

Yaw servo defective Replace yaw servo.

Yaw trim does not work

Yaw trim poti defective Replace yaw trim potentiometer.

Heading Calibration Detail Steps/Work Items Key Items

1 Attach external power.

2 Check all switches OFF, A/P CMPTR CB IN, Turn-Coord CB IN, A/P SERVO CB IN, All IFD CB-s IN

3 Switch on EXT PWR

4 Switch on AUTOPILOT - MASTER

5 Check turn coordinator runs up, off-flag disappears, Autopilot display shows 7 on display, Autopilot display shows rdy, IFD-1 shows AP RDY

6 Wait for 2 minutes to let turn coordinator run up

7 Set IFD to NAV I

8 Tune NAV I to a frequency that has no reception

9 Set course to current heading

10 Select NAV mode on autopilot

11 Adjust the potentiometer between the REV and ALT buttons in small increments until the yoke stops turning

use miniature flat screwdriver






2 Remove IFD-3 or IFD-2. Refer to Chapter 31-60-01.

3 Disconnect electrical wiring.

4 Remove turn coordinator. 4 screws


6 Perform heading calibration procedure Refer to Subject 22-10-00 Heading Calibration





23-00-00 GENERAL

Description The EXTRA 500 is equipped with a speech and entertainment communication system, consisting of the following devices:

1 Avidyne Entegra Release 9 IFD System

2 PS Engineering PMA8000B(-T) Stereo Intercom System

3 COM 1, 2, and Marker Antennas

The system units (1 and 2) are mounted to the instrument panel, the antennas as shown on Figure 23-01.

In Chapter 23-10-00 Speech Communication you will find information about Avidyne Entegra Release 9 IFD System.

The related PS Engineering PM8000B(-T) devices and the COM antennas are subject to Chapter 23-50-00 Audio Integrating.

Chapter 23-60-00 Static Discharging contains a description of the EXTRA 500 bonding system.


No power on load bus Switch on starter/generator or external power.

Unable to transmit or receive

Defective AUDIO-MRK breaker Replace

Unable to transmit or receive COM I

Defective IFD-1 Replace IFD-1

Unable to transmit or receive COM II

Defective IFD-2 Replace IFD-2

Unable to transmit with IFD indication COM [1/2] TX Fault

No or defective antenna cable connections

Check antenna cable connections

Defective transmit button on pilot's side

Replace Unable to transmit from the pilot's side (missing transmit mode indicator on display) Defective wiring between

pilot's transmit button and radio unit

Repair

Defective transmit button on co-pilot's side

Replace Unable to transmit from the co-pilot's side (missing transmit mode indicator on display) Defective wiring between co-

pilot's transmit button and radio unit

Repair

Defective pilot's headset Replace No modulation when transmitting from pilot's seat Defective wiring Repair




Complaint Possible Cause Remedy

Defective co-pilot's headset Replace No modulation when transmitting from co-pilot's seat Defective wiring Repair

Short range in transmit mode; reception without problems

Defective radio unit Repair

Short range in receive mode; signal noise in reception

Defective radio unit Repair

Short range in transmit and receive mode; signal noise in reception

Defective COMM antenna, coaxial cable and plug

Repair or replace

Defective speaker Replace

Defective wiring Repair

Speaker silent, headsets operation normal

Defective intercom unit Replace

Transmit mode indicator on display is always visible COM [1/2] Stuck TX

Transmit button stuck Replace

Defective intercom unit Replace Intercom system inoperative, transmit mode O.K. Defective wiring Repair



23-10-00 SPEECH COMMUNICATION

Description The EXTRA 500 airplane is equipped with an Avidyne 700-00083-000 Integrated Flight Display (IFD-1) in the left main panel (PFD) and a 700-00083-000 IFD (IFD-2) in the center (MFD) position. Optionally a third 700-00083-002 IFD (IFD-3) is installed in the right main panel. A Control Display Unit (CDU) p/n 700-00150-002 is also installed as part of the Entegra Release 9 IFD System and located on the middle console. Refer to Chapter 31-60 for more information.

The system is integrated to:

• S-TEC System 55X Autopilot

• Audio panel

• Remote transponder

• DME (optional)

• Weather detection (optional)

• Traffic advisory (optional)

Operation Refer to POH EXTRA 500.





23-50-00 AUDIO INTEGRATING

23-50-01 Intercom System PS Engineering PMA8000B(-T)

Description The PMA8000B and PMA8000BT are audio isolation amplifier and audio selector that contain an automatic voice activated (VOX) intercom system and integral marker beacon receiver. They can switch two transceivers (Com 1, Com 2) and six receivers (Com 1, Com 2, Nav 1, Nav 2, DME, and MKR).

Operation Refer to EXTRA 500 Pilot's Operating Handbook.

Removal Detail Steps/Work Items Key Items


2 Put a 3/32 Allen wrench into the center access hole between the Com2 and Mon1 push buttons for the locking screw in the front panel. Engage the screw.

3 Turn the screw counter-clockwise until the unit disengages from the mounting rack.

CAUTION Do not pull on the knobs. Do not pry the face plate. You can damage the unit.

CAUTION Do not touch the connector card at the rear of the unit. The electrostatic charge on your body can damage the unit.

4 Pull the sides of the unit gently to remove it from the mounting rack.

5 Install the protective covers on the rear connectors of the unit.

Installation Detail Steps/Work Items Key Items

1 Remove the protective covers from the rear connectors of the unit.

2 Slide the unit into the rack.

3 Engage the locking screw so that the latch front lobe touches the rack.



CA

BIN

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LIG

HTS

AVIO

NIC

MAS

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Figure 24-2 Left Side Panel Switches



Figure 24-3 Left Side Panel Circuit breakers







2 Remove IFD-1 and IFD-2. Refer to Chapter 31-60-01.

3 Remove electrical connection.

4 Remove 2 nuts.

5 Remove regulator.

6 Install in reverse order of removal.

24-30-30 Battery The 24 VDC/28 Ah valve regulated lead acid battery is located in the engine compartment, mounted to the pressure bulkhead and protected by a vented aluminum case. The battery is directly connected to the hot bus. The battery supplies power to the electrical system when BATT switch is switched to ON position.

Recharging the battery may be done with battery installed. There are two procedures:

Charging with external power Detail Steps/Work Items Key Items

WARNING Always keep sparks or any form of ignition away from the battery being charged. Explosive gases are being generated during the charging process.

1 Set external power unit to 28 VDC.

2 Connect external power.

3 Switch on BATT.

4 Switch on EXT PWR.





Charging over charger plug Detail Steps/Work Items Key Items

Always keep sparks or any form of ignition away from the battery being charged. Explosive gases are being generated during the charging process.

Do not charge with more than 5 A.

WARNING

Use only supplied unit or equivalent.

1 Connect the charger to the charger plug.

2 Connect the charger to the wall socket.

Removal/Installation



2 Remove upper engine cowlings. Refer to Ch. 71-10-01/02.

3 Disconnect the quick connect plug.

4 Disconnect the 2 retainers.

5 Remove battery from aircraft.

6 Install in reverse order of removal

24-30-40 Indication Electric system relevant indication is made by the digital indicator cluster installed in the left side of the main panel and the following lights in the annunciator panel:

GENERATOR FAIL (red), see Subject 24-30-10.

LO VOLTAGE (yellow), illuminates as soon as bus voltage drops below 25.5 V.

STANDBY ALTERN ON (yellow), see Subject 24-30-20.

EXTERNAL POWER (green), see Subject 24-40-00.

24-30-41 Indicator Cluster The digital indicator cluster installed in the left side of the main panel indicates three electric system parameters among other engine parameters. Also refer to Chapter 77-40-02 (SN 1002 thru 1004) and 77-40-03 (from SN 1005).




VDC (bus voltage) During normal operation (generator active) a voltage of approx 28 V should be indicated. With standby alternator the indication should be about 26 V. Battery nominal voltage is 24 V.

GEN AMPS (Generator Load) Generator load is indicated on this indicator as long as the generator is active (GENERATOR FAIL warning light off). Generator Load should be kept below 200 A. In case the generator is offline this indicator automatically displays the standby alternator load. The standby alternator load has to stay below 20 A (see also Subject 24-30-20).

BAT AMPS The battery amp indicator shows load or charging current on the battery. A negative indication means battery is being charged, a positive indication means battery is discharged (load on battery).

Removal/Installation For removal/installation procedures refer to Chapter 77-40-02 (SN 1002 thru 1004) and 77-40-03 (from SN 1005).





24-40-00 EXTERNAL POWER

Description An external power receptacle is installed under an access door on the right side of the engine compartment. The use of external power is recommended for engine starting in case aircraft battery is weak, for ground operation of the vapor cycle air condition system or for any prolonged ground operation of aircraft systems. An external power source being connected with the external power receptacle and switched on will be indicated by a green EXTERNAL POWER annunciation light in the annunciator panel. To enable the external power source to supply power to the aircraft the EXT PWR switch on the MAIN section of the left side panel has to be switched on.

CAUTION Do not connect ground power units with a capacity greater than 1200 A for engine start.

NOTE It is not possible to connect the starter-generator and an external power source simultaneously to the aircraft bus system. This is to avoid any uncontrolled currents between these units. Additionally a battery charger plug is installed at the external power receptacle. The battery may be charged with 29.0 V and 5 A.



24-60-00 DISTRIBUTION

Description Electrical power from the various power sources is supplied to the E-box. The E-box incorporates the main devices of the distribution system such as fuses, circuit breakers, relays, and shunts and is installed on the engine side of the firewall. From there power is distributed partly through individual fuses to the following buses:

• Hot Bus,

• Emergency Bus,

• Battery Bus and Avionic Bus

• Load Bus,

The battery directly feeds the hot bus supplying power for equipment, which has to be independent from the battery switch position (e.g. ELT; see Figure 24-2 for location of battery switch).

Turning the battery switch to the ON-position will activate a relay connecting the battery to the battery bus and further to the emergency bus. This allows starting the engine and feeding the other equipment and, if engine is running, recharging the battery with the starter/generator.

The generator is activated by turning GEN switch to the ON-position (see Figure 24-2). So the generator is activated and the generator relay connects the generator to the load, battery and emergency bus.

From the main bus electrical power is distributed to the various busses as outlined on Figure 24-1. The avionic bus can be disconnected by the AVIONICS switch.

The main control switches of the electrical power system are located on the MAIN section of the left side panel (see Figure 24-2) and are marked EXT PWR, BATT, STBY ALT, GEN and GEN TEST.

Push-pull circuit breakers automatically break the current if an overload occurs to prevent damage to the electrical wiring and equipment. The most circuit breakers are installed to the left side panel (see 0). A single circuit breaker is installed on the upper LH engine mount (GCU) and under the external power hatch (EXT PWR) respectively. All other circuit breakers are installed to the E-box located on the engine side of the firewall and are labeled GEAR AUX 2, BATT CHARGE, SPARE, ALT FIELD 2, COURTESY LT, and ELT.

Generally where exclusively wiring shall be protected poly switches are used. They are installed on different locations of the electrical system.



24-60-01 E-box




2 Remove upper engine cowlings. Refer to Ch. 71-10-01/02.

3 Disconnect the SCEET hoses from the oil cooler inlet.

4 Remove 10 attachment screws of the oil cooler inlet.

5 Remove oil cooler inlet.

6 Remove 8 oil cooler outlet attachment screws.

7 Move oil cooler and outlet some centimeters forward.

To get access to the E-box.

8 Disconnect electrical connector

9 Disconnect power lines

10 Remove upper E-box cover. 1 screw

11 Disconnect 3 main power bulkhead feed-throughs.

Hold threaded rod in place by means of an Allen wrench.

12 Remove 3 attachment screws.

13 Remove E-box.

14 Remove cover plate and shell plate. Plates are screwed on.


24-60-02 Switches

Removal/Installation The switches on the instrument panel are accessible from the backside after removal of the IFD-1 and IFD-2. The LANDING GEAR, FLAP, and ELT switch backsides are directly accessible from the legroom.

The backsides of the left side panel switches are accessible when the upper and lower part of the left side panel has been removed.

Generally conventional switches are used, so that removal is done by disconnecting the electrical wiring and removing attachment screws or nuts. Installation is vice versa.





24-60-03 Circuit Breakers

Removal/Installation The circuit breakers on the left side panel are accessible from the backside when the upper and lower part of the left side panel has been removed.

To get access to the E-box circuit breakers the E-box must be removed (refer to Subject 24-60-01).

Generally conventional circuit breakers are used, so that removal is done by disconnecting the electrical wiring (busses) and removing attachment screws or nuts. Installation is vice versa.

24-60-04 Relays Relays are installed in the left side panel, in the E-box and behind the IFD-2.

To get access to the relays either the E-box (see Subject 24-60-01), the left side panel (see Chapter 31-10-01) or the IFD-2 (see Chapter 31-60-01) must be removed

Electrical wiring is generally connected to the relays by means of relay sockets. The relays are mounted to the sockets with bolts.

24-60-05 Shunts Shunts are installed in the E-box.

To get access to the shunts the E-box must be removed (refer to Subject 24-60-01).

Electrical wiring is generally connected to the shunts by means of screws. The shunts are mounted to the supports with bolts.

24-60-06 Fuses The main fuses are installed in the E-box with bolts. They are accessible after removal of the upper E-box cover.





28-40-02 Fuel Quantity Sensor (main or auxiliary compartment) The fuel quantity sensor is installed on the inner tank inspection door of the appropriate tank.

Removal



2 Open appropriate tank access panel. Sensor is on the inner tank inspection door of the corresponding compartment.

3 Remove inspection door.

4 Remove sensor from inspection door. 5 bolts

5 Disconnect electrical connector from sensor.

Installation 1 Ensure BATT switch is OFF and no external

power connected.

2 Connect electrical connector.

NOTE When attaching sensor to hatch observe correct direction. For main compartment: Make sure the float is pointing inboard For auxiliary compartment: Make sure the float is pointing outboard

3 Attach sensor to inspection door.

NOTE If the hatch seal has become partly clear instead of white, slightly pull those patches apart. Clear patches are NOT a sign that the seal is defective!

4 Install inspection door, torque bolts 3-5 Nm (26-44 inch-lbs).

5 After at least one half hour re-torque the bolts.

6 Recalibrate quantity indicator.

7 Reinstall appropriate tank access panel.



28-40-03 Fuel Quantity Gauge From serial no. 1002 thru 1004 the fuel quantity gauges are installed in the right main panel. From ser. no. 1005 fuel quantity is displayed on the MVP-50 (refer to Chapter 77-40-03).




2 Remove IFD-2. Refer to Chapter 31-60-01.

3 Disconnect electrical connector from fuel quantity gauge.

4 Unscrew attachment . 4 screws

5 Install in reverse order of removal.

6 If more than one gauge is replaced, check if indicator shows proper tank.

Calibration This paragraph applies to the configuration of serial no. 1002 thru 1004. From ser. no. 1005 refer to the Fuel Quantity Indication Calibration procedure outlined in Chapter 77-40-03.

The calibration potentiometers are installed on PCB installed behind the IFD-1.



2 Remove IFD-2. Refer to Chapter 31-60-01.

3 Disconnect electrical connector from fuel quantity gauge.

4 Make sure the fuel quantity sensor is installed and laying on the bottom of the compartment (compartment is empty).

5 Measure with a calibrated, digital ohmmeter the resistance between pins 5 and 8.

For collector and main comp:The value must be 50.0 Ohm For auxiliary compartment: The value must be 80.0 Ohm

6 If value is not correct, follow the steps below.

7a Remove IFD-1. Refer to Chapter 31-60-01.

7b Use the potentiometer on the PCB behind the IFD-2 to bring the resistance value to the required value.






7c Reinstall the IFD-1.

8 Connect electrical connector.

9 Re-install the IFD-2.

28-40-04 Fuel Flow Indicator From serial no. 1002 thru 1004 the fuel flow indicator is installed in the RH instrument panel. From serial no. 1005 the fuel flow indicator is installed in the left main panel.




2 Remove IFD-2 (serial no. 1002 thru 1004) resp. IFD-1 (from serial no. 1005)

Refer to Chapter 31-60-01.

3 Disconnect electrical connector from fuel flow indicator.

4 Unscrew attachment. 4 screws


K-Factor Setting Refer to Shadin Avionics Miniflo-L Operating Manual (LOAP 42).

28-40-05 Pressure Transducer For description and maintenance practices refer to Chapter 73-30-01.

28-40-06 Pressure Gauge The fuel pressure gauge is integrated in the Digital Instrument Package (refer to Chapter 77-40-02 (SN 1002 thru 1004) and 77-40-03 (from SN 1005)).





Intentionally left blank.



30-40-02 Windshield Heat Current Sensor The windshield heat current sensor is installed beside the pilot seat, behind the pilot’s legroom LH paneling.



2 Remove pilot seat. Refer to Chapter 25-10-11.

3 Remove all LH forward lower paneling screws.

Refer to Chapter 25-00-01.

4 Carefully swivel the paneling forward to gain access from behind.

5 Remove electrical connections. 4 screws

6 Remove windshield heat current sensor including mounting plate.

2 nuts

7 Remove current sensor from mounting plate. 2 bolts


9. August 2013



30-60-00 PROPELLER

Description The propeller of the EXTRA 500 is equipped with electrically heated boots at the blades for icing protection. All blades are heated continuously when switched on. All necessary information for repair and maintenance of the system is contained in BF Goodrich Aerospace publications as listed in the LOAP 14-17.

30-60-01 Propeller Ammeter From serial N° 1002 thru 1004 a propeller ammeter is installed in the upper left corner of the instrument panel. From SN 1005 it is integrated in the MVP-50T (refer to Chapter 77-40-03)


1 Remove IFD-1 and IFD-2. Refer to Chapter 31-60-01.

2 Disconnect electrical connector ammeter.

3 Remove propeller ammeter. 4 screws






Chapter 31 Indication & Recording Systems



TABLE OF CONTENTS

31-00-00 GENERAL ........................................................................................................ 3 Description.......................................................................................................... 3

31-10-00 INSTRUMENT & CONTROL PANELS....................................................... 4

31-10-01 Left Side Panel .................................................................................................. 4 Description.......................................................................................................... 4 Removal/Installation........................................................................................... 4

31-10-02 Left Main Panel ................................................................................................ 4 Removal/Installation........................................................................................... 4

31-10-03 Right Main Panel .............................................................................................. 5 Removal/Installation........................................................................................... 5

31-10-04 Lower Main Panel ............................................................................................ 5 Removal/Installation........................................................................................... 5

31-10-05 Glare Shield....................................................................................................... 6 Removal/Installation........................................................................................... 6

31-10-06 Control Display Unit ........................................................................................ 6 Removal/Installation........................................................................................... 6 Tests and Checks ................................................................................................ 6

31-50-00 CENTRAL WARNING SYSTEMS................................................................ 7 Description.......................................................................................................... 7

31-50-01 Annunciator Panel (Westcoast Specialties) .................................................... 7 Figure 31-1 Annunciator Panel (Westcoast Specialties)........................................................ 7

Removal/Installation........................................................................................... 7 Lamp Replacement ............................................................................................. 8

31-50-02 Annunciator Panel (EXTRA) .......................................................................... 8 Figure 31-2 Annunciator Panel (EXTRA) .............................................................................. 8

Removal/Installation........................................................................................... 8

31-60-00 CENTRAL DISPLAY SYSTEMS .................................................................. 9 Description.......................................................................................................... 9

31-60-01 Integrated Flight Display (IFD)....................................................................... 9 Removal/Installation........................................................................................... 9 Tests and Checks ................................................................................................ 9 Magnetometer Calibration................................................................................ 10 Magnetometer Check........................................................................................ 11




31-00-00 GENERAL

Description The EXTRA 500 is equipped with several indication systems:

• The left and right main panel

• The left side panel

• The annunciator panel (part of the right main panel)

• Two Integrated Flight Displays (IFD-1 and IFD-2)

• The optional third Integrated Flight Display (IFD-3) (from ser. no. 1005)

• The Control Display Unit (CDU)





31-10-00 INSTRUMENT & CONTROL PANELS

31-10-01 Left Side Panel

Description On the LH of the pilot, most of the switches and circuit breakers are installed in a switch board assembly, the left side panel. This assembly contains all electrical busses excluding the hot bus. This assembly can be taken out of the aircraft as a whole.



2 Remove pilot’s seat. Refer to Chapter 25-10-11.

2 Remove left legroom side paneling. Refer to Chapter 25-00-01.

3 Remove 6 screws of the upper part of the left side panel.

2 screws on the top 4 screws on the side

4 Remove 3 screws of the lower part of the left side panel.

5 Disconnect the 3 electrical connectors and the power connector.

CAUTION Take care not to damage luminescent foil connections

6 Remove the two parts of the left side panel.


31-10-02 Left Main Panel


1 Remove IFD-1 and IFD-2. Refer to Subject 31-60-01

2 Disconnect wiring/piping from back-up flight instruments and propeller ammeter.

3 Remove left main panel. 8 Phillips screws






31-10-03 Right Main Panel


1 Remove IFD-3 (if installed) and IFD-2. Refer to Subject 31-60-01

2 Remove Phillips screws around right main panel.

10 screws; 8 screws if IFD-3 installed

3 Slightly swivel down right main panel Take care not to damage electrical wiring

4 Disconnect electrical wiring from annunciator panel

5 Disconnect wiring from fuel gauges. (SN 1002 thru 1004 only)

6 Disconnect wiring from fuel flow indicator. (SN 1002 thru 1004 only)

7 Disconnect wiring from turn coordinator. (SN 1002 thru 1004 only)


Lower Main Panel


1 Remove LH and RH main panel Refer to Subject 31-10-02/03

2 Remove engine indicators. Refer to Chapter 77-40

3 Disconnect electrical wiring from ELT switch.

4 Disconnect electrical wiring from LANDING GEAR switch.

5 Disconnect electrical wiring from FLAP switch.

6 Remove attachment nuts from the other switches.

7 Disconnect electrical wiring from dimming potentiometers.





8 Disconnect electrical connector from turn coordinator.

From SN 1005

9 Remove lower main panel. 14 bolts


31-10-05 Glare Shield


1 Remove main panels. Refer to Subjects 31-60-02 thru 04

2 Disconnect wiring from autopilot.

3 Remove glare shield. 4 screws


31-10-06 Control Display Unit

Removal/Installation Follow the ACD215 Removal and Installation procedure presented in the Entegra Integrated Flight Display System Product Maintenance Manual (LOAP 24).

Tests and Checks Perform the applicable Return to Service Tests and Checks presented in the Entegra Integrated Flight Display System Product Maintenance Manual (LOAP 24). whenever the unit has been reinstalled.





31-50-00 CENTRAL WARNING SYSTEMS

Description The central warning system in the EXTRA 500 consists of an annunciator panel. The annunciator panel is located on the top RH instrument panel. (Refer to the Emergency Procedures (Amplified) part of Section 3 in the EXTRA 500 Pilot's Operating Handbook for further information to the particular caution and warning lights.)

31-50-01 Annunciator Panel (Westcoast Specialties) The annunciator panel is located on the top RH instrument panel.

r

r

r

r

r

r

r

r

r

r

r

y

y

y

y

y

y

y

y

y

y

y

y

y

y

y

g g g

g g

g g r = red, y = yellow, g = green

Figure 31-1 Annunciator Panel (Westcoast Specialties)


1 Remove IFD-2 or IFD-3 (if installed). Refer to Subject 31-60-01

2 Disconnect electrical wiring from annunciator panel.

3 Remove panel. 4 screws


5 Check if all lamps work by placing the NIGHT/DAY switch located on the left side panel in the TEST position.





Lamp Replacement Each annunciator light (lamp module) is illuminated by two lamps. Relamp by pushing in lamp module approximately 1/16th of an inch and release. The lamp module will partially eject. Pull to disengage, then rotate downward to expose the lamps. When reinserting lamp modules ensure both latching springs engage cap assy by slowly pushing cap with equal force on both sides.

31-50-02 Annunciator Panel (EXTRA) The annunciator panel is located on the top RH instrument panel.

r = red, y = yellow, g = green

Figure 31-2 Annunciator Panel (EXTRA)


1 Unscrew the four inner bolts.

2 Pull the panel out.

3 Disconnect electrical connectors.


5 Check if all lamps work by placing the NIGHT/DAY switch located on the left side panel in the TEST position.

11. July 2012



31-60-00 CENTRAL DISPLAY SYSTEMS

Description The central display system of the EXTRA 500 contains 2 Avidyne Integrated Flight Displays (IFDs). A third screen may be installed in the right main panel.

31-60-01 Integrated Flight Display (IFD)

Removal/Installation Follow the IFD5000i Removal and Installation procedure presented in the Entegra Integrated Flight Display System Product Maintenance Manual (LOAP 24) observing the following aircraft specific hints:

Ensure BATT switch is OFF and no external power connected.

Up to serial no. 1004 the wiring and piping for the IFD-2 is dimensioned in the way that it can be disconnected/connected when the IFD is removed from and held next to the instrument panel. The wiring and piping for the IFD-1 is shorter so that connecting/disconnecting has to be done with IFD installed. For that reason the IFD-2 must be removed to get access to the wiring/piping connectors.

With the introduction of the optional IFD-3 from serial no. 1005 the IFD wiring and piping length has been changed: now the wiring and piping of IFD-2 has the short piping and wiring, the IFD-1 and IFD-3 have the long ones. So IFD-1 or IFD-3 must be removed prior to removal of the IFD-2.

The wiring is marked conforming to the designations on the IFD backsides. However the piping (Pitot/static) is colored as shown in the following:

IMPORTANT The colors of pitot/static lines do not match with the port markings on the backside of the IFDs.

Piping Colors IFD-1 IFD-2

PITOT white blue

STATIC red green

Tests and Checks Perform the applicable Return to Service Tests and Checks presented in the Entegra Integrated Flight Display System Product Maintenance Manual (LOAP 24) whenever the unit has been reinstalled.




Pitot/Static Check Perform applicable Return to Service Pitot/static Check according to FAR 43, Appendix E and AC 43.13-1B CHG1 (or later) Ch. 12-59 whenever the unit has been reinstalled.

Magnetometer Calibration It is advisable to integrate the Compass Swing procedure outlined in Chapter 34-20-02 in this calibration procedure.

It is recommended to perform the calibration with a mobile external power unit.


1 Place the aircraft in a magnetically clean area

2 Attach external power

3 Switch on BATT, EXT PWR, and AVIONICS

4 Wait, until both IFD-1 and IFD-2 have aligned

5 Wait additional 10 minutes.

6 Press ‘SYS’ and select ‘setup’ on both IFD-1 and IFD-2

7 Press ‘Update Databases’ L(ine) S(elect) K(ey)

8 Press ‘Confirm’ LSK

9 Simultaneously hold the LH upper and third LSK for 5 seconds

10 Press ‘Proceed’ LSK

11 Check ‘Technician maintenance mode’ indication

12 Press ‘SYS’ and select ‘cal’

13 Press ‘Cal select – select Magnetometer calibration’

14 Check ‘Calibrate Heading’ indication

IMPORTANT Place the ailerons to neutral and do not move them during calibration and verification.

Calibration

15 Place the aircraft to the magnetic north 360°+/−1°

16 Switch on STROBE

17 Follow the procedure as displayed on IFD-1 and IFD-2

18 After the heading point (330°):

19 Check ‘Magnetometer Calibration Complete’





Detail Steps/Work Items Key Items indication.

20 Wait 10 seconds

21 Press ‘Done’

22 Wait until IFD-1 and IFD-2 have rebooted.

23 Switch off EXT PWR

24 Switch off BATT

25 Wait one minute

26 Verify neither “Mag CAL 1 required” or “Mag CAL 2 required” appears.

Magnetometer Check


1 Place the aircraft in a magnetically clean area

2 Attach external power

3 Switch on BATT

4 Switch on EXT PWR

5 Wait until IFD-1 and IFD-2 to reboot and are aligned

6 Check ‘Mag Cal 1 (or 2) Required’ Caution does NOT appear.

7 Place the aircraft to the given directions. Check if reading in limits and note values.

If values are out of limit perform Magnetometer Calibration Procedure

8 Indicated heading of IFD-1 and IFD-2 within or at 356 to 004° with aircraft at 360° magnetic

Aircraft: 360°

IFD-1: IFD-2:

9 IFD-1 and IFD-2 within or at 2° of each other with aircraft at 360° magnetic

10 Indicated heading of IFD-1 and IFD-2 within or at 86 to 94 ° with aircraft at 90° magnetic

Aircraft: 90°

IFD-1: IFD-2:



Aircraft: 180°

IFD-1: IFD-2:








Aircraft: 270°

IFD-1: IFD-2:


16 Switch off EXT PWR

17 Switch off BATT





34-00-00 GENERAL

Pitot/Static Pressure Systems Providing pitot and static pressure for the pilot's and copilot's instruments two independent systems are installed (refer to Figure 34-1). Each system consists of a heated pitot head located at about 3/4 of the wing span, the tubing including a drain and the respective instruments. The heated static ports are located on both sides of the rear fuselage. The two toggle-type drains are located at the fuselage underside, between the keel beams. They are accessible by the forward keel beam access panel.

When the pitot heat switches are placed in the ON position, the heating elements in the pitot heads and the static port for the autopilot are electrically energized to maintain proper operation of the systems during icing conditions.

Normally, the heating elements can only be activated when airborne. On ground the system is deactivated by the squat switch, which detects aircraft being on ground.

For testing on ground, pitot heat switches provide a TEST position (momentary ON).

CAUTION In testing mode, do not operate pitot & static heat longer than 10 seconds to prevent overheating of the heating elements.

WARNING Care should be taken when an operational check of the heated pitot heads is being performed on the ground. The units become very hot. An additional static system is installed in the tail cone for the autopilot. The static port is located on the lower aft part of the vertical stabilizer. The static line is routed from there to the bottom of the tail cone compartment. There, on the lowest point of the system a plugged hose serves as a drain. Remove the plug for draining. The static line is further routed via T-fitting to the autopilot pressure transducer.

Avionics The EXTRA 500 is equipped with Avidyne Entegra equipment. Please refer to Chapter 31. This chapter will deal with other avionics apart from Back-up altimeter and airspeed indicator:

• Back-up attitude indicator

• Magnetic compass

• XPDR

• DME (option)

• TAS (option)

• TWX (option)

IMPORTANT Avionics service and repair work requires special skills, tools and test equipment. In case of instrument failure or malfunction contact manu-facturer or authorized service center.

9. August 2013



IFD

-1A

DA

HR

SIF

D-2

AD

AH

RS

Bac

k-up

altim

eter

Bac

k-up

airs

peed

indi

cato

rPi

tot R

H

Pito

t LH

Stat

ic p

ort R

H

Stat

ic p

ort

verti

cal t

ail

Stat

ic p

ort L

H

LH P

itot S

yste

mR

H P

itot S

yste

mA

utop

ilot

blue

blue

blue

blue

gree

n

gree

ngr

een

gree

n

gree

n

blue

red

red

red

red

red

red

red

red

red

whi

tew

hite

whi

te

whi

te

open

Cab

inal

timet

er

Tran

sduc

erP5

50-5

070

Figure 34-1 Pitot Static System Schematic





34-10-00 FLIGHT ENVIRONMENTAL DATA

NOTE When any connections in the static system are opened for checking, a static leak check per AC 43-6C §9a must be performed.

34-10-01 Altimeter (2” type)


Excessive scale error Improper calibration adjustment

Contact manufacturer

Excessive pointer oscillation Defective mechanism Contact manufacturer

High or low reading Improper venting Eliminate leak in static pressure system

Setting knob is hard to turn Wrong lubrication or lack of lubrication


Inner reference marker fails to move when setting knob is rotated

Out of engagement Contact manufacturer

Setting knob set screw loose or missing

Not tight when altimeter was reset

Tighten instrument screw, if loose. Contact manufacturer, if screw is missing

Cracked or loose cover glass Case gasket hardened Contact manufacturer

Dull or discolored markings Age

Barometric scale and reference markers out of synchronism

Slippage of mating parts Contact manufacturer

Barometric scale and reference markers out of synchronism with pointers

Drift in mechanism Contact manufacturer

Altimeter sticks at altitude or does not change with change of altitude

Water or restriction in static line

Remove static lines from all instruments; blow line clear from cockpit to static ports

Altimeter changes reading as aircraft is banked

Water in static line Remove static lines from all instruments; blow lines clear from cockpit to static ports

Altimeter requires resetting frequently

Temperature compensator inoperative


9. August 2013





2 Remove IFD-1. Refer to Chapter 31-60-01

3 Disconnect (red) static pressure hose

4 Remove altimeter 3 screws

5 Disconnect electrical connector

6 Install in reverse sequence of removal

7 Perform Pitot/static check According to FAR 43, Appendix E and AC 43.13-1B CHG1 (or later) § 12-59

34-10-02 Airspeed Indicator (2” type)


Pointer does not indicate properly

Leak in instrument case, in Pitot or static lines

Check for leak and seal

Pointer of instrument oscillates Defective mechanism Replace instrument

Instrument reads high Pointer not on zero

Leaking static system

Replace instrument

Find leak and correct

Instrument reads low Pointer not on zero

Leaking Pitot system

Replace instrument

Find leak and correct

Airspeed changes as aircraft is banked

Water in pitot line Remove line from all instruments and blow out line from cockpit to Pitot head



2 Remove IFD-1 Refer to Chapter 31-60-01

3 Disconnect (red) static pressure hose and (white) Pitot hoses

4 Remove airspeed indicator. 4 screws

5 Disconnect electrical connector.





34-20-00 ATTITUDE AND DIRECTION

34-20-01 Attitude Indicator




3 Remove attitude indicator. 4 screws


34-20-02 Magnetic Compass


1 Remove compass 2 screws



4 Make compass swing, if new unit is installed.

5 Replace deviation card if necessary.

Bulb Replacement Detail Steps/Work Items Key Items


2 Lift cap on upper front surface.

3 Remove bulb.

4 Insert new bulb. 24 VDC

5 Refit cap.

Compass Swing Refer to the Compensation Instructions of Airpath Instrument Company (LOAP 40). It is advisable to perform this compass swing simultaneously with the IFD Magnetometer Calibration outlined in Chapter 31-60-01.





34-40-00 INDEPENDENT POSITIONING DETERMINING

Description The EXTRA 500 can be equipped with the following optional equipment:

• TAS (Traffic Avoidance System)

• TWX (Lightning detection system)


TAS shows aircraft on the wrong side (left or right)

Antenna cables of upper antenna swapped

Swap antenna cables

TAS shows aircraft on the wrong side (front or aft)

Antenna cables of lower antenna swapped

Swap antenna cables

34-40-01 TAS Processor The TAS processor is installed on the back of the aft baggage compartment paneling.



2 Remove aft baggage compartment paneling. Refer to Chapter 25-00-01

3 Disconnect electrical connectors and antenna cables from TAS processor.

4 Unscrew the locking screws of the TAS processor mounting tray.

5 Slide the TAS processor out of the tray.

6 Install in reverse sequence of removal. Observe the following hint

CAUTION Make sure all antenna cables are connected to both antennas and TAS processor before applying power to the processor. Failing to do so may damage the processor.



73-00-00 GENERAL

For specific repair and replacement information refer to Rolls-Royce 250-B17F Series Engine Operation and Maintenance Manual (LOAP 1).

73-30-00 Indicating

Description The fuel indication consists of fuel pressure and a low fuel pressure warning in the annunciator panel. The fuel pressure indication is described in 77-40-02 (SN 1002 thru 1004) and 77-40-03 (from SN 1005).

73-30-01 Fuel Pressure Transducer

Description The fuel pressure transducer is located in the engine compartment, in the sensor block mounted on the LH side of the battery mount, the most forward upper sensor (refer to Figure 77-1).



2 Remove LH upper cowling. Refer to Chapter 71-10-01


WARNING Fuel may be pressurized (30 psi max). Fuel may spill. Protect yourself and catch spilling fuel in a suitable container.

4 Remove transducer from fuel pressure manifold.

5 Install in reverse sequence of removal. Replace O-ring when necessary (SN 1002 thru 1004)





73-30-02 Low Fuel Pressure Switch

Description The low fuel pressure switch is located in the engine compartment, in the sensor block mounted on the LH side of the battery mount, the most forward sideward sensor (refer to Figure 79-1).





WARNING Fuel may be pressurized (30 psi max). Fuel may spill. Protect yourself and catch spilling fuel in a suitable container.

CAUTION Never force the body of the sensor to turn against friction. It may change the set-point. Always use a key on the attachment fitting for removal and installation

4 Remove sensor.




Chapter 77 Engine Indicating



Table of Contents

77-00-00 GENERAL ........................................................................................................ 3 Description.......................................................................................................... 3 Engine Indication Check .................................................................................... 4 Normal Ground Idle Engine Indication .............................................................. 4

77-00-01 Gas Generator Turbine Tachometer (N1)...................................................... 4 Removal.............................................................................................................. 4 Installation .......................................................................................................... 5

77-10-00 POWER ............................................................................................................. 6

77-10-01 Torque Transducer........................................................................................... 6 Figure 77-1, Sheet 1 Engine Indication Transducers and Switches SN 1002 thru 1004 ..................... 6 Figure 77-1, Sheet 2 Engine Indication Transducers and Switches from SN 1005 ............................. 7

Removal.............................................................................................................. 7 Installation .......................................................................................................... 7

77-10-02 Torque Switch ................................................................................................... 8 Removal/Installation........................................................................................... 8

77-10-03 Propeller/Power Turbine RPM Sensor (N2) .................................................. 8 Removal.............................................................................................................. 8 Installation .......................................................................................................... 8

77-20-00 TEMPERATURE ............................................................................................. 9

77-20-01 Thermocouple Wiring ...................................................................................... 9

77-20-02 Thermocouple Terminal Block........................................................................ 9

77-40-00 INTEGRATED ENGINE INSTRUMENT SYSTEMS............................... 10

77-40-01 Analog Engine Indicator Cluster .................................................................. 10 Removal/Installation......................................................................................... 10

77-40-02 Digital Engine Indicator Cluster ................................................................... 10 Removal/Installation......................................................................................... 10

77-40-03 Electronics International MVP-50 ................................................................ 11 Removal/Installation......................................................................................... 11 Fuel Quantity Indication Calibration................................................................ 11

Figure 77-2 Preparing Fuel Quantity Sensor Float ............................................................. 12





77-00-00 GENERAL

For specific repair and replacement information refer to Rolls-Royce 250-B17F Series Engine Operation and Maintenance Manual (LOAP 1).

Description For SN 1002 thru 1004 the indication of engine parameters is presented on two integrated engine instruments in the LH instrument panel. The upper unit is an analog-digital unit which displays:

• TRQ in percent

• TOT in degree Celcius

• N1 (compressor) in percent

• N2 (propeller) in RPM

• Oil pressure in psig

• Oil temperature in degree Celcius

Although these parameters are displayed in one unit, they all have their separate modules and are independent of each other. The same is valid for the lower display unit which displays digital values only:

• Bus voltage

• Generator current in ampere

• Battery current in ampere

• Indicated outside air temperature in degree Celcius

• Fuel temperature in degree Celcius

• Fuel pressure in psig

From SN 1005 all the above parameters plus fuel quantity and propeller heat amperage but minus OAT is indicated on the MVP-50T.





Engine Indication Check The engine indication check consists of a engine run test in which the plausibility of the indications are checked apart from obvious things like oil system leakage if the oil pressure sensor has been exchanged.


1 Before the engine run, check that all pressure and RPM indications are zero and temperature indications in line with the OAT.

2 Start the engine. Follow EXTRA 500 Pilot’s Operating Handbook procedures.

3 Set in ground idle.

4 Check engine indication is around the values given in the following table.

Refer to Normal Ground Idle Engine Indication table

Normal Ground Idle Engine Indication TRQ ~10% TOT ~540°C N1 ~65% N2 ~1750 RPM OP ~90 psig OT In green area FP >10 psig

77-00-01 Gas Generator Turbine Tachometer (N1) The gas generator turbine tachometer is installed on the LH forward engine gearbox.








4 Remove tachometer


1 Reverse sequence of removal. Apply some engine oil to the drive-spline before installing.

2 Perform engine indication check. Refer to Subject 77-00-00



77-10-00 POWER

77-10-01 Torque Transducer The torque transducer is located in the engine compartment, on the LH side of the battery, the aft sensor.

TRQOIL

FUEL

Transducers

Switches

Sensing linesTo accumulator

Battery attachment frame

Firewall

Side Viewfwd

Figure 77-1, Sheet 1 Engine Indication Transducers and Switches SN 1002 thru 1004





TRQOIL

FUEL

Transducers

Switches

Sensing linesTo accumulator

Battery attachment frame

Firewall

Side Viewfwd

Figure 77-1, Sheet 2 Engine Indication Transducers and Switches from SN 1005





4 Remove lock-wire. (SN 1002 thru 1004 only)

5 Remove torque transducer


1 Reverse sequence of removal. Replace o-ring (SN 1002 thru 1004 only) when necessary.







77-10-02 Torque Switch The torque switch is located in the engine compartment, on the LH side of the battery, the aft sideward sensor (refer to Figure 79-1).




CAUTION Never force the body of the sensor to turn against friction. It may change the set-point. Always use a wrench on the spanner flats of the attachment fitting for removal and installation.

3 Remove torque switch.

4 Reverse sequence of removal. Apply Loctite 577 to torque switch thread

77-10-03 Propeller/Power Turbine RPM Sensor (N2) The propeller tachometer is installed on the RH forward engine gearbox.



2 Remove upper cowlings. Refer to Ch. 71-10-01/02


4 Remove tachometer.


1 Reverse sequence of removal. Apply some engine oil to the drive-spline before installing.






77-20-00 TEMPERATURE

Engine temperature is measured using K-type thermocouples and indicated as TOT to the pilot.

77-20-01 Thermocouple Wiring The thermocouple wiring from the terminal block (77-20-02) to the indicator is Chromel – Alumel for the entire length, including connector pins. If any of this wiring is to be replaced, wiring of the same material shall be used. Perform engine indication check as per Subject 77-00-00.

77-20-02 Thermocouple Terminal Block Engine thermocouple wiring and aircraft thermocouple wiring is connected at the thermocouple terminal block. It is installed in the engine compartment on the RH engine fire-shield.

It is crucial that the Chromel and Alumel wires from the engine are correctly connected to those of the aircraft. Observe the following table:

Material Aircraft wiring Engine wiring

Chromel Pos (+) Yellow White Small diameter stud

Alumel Neg (-) Red Green Large diameter stud



77-40-00 INTEGRATED ENGINE INSTRUMENT SYSTEMS

77-40-01 Analog Engine Indicator Cluster From serial N° 1002 thru 1004 an analog engine indicator cluster is installed in the LH instrument panel.



2 Remove IFD-1 and IFD-2. Refer to Chapter 31-60-01

3 Disconnect both electrical connectors

4 Remove indicator cluster.



77-40-02 Digital Engine Indicator Cluster From serial N° 1002 thru 1004 a digital engine indicator cluster is installed in the LH instrument panel just below the analog engine indicator cluster.



2 Remove IFD-1 and IFD-2. Refer to Chapter 31-60-01


4 Remove 4 bolts Use a ratchet with adequate prolongation for holding nuts in place.

5 Remove indicator.







77-40-03 Electronics International MVP-50 From serial N° 1005 a MVP-50 electronic engine monitor is installed in the LH instrument panel.




3 Disconnect MVP-50 electrical connector.

4 Remove 4 screws.

5 Remove MVP-50.



Fuel Quantity Indication Calibration The following procedure is prepared for calibrating all fuel quantity sensors as well as calibrating one or more single sensors. In the latter case the instructions for the not affected tanks and sensors can be ignored. However when draining or refilling it has to be considered that the collector and main tanks are interconnected.

The procedure requires both the complete empty tank and the complete full tank configuration for each sensor to be calibrated. This allows noting the respective Current Sensor Counts on the MVP-50T.

To avoid refilling the complete fuel quantity during the calibration procedure the full tank position of the four outer sensor floats can be simulated as shown in Figure 77-2. Also refer to Chapter 28-40-02 for fuel quantity sensor Removal/Installation instructions. However filling the collector tank cannot be avoided and is achieved by transferring fuel from the main compartment.

IMPORTANT During the procedure as used for the EXTRA 500 and outlined below the MVP-50T function “Use Current Count” on the Fuel Tank Calibration screen must not be used, because it leads to faulty results.

Do not change the fuel quantity values on the same screen.





access panelin closed position

carefully pull up

waxed rope

floatin upper position

fuel quantity sensor

Figure 77-2 Preparing Fuel Quantity Sensor Float


1 Check applicable tank(s) empty. For Draining refer to Chapter 12-10-02

2 Ensure the applicable inner fuel compartment access panels are installed and fuel quantity sensor floats are on the lower surface of the tanks.

The inner fuel compartment access panels are equipped with fuel quantity sensors. Refer to Chapter 51-00-01

3 Attach external power.

4 Check all switches OFF and

ENG-INS-1 CB in

ENG-INS-2 CB in

VOLT-MON CB in

FUEL-QTY CB in

FUEL-TR-L CB in

FUEL-TR-R CB in

DANGER Explosion hazard.

Ground aircraft. Avoid unnecessary switching operation and permit no smoking or open flame within 50 ft of the aircraft.

5 Switch ON EXT PWR. MVP-50T now booting






6 Press EXIT on MVP-50T after main screen is indicated.

Refer to Electronics International Glas Panel Monitor MVP-50T Operating Instructions (LOAP 41)

7 Press MENU.

8 Select System Configuration Screen menu and press SELECT.

9 Enter 00200.

10 Press EXIT.

11 Select Fuel Tank Calibration and press SELECT.

12 Select applicable tank(s) one by one and note Current Sensor Count with tanks empty (count_empty) as indicated on the MVP-50T.

FQY CL: ……………………

FQY CR: ……………………

FQY ML: ……………………

FQY MR: ……………………

FQY AL: ……………………

FQY AR: ……………………

13 Prepare the applicable outer sensor floats to lay on the upper surface of the tanks (waxed ropes).

Refer to Figure 77-2 and to Chapter 28-40-02.

14 Select the applicable outer tanks one by one and note Current Sensor Count with sensor floats in upper (full tank) position (count_full) as indicated on the MVP-50T.

FQY ML: ……………………

FQY MR: ……………………

FQY AL: ……………………

FQY AR: ……………………

15 To fill the LH collector tank, fill the adjacent main tank with exactly 45 kg JET-A1.

Follow procedures and safety hints in Chapter 12.

16 Check external power voltage is 28.0 VDC.

17 Select LH collector tank on MVP-50T.

18 Switch ON FUEL – TRANSFER LEFT Left collector compartment fills within maximum 8 min 0 sec.

19 Switch OFF FUEL – TRANSFER LEFT if Count has stabilized for more than 15 sec.

20 Note Current Sensor Count of LH collector tank (count_full).

FQY CL: ……………………

21 Follow steps 15 thru 19 for the RH collector tank and note Current Sensor Count of RH collector tank (count_full).

FQY CR: ……………………






22 Calculate the Actual Count Values for the Calibration Points of each applicable individual tank using the tables below.

Due to the unusable fuel the 0 Gallon value for the Collector compartment is NOT the Empty value as determined above.

Refer to Calculating Actual Count Values Paragraph

23 Transfer the values as calculated into the MVP-50T.

24 Press EXIT 3 times.

25 Switch OFF EXT PWR.

26 Detach external power.

27 Remove waxed ropes from the transducers (if applicable).

28 Check float wire (if applicable).

29 Check access panels properly installed. Refer to Chapter 28-40-02.





Calculating Actual Count Values: Actual Count Value = count_empty + (count_full – count_empty) × normed_value

Collector Compartments: Calibration Point

(US Gallon) normed_value

of counts between empty and full values

Actual Count Values (as put in MVP-50T)

0.0000 Unusable fuel

0 0.4671

1.0 0.5934

2.0 0.7197

3.0 0.8459

4.2 1.0000

Main Compartments: Calibration Point




0 0.0000

13.4 0.2500

26.8 0.5000

40.2 0.7500

53.6 1.0000

Auxiliary Compartments: Calibration Point




0 0.0000

7.0 0.1751

14.0 0.4001

21.0 0.6751

28.0 1.0000






1 Reverse sequence of removal. Replace o-ring (SN 1002 thru 1004) when necessary.

2 Perform engine indication check. Refer to Chapter 77-00-01

79-30-02 Oil Temperature Sensor The oil temperature sensor is installed in the engine compartment on the LH forward engine gearbox, at oil-in-connection fitting.




3 Remove lock-wire.

4 Remove oil temperature sensor from fitting. Use a funnel to collect oil from line in a suitable container.

5 Plug oil temperature sensor fitting.


1 Reverse sequence of removal. Replace o-ring when necessary.

2 Perform engine indication check Refer to Chapter 77-00-01

79-30-03 Oil Pressure Switch The oil pressure switch is located in the engine compartment, on the LH side of the battery, the middle sideward sensor (refer to Figure 79-1).









CAUTION Never force the body of the sensor to turn against friction. It may change the set-point. Always use a wrench on the spanner flats of the attachment fitting for removal and installation.

3 Remove oil pressure switch.


1 Reverse sequence of removal. Apply Loctite 577 to pressure switch thread

2 Perform engine indication check Refer to Chapter 77-00-01

9. August 2013



Chapter 91 Charts



Table of Contents

EA-9B213.30A Cabin Pressure Control, HP up to serial N° 1002 EA-9B213.30B Cabin Pressure Control, HP Serial N° 1003 thru 1004 EA-9B213.30C Cabin Pressure Control, HP from serial N° 1005 EA-9B215.10B Air Condition, HB EA-9B215.20A Bleed Air System up to serial N° 1002 EA-9B215.20B Bleed Air System from serial N° 1003 EA-9B235.17 MKR / Audio, RM up to serial N° 1004 EA-9B235.17B MKR / Audio, RM from serial N° 1005 EA-9B243.10A DC Generation I, PP up to serial N° 1002 EA-9B243.10B DC Generation I, PP Serial N° 1003 thru 1004 EA-9B243.10D DC Generation I, PP from serial N° 1005 EA-9B243.20A DC Generation II, PR up to serial N° 1002 EA-9B243.20B DC Generation II, PR from serial N° 1003 EA-9B243.40A E-Box up to serial N° 1004 EA-9B243.40C E-Box from serial N° 1005 EA-9B243.41A PCB Board E-Box EA-9B244.10A External Power, PD up to serial N° 1002 EA-9B244.10B External Power, PD from serial N° 1003 EA-9B244.20 Battery charge, PL EA-9B246.10A DC Distribution up to serial N° 1002 EA-9B246.10B DC Distribution Serial N° 1003 thru 1004 EA-9B246.10D DC Distribution from serial N° 1005 EA-9B252.10A 12V Power receptacle (Cigar Lighter), MM EA-9B252.11A 12V Sockets,TH EA-9B256.11 ELT ARTEX ME 406, DA EA-9B271.17B AutoPilot-STEC-55X, CA up to serial N° 1004 EA-9B271.17D AutoPilot-STEC-55X, CA from serial N° 1005 EA-9B271.18A Yoke (Control stick) Left, Right EA-9B273.30A Stall Warning, WH up to serial N° 1002 EA-9B273.30B Stall Warning, WH Serial N° 1003 thru 1004 EA-9B273.30C Stall Warning, WH from serial N° 1005 EA-9B275.20A Flap-System, CG up to serial N° 1002 EA-9B275.20B Flap-System, CG Serial N° 1003 thru 1004 EA-9B275.20C Flap-System, CG from serial N° 1005 EA-9B276.10A Prop Overspeed, ES EA-9B284.10A Fuel QTY Indication, QX up to serial N° 1004 EA-9B284.11 Fuel QTY Indication, QX from serial N° 1005 EA-9B284.13A PCB-Board 1 up to serial N° 1004 EA-9B284.13C PCB-Board 1 from serial N° 1005 EA-9B284.30 Low Fuel Warning, WW up to serial N° 1002 EA-9B284.30A Low Fuel Warning, WW from serial N° 1003 EA-9B303.10A Pitot-Static-Stall-Heat, HG up to serial N° 1002 EA-9B303.10B Pitot-Static-Stall-Heat, HG Serial N° 1003 thru 1004 EA-9B303.10C Pitot-Static-Stall-Heat, HG from serial N° 1005 EA-9B304.10A Anti ICE Intake, HM up to serial N° 1002 EA-9B304.10B Anti ICE Intake, HM from serial N° 1003 EA-9B304.20A Windshield Heat, HF up to serial N° 1002 EA-9B304.20B Windshield Heat, HF from serial N° 1003 EA-9B310.10A Boots, HH up to serial N° 1002




EA-9B310.10B Boots, HH from serial N° 1003 EA-9B314.30B Airspeed Warning, WV up to serial N° 1004 EA-9B314.30D Airspeed Warning, WV from serial N° 1005 EA-9B315.80B Annunciator Panel, WW up to serial N° 1002 EA-9B315.80C Annunciator Panel, WW Serial N° 1003 thru 1004 EA-9B315.80D Annunciator Panel, WW from serial N° 1005 EA-9B315.81 PCB-Board Warning/Annunciator up to serial N° 1002 EA-9B315.90B Low Voltage Monitor, WL up to serial N° 1002 EA-9B315.90C Low Voltage Monitor, WL from serial N° 1003 EA-9B316.40A Digital Instrument, EY up to serial N° 1004 EA-9B316.41 Digital Instrument, EY from serial N° 1005 EA-9B316.50A Engine Instrument, EZ up to serial N° 1004 EA-9B316.51 Engine Instrument, EZ from serial N° 1005 EA-9B317.10A Engine Warning, LW up to serial N° 1002 EA-9B317.10B Engine Warning, LW from serial N° 1003 EA-9B323.10A-1 Landing Gear Control, GA up to serial N° 1002 EA-9B323.10C Landing Gear Control, GA from serial N° 1003 EA-9B323.20A Gear Warning, GA up to serial N° 1002 EA-9B323.20B Gear Warning, GA Serial N° 1003 thru 1004 EA-9B323.20C Gear Warning, GA from serial N° 1005 EA-9B334.10A Strobe Light, LB up to serial N° 1004 EA-9B334.10B Strobe Light, LB from serial N° 1005 EA-9B334.20A NAV Light, LC up to serial N° 1004 EA-9B334.20B NAV Light, LC from serial N° 1005 EA-9B334.35A Landing Light, LA up to serial N° 1002 EA-9B334.35B Landing Light, LA from serial N° 1003 EA-9B334.40A Cabin-Dome-MAP Light, LJ EA-9B334.50A Courtesy Light, LY EA-9B334.55A Ice Light, LN EA-9B334.60A Recognition Lights, LF up to serial N° 1002 EA-9B334.60B Recognition Lights, LF Serial N° 1003 thru 1004 EA-9B334.60C Recognition Lights, LF from serial N° 1005 EA-9B334.75A Glare Light EA-9B334.81A Luminiszenz-Backlighting EA-9B334.90A Dimming, LH up to serial N° 1004 EA-9B334.90B Dimming, LH from serial N° 1005 EA-9B334.91A PCB Dimmer up to serial N° 1004 EA-9B342.65 IFD LH, FG up to serial N° 1002 EA-9B342.65A IFD LH, FG Serial N° 1003 thru 1004 EA-9B342.65C IFD-1, FG from serial N° 1005 EA-9B342.66 IFD RH, FG up to serial N° 1002 EA-9B342.66A IFD RH, FG Serial N° 1003 thru 1004 EA-9B342.66C IFD-2, FG from serial N° 1005 EA-9B342.67 Keypad, FG up to serial N° 1004 EA-9B342.67B Keypad, FG serial N° 1005 EA-9B342.68 IFD-3, FG from serial N° 1005 EA-9B342.73 Attitude Gyro, FM EA-9B344.12A Weather Radar, SB from serial N° 1005 EA-9B344.14 Weather Detec TWX-670, SS up to serial N° 1004 EA-9B344.14B Weather Detec TWX-670, SS from serial N° 1005 EA-9B344.15 Traffic System TAS-610, SD up to serial N° 1004 EA-9B344.15B Traffic System TAS-610, SD from serial N° 1005




EA-9B344.16 Broadcast MLB-700, TL up to serial N° 1004 EA-9B344.16B Broadcast MLB-700, TL from serial N° 1005 EA-9B344.17 Datalink 2-way MLX-770, TS up to serial N° 1004 EA-9B344.17B Datalink 2-way MLX-770, TS from serial N° 1005 EA-9B345.47 DME KDM 706A, SN up to serial N° 1004 EA-9B345.47B DME KDM 706A, SN from serial N° 1005 EA-9B345.58 ATC BXP6402-1R, SH up to serial N° 1002 EA-9B345.58A ATC BXP6402-1R, SH Serial N° 1003 thru 1004 EA-9B345.58C ATC BXP6402-1R, SH from serial N° 1005 EA-9B360.11 Prop Heat, HI up to serial N° 1002 EA-9B360.11A Prop Heat, HI Serial N° 1003 thru 1004 EA-9B360.11B Prop Heat, HI from serial N° 1005 EA-9B410.30A_1 PCB Dimmer EA-9B410.30A_2 PCB Dimmer EA-9B410.30A_3 PCB Dimmer EA-9B410.30B_4 PCB Dimmer from serial N° 1005 EA-9B411.50_1 PCB Board 1 EA-9B411.50_2 PCB Board 1 EA-9B411.50_3 PCB Board 1 up to serial N° 1004 EA-9B411.50A_3 PCB Board 1 from serial N° 1005 EA-9B411.60_1 PCB Board 2 EA-9B411.60_2 PCB Board 2 EA-9B411.60_3 PCB Board 2 EA-9B411.70A_1 PCB Annunciator from serial N° 1003 EA-9B411.70A_2 PCB Annunciator from serial N° 1003 EA-9B527.10 Door Warning up to serial N° 1002 EA-9B527.10A Door Warning from serial N° 1003 EA-9B731.10A Fuel Pump / Filter, QB up to serial N° 1002 EA-9B731.10B Fuel Pump / Filter, QB from serial N° 1003 EA-9B731.30A Fuel Trans, QF up to serial N° 1002 EA-9B731.30B Fuel Trans, QF Serial N° 1003 thru 1004 EA-9B731.30C Fuel Trans, QF from serial N° 1005 EA-9B731.40A Fuel Flow, QY up to serial N° 1004 EA-9B731.40B Fuel Flow, QY from serial N° 1005 EA-9B743.10A Start / Ignition, JB up to serial N° 1002 EA-9B743.10B Start / Ignition, JB Serial N° 1003 thru 1004 EA-9B743.10C Start / Ignition, JB from serial N° 1005 EA-9B752.15A Panel Fan, HK



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Letzte Bearbeitung:

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RW

13H

B

14H

B

Mod

ul 5

0

HB10E-12N

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA


von Version zu


zu entnehmen.


*/*

in a

llen

Feldern angegeben.

04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberfläche

nschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gepr.:

Flugzeugbaureihe


EA

-9B

215.

20

EA

400

-500

BL

EE

D A

IR, H

A

BATT

ERY

BU

S P

P2

PB

ENV

-BLE

ED1H

A

5A

27

9 20

36

8

CABI

N T

EMPE

RATU

R CO

NTR

OLL

ER

28VDC

28VDC

Overtemp Ind Light

25

35

3 6 37

TEM

P

P16N

M10

3KA

9HA

-A

10H

A-A

14H

A-A

Airf

ram

e G

roun

d 0017

58 2

12 0

21V

N-3

TEM

P. M

OD

ULA

TIN

G V

ALV

E

CABI

N T

EMP.

SEN

SOR

DU

CT T

EMP

SEN

SOR

B CAD

A B10

32

A B CD

0017

58 2

12 0

2

8VN

-A

23

2 22

1 27

9 13

MA

SS F

LOW

CO

NTR

OLL

ER

28VDC

28VDC

Hi/Low Switch GND

30

18

35

0017

58 2

12 0

21V

N-3

11H

A-A

VA

LVE-

FLO

W C

ON

TRO

L

A C B D

23

2 22

1

MA

SS F

LOW

SEN

SOR

A CB D

24

31

5 7 8 36

26

529

31

Auto/Manual SW

Switch GND

Switch Power +15VDC

Pilot Control

Bypass GND

Bypass +28V

H.Exchanger GND

H.Exchanger +28V

Duct Sensor pos.

Duct Sensor GND

2HA

3HA

9HA

10H

A

14H

A

11H

A

12H

A

HA

1G-2

2

HA

3E-2

2S

HA

4E-2

2S

Pilot Control +VA

Pilot Control GND

HA

5E-2

2S

HA

6E-2

2S

HA

7E-2

2S

HA

27E-

22S

12

33

HA

8E-2

2S

HA

9E-2

2N

HA2F-22

HA

10E-

22N

HA

11G

-22

HA

12E-

22

HA

13E-

22

HA

14E-

22

10k

Open +28VDC

Open GND

Close +28VDC

Clos

e GND

HA

15E-

22S

HA

16E-

22S

Flow Sensor +15V

Flow Sensor GND

Flow Sensor Input

Flow Sensor GND

HA

17E-

22S

HA

18E-

22S

HA

19E-

22N

0017

58 2

12 0

22V

N-A

PRIM

. SH

UT

OFF

VA

LVE

Prim. Bleed N/C

15H

A

Standby ON

Manual Bypass

Man H. Exchanger

MAN

CO

NTR

OL

AUTO

/MAN

UAL

Airf

ram

e G

roun

d

Airf

ram

e G

roun

d

Trie

bwer

krau

mlin

ks

Co P

ilot

Ove

rhea

d

Trie

bwer

krau

mBr

ands

pant

rech

ts

Trie

bwer

krau

m

Bugf

ahrw

erkk

aste

n

links

an 1

1HA

Flo

w V

alve

13

Stadby ON

7HA

HA

3F-2

2S

HA4F-22S

Powe

r GND

Logi

c GND

Powe

r GND

Chas

sis GND

Power GND

Cabin Sensor Pos

Cabin Sensor GND

Low

High

E F G H

12H

A-A

32

4

ws

org

bl

VV

99

VV

100

VV

101

VV

102

231

ENV

BLEE

D

ON

OFF

16H

A:1

07.2

.1.1

3

HA

23E-

22N

HA28F-22

HA

22E-

22

Mic

rosw

itch

am

18H

ACond

ition

-Lev

er

Splic

eCu

t Off

28VDC

ws

bl org

bl ws

ws

bl ws

bl ws

bl ws

bl

ws

bl ws

bl

ws

bl org

bl ws

ws

bl ws

bl ws

bl ws

bl

ws

bl ws

bl ws

bl ws

bl

ws

bl

Tem

p. P

oti.

Ans

icht

von

hin

ten.

Cabin leftside

A

T D

C

VV

98

VV

103

VV

104

17.0

2.04

N/C

Tem

p Se

nsor

21H

AN

C

EA-0

B833

-09

HA

34E-

22N

Splic

eVV108

VV109

E

SN 1

3004

64-1

5EA

-0B8

33.0

6

3HA

-A

37po

l DSu

b

SN 1300360-17EA-0B836.30

SN 1300350-27EA-0B836.31

Env.

Ble

ed T

emp

EA-0

B836

.33

SN 1

3004

90-1

3Open +

Open -

Close +

Close -

GND

Sensor +

Sensor -

EA-0

B833

.08

SN 1

3004

40

Sensor +

Sensor -

EA-0

B833

.07

SN 1

3004

50-1

Bypass +

Exch +

Bypass -

Exch -

EA-0

B836

.26

SN 1

3003

30

N/C

N/C

N/C

N/C

Flow Sens +

Flow Sens -

Flow Sens In

Flow Sens Gnd

EA-0

B836

.32

HA

1E-2

2

2154

4-3-

60-2

Turb

ine

lefts

ide

NC

NO

334-

870

KA

BIN

E

CB-T

renn

steck

er

ST4

FIRE

WA

LL

FIRE

WA

LL

CB-T

renn

steck

er

66

67 43

68

69

42

70

71

41

40

72

73

74

75

39

38

76

77

78

79

37

21

22

20

HA

6F-2

2S

HA

7F-2

2S

HA

27F-

22S

HA

15F-

22S

HA

16F-

22S

HA

17F-

22S

HA

18F-

22S

HA20F-22

HA

21G

-22

HA

21F-

22H

A21

E-22

HA

22F-

22

HA

22G

-22

HA28G-22

HA1G-22 HA11F-22

HA

20G

-22

HA

28E-

22H

A4G

-22

HA

5F-2

2S

HA

28F-

22

D:9

2

D:8

2

D:1

02

45

6

:2

C:10

1

HA1F-22

1A3

1

HA

20F-

22

HA

15F-

22S

HA

16F-

22S

HA

17F-

22S

HA

18F-

22S

ST4

J4

HA

1F-2

2

see

EA-9

B246

.10

DC-

DIS

TRIB

UTI

ON

231

4HA

07.1

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7

231

MA

N

AUT

O5A

H:1

07.2

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34

56

5WW

-D

44

AN

NU

NCI

ATO

R BO

ARD

EA

-9B4

11.7

0

5WW

AN

NU

NCI

ATO

R PA

NEL

K2

G6A

-234

PD

38

BYW

56

D03

LIG

HT

TEST

(GN

D)

+ V

OLT

DIM

M

39H

A33

E-22

5WW

-A WW

39-2

0N9

ST12

1 2

ws

bl

3 4

HA

8E-2

2SH

A8F

-22

HA

2F-2

2H

A10

F-22

NH

A2G

-22

see

EA-9

B334

.40

CABI

N-D

OM

E-LI

GH

T&

EA

-9B2

35.1

7 M

KR-

AU

DIO

HA

21F-

22

CIRC

UIT

BRE

AK

ER/S

WIT

CH P

AN

EL

B:3

1

B:4

1

B:5

1

B:7

1

B:8

1

B:6

1

B:9

1

B:1

01

HA

3E-2

2S

HA

4E-2

2S

HA

5E-2

2S

2HA

-A

50po

l DSu

b

D:1

41

D:1

51

B:1

11

B:1

21

B:1

31

B:2

1

HA

21E-

22

see

EA-9

B246

.10

DC-

DIS

TRIB

UTI

ON

CB-T

renn

steck

er

06.1

0.10

HW

ÄM

-400

-09-

01A

9B21

520T

B

D1

BYW

56H

A6F

-22S

HA

7F-2

2S

ST4

J4

HA

22F-

22

HA

6E-2

2S

HA

7E-2

2S

HA

27E-

22S

C

HW

ÄM

-400

-10-

0408

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11B

L103

L203 5

Übe

r 5LH

-A P

in 9

an

F1

+ 28

V P

ower

WW

41E-

20

see

EA

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34.9

0

see E

A-9

B315

.80

AN

NU

NCI

ATO

R PA

NEL

Ann

unci

ator

Pan

el Blee

d O

vert

Stal

l-War

n

Win

dsh-

Heat

Pito

t Hea

t RPi

tot H

eat L

Stal

l Hea

t

Oil

Pres

s

Fuel

Pre

ss

Prop

Low

Pitc

h

ABCDE

FGHJK

0011

15-2

02-0

2M

odul

1

0017

58 2

12 0

21V

N-1

1VN

-5

0017

58 2

12 0

2K

2

3

4or

g

blws

org

blw

s

ws bl ws

bl ws

bl ws

bl ws

bl ws

bl ws

bl

ws

bl ws

bl ws

bl ws

blws bl ws

bl ws

bl

HA

20G

-22

HA

8F-2

2H

A10

F-22

NH

A2G

-22

OV

ERH

EAD

HA

24E-

22H

A24

E-22

HW

22.0

2.12

HA

4G-2

2

HA

15E-

22S

HA

16E-

22S

HA

17E-

22S

HA

18E-

22S

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA


von Version zu


zu entnehmen.



04

03

02

01

Ver.Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gepr.:

Flugzeugbaureihe


29.1

1.10

HW

EA

400

-500

MK

R/A

UD

IO, R

M

EA

-9B

235.

17

COM 1 SPKR LOAD GND

COM 1 SPKR LOAD

DME AUDIO LO

DME AUDIO HI

TEL RINGER IN

PILOT MIC GND

TEL RINGER GND

PILOT MIC IN

PILOT MIC KEY

PASS HEADSET R

PASS HEADSET L

PASS HEADSET GND

EXT BLUE LAMP (O)

EXT WHITE LAMP (A)

MKR ANTENNE

MKR ANTENNE GND

EXT AMBER LAMP (M)

25 26 21 2244 43 3335 34 42 40 41 1 2

2SN

-AK

DM

706

A

Audio Hi

Audio Lo

3FG

2SN

21 17

ws

bl

1RM

27,5 VDC

27,5 VDC

INSTR. LIGHT

Light GND

PILOT HEADSET GND

PILOT HEADSET L

PILOT HEADSET R

COPILOT HEADSET GND

COPILOT HEADSET L

COPILOT MIC KEY

PASS1 MIC GND

COPILOT HEADSET R

COPILOT MIC GND

PASS1 MIC

COPILOT MIC IN

SPEAKER OUT

SPEAKER GND

GND

GND

P340

11R

M-A

8 976 116 3123 4 3433323635 3740 4241 25 2338 2439 4344 10 11

P340

21R

M-B

COM 2 SPKR LOAD GND

COM 2 SPKR LOAD

27 28

DM

E

Pilo

t PT

T

Cop

ilot P

TT

PTT

LH A

rmre

st

4RZ5R

Z

6RZ

12CA

-A12

CA-a

MIC

11 12

Pilo

t MIK

E

gelb

grün

rt ws/g

rün

ws

bl

2x 0

0111

5 20

4 02

PTT

Mitt

elko

sole

13RZ

MIC

HA

ND

MIK

Ew

sbl

A BF G

C DH J

A BGF

blbl

ws

bl

Spira

lkab

el

Spira

lkab

el

see

EA-9

B27

1.17

AU

TOPI

LOT

14RZ

-A14

RZ-a

1 2 3

PASS

2

PASS

1

CO

PIL

OT

PASS

3

PASS

4

rt sw ws/

blw

s

ws

sw rt sw ws/

blw

s

ws

sw

15RZ

-A15

RZ-a

1 2 3 4 5 6 7 8 916

RZ-A

16RZ

-a

17RZ

-A17

RZ-a

18RZ

-A18

RZ-a

19RZ

-A19

RZ-a

20RZ

-A20

RZ-a

PIL

OT

1 2 3 4 5 6 7 8 9

1 2 3 4 5 6 7 8 9

1 2 3 4 5 6 7 8 9

1 2 3 4 5 6 7 8 9

1 2 3 4 5 6 7 8 9

MK

R A

nt. 2R

M

CI 1

18-5

LO

AD

BU

S

PP3

PASS2 MIC GND

PASS2 MIC

PASS3 MIC GND

PASS3 MIC

PASS4 MIC GND

PASS4 MIC

2x 0

0111

5 20

8 02

SPK

R5R

M

Pilo

t PH

ON

E

3RZ

PHO

NEB

UCH

SE

PMA

8000

B o

der

F

LE

A

31 32

0017

58 2

12 0

21VN

-3R

ALT WRN GND

5Light GND

see

EA-9

B33

4.90

DIM

MIN

G

A B D

C E

A B D

C E

FG

F G J

H K

RM

12E-

24SRZ

2E-2

4S

RZ9E

-24S

13 14ICS MUTE INHIBIT

ICS MUTE INHIBIT RETURN

HJK

RZ9F

-24S

RZ9K-24S

RZ9H

-24S

RZ9E

-24S

Modul 2 Modul 4

C D E

H J K

EK

ws

ws

ws

bl

ws

bl blorg

ws

Modul 5 Modul 6

bl org

ws

Mod

ule

Pilo

t lin

ks

ABC

DEF

GHJ

KLM

NPR

STU

1VN

-3

0017

58-2

12-0

2

1 2 11 12

Steu

erho

rn-S

teck

erle

iste

ALT WRN IN

org

ws

bl

RZ4F

-24S

RZ13

F-24

S

RZ13

E-24

Sblorg w

s

ws

org

RZ16

F-22

RZ16

F-22

ws

orgbl

ws

org

bl

bl ws

org

ws

org

bl ws

bl

ws

org

bl ws

bl

ws

org

org

bl

ws

bl

RZ16

J-24

RZ9F

-24S

RZ11

E-24

S

RZ16

H-2

4

RZ9G

-24S

RZ10

E-24

S

RZ16

J-24

RZ16

N-2

4

RZ16

M-2

4

RZ9H

-24S

RZ7E

-24S

RZ16

G-2

4

RZ9K

-24S

RZ8E

-24S

RZ5E

-24S

RZ4E

-24S

RZ2J

-24S

24M

odul

17

Pin

H

WH

13-2

2N

RZ1F

-22

LG3E

-22

RM15

E-22

N

RZ4E

-24S

RZ5E

-24S

RZ13

E-24

S

TZ7E

-24S

RZ8E

-24S

RZ11

E-24

S

RZ10

E-24

S

RM14

E-22

S

RZ17

E-22

NRZ

18E-

22N

RZ19

E-22

N

RZ13

F-24

S

RZ2F

-24S

RZ2G

-24S

RZ2H

-24S

RZ1E

-22

31se

e EA

-9B2

84.1

3 PC

-BO

ARD

1 P

in 8

VV10 VV11

VV22

VV21

VV23

VV24 VV25

RZ16

E-22

CB Trennstecker

RZ1F

-22

VV145

AU

DIO

-MR

K1R

Z5A

D:3

2

D:4

2

1A2

1

16

7RZ

BOSE

16

8RZ

BOSE

V+

MIC

HI

MIC

LO

LEFT

EA

R

GN

D

RIG

HT

EAR

V+

MIC

HI

MIC

LO

LEFT

EA

R

GN

D

RIG

HT

EAR

V+

MIC

HI

MIC

LO

LEFT

EA

R

GN

D

RIG

HT

EAR

V+

MIC

HI

MIC

LO

LEFT

EA

R

GN

D

RIG

HT

EAR

V+

MIC

HI

MIC

LO

LEFT

EA

R

GN

D

RIG

HT

EAR

V+

MIC

HI

MIC

LO

LEFT

EA

R

GN

D

RIG

HT

EAR

16

9RZ

BOSE

16

10RZ

BOSE

16

11RZ

BOSE

16

12RZ

BOSE

2RZ 1A

RZ16

G-2

4RZ

16H

-24

RZ16

K-2

4

blorg

ws

bl org

ws

ws

blws

blws

blws

bl ws

blws

bl

A B DC E

F G

0011

15-2

02-0

2

H J KRZ

16K

-24

RZ16N-24RZ16M-24

RZ9G

-24S

PASS

2PA

SS 1

PASS

3PA

SS 4

CO

PILO

TPI

LOT

Pilo

t PH

ON

E

Pilo

t PTT

Cop

ilot P

TT

Pilo

t MIK

E

HA

ND

MIK

E

Pilo

t

LH A

rmre

st

AU

DIO

& M

AR

KER

CIR

CU

IT B

REA

KER

/SW

ITC

H P

AN

EL

see

EA-9

B24

6.10

DC

-DIS

TRIB

UTI

ON

ST12 C1

5P

11 8w

sbl

see

EA-9

B34

4.14

WEA

THER

DET

ECTI

ON

MICROPHONE #1

TX KEY #1

HEADPHONE #2

HEADPHONE #2 LO

HEADPHONE #1 LO

HEADPHONE #1

HEADPHONE #3

HEADPHONE #3 LO

11 5 13 29 44 30 43 28

11 12 17 18 7 89 10

COM 1 MIK AUDIO OUT

COM 1 MIK KEY OUT

NAV #1 RX HI

NAV #1 RX LO

COM #1 RX LO

COM #1 RX HI

MONITOR #1 RX HI

MONITOR #1 RX LO

P114

4

ws

blw

sbl

ws

blw

sbl

ws

blbl

ws

blw

sbl

3029

MICROPHONE #1

TX KEY #1

HEADPHONE #2

HEADPHONE #2 LO

HEADPHONE #1 LO

HEADPHONE #1

HEADPHONE #3

HEADPHONE #3 LO

11 5 13 44 43 28

15 30 19 20 13 14

COM 2 MIK AUDIO OUT

COM 2 MIK KEY OUT

NAV #2 RX HI

NAV #2 RX LO

COM #2 RX LO

COM #2 RX HI

P214

4

ws

blw

sbl

ws

blw

sbl

ws

blw

sbl

CFG DISCRETE IN 0

CFG DISCRETE IN 1

CFG DISCRETE IN 2

62 63 823637 38

J112

1

DISCRETE IN 7

DISCRETE IN 6

38 37

COM SPLIT SELECTED

ACTIVE COM SELECTED

P112

22524

DISCRETE IN 7

DISCRETE IN 6

38 37

P212

2

DISCRETE OUT 10

21

20COM SWAP

DISCRETE OUT 10

21

CFG DISCRETE IN 0

CFG DISCRETE IN 1

CFG DISCRETE IN 2

62 63 82

J212

1

IFD

-1IF

D-5

000i

IFD

-2IF

D-5

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see

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Änd

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Letzte Bearbeitung:

Datum

Name

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Gepr.:

Maßstab

SI.-Klasse

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4 St

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4 St

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BOOTS TIMER 310.10

45

6

18PP

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23

1

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07.2.1.13

21

3

EMER

GEN

CY

19PP

07.1.1.13

21

3

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07.1.1.13

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1

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07.1.1.17

23

1

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21 3

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07.1

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2 13

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07.2.1.40 901645

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2

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PR19E-20

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B:3

2

B:1

2

B:2

2

B:4

2

B:5

2

A:1

1

A:4

1

A:51

A:6

1

A:7

1

A:8

1

A:9

1

A:1

0

1

A:1

1

1

A:1

2

1

B:1

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B:10

1B:

31

B:4

1B:

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B:6

1B:

81

B:2

1B:

91

B:11

1B:

121

A:1

2

A:2

2 A:3

2

A:4

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A:6

2

A:7

2

A:8

2

A:9

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A:1

0

2

A:1

1

2

A:1

2

2

C:1

1

C:2

1

C:4

1

C:3

1

C:5

1

C:6

1

C:7

1

C:8

1

C:9

1

C:12

1

C:13

1

C:14

1

C:15

1

C:16

1

C:17

1

C:18

1

C:19

1

C:20

1

D:1

1

D:2

1

D:4

1

D:5

1

D:6

1

D:7

1

D:8

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D:9

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D:1

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D:1

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D:1

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1

D:1

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D:1

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D:3

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D:1

51

D:1

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D:1

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1

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C:1

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C:2

3

C:3

3

C:4

3

C:5

3

C:6

3

C:7

3

C:8

3

A:1

3

A:2

3

A:3

3

A:4

3

A:5

3

A:6

3

A:7

3

A:8

3A

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3

B:1

3B:

2

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B:4

3

B:3

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B:5

3B:

63

B:7

3B:

83

B:9

3

D:1

2

D:2

2D

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D:5

2

D:6

2

D:7

2

D:8

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D:1

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D:1

72

D:1

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C:4

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334.50

334.81 LUMI FOLIE

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VV

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99

Buc

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93

Buc

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195

Mod

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Mod

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Mod

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Mod

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412

DC-GEN 2 243.20

DC-GEN I 243.10

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D:1

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D:1

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D:2

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WV8E-22

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LT1E-20

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VMO WARN 314.30

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HB

4E-2

0

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PP34E-12

PP36E-16N

2X2

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20-A

7-A

1025

A

30PP

M32

0-B4

N

CG51H-22

VENT RIGHT

752.15HK1F-22

DUMP 213.30

1A

21


von Version zu


zu entnehmen.



04

03

02

01

Ver.

Beze

ichn

ung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letzte Bearbeitung:

Dat

umNa

me

Bearb.:

Gepr.:

Maßs

tab

SI.-

Klas

seOb

erfl

äche

nsch

utz

Proj

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onFr

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146

569

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xe, G

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any

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1FG1E-14 IFD-1IFD-1

C:10

1

342.65

256.11

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2

C:11

1

HA28E-22

MAN

AUTO

HA22E-22

HA21E-22

ENV BLEED 215.20

HA

4G-2

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ON

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3

1

ENV

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16H

A:1 07.2.1.134

56

TEM

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D:3

3

T&B

3CA5A TURN COORDINATORCA2E-22

HH1E-22

WV1E-22VN

E-W

AR

N

1WV1A 314.30Vmo WARNING

1

1

271.17

243.20

323.10

54

6CABIN PRESS 213.30HP2E-22

CABIN PRESS 213.30HP10E-22N

CABIN PRESS 213.30HP9G-22

ON

OFF

B:13

1

B:14

1

B:15

1B:

16

1

B:17

1

B:18

1

B:19

1

B:20

1

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3HI

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EXT-LADER

CB2 5A EXT-LADER 244.20

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B:12

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Pin

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1

P 8A

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2

P 8A

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3123

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5 6

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1234

5 6

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1 2 3 4

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WEATHER RADAR

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SB1H-20

A:1

2

3

A:1

1

3

ÄM-4

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2-07

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D03

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BYW56 16EZ 1A

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DIGITAL INSTR 316.41

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EZ1G-20

EZ5E-20

15EZ

BYW56

14EZ

BYW56

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IFD-3 342.68IFD

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1

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PROP HEAT 360.11HI4E-22

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Mai

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Man

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5X, C

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271.

17

17 32 33 48 47 1415165039 10 11 4429 9 8 2742 233 28 30 315 6 45

Trim Motor + Down

Trim Motor + UP

Trim Solonoid

GND Solonoid

Shield GND

Shield GND

Shield GND

Trim Interrupt

Manual Down SW

Manual UP SW

28 VDC Trim

10 VDC Paralax Pot.

Pitch Str. Centering

FD Pot. GND

Sig. Ref.

FD. Flag

FD Enable

Audio Output

GND

Alt. Sel. Jumper

Roll Sol. Logic YD.

Pitch Flap Pot.

Signal Reference

Trim FlaP Pot

CWS

CWS GND

Lights

15 34 17 9 10 3525 39 4316 33 50 46 7 8 26 27425 6 24 41 2 21 4 20 3 22 23 40 19 18 1 3639

Shield Gnd.

Shield Gnd.

Shield Gnd.

Shield Gnd.

Shield Gnd.

A/P A+

A/P Disconnect

Ground for DG

Ground

Airframe Ground

Exitation

EXC. Ground

EXC. + 10 V

Transducer Ground

10 VDC

Transducer Signal

AC Heading

AC Course

Exitation Ref.

Signal Ref.

Rate Gyro Tach.

Rate Gyro Ref.

Rate Gyro Signal

Pitch Solonoid GND

Pitch Motor

Trim Switch DN

Pitch Solonoid

Pitch Motor

Trim Switch UP

Trim Switch Com.

Roll Motor

Roll Solonoid

Roll Motor

Roll Solonoid GND

1 234

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CA

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4S

CA

6E-2

2

CA

8E-2

2

CA

18F-

221013

3 1 2 64

197 8

Y CTR

YD ON / OFF

Y Solenoid

Y Motor 1

Y Motor 2

GND

GND

A+ GND

10 VDC out

Y Solenoid

Y Motor 1

Y Motor 2

GND

12C

A-A

YA

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AM

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CA

12E-

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CA

13E-

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CA

17E-

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CA

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CA

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CA

20E-

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CA

23E-

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PB

T&

B3C

A

5A

AP-

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VO 1C

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5A

4CA

1A2

1


von Version zu


zu entnehmen.



04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gepr.:

Flugzeugbaureihe


CA

1E-2

0

CA

1F-2

0

A:5

3

A:6

3

AP

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MPT

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CA1H-20

CA

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0

CA

3E-2

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CA

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1

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see

Det

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16C

A:1

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16C

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07.2

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21 3

Off

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AI ENERGIZE

K1C-NO

K1D-NO

K2D-NO

K2C-NO

K2B-NO

K1A-NO

K3D-NO

K3B-NO

K2A-NO

K3A-NO

K4B-NO

K4D-NO

K4C-NO

K4A-NO

K2D-W

K2C-W

K1C-W

K1D-W

K2B-W

K1A-W

K3D-W

K4D-W

K4C-W

K4A-W

K3B-W

K2A-W

K3A-W

K4B-W

7228V RELAY POWER

ws

bl ws

blws

bl

L-R +RT

L-R -RT

3031

DC HDG HI (KCS 55)

HDG RETURN

DC CRS HI (KCS 55)

CRS RETURN

G/S UP +

VS SIGNAL

SHIELD GROUND

2829 111218 22 44

ALT ENGAGE SIGNAL

ALT SEL CONTROL

SHIELD GROUND

SHIELD GROUND

G/S FLAG +

G/S FLAG -

LOC SWITCH

NAV FLAG +

NAV FLAG -

20 213949 1 2 3213 14

ROLL STEERING 429A

ROLL STEERING 429B

SHIELD GROUND

36 37 46

ws

bl ws

blws

bl ws

bl

SHIELD GROUND

45

ws

bl

DISCRETE OUT 0

DISCRETE OUT 0+

DISCRETE OUT 1

DISCRETE OUT 0-

DISCRETE OUT 2

GROUND

GROUND

DISCRETE OUT 1+

ANALOG OUT 0

DISCRETE OUT 1-

ANALOG GROUND

429 TX0+

ANALOG OUT 2

429 TX0+

ANALOG OUT 3

GROUND

ANALOG REF

ANALOG OUT 5

ANALOG OUT 6

DISCRETE OUT 4

2 3 4 15 102612 13 2719 640 2560 3920 4110 31 14

P112

2ws

bl ws

bl ws

bl

DISCRETE OUT

DISCRETE OUT 0+

DISCRETE OUT 1

DISCRETE OUT 0-

DISCRETE OUT 2

GROUND

GROUND

DISCRETE OUT 1+

ANALOG OUT 0

DISCRETE OUT 1-

429 TX0+

ANALOG OUT 2

429 TX0+

ANALOG OUT 3

GROUND

ANALOG OUT 5

ANALOG OUT 6

2 3 4 15 102612 13 27 19 406020 4110 31 14

P212

2 ws

bl ws

bl ws

bl

ws

bl ws

blws

bl

25 426 27222330 29 8 32333634 35

K1C-NC

K1D-NC

K2D-NC

K2C-NC

K2B-NC

K1A-NC

K3D-NC

K3B-NC

K2A-NC

K3A-NC

K4B-NC

K4D-NC

K4C-NC

K4A-NC

P112

1

P212

1

DISCRETE IN 3

ANALOG IN 1

ANALOG IN 0

DISCRETE IN 0

DISCRETE IN 2

DISCRETE IN 1

GROUND

429 RX0+

429 RX0-

23 41 40 22 7 8 15

51 72

PITCH STR SIG

ROLL STR SIG

1312

ANNUN LOAD

ANNUN CLOCK

ANNUN DATA

24 25 2640SHIELD GROUND

FD LOGIC

4

ws

bl

429 TX+

48429 TX-

37

J112

2

blws

ws

bl

DISCRETE IN 3

ANALOG IN 1

ANALOG IN 0

DISCRETE IN 0

DISCRETE IN 2

DISCRETE IN 1

GROUND

429 RX0+

429 RX0-

23 41 40 22 7 8 15

51 72

J212

2

blws

ANALOG GROUND

ANALOG REF

25 39

ws

bl

bl

wsbl

ws

IFD

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IFD

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see

EA-9

B34

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0008

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see

EA-9

B34

2.66

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0008

3-() 7FG

CA15H-22

CA

15H

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CA

15E-

20

CA15E-20

CA

8E-2

2

CA

21E-

24

CA

22E-

24S

CA

9E-2

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CA

19E-

24S

CA

21E-

24

CA

30E-

22

CA

31E-

24S

CA

32E-

24S

CA

33E-

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CA

34E-

24S

CA

35E-

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CA

36E-

24S

CA

37E-

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A38

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CA

39E-

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CA

40E-

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CA

41E-

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CA

42E-

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CA

45E-

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CA

46E-

24S

CA

47E-

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CA

49E-

24

CA

50E-

24S

CA

51E-

24S

CA

52E-

24S

CA

53E-

24S

CA

54E-

24S

CA

55E-

24

CA

56E-

24C

A57

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CA

58E-

24

CA

59E-

24S

CA

60E-

24S

CA

61E-

24S

CA

62E-

24S

CA

63E-

24S

CA

64E-

24S

CA

65E-

24S

CA

66E-

24S

CA

67E-

22

CA

69F-

22

CA

70F-

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CA

71F-

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CA

72F-

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CA

77E-

22N

CA

73E-

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A74

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CA

75E-

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CA

67E-

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CA

30E-

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CA

76E-

22

CA

73E-

22C

A74

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CA

75E-

22C

A76

E-22

CA

56E-

24C

A57

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CA

58E-

24

CA

59E-

24S

CA

60E-

24S

CA

61E-

24S

CA

62E-

24S

CA

63E-

24S

CA

64E-

24S

CA

65E-

24S

CA

66E-

24S

CA

47E-

24C

A48

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CA

49E-

24

CA

50E-

24S

CA

51E-

24S

CA

52E-

24S

CA

53E-

24S

CA

54E-

24S

CA

55E-

24

CA

44E-

24S

CA

45E-

24S

CA

46E-

24S

CA

31E-

24S

CA

32E-

24S

CA

33E-

24S

CA

34E-

24S

CA

35E-

24S

CA

36E-

24S

CA

37E-

24S

CA

38E-

24S

CA31F-24SCA32F-24SCA33F-24SCA34F-24SCA35F-24SCA36F-24S

CA

31F-

24S

CA

32F-

24S

CA

33F-

24S

CA

34F-

24S

CA

35F-

24S

CA

36F-

24S

CA

37F-

24S

CA

37F-

24S

CA38F-24S

CA

39E-

24S

CA

40E-

24S

CA

41E-

24S

CA

42E-

24C

A43

E-24

9CA

PTT

Pilo

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e EA

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235.

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KR

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grün

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0.10

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Roll Sign. Ref.

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F-24

Sw

sbl

D

R1

2K0

R2

2K0

0,25

W

ST13

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SIM

12

DR

UC

KSC

HO

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INTE

N

CA

70E-

22

CA

71E-

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CA

72E-

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CA

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2

CA

69E-

22

11 7 6 13

ST14

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ST13

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SIM

1

DR

UC

KSC

HO

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N

10

ST14

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ws

bl ws

bl

ws

bl ws

bl5423 D

RU

CK

SCH

OTT

HIN

TEN

16 171514 1812

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bl ws

bl ws

org

bl

ws

bl ws

bl ws

org

bl

11 19

6 8

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SIM

7 9

ws

org

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ws

org

bl

DR

UC

KSC

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N

2013

ST14

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X1 X2

A1

A3A2

B1

B3B2

55C

A

REL

M21

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CA

4F-2

4S

CA

5F-2

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1234 5 6 789 10

1112

1314

15

CA

20F-

24S

17 26

P1

PC-B

OA

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!

D32

D11D21

D31

12

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D

Mai

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ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

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Die

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04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

Ober

fläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

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er B

auak

te b

zw.

18.0

8.04

PB

EA

400

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STA

LL

WA

RN

ING

, WH

EA

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273.

30

EM

ER

GE

NC

Y B

US

PP4

AN

NU

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13

12

30

35

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0

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0 13

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1

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WV

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2

CA

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0

CA

1E-2

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1

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EA-9

B315

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NU

NCI

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BA

TT

ER

Y B

US

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AV

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BU

S

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see

EA-9

B303

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see

EA-9

B314

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SPEE

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ARN

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(TO

NE

TEST

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V8F

22

see

EA-9

B314

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AIR

SPEE

D W

ARN

ING

(IF

D L

EFT)

GW

1F-2

2

WV

1F-2

2

WH

5E-2

2N

WH

4E-2

2

WH

1H-2

2

WH

10E-

22

TON

E-G

ENER

ATO

R

TON

E-G

ENER

ATO

R

TON

E-G

ENER

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R

WH

11E-

22

46

STA

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AN

NU

NCI

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M

see

EA-9

B315

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NU

NCI

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CG37

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N

GW

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2

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2

WH

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2

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A-9

B246

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D32

D12

D13

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2

9B27

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01.0

7.10

HW

ÄM

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01A

see

EA-9

B284

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PCB-

BOA

RD 1

C

HG

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HG

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HW

ÄM

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B323

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PC-B

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2

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WH

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(GEA

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ARN

ING

)

2

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HW

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Nr.:

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Mai

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Man

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XTR

A 5

00

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N°

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2-TR

-03-

2013

1212

11

22

33

44

55

66

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88

DD

CC

BB

AA


von Version zu


zu entnehmen.



04 03 02 01 Ver.

Bezeichnung

Nr.:

Ände

rung

/Mod

. Nr.:

Dat

umN

ame

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Heid

e 21

4656

9 H

ünxe

, Ger

man

y

Gepr.:

Flugzeugbaureihe


EA 4

00-5

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AP

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G

GN

M 4

175A

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G

N O

N C

C12

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C11

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C

13C

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N C

C

14C

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N C

C

15C

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C

16C

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SW

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SW

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SW

L U

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MIT

SW

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G L

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14° L

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A

15° L

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2.03

UP

REL

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DO

WN

REL

AIS

8888

8787

87a

87a

88a

88a

8585

8686

321-

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links

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CG12E-22S

CG41

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CG42E-22

CG25F-22M

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CG52F-22N

CG21E-22

CG34

F-22

CG32

F-22

CG33

F-22

CG1G

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CG1E

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CG25

E-22

CG24

E-22

CG20

F-22

CG26

F-22

CG1J-22

CG15

G-2

2CG

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CG23

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N

CG22

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N

CG50

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0

CG51

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0

CG8E

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19 16 18 1712

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CG36

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CG39

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13 14 15

AF B

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CG21E-22CG19E-22

CG42E-22CG41E-22

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109 11

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CG36

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Flap Inhibit/28V

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15° LED

Up RelayDown Relay

Pos. Switch 30°

Pos. Switch 15°

Pos. Switch 0°28VDC Power In

7CG

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590

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6CG

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590

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gre

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8CG

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am

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CG34

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8CG

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10

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CG32

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CG33E-22

CG3

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1758

212

02

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N

T

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2

CG12

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S

CG9E

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NC

CG32

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X1X2

A1A3A2

B1B3B2

Sock

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5-A1

33CG

M21

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A B C D E

F G H J K

Mod

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1

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2

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A B C D E

F G H J K

Mod

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AB

C

DE

F

GH

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KL

M

NP

R

ST

U

20V

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, 3V

N-A

, 1V

N-C

VV119

VV120

VV121

VV122

VV123

VV124

VV125

VV126

VV127

VV128

VV129

VV130

VV131

VV132

VV133

VV135

VV136

VV137

VV138

CG8G

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CG1F

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CB Trennstecker

Doc

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56.0

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7.5A

FLA

P-C

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3

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A:3

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J 6a-

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AV

ION

IC B

AY

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F-22

CG51

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01

19 20

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P600

M

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F-22

see E

A-9

B334

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COU

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Y L

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1

32CG

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CG

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UIT

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B246

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A-9

B315

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NCI

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LIG

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CG39

E-22

CG36

E-22

CG40

E-22

LY10

F-22

20

X1 X2

A1

A3A2

B1

B3B2

Sock

el S2

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5A1

36C

GRE

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155

12

314

106

138

911

7

A1A2

X1X2

X1A1A2 X2

X1X2

A2B2D2

D3

B3 A3

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nten

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Man

ual E

XTR

A 5

00

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91

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2-TR

-03-

2013

1212

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22

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44

55

66

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04 03 02 01 Ver.

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Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

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auf

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de 2

146

569

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nten

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Man

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XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

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DD

CC

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tor

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von Version zu


zu entnehmen.



04

03

02

01

Ver.Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

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M

Mai

nten

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Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

Die

Gül

tigke

itszu

ordn

ung

von

Ver

sion

zu

dem

jew

eilig

en F

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en.

Zuor

dnun

g lin

ks /

rech

ts w

ird m

it*/

* in

alle

n Fe

lder

n an

gege

ben.

04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

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400

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D 1

EA

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HW

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Name

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Maßstab

SI.-Klasse

Oberflächenschutz

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Freimaßtoleranz

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04

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02

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Ver.Bezeichnung

Nr.:

Änd

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g/M

od. N

r.:D

atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

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7 624 25PRESS CH 3 (+In)

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11 1028 29PRESS CH 5 (+In)

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37 19POWER

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Man

ual E

XTR

A 5

00

Ch.

91

N°

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2-TR

-03-

2013

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11

22

33

44

55

66

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88

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sion

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04 03 02 01 Ver.

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Nr.:

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erun

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od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bear

b.:

Gep

r.:

Maßstab

SI.-Klasse

Oberfläche

nschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

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r.:

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zeug

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20

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0

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OR

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D

NO

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AR

GN

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P

CLE

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2

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1

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0

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C

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see E

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0

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unci

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62

63

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GA

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22

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EM

ER

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NC

Y B

US

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GW

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31

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AK

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CH P

AN

EL

see E

A-9

B246

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DC-

DIS

TRIB

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ON

GA

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GA

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22

GA

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CG15

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2

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DIM

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DIM

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G (T

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DIM

MIN

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RIG

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LEFT

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321

GA

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22

GA

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22

VV

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187

GA

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22

GA

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22

ST10

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A26

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2

GA

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GA

24H

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GA

25E-

22

GA

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22

8

see E

A-9

B323

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GEA

R C

ON

TRO

L

BOD

ENST

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ING

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RIG

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8 12 30 14

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2

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22

VV

120

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N

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yel

red

5LH

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3 22 164

WH

12E-

22

A B C D E

F G H J K

LH8E

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DIM

MIN

G B

OA

RD

see

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B334

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DIM

MIN

G

5LH

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ul 1

5

GA

27E-

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A27

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GA

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D

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D

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D

GA

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GA

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GA

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GA

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22

GA

25J-

22

GA

26J-

22

34

D3

D2

D1

D6

D4

D5

D7

16 1

K3:

1

46

5

38

7

16 1

K2:

1

1311

12

149

10

16 1

K1:

1

1311

12

149

10

161

K4:

1149

10

16 1

K6:

1

1311

12

38

7

46

5

16 1

K7:

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46

5

38

7

16 1

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12

149

10

46

5

38

7

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UB

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HW

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0302

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GN

D

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

DD

CC

BB

AA

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EA 4

00-5

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1 2 3

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F G H J K

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01

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red blk

wht

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BE L

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T PO

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LY R

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red

blk

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28 VDC

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04

8VN

Mas

sebo

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LB2F

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LB13

E-20

LB3E

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N

5LB-

A

LB2E

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LB10

E-20

LB4E

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7LB-

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B-b

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E-20

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LB20

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LB10

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red

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a

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Strobe Light right

Strobe Light left

AM

P Cr

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uchs

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PN 01-0770028-05

Power Input

Trigger Select

3LB

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Brücke VV193

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122

0

10

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3

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11

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von

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sion

zu

dem

jew

eilig

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ungs

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agzu

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en.

Zuor

dnun

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ks /

rech

ts w

ird m

it*/

* in

alle

n Fe

lder

n an

gege

ben.

04

03

02

01

Ver.Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bear

b.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche

Schut

zverme

rk nac

h DIN 34 beac

hten.

EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

CIR

CU

IT B

REA

KER

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ITC

H P

AN

EL

AM

P St

ecke

r 1-0

4803

05-0

AM

P Bu

chse

1-0

4803

05-0

AM

P Cr

impk

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kt B

uchs

e 1

6355

7-2

AM

P Cr

impk

onta

kt P

in 1

6355

8-2

LB2F

-20

LB20

E-20

see

EA-9

B24

6.10

DC

-DIS

TR

IBU

TIO

N

STRO

BE L

IGH

T RE

AR

STRO

BE L

IGH

T PO

WER

SU

PPLY

3LB

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BE L

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T RI

GH

T

STRO

BE L

IGH

T LE

FT

6LB

4LB

5LB

LB13

E-20

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HW

ÄM-4

00-0

9-01

01.0

8.10

A

B

LB2G

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TT H

INTE

NST

13-C

SIM

6

AM

P St

ecke

r 1-0

4803

05-0

AM

P Bu

chse

1-0

4803

05-0

AM

P Cr

impk

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kt P

in 1

6355

8-2

AM

P Cr

impk

onta

kt B

uchs

e 1

6355

7-23

19V

N-A

0017

58 2

12 0

2L

LB20

F-20

N

TREN

NST

ECK

ER S

EITE

NRU

DER

ABD

ECK

UN

G

HW

ÄM-4

00-1

2-03

02.0

4.12

B

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

EA

400

-500

NA

V L

IGH

T, L

C

EA

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20

DRU

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LC2H

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LC2M

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NA

V L

IGH

T RI

GH

T

NA

V L

IGH

T RE

AR

NA

V L

IGH

T LE

FT

ST5-

1B

SIM

122

0

9

NA

V-L

T1L

C

5A

21 3

NA

V

ON

OFF

2LC 07

.1.1

.13

D:3

1

D:4

1

1A3

1

Die

Gül

tigke

itszu

ordn

ung

von

Ver

sion

zu

dem

jew

eilig

en F

ertig

ungs

auftr

agzu

ent

nehm

en.

Zuor

dnun

g lin

ks /

rech

ts w

ird m

it*/

* in

alle

n Fe

lder

n an

gege

ben.

04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

Ober

fläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

TREN

NST

ECK

ER O

VER

HEA

D

LC2K

-22

LC2H

-22

CIRC

UIT

BRE

AK

ER/S

WIT

CH P

AN

EL

see E

A-9

B246

.10

DC-

DIS

TRIB

UTI

ON

9B33

420T

HW

ÄM

-400

-09-

0101

.08.

10A

B

ST13

-D

SIM

15

A B C D E

F G H J K

MO

DU

L 40

0011

15 2

09 0

2

LC2N

-22

LC2L

-22

LC2M

-22

LC2N

-22

LF2H

-22

LF2G

-22

LF2J

-22

see

EA-9

B334

.60

RECO

GN

ITIO

N L

IGH

T

HW

ÄM

-400

-12-

0302

.04.

12B

4LC

-B4L

C-b

TREN

NST

ECK

ER S

EITE

NRU

DER

ABD

ECK

UN

G

3

LC2J

-22

LC2J

-22

19V

N-A

0017

58 2

12 0

2M

LC2K

-22

LC4E

-22N

LC4F

-22N

AM

P St

ecke

r 1-0

4803

05-0

AM

P Bu

chse

1-0

4803

05-0

AM

P Cr

impk

onta

kt P

in 1

6355

8-2

AM

P Cr

impk

onta

kt B

uchs

e 1

6355

7-2

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

31.0

8.04

PB

EA

400

-500

CA

BIN

-DO

ME-

MA

P-LI

GH

T, L

J

EA

-9B

334.

40

LO

AD

BU

S PP

31L

J

8VN

-A

0017

58 2

12 0

2

9LJ

13LJ

14LJ

3LJ

7LJ

8LJ

17LJ

19LJ

MA

P LI

GH

T

VV19

5VV

196

VV

197

VV198

LJ1E

-22

LJ2E

-22

LJ2F

-22

LJ3E

-22N

DO

ME

LIG

HT

LJ1F

-22

LJ1G

-22

LJ1H

-22

LJ5E

-22

LJ5F

-22

LJ6F

-22N

LJ4E

-22N

CA

BIN

-LT

1LJ

21 3

CA

BIN

ON

OFF

16LJ

21 3

MA

P

ON

OFF

15LJ

C:8

1

D:2

1

D:1

1

5LY

P600

M

see

EA-9

B334

.50

COU

RTES

Y L

IGH

T

WA

TSK

I 101

727

(Art.

no.

4678

10)

(332

60)

PILO

T

COPI

LOT

PILO

T

COPI

LOT

LY15

F-22

LY5H

-22

LY5E

-22

CABI

N L

IGH

T

1

11

1

1A3

1

Die

Gül

tigke

itszu

ordn

ung

von

Ver

sion

zu

dem

jew

eilig

en F

ertig

ungs

auftr

agzu

ent

nehm

en.

Zuor

dnun

g lin

ks /

rech

ts w

ird m

it*/

* in

alle

n Fe

lder

n an

gege

ben.

04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

Ober

fläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

CIRC

UIT

BRE

AK

ER/S

WIT

CH P

AN

EL

18LJ

2-a

18LJ

1-A

2121

M78

15C

V

SPA

NN

UN

GSR

EGLE

R

INO

UT

GN

D

18LJ

IN GN

DO

UT

TO22

0

5 10 9 6 7

LJ1K

-22

LJ5G

-22

LJ6H

-22N

LJ4G

-22N

LY15

E-22

23LJ

P600

M

21 3

8VN

-A

0017

58 2

12 0

2

CABI

N

COCK

PIT

12

3

Geh

äuse

P 1

-048

0305

-0FE

4308

Pin

1635

58-2

FE43

06

Geh

äuse

B 1

-048

0303

-0FE

4307

Buch

se 1

6355

7-2

FE43

05

2LJ-

A2L

J-a

& E

A-9

B334

.50

COU

RTES

Y L

IGH

T

see E

A-9

B235

.17

MK

R-A

UD

IO&

EA

-9B2

15.2

0 BL

EED

AIR

see E

A-9

B246

.10

DC-

DIS

TRIB

UTI

ON

9B33

440T

HW

ÄM

-400

-09-

0120

.10.

10A

A

ST12

LJ2G

-22

LJ3F-22N

LJ2H

-22

LJ3E

-22N

LY5H

-22

LJ2G

-22

2

2PN

. : 1

1-07

800

(LE

D 1

4VD

C)

(

3053

1)

22LJCA

BIN

LJ1H

-22

LJ5F

-22

OS-

LM10

A-W

1-84

7

W

Läng

e 20

0 cm

= 2

0 Ei

nhei

ten

+ G R B

OS-

LM10

A-W

1-84

7

W+ G R B

OS-

LM10

A-W

1-84

7

W+ G R B

OS-

LM10

A-W

1-84

7

W+ G R B

OS-

LM10

A-W

1-84

7

W+ G R B

OS-

LM10

A-W

1-84

7

W+ G R B

HW

11.1

0.11

9LJ-

A9L

J-a

3LJ-

A

3LJ-

a

10LJ

4LJ10

LJ-A

10LJ

-a

4LJ-

A

4LJ-

a

11LJ 5L

J

11LJ

-A

11LJ

-a

5LJ-

A

5LJ-

a

12LJ

6LJ

12LJ

-A

12LJ

-a

6LJ-

A

6LJ-

aCA

BIN

LIG

HT

CABI

N L

IGH

TCA

BIN

LIG

HT

11

21 321 3

12

3

12

31

23

12

3

12

31

23

E

FD

LJ2J-22

LJ2K

-22

LJ2L-22

LJ2F

-22

LJ3G

-22N

LJ3H-22N LJ3J-22N

LJ3K-22N

LJ3L

-22N

LJ3M-22N LJ3N-22N

LJ3O-22N

LJ9E-22

LJ7E

-22

LJ12E-22

LJ10E-22

LJ11E-22

PASS

REC

HTS

VO

RNE

PASS

REC

HTS

HIN

TEN

PASS

LIN

KS

HIN

TEN

PASS

LIN

KS

VOR

NE

wht

wht

blk

blk

red

red

wht

blk

red

wht

blk

red

wht

blk

red

wht

blk

red

blk

red

red

blk

LJ2H-22

LJ3G-22N

LJ2K-22LJ3L-22N

LY5E

-22

LY15

F-22

LJ1K

-22

LY15

E-22

1LY

-A

91

PC-B

OA

RD 2

1LY

D11

P600

M

D12 P6

00M

LJ6F-22N

LJ4E

-22N

LJ5G

-22

LJ4F

-22N

LJ4F

-22N

LJ4G-22N

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

21.0

6.05

HW

EA

400

-500

CO

UR

TES

Y L

IGH

T, L

Y

EA

-9B

334.

50

HO

T B

US

PP1

CO

UR

TESY

LT

CB5

5A

ST1A

T

TS2-

b-24

V-2

5S

K13

cycl

e 5H

z

5LY

P600

M

D14

BYW

56L2 red

L1 gree

n

TAST

ER 1

241.

6403

DO

OR

SWIT

CH

T1

LIG

HT

ON

23LJ

P600

M

D11

P600

M

BATT

ERY

REL

AY

K4

26.5

7.71

0

5LY

P600

M

D12

P600

M

N O

N C

C

16CG

RIG

HT

UP

LIM

IT

N O

N C

C

12CG

LEFT

UP

LIM

IT

EA-9B334.40 CABIN-DOME LIGHT


see

EA-9

B275

.20

FLA

P SY

STEM

EA-9

B243

.40

E-BO

X EA-9

B243

.10

DC

DIS

TRIB

UTI

ON

FLA

P U

P-RE

LAIS

23CG

26.7

2.03

+

M21

0-B4

MS2

10-A

5A1

K11

D

VP

LY3F

-22

LY4F

-22

LY4E-22

LY3E-22

LY2E

-22

LY1E-22

LY1F-22

LY15

E-22

LY9E-22N

LY8E-22N

LY10E-22

LY11E-22

LY6E-22

LY7E-22

LY5E

-22

D13

P600

M

(del

ay 1

00se

c af

ter b

att o

ff

(1LY

or 8

LY o

n)

(bat

t off

+ fla

p no

t up)

cycl

e 5H

z

(8LY

on)

(5LJ

on

or 1

00se

c de

lay

1LY

or 8

LY o

n)(7

LJ o

n or

100

sec

dela

y 1L

Y o

r 8LY

on)

(Pos

ition

NO

T up

)

CG24

E-22

0011

15_2

07_0

3

Mod

ul 2

0H

KCG

27E-

22

1A3

1

Die

Gül

tigke

itszu

ordn

ung

von

Ver

sion

zu

dem

jew

eilig

en F

ertig

ungs

auftr

agzu

ent

nehm

en.

Zuor

dnun

g lin

ks /

rech

ts w

ird m

it*/

* in

alle

n Fe

lder

n an

gege

ben.

04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

Ober

fläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

(on ground)

34G

A

SQU

AT

RELA

Y I

(bat

t on

+ ai

rcra

ft on

Gro

und

or+

gene

rato

r off

+ fla

p no

t up)

D16

BYW

56

D15

BYW

56

(bat

t on

+ ai

rcra

ft on

gro

und

or

(on air)D

32

1

PC-B

OA

RD 2

EA

-9B4

11.6

0

EF

16 1

K6:

1

1311

12

GEN

ERA

TOR

RELA

Y

D17

BYW

56

(gen off)

3LY

57

9 1

12

13 6

34

314

1511

48

+ fla

p no

t up)

+ fla

ps n

ot u

p)

3LY

-a

12

1LY

-A

1LY

3LY

-A

J2

LY12

F-22

LY4G

-22

LY12F-22LY13F-22

LY3F-22

LY4F-22

LY13E-22

LY12E-22

LY13F-22

10

LY12F-22LY13F-22

LY3F-22

LY4F-22

ST1

TV

PE

FFI

REW

ALL

PP6E-22

PP4E-22

EMERGENCY 243.10

PP5E-22N

PR205E-22 DC-GEN II 243.20

PP3G-22

PR205F-22

ON

OFF

ON

OFF

45

6

18PP

:2

23

1

BA

TT

:1

07.2.1.13

21

3

EMER

GEN

CY

19PP

07.1.1.13

DC-GEN-I 243.10

D:1

4

2

D:1

5

2

D:1

8

2

D:1

7

2

29CG

-DST

6A

VIO

NIK

BAY

E-BO

X

CIRC

UIT

BRE

AK

ER/S

WIT

CH P

AN

EL

see EA-9B246.10 DC-DISTRIBUTION

REL

AY

BRA

CK

ET

see E

A-9

B323

.10

GEA

R CO

NTR

OL

20

D10

BYW

56

LJ2F-22

LJ3E-22N

LY5E

-22

21

3

0017

58 2

12 0

28V

N-A

12

3

Geh

äuse

P 1

-048

0305

-0FE

4308

Pin

1635

58-2

FE43

06

Geh

äuse

B 1

-048

0303

-0FE

4307

Buch

se 1

6355

7-2

FE43

05

2LJ-

A

ST12

510

7

5LJ

OSR

AM

563

7 2

4V 1

0W (0

,42A

)1

see E

A-9

B334

.40

CABI

N-D

OM

E-LI

GH

Tse

e EA

-9B2

35.1

7 M

KR-

AU

DIO

see E

A-9

B215

.20

BLEE

D A

IR

32

2

21

13 16 24

12 9 3-

+ 232221

64

(del

ay 1

00se

c)(b

att "

off"

+ T1

"tas

t")

H3F

A-A

U

K11

21

13 16 24

12 9 3-

+ 232221

64

(del

ay 1

00se

c af

ter b

att "

off")

H3F

A-A

U

K12

Text

Text

Text

110K14

:1

342

110

K15

:1

342 C1

47u-

63V

D18

BYW

56

D19

BYW

56

D20

BYW

56

see E

A-9

B243

.40

E-BO

X

9B33

450T

HW

ÄM

-400

-09-

0120

.10.

10A

A

Scha

lters

tellu

ng A

/C o

n A

ir

22LJ

CA

BIN

LJ3E-22N

LY5H-22

LY15F-22

LJ1K-22

LJ6F-22N

LJ3E-22NLJ3E-22N

LY5H-22

LY15F-22

LJ1K-22

LJ6F-22N

LJ6H

-22N

LJ1H-22

LJ6H-22N

LJ3F

-22N

OS-LM10A-W1-847

W

+

OS-LM10A-W1-847

W

+

OS-LM10A-W1-847

W

+

OS-LM10A-W1-847

W

+

LY10E-22

LY10

F-22

CG24

F-22

CG22

E-22

NCG

22E-

22N

CG20

E-22

CG26

E-22

J

1VN

-1

D

HW

14.0

9.11

OS-LM10A-W1-847

W

+

OS-LM10A-W1-847

W

+


EF

LJ2H-22

LJ3G-22N

LJ2K-22LJ3L-22N

13LJ wht

blk red

1LY

-A

1LY

-A

LY10F-22

VV19

5VV

196

GN

D=W

OW

PP3E

-22

J37

J36

LY5E

-22

EA-9

B411

.80

AM

P

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

EA

400

-500

ICE

-LIG

HT

, LN

EA

-9B

334.

55

BA

TTE

RY

BU

S PP

2

3LN

ICE

LIG

HT

LN3E

-20N

LN1E

-20

LN2G

-20

1 2

3LN

-A3L

N-a

01.0

9.04

PB

0017

58 2

12 0

22VN

-AB

(EXT-PWR Blech)

ST2

Plug

with

Shi

eld

MS

3899

9 III

26K

F 3

2 SN

(32

X #

20)

LN2E

-20

LN2F

-20

TREN

NST

ECK

ER F

IREW

ALL

CB T

renn

steck

er

ICE

-LT

1LN

7.5A

21 3

ICE

ONOFF

2LN

07.1

.1.1

3B:

43

1A3

1

Die

Gül

tigke

itszu

ordn

ung

von

Ver

sion

zu

dem

jew

eilig

en F

ertig

ungs

auftr

agzu

ent

nehm

en.

Zuor

dnun

g lin

ks /

rech

ts w

ird m

it*/

* in

alle

n Fe

lder

n an

gege

ben.

04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

Ober

fläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

D

CIRC

UIT

BRE

AK

ER/S

WIT

CH P

AN

EL

see E

A-9

B246

.10

DC-

DIS

TRIB

UTI

ON

9B33

455T

HW

ÄM

-400

-09-

0101

.08.

10A

A

HW

14.0

9.11

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

01.0

9.04

PB

EA

400

-500

RE

CO

GN

ITIO

N L

IGH

TS,

LF

EA

-9B

334.

60

LO

AD

BU

S PP

3

3LF

01-0

7711

25-(X

X)

r. Fl

äche

LIN

KE

FLÄ

CHE

12V

N

12V

N-C

Lag

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04 03 02 01 Ver.

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od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

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Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

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maßtoleranz

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fläche


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erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

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Name

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rb.:

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Maßstab

SI.-Klasse

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ektion

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von Version zu


zu entnehmen.



04

03

02

01

Ver.Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

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EDV-Kennung:

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146

569

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1FG

8E-2

4S

1FG

11E

-RG

400

1FG

12E

-RG

400

2FG

11E

-RG

400

2FG

12E

-RG

400

FG14E-TC746

FG

15F

-TC

746

FG

15G

-TC

746

FG

15G

-TC

746

FG

19E

-22S

FG

21E

-22S

CA

15H

-22

9CA

TL

9E-2

4S

TL

9E-2

4S

SS

12E

-24S

SS

13E

-24S

SS

13F

-24S

SD

6E-2

4S

SD

13E

-22

ws

blws

bl ws

bl

ST

5-1A

SIM

ws

blws

bl ws

bl

1FG

6F-2

4S

1FG

7F-2

4S

1FG

8F-2

4S

2 7 12

3 8 13

1 6 11

ws

blws

bl429 TX+

48

429 TX-

37

ws

bl

see

EA

-9B

271.

17 A

P-S

TE

C-5

5X

P11

21

ws

bl

9B

34

26

5T

5

ws

bl ws

blws

blws

bl

ST

13-A

SIM w

sblw

sbl

ws

bl ws

bl

SH

7F-2

4S

SH

8F-2

4S

SH

7E-2

4S

SH

8E-2

4S

SH

7E-2

4S

SH

8E-2

4S14

12

11

13

15

20

SH

7F-2

4S

SH

8F-2

4S

31 2

ST

13-A

SIM

TS

3E-2

4Sor

gblw

sT

S3F

-24S

ws

org

bl

16

2QY

DR

UC

KS

CH

OT

T H

INT

EN

1RM

1E-2

4S

1RV

1E-2

4S

1RV

2E-2

4S

1RV

3E-2

4S

RM

1E-2

4R

M2E

-24

RM

3E-2

4

RM1E-24RM2E-24RM3E-24

RM

1E-2

4R

M2E

-24

RM

3E-2

4

RM

1F-2

4R

M2F

-24

RM

3F-2

4

1RV

4E-2

41R

V5E

-24

1RV

4F-2

41R

V5F

-24

1RV

4E-2

41R

V5E

-24

1RV

4F-2

41R

V5F

-24

RV

1E-2

4

RV

1F-2

4R

V1F

-24

RV

1E-2

4

CA

39E

-24S

CA

40E

-24S

CA

41E

-24S

CA

42E

-24

CA

43E

-24

CA

22E

-24S

CA

9E-2

4S

CA

19E

-24S

CA

21E

-24

CA

37F

-24S

CA

37E

-24S CA38F-24S

CA

38E

-24S

CA

38E

-24S

CA

31E

-24S

CA

32E

-24S

CA

33E

-24S

CA

34E

-24S

CA

35E

-24S

CA

36E

-24S

CA

31E

-24S

CA

32E

-24S

CA

33E

-24S

CA

34E

-24S

CA

35E

-24S

CA

36E

-24S

CA31F-24S

CA32F-24S

CA33FF-24S

CA34FF-24S

CA35F-24S

CA36F-24S

CA

37E

-24S

CA

44E

-24S

CA

45E

-24S

CA

46E

-24S

CA

47E

-24

CA

48E

-24

CA

49E

-24

CA

50E

-24S

CA

51E

-24S

CA

52E

-24S

CA

53E

-24S

CA

54E

-24S

CA

55E

-24

1VN

-4 0017

58 2

12 0

2

1VN G

1VN

AV

ION

IK B

AY

1FG

9E-R

G40

0

1FG

10F

-RG

400

16B

NC

-50-

3-7

4 X

16B

NC

-50-

3-7

16B

NC

-50-

3-7

11B

NC

-50-

3-52

11T

NC

-50-

3-11

711

TN

C-5

0-3-

117

18F

G-A

16T

NC

-50-

3-11

1

18F

G-B

11T

NC

-50-

3-11

7

18F

G

34 T

NC

-50-

0-4

HW

ÄM-400-11-04

11.10.11

A

C

FG

13E

-RG

400

FG

13G

-RG

400

11B

NC

-50-

3-52

17F

G-A

17F

G

DR

UC

KS

CH

OT

T

24B

NC

-50-

3-25

11B

NC

-50-

3-52

21F

G-A

21F

G

24B

NC

-50-

3-25

FG

13F

-RG

400

SE

ITE

NL

EIT

WE

RK ÄM-400-12-02

blw

sbl

blw

sbl

ws

ws

HW

ÄM-400-12-03

29.03.12

B

VO

R/L

OC

/GS

AN

TE

NN

A

CI-

158/

C

13F

G

13F

G-A

11B

NC

-50-

3-52

SS13E-24S

TR

EN

NS

TE

CK

ER

OV

ER

HE

AD

ÄM-400-12-08

IFD

-3

IFD

-500

0i

see

EA

-9B

342.

68 I

FD

-3

700-

0008

3-00

2

23F

G

FG

14E

-TC

746

P41

02

GROUND

BYTE FLIGHT BUS 1+

BYTE FLIGHT BUS 1-

13

12

25

ws

bl

P41

01

GROUND

7

BYTE FLIGHT BUS 2+

BYTE FLIGHT BUS 2-

14

15

ws

bl

FG

14F

-TC

746

FG15E-TC746

blws

FG

15E

-TC

746

FG

14F

-TC

746

OPTION

ws

bl blws

ws

blws

bl

SB

6F-2

2S

SB

7F-2

2S

ws bl

ws bl ws bl

ws bl

J5-2

A

SB

6E-2

2S

SB

7E-2

2S

4 9 14

15

5 10

20

ST

5-2A

SB

15F

-22S

ws bl

ws bl

SB

15E

-22S

17

18

19

97

98

13

34

ws bl ws bl

SB

6F-2

2S

SB

7F-2

2S

16

37

ws bl

SB

15F

-22S

RADAR 453 RXO+

RADAR 453 RXO-

429 TX3+

429 TX3-

429 TX5+

429 TX5-

TR

AG

FL

ÄC

HE

OV

ER

HE

AD

429 RX 1A

429 RX 1B

453 TX A

453 TX B

2 3

42

43

ws bl ws bl

PITCH/ROLL

429 A/B

8 9

ws bl

AN

TE

NN

A-R

EC

EIV

ER

3SB

-A

AR

T 2

000

see

EA

-9B

344.

12 W

EA

TH

ER

RA

DA

R

3SB

OP

TIO

N

HW

ÄM-400-12-09

15.01.13

C

SN

24E

-24

N2

9N2

N1

19

N1

10

20

SN

12E

-24

SN

24E

-24

CO

M A

NT

EN

NA

1

GP

S A

NT

EN

NA

1

1RM

-B

P1

see

EA

-9B

345.

47 D

ME

P70

41D

ME

IN

DIC

AT

OR

KD

I 57

4S

N12

E-2

4OPTION

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

EA 4

00 -

500

EA-9

B342

.66

IFD

-2,

FG

1A2

1

Die

Gül

tigke

itszu

ordn

ung

von

Vers

ion

zu

dem

jew

eilig

en F

ertig

ungs

auftr

agzu

ent

nehm

en.

Zuor

dnun

g lin

ks /

rech

ts w

ird m

it*/

* in

alle

n Fe

lder

n an

gege

ben.

04

03

02

01

Ver.Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bear

b.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

LOA

D B

US

PP3

IFD

-2-A

5FG

10A

CIR

CU

IT B

REA

KER

/SW

ITC

H P

AN

EL

IFD

-2-B

6FG

10A

2FG

1F-1

4

2FG

3F-1

4

2FG

2E-1

4

2FG

4E-1

4

2FG

1F-1

4

2FG

3F-1

4

MO

DU

L 2

Pin

Gse

e EA

-9B3

34.9

0 D

imm

ing

LG9E

-22

LG10

E-22

N

L-R +RT

L-R -RT

30

31

39

DC HDG HI

HDG RETURN

DC CRS HI

CRS RETURN

SHIELD GROUND

G/S UP +

SHIELD GROUND

G/S DOWN -

VS SIGNAL

PITCH STR SIG

ROLL STR SIG

SHIELD GROUND

SIG REF

GND

SHIELD GROUND

28

29

11

12

18

19

39

22

13

12

44

743

41

4CA

-A

ANNUN LOAD

ANNUN CLOCK

ANNUN DATA

24

25

26

40

SHIELD GROUND

ALT ENGAGE SIGNAL

ALT SEL CONTROL

SHIELD GROUND

FD LOGIC

SHIELD GROUND

G/S FLAG +

G/S FLAG -

LOC SWITCH

NAV FLAG +

NAV FLAG -

20

21

39

449

1 2 32

13

14

ROLL STEERING 429A

ROLL STEERING 429B

SHIELD GROUND

36

37

46

4CA

-B P2ws

bl ws

blws

bl ws

bl

S-TE

C 5

5X

AU

TOPI

LOT

SHIELD GROUND

45

RS-232 COM 2RX

RS-232 GND

RS-232 COM2 TX

SATE

LLIT

E W

X

MLB

-700

626

5

J1

98 21

22

ws

blB

XP-

6402

-1R

-(01

)

TRA

NSP

ON

DER

ws

blRS422 TX+

RS422 TX-

RS422 RX-

RS422 RX+

P9

OPTION

P212

2

P212

1

P210

2

P210

1

P212

1

P212

2

ws

bl ws

bl ws

bl

P1

4CA

-B P1

ws

bl ws

blws

bl

ws

bl

ws

bl ws

blws

bl ws

bl

25

426

27

22

23

30

29

8

ws

bl

#22

ws

bl

32

33

36

34

35

5 44

42

43

46

47

48

50

954

55

16

ws

blw

sbl

12

13

blws

9CA

-A9C

A-A

9CA

-A9C

A-A

see

EA-9

B344

.16

DAT

A LI

NK

BRO

AD

CAST

see

EA-9

B345

.58

TRA

NSP

ON

DER

see

EA-9

B271

.17

AP-

STEC

-55X

see

EA-9

B342

.65

IFD

-1

see

EA-9

B271

.17

AP-

STEC

-55X

AIS

240

-35

A/P

REL

AY

K1C-NC

K1D-NC

K2D-NC

K2C-NC

K2B-NC

K1A-NC

K3D-NC

K3B-NC

K2A-NC

K3A-NC

K4B-NC

K4D-NC

K4C-NC

K4A-NC

K2D-W

K2C-W

K1C-W

K1D-W

K2B-W

K1A-W

K3D-W

K4D-W

K4C-W

K4A-W

K3B-W

K2A-W

K3A-W

K4B-W

SIGNAL GROUND

40

ws

blws

blws

org

bl

ws

org

bl

P214

1

P214

2

2 X

11B

NC-

50-3

-52

see

EA-9

B342

.65

IFD

-1

SIGNAL RS-232 TX2

SIGNAL RS-232 GND

SIGNAL RS-232 RX2

5 626

TS4F

-24S

SHA

DIN

MIN

IFLO

W L

MLX

-770

J1-A

OPTION

see

EA-9

B344

.17

DAT

A LI

NK

2 W

AY

ws

org

bl

ws

org

bl

DAT

A L

INK

2 W

AY

Px

ws

ws

bl

2FG

1E-1

4

2FG

3E-1

4C:

42

D:3

3

see

EA-9

B246

.10

DC-

DIS

TRIB

UTI

ON

AVIO

NIC

S BU

S PP

5

72

28V RELAY POWER

see

EA-9

B271

.17

AP-

STEC

-55X

96RS-232 TX

RS-232 RX

9120

41T-

Dbl

TS4E

-24S

ws

blse

e EA

-9B3

42.6

5 IF

D-1

see

EA-9

B731

.40

FUEL

FLO

W

QY

4E-2

4S

QY

4F-2

4S

QY

4F-2

4S

1FG

11E-

RG40

0

1FG

12E-

RG40

0

2FG

11E-

RG40

0

2FG

12E-

RG40

0

9CA

TL10

E-24

S

TL10

E-24

S

ws

bl429 TX+

48

429 TX-

37

ws

bl

see

EA-9

B271

.17

AP-

STEC

-55X

9B34

266T

CA

15H

-22

30

29

28V POWER BUS A


DIM BUS COMMON

BEZEL DIMMING

28V POWER BUS B


CHANNEL ID 2

GROUND

CHANNEL ID 1

GROUND

A1

A2

20

7 A1

A2

6 13

5 12

DISCRETE OUT

DISCRETE OUT 0+

DISCRETE OUT 1

DISCRETE OUT 0-

DISCRETE OUT 2

GROUND

GROUND

DISCRETE OUT 1+

ANALOG OUT 0

DISCRETE OUT 1-

ANALOG GROUND

429 TX0+

ANALOG OUT 2

429 TX0+

ANALOG OUT 3

GROUND

ANALOG REF

ANALOG OUT 5

ANALOG OUT 6

2 3 4 15

10

26

12

13

27

19

40

25

60

39

20

MAG RS422 TX+

41

MAG RS422 TX-

10

MAG RS422 RX-

31

MAG RS422 RX+

14

28V MAG POWER +

28V MAG POWER -

MICROPHONE #1

TX KEY #1

HEADPHONE #2

HEADPHONE #2 LO

HEADPHONE #1 LO

HEADPHONE #1

HEADPHONE #3

HEADPHONE #3 LO

11

5 13

DISCRETE IN 3

ANALOG IN 1

44

ANALOG IN 0

DISCRETE IN 0

DISCRETE IN 2

43

DISCRETE IN 1

28

2

429 RX0+

15

429 RX0-

1

23

14

41

4

40

17

22

DISCRETE IN 7

7

DISCRETE IN 6

8

DISCRETE OUT 10

38

51

37

72

21

USB VCC +5V

USB GROUND(DRAIN)

USB +

USB -

GROUND

BYTE FLIGHT BUS 1+

RS232 RX1

BYTE FLIGHT BUS 1-

RS232 COMMON

GROUND

91

10

96

23

11

7

24

13

12

25

BYTE FLIGHT BUS 2+

BYTE FLIGHT BUS 2-

14

CFG DISCRETE IN 0

15

DISCRETE OUT 8

CFG DISCRETE IN 1

19

CFG DISCRETE IN 2

61

64

22

TX0-RX0 COMMON

RS422-232 TX0

RS422-232 RX0

46

66

24

TX2-RX2 COMMON

62

RS422-232 TX2

63

RS422-232 RX2

82

76

78

57

36

15

SHIELD GROUND

ARINC 429 RX5+

ARINC 429 RX5-

ARINC 429 TX4-

ARINC 429 TX4+

25

486

RS232 RX0

85

RS232 TX0

RS422 RX3-

TX0-RX0 COMMON

RS422 RX3+

89

RS422 TX3-

88

RS422 TX3+

87

38

ARINC 429 RX7+

17

ARINC 429 RX7-

80

ARINC 429 TX6-

59

ARINC 429 TX6+

GF D C

700-

0001

1-()

MA

G/O

AT II

H B

MAG RS422 TX+

MAG RS422 TX-

MAG RS422 RX-

MAG RS422 RX+

28V MAG POWER +

28V MAG POWER -

P230

01

TAS-

610

TRA

FFIC

AD

VIS

ORY

SY

STEM

P1w

sbl

429 RX2+

429 RX2-

12

13

5SHIELD GROUND

RS422-232 TX3

20

RS422-232 RX3

22

RS232 COMMON

5TAS MUTE

SD11

E-22

15 30 19 20 21 2213 14

COM 2 MIK AUDIO OUT

COM 2 MIK KEY OUT

NV #2 RX HI

NV #2 RX LO

COM #12RX LO

COM #2 RX HI

MONITOR #2 RX HI

MONITOR #2 RX LO

COM SPLIT SECECTED

ACTIVE COM SECECTED

36

37

38

OUTER MARKER

MIDDLE MARKER

INNER MARKER

AU

DIO

/MA

RK

ERPM

A-8

000B

1RM

-A

IFD

-3

IFD

-500

0i

12

13

14

RS232 TX2

RS232 RX2

RS232 COMMON

29

30

429 RX2+

429 RX2-

WEA

THER

DET

ECTI

ON

TWX

-670

P1

ws

bl

J214

4

P210

1

P210

2

IFD

-1

IFD

-500

0i

P110

2

P110

1

GROUND

BYTE FLIGHT BUS 1+

BYTE FLIGHT BUS 1-

GROUND

713

12

25

BYTE FLIGHT BUS 2+

BYTE FLIGHT BUS 2-

14

15

ws

bl

ws

bl

ws

bl

P212

2

P212

2P2

121

J214

4

1RM

-B

20

COM SWAP

21

25

24

37

38

P112

2

DISCRETE IN 7

DISCRETE IN 6

DISCRETE OUT 10

82

63

62

P112

1

CFG DISCRETE 0

CFG DISCRETE 1

CFG DISCRETE 2

P212

1

see

EA-9

B342

.68

IFD

-3

see

EA-9

B342

.65

IFD

-1

see

EA-9

B344

.14

WEA

THER

DET

ECTI

ON

see

EA-9

B344

.15

TRA

FFIC

AD

VIS

ORY

see

EA-9

B235

.17

MK

R-A

UD

IO

ws

org

blw

s

org

bl

ws

org

bl

ws

org

bl

bl

ws

bl

MA

G-3

00IF

D-5

000i

700-

0008

3-()

700-

0008

3-00

2

700-

0008

3-()

VOR / LOC ANTENNA

GS ANTENNA

11FG

-A

11BN

C-50

-3-5

2

DM

C70

-4P2

145

COM ANTENNA

11FG

12FG

-A

11TN

C-50

-3-1

17

CI 4

28-2

00P2

131

GPS ANTENNA

12FG

21

KD

I 574

DM

E IN

DIC

ATO

RP7

041

1 MC

1 MD

see

EA-9

B345

.47

DM

E

1 ME

1 MA

DISCRETE OUT 3

DISCRETE OUT 4

DISCRETE OUT 5

DISCRETE OUT 6

DISCRETE OUT 9

DISCRETE OUT 11

DISCRETE OUT 12

DISCRETE OUT 13

DISCRETE OUT 14

5 6 16

17

20

31

32

33

34

OPTION

OPTION

Select 2X5 Code

NAV 1 COMMON

48

38

20

37

41

42

43

44

39

35

RS232 RX2

RS232 TX2

TX0-RX0 COMMON

65

23

67

RS232 TX1

44

7FG

8FG

3FG

23FG

ws

blw

sbl

ws

blw

sbl

ws

blw

sbl

2FG

6E-2

4S

2FG

7E-2

4S

2FG

8E-2

4S

2FG

9E-R

G40

0

2FG

10E-

RG40

0

FG14E-TC746

FG15

E-TC

746

FG15

F-TC

746

SS14

E-24

S

SS15

E-24

S

SS15

F-24

S

SD8E

-24S

SD11

E-22

ws

blws

bl ws

bl

ws

bl ws

bl ws

blw

sblw

sbl w

sbl

ST5-

1ASI

M

ws

blws

bl ws

bl

16

17

18

10

5 15

4 9 14

2FG

6F-2

4S

2FG

7F-2

4S

2FG

8F-2

4S

OPTION

10

54 9 19

ST13

-ASI

M ws

blws

blw

sbl w

sbl

SH3F

-24S

SH4F

-24S

18

SH3E

-24S

SH4E

-24S

SH3E

-24S

SH4E

-24S

86 7

ST13

-ASI

M

TS4E

-24S

org

blws

TS4F

-24S

ws

org

bl

17

2QY

DRU

CKSC

HO

TT H

INTE

N

CA39

E-24

S

CA40

E-24

S

CA41

E-24

S

CA42

E-24

CA43

E-24

CA22

E-24

S

CA9E

-24S

CA19

E-24

S

CA21

E-24

CA56

E-24

CA57

E-24

CA58

E-24

CA59

E-24

SCA

60E-

24S

CA61

E-24

SCA

62E-

24S

CA63

E-24

S

CA64

E-24

S

CA65

E-24

S

CA66

E-24

S

CA37

E-24

S

CA37

F-24

SCA

37F-

24S

CA31

F-24

SCA

32F-

24S

CA33

F-24

SCA

34F-

24S

CA35

F-24

SCA

36F-

24S

CA31

F-24

SCA

32F-

24S

CA33

F-24

SCA

34F-

24S

CA35

F-24

SCA

36F-

24S

CA31E-24SCA32E-24SCA33E-24SCA34E-24SCA35E-24SCA36E-24S

CA38

F-24

S

CA38E-24S

CA38

F-24

S

RM1F

-24

RM2F

-24

RM3F

-24

1RV

4E-2

41R

V5E

-24

2RM

1E-2

4S

2RV

1E-2

4S

2RV

2E-2

4S

RV1E

-24

RV1F

-24

1RV

4E-2

41R

V5E

-24

1RV

4E-2

41R

V5E

-24

RV1E

-24

RV1F

-24

1RV

4E-2

41R

V5E

-24

RM1F

-24

RM2F

-24

RM3F

-24

RM1E

-24

RM2E

-24

RM3E

-24

RM1E-24RM2E-24RM3E-24

HW

24.0

2.11

VO

R/L

OC

/GS

AN

TEN

NA

FG13

E-RG

400

CI-

158/

C

13FG

FG13

G-R

G40

0se

e EA

-9B3

42.6

5 IF

D-1

1VN

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58 2

12 0

2

1VN D

1VN

SN13

E-24

SN14

E-24

SN15

E-24

SN16

E-24

SN17

E-24

SN18

E-24

SN19

E-24

SN20

E-24

SN21

E-24

16TN

C-50

-3-1

11

20FG

-A

11TN

C-50

-3-1

17

20FG

-B20

FGAV

ION

IC B

AY

2FG

10F-

RG40

0

24BN

C-50

-3-2

5

19FG

11BN

C-50

-3-5

2

19FG

-AD

RU

CK

SCH

OTT

2FG

9F-R

G40

0

4 X

16B

NC

-50-

3-7

11B

NC

-50-

3-52

34TN

C-50

-0-4

11TN

C-5

0-3-

117

16FG

-A16

FG-B

16FG

-C

NAV

CO

UPL

ER

HIN

TER

I-B

RET

T

16FG

CI 1

125

16FG

-D

16FG

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16B

NC

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3-7

13FG

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11B

NC

-50-

3-52

17FG

-A17

FG

DR

UC

KSC

HO

TT

24B

NC

-50-

3-25

11B

NC

-50-

3-52

HW

ÄM

-400

-11-

0411

.10.

11A

C

11B

NC

-50-

3-52

21FG

-A21

FG

24B

NC

-50-

3-25

FG13

F-RG

400

SEIT

ENLE

ITW

ERK

ÄM

-400

-12-

02H

WÄ

M-4

00-1

2-03

02.0

4.12

B

SN13

E-24

SN14

E-24

SN15

E-24

SN16

E-24

SN17

E-24

SN18

E-24

SN19

E-24

SN20

E-24

SN21

E-24

TREN

NST

ECK

ER F

LÜG

ELN

ASE

HW

ÄM

-400

-12-

0812

.01.

13C

IFD

-2

14

1BYTE FLIGHT BUS +

BYTE FLIGHT BUS -

KEY

BO

AR

D

AC

D-2

15J3

010

see

EA-9

B342

.67

KEY

BOA

RD

ws

bl70

0-00

150-

()

10FG

FG15

F-TC

746

P410

2

GROUND

BYTE FLIGHT BUS 1+

BYTE FLIGHT BUS 1-

13

12

25

ws

bl

ws

bl

P410

1

GROUND

7

BYTE FLIGHT BUS 2+

BYTE FLIGHT BUS 2-

14

15

ws

bl

FG14

F-TC

746

FG15

G-T

C746

FG14

E-TC

746

FG15E-TC746

blws

OPTION

.1 MA

.1 ME

.1 MC

.1 MD

.01 MC

ws

bl blws

FG14

F-TC

746

FG15G-TC746

25.0

6.13

HW

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

EA

40

0 -

50

0

EA

-9B

342.6

7

01,08,10

HW

KE

YP

AD

,

FG

1A2

1

Die

Gül

tigk

eits

zuor

dnun

gvo

n V

ersi

on z

u

dem

jew

eili

gen

Fer

tigu

ngsa

uftr

agzu

ent

nehm

en.

Zuo

rdnu

ng l

inks

/ r

echt

s w

ird

mit

*/*

in a

llen

Fel

dern

ang

egeb

en.

04

03

02

01

Ver.Bezeichnung

Nr.

:Ä

nder

ung/

Mod

. Nr.

:D

atum

Nam

e

Let

zte

Bea

rbei

tung

:Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Sch

war

ze H

eide

21

4656

9 H

ünxe

, Ger

man

y

Gep

r.:

Flu

gzeu

gbau

reih

eis

t de

r B

auak

te b

zw.

EM

ER

GE

NC

Y B

US

P

P4

KE

YP

AD

9FG

1A

CIR

CU

IT B

RE

AK

ER

/SW

ITC

H P

AN

EL

GROUND

BYTE FLIGHT BUS 1+

BYTE FLIGHT BUS 1-

GROUND

7 13

12

25

BYTE FLIGHT BUS 2+

BYTE FLIGHT BUS 2-

14

15

KE

YB

OA

RD

AC

D-2

15J3

010

P41

01

P41

02

IFD

-2 I FD

-500

0i

P11

02

GROUND

7

BYTE FLIGHT BUS 2+

BYTE FLIGHT BUS 2-

14

15

ws

bl

ws

bl

ws

bl

see

EA

-9B

342.

65 I

FD

-1

700-

0015

0-()

700-

0008

3-()

FG

16E

-20

see

EA

-9B

246.

10 D

C-D

IST

RIB

UT

ION

The

rmax

TC

746,

120

Ohm

The

rmax

TC

746,

120

Ohm

USB VCC +5V

USB GROUND(DRAIN)

USB +

USB -

GROUND

BYTE FLIGHT BUS 1+

BYTE FLIGHT BUS 1-

10

23

11

24

13

12

25

IFD

-1

9 10

21

22

14

1

USB VCC +5V

USB GROUND (DRAIN)

USB +

USB -

BYTE FLIGHT BUS +

BYTE FLIGHT BUS -

P11

01

ws

ws

bl

IFD

-500

0i

The

rmax

TC

746,

120

Ohm

see

EA

-9B

342.

66 I

FD

-2

7 20

POWER GROUND # 1FD

POWER GROUND # 2FD

6 8

28V IN #1FD

28V IN # 2FD

700-

0008

3-00

2

A:1

12

10F

G

3FG

24F

G

FG

16F

-20

FG

17E

-20N

FG

18E

-20N

FG

14E

-TC

746

FG

15E

-TC

746

FG

14F

-TC

746

FG

15F

-TC

746

FG

14F

-TC

746

FG

15E

-TC

746

FG

16F

-20

9B

34

26

7T

1

1

SP

LIC

E N

O F

AR

TH

ER

TH

EN

2 I

NC

H (

50m

m)

FR

OM

PIN

S

1VN

-400

1758

212

02

EF

FG

19E

-22S

FG

21E

-22S

blw

sbl

blw

sbl

ws

ws

FG

19E

-22S

FG

21E

-22S

HW

ÄM-400-12-02

12.03.12

A

BHW

ÄM-400-12-08

16.01.13

B

GROUND

BYTE FLIGHT BUS 1+

BYTE FLIGHT BUS 1-

GROUND

713

12

25

BYTE FLIGHT BUS 2+

BYTE FLIGHT BUS 2-

14

15

P21

01

P21

02

IFD

-3IFD

-500

0i

ws

bl

ws

bl

see

EA

-9B

342.

68 I

FD

-3

700-

0008

3-() 7F

G

FG

14E

-TC

746

FG

15F

-TC

746

ws

blws

bl

FG

15G

-TC

746

FG

15G

-TC

746

1

ws

bl ws

bl

OPTION

1

23F

G

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

EA

40

0 -

50

0

EA

-9B

342.6

8

15.01.13

HW

IFD

-3, F

G

1A3

1

Die

Gül

tigk

eits

zuor

dnun

gvo

n V

ersi

on z

u

dem

jew

eili

gen

Fer

tigu

ngsa

uftr

agzu

ent

nehm

en.

Zuo

rdnu

ng l

inks

/ r

echt

s w

ird

mit

*/*

in a

llen

Fel

dern

ang

egeb

en.

04

03

02

01

Ver.Bezeichnung

Nr.

:Ä

nder

ung/

Mod

. Nr.

:D

atum

Nam

e

Let

zte

Bea

rbei

tung

:Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Sch

war

ze H

eide

21

4656

9 H

ünxe

, Ger

man

y

Gep

r.:

Flu

gzeu

gbau

reih

eis

t de

r B

auak

te b

zw.

GROUND

BYTE FLIGHT BUS 1+

BYTE FLIGHT BUS 1-

GROUND

713

12

25

BYTE FLIGHT BUS 2+

BYTE FLIGHT BUS 2-

14

15

KE

YB

OA

RD

AC

D-2

15

P41

01

P41

02

IFD

-2IFD

-500

0i

P11

02

GROUND

7

BYTE FLIGHT BUS 2+

BYTE FLIGHT BUS 2-

14

15

ws

bl

ws

bl

ws

bl

see

EA

-9B

342.

65 I

FD

-1

700-

0015

0-()

700-

0008

3-()

The

rmax

TC

746,

120

Ohm

The

rmax

TC

746,

120

Ohm

GROUND

BYTE FLIGHT BUS 1+

BYTE FLIGHT BUS 1-

13

12

25

IFD

-1

P11

01

ws

bl

IFD

-500

0i

see

EA

-9B

342.

66 I

FD

-2

700-

0008

3-00

2

10F

G

3FG

23F

G

FG

14E

-TC

746

FG

15E

-TC

746

FG

14F

-TC

746

FG

15F

-TC

746

FG

14F

-TC

746

FG

15E

-TC

746

9B

34

26

8T

GROUND

BYTE FLIGHT BUS 1+

BYTE FLIGHT BUS 1-

GROUND

7 13

12

25

BYTE FLIGHT BUS 2+

BYTE FLIGHT BUS 2-

14

15

P21

01

P21

02

IFD

-3 I FD

-500

0i

ws

bl

ws

bl

700-

0008

3-()7F

G

FG

14E

-TC

746

FG

15F

-TC

746

ws

blws

bl ws

bl

FG

15G

-TC

746

FG

15G

-TC

746

LO

AD

BU

S P

P3

IFD

-3

22F

G

5A

CIR

CU

IT B

RE

AK

ER

/SW

ITC

H P

AN

EL

3FG

1F-2

03F

G1E

-20

B:6

2

see

EA

-9B

246.

10 D

C-D

IST

RIB

UT

ION

see

EA

-9B

342.

67 K

EY

PAD

BYTE FLIGHT BUS +

BYTE FLIGHT BUS -

14

1

J301

0

ws

bl

3FG

1F-2

0

3FG

2E-2

0

5LH

-A P

in 3

3se

e E

A-9

B33

4.90

Dim

min

gL

G14

E-2

2

LG

18E

-22N

P41

02

P41

01

28V POWER BUS A


DIM BUS COMMON

BEZEL DIMMING

28V POWER BUS B


CHANNEL ID 0

GROUND

CHANNEL ID 2

GROUND

A1

A2

20

7 A1

A2

4 11

6 13

USB VCC +5V

USB GROUND(DRAIN)

USB +

USB -

10

23

11

24

1VN

-300

1758

212

02

1VN B

OPTION

1

1S

PL

ICE

NO

FA

RT

HE

R T

HE

N 2

IN

CH

(50

mm

) F

RO

M P

INS

1

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

EA

-9B

342.

73

EA

400

-500

AT

TIT

UD

E G

YR

O,

FM

01.0

9.10

HW

2FM

-A

MS3

112E

8-4S

C B A D

+10 to 32VDC POWER

LIGHTING (+)

POWER/LIGHTING RETURN

NC

EM

ER

GE

NC

Y B

US

PP4

FM2E

-22N

ATT

ITU

DE

GY

RO

1VN

-200

1758

212

02

FM2E-22N

4200

-11

2FM

FM1E

-22

FM1F

-22

STBY

-GY

RO

1FM 2A

C:7

1

1A3

1

Die

Gül

tigke

itszu

ordn

ung

von

Ver

sion

zu

dem

jew

eilig

en F

ertig

ungs

auftr

agzu

ent

nehm

en.

Zuor

dnun

g lin

ks /

rech

ts w

ird m

it*/

* in

alle

n Fe

lder

n an

gege

ben.

04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

Ober

fläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

CIRC

UIT

BRE

AK

ER/S

WIT

CH P

AN

EL

see E

A-9

B246

.10

DC-

DIS

TRIB

UTI

ON

FM1F

-22

see E

A-9

B334

.90

DIM

MIN

G S

YST

EMLG

13E-

22

C

28V

LIG

HTI

NG

9B34

273T

16.0

9.11

HW

Mai

nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

DD

CC

BB

AA

4SB

13.09.04

PB

EA

40

0-5

00

WE

AT

HE

R R

AD

AR

, S

B

EA

-9B

344.1

2

+ 2

8 V

DC

GN

DG

ND

Str

ut S

wit

ch

429

RX

1A

429

RX

1B

453

TX

A45

3 T

X B

R/T

ON

#1

Mod

ule

GN

D O

UT

Con

fig

/ R

T D

ata

InR

T /

Con

fig

Chi

p S

elec

t 1

RT

/ C

onfi

g C

hip

Sel

ect

2R

T /

Con

fig

Clo

ck O

UT

RT

/ C

onfi

g D

ata

OU

TM

odul

e +

5 V

DC

OU

T

CO

NF

IG M

OD

UL

Pow

er G

ND

Con

fig

to A

ir D

ata

AR

T t

o C

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hip

sele

ct 1

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o C

onfi

g C

hip

sele

ct 2

AR

T t

o C

onfi

g C

lock

AR

T t

o C

onfi

g D

ata

+ 5

VD

C

TT

L1

(R/T

ON

)

RA

DA

R 4

53 R

XO

+R

AD

AR

453

RX

O-

429

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3+42

9 T

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P50

01

4SB

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34 35 36 37 1 32 4 5 31 2 3 42 43 44 45 464748 49 50 1 24 56 89

9

97 9813 34

ws

blw

sbl

TR

AG

FL

ÄC

HE

LIN

KS

ws

bl

see

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323.

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EA

R C

ON

TR

OL

mit

Kab

elös

en a

m B

litz

schu

tz

ws

bl

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AC

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2S

SB

7E-2

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SB

14E

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13E

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12E

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2

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r

TR

AG

FL

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OV

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BA

CK

SH

EL

L

BA

CK

SH

EL

L

WX

1SB

5A

1A3

1


von Version zu


zu entnehmen.



04030201

Ver.Bezeichnung

Nr.:

Änderung/Mod. Nr.:

Datum

Name

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Sch

warz

e H

eide

21

46569 H

ünxe

, G

erm

any

Gepr.:

Flugzeugbaureihe


9B34

412T

SB

6F-2

2S

SB

7F-2

2S

SB

1F-2

0S

B1J

-20

ws

blw

sbl

CIR

CU

IT B

RE

AK

ER

/SW

ITC

H P

AN

EL

s ee

EA

-9B

246.

10 D

C-D

IST

RIB

UT

ION

ÄM-400-12-09

HW

15.01.13

Ä

A

AV

ION

ICS

BU

S P

P5

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nten

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Man

ual E

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A 5

00

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91

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Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bear

b.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

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de 2

146

569

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xe, G

erm

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ben.

04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bear

b.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

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von Version zu


zu entnehmen.



04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gepr.:

Flugzeugbaureihe


D.C. POWER INPUT

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10

11

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12

13

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15

16

17

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22

23

20

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04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bear

b.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

D.C. INPUT POWER

D.C. INPUT POWER

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04

03

02

01

Ver.Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

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Man

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von Version zu


zu entnehmen.



04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gepr.:

Flugzeugbaureihe


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Mod

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atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

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Mai

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Man

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91

N°

0B70

2-TR

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2013

1212

Maintenance Manual EXTRA 500 Ch. 91 N° 0B702-TR-03-20131212

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22

33

44

55

66

77

88

DD

CC

BB

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1-34

1-9

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2-18

2-21

2-9

2-10

2-7

2-23

2-22

2-20

2-19

2-17

2-5

2-4

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2-15

2-3

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2-11

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3-2

3-6

3-7

3-5

3-9

3-8

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1-11

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1-29

1-30

1-26

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1-37

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1-15

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1-21

1-22

1-23

1-24

1-25

1-26

1-27

1-28

1-29

1-30

1-31

1-20

1-32

1-14

1-16

1-17

1-18

1-19

1-34

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1 20 2 21 3 22 4 23 5 24 6 25 7 26 8 27 9 28 10 29 11 30 12 31 13 32 14 33 15 34 16 35 17 36 18 37 19

J1 DB

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2-2

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2-10

2-11

2-12

2-13

2-15

2-21

2-22

2-23

2-24

2-25

2-20

2-14

2-16

2-17

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3-1

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09.09.04

PB

EA

40

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B D

IMM

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EA

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410.3

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4


von Version zu


zu entnehmen.



04

03

02

01

Ver.Bezeichnung

Nr.

:Ä

nder

ung/

Mod

. Nr.

:D

atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

Oberfläche


EDV-Kennung:

auf

Blatt von

Sch

war

ze H

eide

21

4656

9 H

ünxe

, Ger

man

y

Gepr.:

Flugzeugbaureihe


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Mai

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Man

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XTR

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91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

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04030201

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r.:D

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Nam

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Letz

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Datum

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Maßstab

SI.-Klasse

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1 14 2 15 3 16 4 17 5 18 6 19 7 20 8 21 9 22 10 23 11 24 12 25 13

259-

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2

3

4

5

6

7

8

9

10

11

12

13

14

15

163518 19

33

21

22

23

24

25

26

27

28

29

30

31

20

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Man

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Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

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04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

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g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

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Datum

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rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Projektion

Freimaßtoleranz

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EDV-Kennung:

auf

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Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

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R21

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R23

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R11

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R13

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22

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nten

ance

Man

ual E

XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

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Die

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lder

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04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

Ober

fläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

zw.

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400

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2

EA

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60

HW

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3

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n H

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D2

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56

D4

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56

D5

BY

W56

D7

BY

W56

+28V

K1

K2

K3

K4

K5

K6

K7

15/12

14

13

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TCAD

161

K1:

1 REL

MT4

465

387

161

K2:

1

REL

MT4

131112

14910

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K3:

1

REL

MT4

131112

14910

161

K4:

1

REL

MT4

14910

161

K6:

1 REL

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465

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2-11

2-12

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1-9

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1-13

1-15

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1-1

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1-3

1-4

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A 5

00

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91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

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ks /

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lder

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ben.

04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

Ober

fläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

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left

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Mai

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Man

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XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

77

88

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1 2 34 5 67 8 9

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sion

zu

dem

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ks /

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lder

n an

gege

ben.

04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letz

te B

earb

eitu

ng:

Datum

Name

Bea

rb.:

Gep

r.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

Ober

fläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gep

r.:

Flug

zeug

baur

eihe

ist d

er B

auak

te b

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AK

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see E

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Mai

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Man

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XTR

A 5

00

Ch.

91

N°

0B70

2-TR

-03-

2013

1212

11

22

33

44

55

66

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von Version zu


zu entnehmen.



04 03 02 01 Ver.

Bezeichnung

Nr.:

Änd

erun

g/M

od. N

r.:D

atum

Nam

e

Letzte Bearbeitung:

Datum

Name

Bearb.:

Gepr.:

Maßstab

SI.-Klasse

Oberflächenschutz

Proj

ektion

Frei

maßtoleranz

Ober

fläche


EDV-Kennung:

auf

Blatt von

Schw

arze

Hei

de 2

146

569

Hün

xe, G

erm

any

Gepr.:

Flugzeugbaureihe


CIRC

UIT

BRE

AK

ER/S

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CH P

AN

EL

24Annunciator Panel EA-9B315.80

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NU

NC

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R BO

ARD

EA

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11.7

0

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NU

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291-

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