SUPPLEMENTAL AIRPLANE MAINTENANCE

Transcription

System O03
DA 42 NG
Retrofit Installation
Supplemental AMM
of Austro Engine E4-B
SUPPLEMENTAL AIRPLANE MAINTENANCE MANUAL
DA 42 NG
RETROFIT INSTALLATION OF
AUSTRO ENGINE E4-B
This supplemental AMM is approved in conjunction with the Optional Design Change Advisory
OÄM 42-171 and OÄM 42-176 and is valid in conjunction with the basic DA 42 NG Airplane
Maintenance Manual (AMM), Doc. No. 7.02.15.
The limitations and information contained herein either supplement or, in the case of conflict,
override those in the AMM.
Doc. No.
:
7.02.15-O03
Date of Issue
:
01-Jun-2009
Design Change Advisory :
OÄM 42-171 and
OÄM 42-176
The technical information contained in this document has been approved under the authority of
DOA No. EASA.21J.052.
DIAMOND AIRCRAFT INDUSTRIES GMBH
N.A. OTTO-STR. 5
A-2700 WIENER NEUSTADT
AUSTRIA
System O03
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Supplemental AMM
Intentionally left blank.
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COVER
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TABLE OF CONTENTS
CHAPTER 01 – INTRODUCTION ...........................................................................................1
1.
General................................................................................................................................... 1
CHAPTER 03 – GENERAL DESCRIPTION OF THE AIRPLANE ..........................................1
3.
Equipment Data ..................................................................................................................... 1
CHAPTER 05 – TIME LIMITS AND MAINTENANCE CHECKS .............................................1
Section 05-20 – Scheduled Maintenance Checks............................................................1
Maintenance Practices – Maintenance Checklist DA 42 NG...........................................1
4.
Maintenance Checklist Zones................................................................................................ 1
7.
Maintenance Check Flight Report.......................................................................................... 2
CHAPTER 11 – PLACARDS AND MARKINGS......................................................................1
Section 11-20 – Exterior Placards and Markings.............................................................1
1.
General................................................................................................................................... 1
Section 11-30 – Interior Placards and Markings ..............................................................1
2.
Description ............................................................................................................................. 1
CHAPTER 22 – AUTO FLIGHT...............................................................................................1
Section 22-11 – KAP 140 Autopilot ...................................................................................1
1.
General................................................................................................................................... 1
2.
Description ............................................................................................................................. 1
Maintenance Practices ...................................................................................................201
1.
General............................................................................................................................... 201
2.
Remove/Install the Flight Control Computer ...................................................................... 201
3.
Remove/Install the KCM 100 Configuration Module.......................................................... 203
5.
Remove/Install the Roll Servo............................................................................................ 205
6.
Remove/Install the Roll Servo Clutch ................................................................................ 206
7.
Remove/Install the Pitch Servo.......................................................................................... 208
8.
Remove/Install the Pitch Servo Clutch............................................................................... 209
9.
Remove/Install the Pitch Trim Servo.................................................................................. 211
10.
Remove/Install the Pitch Trim Servo Clutch ...................................................................... 212
11.
Adjust the Bridle Cable Tension......................................................................................... 213
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12.
Adjust the Servo Clutch Torques ...................................................................................... 214
13.
Mechanical Test of the Autopilot System.......................................................................... 215
CHAPTER 31 – INDICATING SYSTEMS................................................................................1
Section 31-10 – Instrument and Control Panels ..............................................................1
2.
Instrument Panel Description ................................................................................................. 1
CHAPTER 52 – DOORS..........................................................................................................1
Section 52-10 – Canopy and Passenger Door .................................................................1
2.
Canopy Description and Operation........................................................................................ 1
3.
Passenger Door Description and Operation .......................................................................... 3
CHAPTER 92 – WIRING DIAGRAMS .....................................................................................1
1.
General................................................................................................................................... 1
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CONTENTS
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CHAPTER 01 – INTRODUCTION
1.
General
This Supplemental AMM supplies the information necessary to do the maintenance of a DA 42 NG
previously manufactured as a DA 42 with subsequent installation of Austro Engine E4-B engines.
The information contained in this Supplemental AMM is to be used in conjunction with the complete
DA 42 NG AMM, Doc. No. 7.02.15.
Further, use the following manuals in conjunction with the Airplane Maintenance Manual, and the
related Service Bulletins (if the KAP 140 A/P is installed):
− The Honeywell Flightline Maintenance Manual Bendix/King KAP 140 Flight Control System,
Manual Number 006-15574-0002.
− The Honeywell Installation Manual Bendix/King KAP 140 Flight Control System, Manual
Number 006-00991-0006.
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CHAPTER 03 – GENERAL DESCRIPTION OF THE AIRPLANE
3.
Equipment Data
In any case, the parts must have exactly those part numbers shown in the Equipment List in
Chapter 6 of the
− Airplane Flight Manual, Doc. No. 7.01.15-E, latest revision, or
− Airplane Flight Manual Supplement O03, Doc. No. 7.01.15-E-O03, latest revision, or
− Airplane Flight Manual Supplement A13, Doc. No. 7.01.15-E-A13, latest revision (if the KAP 140
A/P is installed).
ATA
Chapter
22
Equipment/System
Manufacturer/Address
Autopilot System
Honeywell International Inc.
(if KAP 140 A/P is installed):
One Technology Center
Direct
Shipping
Approved
yes
23500 West 105th Street
Olathe, Kansas 66061
USA
Tel: (913) 712-0400
Fax: (913) 791-1302
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CHAPTER 05 – TIME LIMITS AND MAINTENANCE CHECKS
Section 05-20 – Scheduled Maintenance Checks
Maintenance Practices – Maintenance Checklist DA 42 NG
4.
Maintenance Checklist Zones
C.
Cabin
(3) Flight Control System in Cabin
Interval
Inspection Items, Flight Control System in Cabin
Note:
100 200 1000 2000 Time
Initials
The mechanical check of the KAP 140 autopilot system (if installed) is not
mandatory. It is however recommended to do this check at the times shown
below.
14.
Do a mechanical check of the KAP 140 autopilot system
(if installed).
X
X
1yr.
Refer to Section 22-11 of this Supplemental AMM.
(5) Miscellaneous Items in Cabin
Inspection Items, Cabin, Miscellaneous
4.
If the sun visors (OÄM 42-101 or OÄM 42-142) are
installed:
100 200 1000 2000 Time
X
X
Initials
X
− Check for obvious damage.
− Check press-studs for lack of retention force.
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7.
Maintenance Check Flight Report
MAINTENANCE CHECK FLIGHT
DA 42 NG
(See Maintenance Checklist for Applicability)
Supplemental O03 Page
AIRCRAFT
Registration:
Pilot:
Airdrome:
Date:
Take-Off:
Landing:
Findings
Functional Check, Flight Behavior
N/A
NO
YES
ON GROUND, ENGINES ON
If KAP 140 A/P is installed:
Altimeters (G1000 and backup), autopilot: QNH adjustment.
CRUISE (in accordance with AFM)
Autopilot ( if KAP 140 A/P is installed):
‒ Wings level mode.
‒ HDG mode.
‒ NAV mode (if required).
‒ ALT / VS preselect and hold.
‒ CWS (control wheel steering) button.
‒ Disconnect (red button).
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CHAPTER 11 – PLACARDS AND MARKINGS
Section 11-20 – Exterior Placards and Markings
1.
General
Canopy/Door Operation Placards if MÄM 42-097 Is Not Carried Out:
Figure 1: Exterior Placards and Markings - MÄM 42-097 Not Carried Out
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Section 11-30 – Interior Placards and Markings
2.
Description
On LH canopy Frame if the KAP 140 A/P Is Installed:
Limitations for KAP 140 Autopilot System:
Engine Power (LH & RH) is limited to max. 80% Load
Indication during Autopilot Operation.
Do not use AP during single engine operation.
Autopilot DISC during take-off and landing.
Maximum speed for autopilot operation is 180 KIAS.
Minimum speed for autopilot operation is 90 KIAS.
Minimum Altitude for Autopilot Operation:
Cruise, Climb, Descent and Maneuvering
: 800 feet AGL
Approach (130 KIAS or less)
: 200 feet AGL
Approach (above 130 KIAS)
: 250 feet AGL
Departure
: 200 feet AGL
Figure 1: Interior Placards and Markings – KAP 140 A/P Installed
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Canopy/Door Operation Placards if MÄM 42-097 Is Not Carried Out:
Figure 2: Exterior Placards and Markings - MÄM 42-097 Not Carried Out
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CHAPTER 22 – AUTO FLIGHT
Section 22-11 – KAP 140 Autopilot
1.
General
This Section tells you about the KAP 140 autopilot system that is installed in the DA 42 NG. Refer
to Section 22-10 in the AMM, Doc. No. 7.02.15, latest revision if the GFC 700 autopilot system is
installed.
2.
Description
The KAP 140 autopilot system is a digital flight control system that provides roll, pitch, and pitch
trim steering with altitude preselect.
The system has the following components (refer to Figure 1):
− KC 140 flight control computer (FCC).
− KCM 100 configuration module.
− Turn coordinator with autopilot pick-off.
− KS 271C roll servo.
− KS 270C pitch servo.
− KS 272C pitch trim servo.
− KM 275 and KM 277 servo mounts.
− Coupling to the Garmin G1000 integrated cockpit system (ICS).
Heading input is supplied for the KAP 140 autopilot by the Garmin G1000 integrated cockpit
system (ICS). Refer to Section 31-40 in the AMM for more data about the ICS.
The KAP 140 roll axis features include wing leveler, heading select, and VOR/LOC intercept and
tracking. The KAP 140 is also coupled to the ICS for navigation information. Roll rate information is
derived from the turn coordinator.
Pitch axis features include vertical speed, glideslope and altitude hold along with the optional
altitude preselect. Pitch information is derived from a pressure sensor and accelerometer. Internal
monitors keep constant track of the KAP 140’s status and provide for automatic shutdown of the
autopilot or trim system in the event of a malfunction.
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Figure 1: KAP 140 Autopilot System Schematic Diagram
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A.
Bendix/King KAP 140 Flight Control Computer
Figure 2 shows the Bendix/King KAP 140 flight control computer. It is located in the instrument
panel, at the bottom.
The Bendix/King KAP 140 has the following annunciators on the front panel, above the AP button:
− 'P' (pitch axis) annunciator. It indicates failure of the pitch axis and will either disengage the
autopilot or does not allow engagement of the pitch axis. The 'P' annunciator may illuminate
with the autopilot disengaged. This condition can occur during maneuvering flight when
g thresholds are exceeded. The autopilot monitor will not allow engagement during
illumination.
− 'R' (roll axis) annunciator. It indicates failure of the roll axis and will disengage the autopilot
or does not allow engagement.
The Bendix/King KAP 140 controls the following annunciator on the ICS alerts panel (also see
Section 31-40 in the AMM):
− TRIM FAIL annunciator. It illuminates whenever the automated pre-flight self test detects a
pitch trim fault or a continuous monitoring system detects a pitch trim fault in flight. Refer to
the EMERGENCY PROCEDURES for proper response to a pitch trim fault.
The Bendix/King KAP 140 has a display which shows the following:
− Pitch and roll mode displays. Displays the active pitch modes (VS, ALT, ARM, ALT, GS
ARM, GS) and roll modes (ROL, HDG, NAV ARM, NAV, APR ARM, APR, REV ARM, REV).
Also displayed will be a flashing AP annunciation (5 seconds) at each autopilot disconnect,
accompanied by an aural alert (for 2 seconds).
− PT (pitch trim) annunciation. It indicates the direction of required pitch trim. With electric trim
installed, the annunciation simply provides status to the autopilot request for auto trim. A
solid indication represents the lowest demand level for trim, whereas a flashing annunciation
implies a greater demand. A solid PT annunciation without an arrow head is an indication of
a pitch trim fault. During MET operation, this annunciation can be caused by a stuck MET
switch. If the stuck switch fault clears, trim operation will resume.
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Figure 2: Bendix/King KAP 140 Flight Control Computer
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ALERT (altitude alert) annunciation.
− It illuminates continuously in the region of from 200 to 1000 feet from the selected altitude if
the airplane was previously outside of this region.
− It flashes for two seconds the first time the airplane crossed the selected altitude.
− If flashes continuously in the 200 to 1000 feet region if the airplane was previously inside of
this region (i.e., at the selected altitude). Associated with the visual alerting is an aural alert
(5 short tones) which occurs 1000 feet from the selected altitude upon approaching the
altitude and 200 feet from the selected altitude on leaving the altitude.
− Altitude alert/vertical speed/baro setting display. Normally the altitude alerter selected
altitude is displayed. If the UP or DN button is pushed while in VS hold, the display changes
to the command reference for the VS mode in FPM for 3 seconds. If the BARO button is
pushed, the display changes to the autopilot baro setting in either IN HG or HPA for
3 seconds.
The flight control computer has these controls on the front panel:
− Rotary knobs. These are used to set the altitude alert reference altitude; or may be used
immediately after pressing the BARO button, to adjust the autopilot baro setting to match
that of the airplane’s altimeter when manual adjustment is required.
− AP (autopilot engage/disengage) button. When pushed, it engages the autopilot if all logic
conditions are met. The autopilot will engage in the basic roll (ROL) mode which functions as
a wing leveler and in the vertical speed (VS) hold mode. The commanded vertical speed
may be displayed manually in the upper right corner of autopilot display area if either UP or
DN button is pressed. The captured VS will be the vertical speed present at the moment of
AP button press. When pressed again, it will disengage the autopilot.
− HDG (heading) mode selector button. When pushed, it will select the 'heading' mode, which
commands the airplane to turn to and maintain the heading selected by the heading bug on
the HSI. A new heading may be selected at any time and will result in the airplane turning to
the new heading. The button can also be used to toggle between HDG and ROL modes.
This button may be used to engage the autopilot.
− NAV (navigation) mode selector button. When pushed, will select the navigation mode. The
mode provides automatic beam capture and tracking of VOR, LOC or GPS as selected for
presentation on the HSI. NAV mode is recommended for enroute navigation tracking.
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− APR (approach) mode selector button. When pushed, it will select the navigation mode. The
mode provides automatic beam capture and tracking of VOR, GPS, LOC, and glideslope
(GS) on an ILS, as selected for presentation on the ICS. APR mode tracking sensitivity is
recommended for instrument approaches.
− REV (back course approach) mode selector button. When pushed, it will select the back
course approach mode. This mode functions identically to the approach mode except that
the autopilot response to LOC signals is reversed.
− ALT (altitude hold) mode select button. When pushed, it will select the altitude hold mode.
This mode provides capture and tracking of the selected altitude. The selected altitude is the
altitude at the moment the ALT button is pressed. If the ALT button is pressed with an
established VS rate present, there will be approximately a 10 % (of VS rate) overshoot, with
the airplane returned positively to the selected altitude.
− UP/DN (vertical trim) buttons. The action of these buttons is dependent upon the vertical
mode present when pressed. If VS mode is active, the initial button stroke will bring up the
commanded vertical speed in the display. Subsequent immediate button strokes will
increment the vertical commanded either up or down at the rate of 100 ft/min per button
press, or at the rate of approximately 300 ft/min per second if pressed continuously. If the
ALT mode is active, incremental button strokes will move the altitude hold reference altitude
either up or down by 20 feet per press, or if held continuously will command the airplane up
or down at the rate of 500 ft/min, synchronizing the altitude hold reference to the actual
airplane altitude upon button release. (Note that the altitude hold reference is not displayed.
The display will continue to show the altitude alert reference.)
− ARM (altitude arm) button. It toggles altitude arming on or off. When ALT ARM is
annunciated, the autopilot will capture the altitude alert displayed altitude (provided the
airplane is climbing or descending in VS to the displayed altitude). ALT hold arming when
the autopilot is engaged is automatic upon altitude alert altitude selection via the rotary
knobs. Note that the alert functions are independent of the arming process, thus providing
full time alerting, even when the autopilot is disengaged.
− BARO (baro set) button. When pushed and released, it will change the display from the
altitude alert selected altitude to the baro setting display (either IN HG or HPA) for
3 seconds. If pushed and held for 2 seconds, it will change the baro setting display from IN
HG to HPA or vice versa. Once the baro setting display is visible, the rotary knobs may be
used to manually adjust the baro setting if the system configuration does not employ
automatic correction.
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The flight control computer is connected to these controls on the control sticks:
− AP DISC (autopilot disconnect) switch on pilot’s and co-pilot’s stick. When pressed, it will
disengage the autopilot, and interrupt electric trim power.
− Manual electric trim switches on the pilot’s stick. When both switches are pressed in the
same direction, they will activate pitch trim in the selected direction. If only one switch is
moved, the trim system will not operate. If one switch fails or is moved and held for 3
seconds, the trim monitoring system will detect a switch failure resulting in a PT
annunciation on the autopilot display and the disabling of the electric trim system. Autopilot
power will have to be cycled to clear the fault. Use of manual electric trim during autopilot
operation will disengage the autopilot.
− CWS (control wheel steering) mode button on the pilot’s stick. When pressed and held, it
disengages the pitch, roll and pitch trim clutches allowing the pilot to maneuver the airplane
by hand. Pressing the CWS button will also sync the autopilot ALT or VS commands to the
actual altitude or vertical speed present at the time the button is released.
B.
KCM 100 Configuration Module
The data which is specific to the DA 42 NG (for example: gain settings) is stored in the KCM 100
configuration module.
C.
KS 271C Roll Servo
The roll servo is located behind the rear main bulkhead on the right side. It is mounted on a
mounting plate which is made from sheet aluminum. Two aluminum clamps connect a bridle cable
to the aileron push-rod.
D.
KS 270C Pitch Servo
The pitch servo is located aft of the baggage compartment frame. It is mounted on a mounting
plate which is made from sheet aluminum. Two aluminum clamps connect a bridle cable to the
elevator push-rod.
E.
KS 272C Pitch Trim Servo
The pitch trim servo is located under the co-pilot's seat. It is mounted on a mounting plate which is
made from sheet aluminum and mounting bracket which is made from GFRP. Servo movement is
transmitted to the trim wheel through a chain gear on the servo, a cardan shaft, and a chain gear
next to the trim wheel on the right side.
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Maintenance Practices
1.
General
These Maintenance Practices tell you how to install the components of the KAP 140 autopilot
system. They also tell you how to test and adjust the KAP 140 autopilot system.
2.
Remove/Install the Flight Control Computer
A.
Remove the Flight Control Computer
Detail Steps/Work Items
Key Items/References
(1)
Open the AUTOPILOT circuit breaker.
(2)
Put a 3/32 Allen wrench into the access hole for
the locking screw. 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. IF
YOU PULL ON THE KNOBS, OR 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 gently on the sides of the unit to remove it
from the mounting rack.
(5)
Install the protective covers on the rear
connectors of the flight control computer.
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B.
Install the Flight Control Computer
(1)
Remove the protective covers from the
connectors on the replacement unit.
(2)
Slide the unit into the rack. Engage the locking
screw so that the latch front lobe touches the
rack.
(3)
Turn the locking screw clockwise so that the rear
lobe engages the mounting rack.
CAUTION:
DO NOT OVER-TIGHTEN THE LOCKING SCREW. YOU CAN DAMAGE
THE LOCKING MECHANISM.
(4)
Continue to turn the screw until the unit is fully
installed in the mounting rack.
(5)
Close the AUTOPILOT circuit breaker.
(6)
Check and adjust the servo “nulls”.
(7)
Do a test of the autopilot system:
Refer to the Installation Manual for the
KAP 140 Flight Control System.
− Set the ELECT. MASTER switch to ON.
− Set AV. MASTER switch to ON.
− Observe selftest of the flight control
computer.
If no error message appears, the
system is operative.
− Set AV. MASTER to OFF.
− Set ELECT. MASTER switch to OFF.
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3.
Remove/Install the KCM 100 Configuration Module
A.
Remove the KCM 100 Configuration Module
(1)
Open the AUTO PILOT circuit-breaker.
Instrument panel, right side.
(2)
Remove instrument panel cover.
Refer to Section 25-10 in the AMM.
(3)
Remove the KCM 100:
− Remove the two screws that attach the
KCM 100 to the mounting rack.
− Disconnect the electric cable.
− Move the configuration module free of the
instrument panel.
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B.
Install the the KCM 100 Configuration Module
CAUTION:
WHEN A NEW CONFIGURATION MODULE IS INSTALLED, YOU MUST
MAKE SURE THAT IT HAS THE PART NUMBER WHICH IS SHOWN IN
THE EQUIPMENT LIST IN CHAPTER 6 OF THE AIRPLANE FLIGHT
MANUAL. IF A NEW CONFIGURATION MODULE IS INSTALLED, A
COMPLETE CONFIGURATION PROCEDURE INCLUDING SOFTWARE
UPLOAD IS NECESSARY.
(1)
Put the KCM 100 in place on the instrument
panel. Connect the electric cable and engage the
two locking screws.
(2)
Install the instrument panel cover.
(3)
Close the AUTO PILOT circuit breaker.
Instrument panel, right side.
(4)
− Set the ELECT. MASTER switch to ON.
− Observe self-test of the flight control
computer.
If no error message appears, the system
is operative.
− Set AV. MASTER to OFF.
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5.
Remove/Install the Roll Servo
A.
Remove the Roll Servo
(1)
Remove the passengers seat.
(2)
Disconnect the connector from the servo.
(3)
Remove the 2 screws which attach the servo to
the mounting plate and the clutch.
(4)
Remove the servo clear of the airplane.
B.
Hold the servo.
Install the Roll Servo
(1)
Put the servo in place on the mounting plate.
(2)
Install the 2 screws which attach the servo to the
mounting plate and clutch.
(3)
Connect the connector to the servo.
(4)
− Set ELECT. MASTER switch to ON.
computer.
If no error message appears, the
system is operative.
− Set AV. MASTER switch to OFF.
(5)
Install the passengers seat.
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6.
Remove/Install the Roll Servo Clutch
A.
Equipment
Item
Cable tension gauge.
B.
Quantity
Part Number
1
Commercial.
Remove the Roll Servo Clutch
(1)
Remove the roll servo.
(2)
Release the clamps which connect the bridle
cable to the aileron push-rod.
(3)
Remove the bridle cable.
(4)
Remove the 2 screws which attach the clutch to
the mounting plate.
(5)
Remove the clutch clear of the airplane.
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Refer to Paragraph 5.
Hold the clutch.
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C. Install the Roll Servo Clutch
(1)
Remove the pilot's seat or the co-pilot's seat.
(2)
Put the clutch in place on the mounting plate.
(3)
Install the 2 screws which attach the clutch to
the mounting plate.
(4)
Center the aileron control system with a rigging
pin at one control stick.
(5)
Center the capstan.
The recess for the ball in the middle of
the bridle cable must be in the
uppermost position.
(6)
Install bridle cable to capstan.
The ball in the middle of the bridle cable
must engage in the recess on the
capstan. Wrap bridle cable around
capstan one turn to each side.
(7)
Connect the ends of the bridle cable to the
aileron pushrod with the clamps.
Tighten clamps lightly to allow
adjustment (see next step).
(8)
Using a small plastic hammer, move the clamps
along the pushrod to adjust the bridle cable
tension.
Adjust tension to 89 ±22 N (20 ±5 lbf).
Measure cable tension with cable
tension gauge.
(9)
Tighten the clamps.
(10)
Remove the rigging pin from the control stick.
(11)
Install the front seat which was removed.
(12)
Install the roll servo.
Doc. # 7.02.15-O03
Rev. 0
Refer to Section 25-10 in the AMM to
give access for the rigging pin.
22-11-00
Page 207
01 Jun 2009
System O03
DA 42 NG
Supplemental AMM
7.
Remove/Install the Pitch Servo
A.
Remove the Pitch Servo
(1)
Remove the trim/cover from the front face of the
baggage compartment and remove the lower
access panel from the baggage compartment
insert.
(2)
Disconnect the connector from the servo.
(3)
(4)
B.
Hold the servo.
Install the Pitch Servo
(1)
(2)
Install the 2 screws which attach the servo to
the mounting plate and clutch.
(3)
(4)
− Set ELECT. MASTER switch to ON.
− Observe selftest of the flight control
computer.
is operative.
− Set AV. MASTER switch to OFF.
− Set ELECT. MASTER to OFF.
(5)
Install the baggage compartment lower access
panel and install the trim/cover to the front face
of the baggage compartment.
Page 208
01 Jun 2009
22-11-00
Doc. # 7.02.15-O03
Rev. 0
System O03
DA 42 NG
Supplemental AMM
8.
Remove/Install the Pitch Servo Clutch
A.
Equipment
Item
B.
Quantity
Part Number
1
Commercial.
Remove the Pitch Servo Clutch
(1)
Remove the pitch servo.
(2)
Release the clamps which connect the bridle
cable to the elevator pushrod.
(3)
Remove the bridle cable.
(4)
Remove the 2 screws which attach the clutch to
the mounting plate.
(5)
Remove the clutch from the airplane.
Doc. # 7.02.15-O03
Rev. 0
Hold the clutch.
22-11-00
Page 209
01 Jun 2009
System O03
DA 42 NG
C.
Supplemental AMM
Install the Pitch Servo Clutch
(1)
Remove the pilot's seat or the co-pilot's seat.
(2)
Put the clutch in place on the mounting plate.
(3)
Install the 2 screws which attach the clutch to
the mounting plate.
(4)
Center the elevator control system with a
rigging pin at one control stick.
(5)
Center the capstan.
The recess for the ball in the middle of
the bridle cable must be in the
uppermost position.
(6)
Install bridle cable to capstan.
The ball in the middle of the bridle cable
must engage in the recess on the
capstan. Wrap bridle cable around
capstan one turn to each side.
(7)
Connect the ends of the bridle cable to the
elevator push-rod with the clamps.
Tighten clamps lightly to allow
adjustment (see next step).
(8)
along the push-rod to adjust the bridle cable
tension.
Adjust tension to 89 ± 22 N (20 ±5 lbf).
tension gauge.
(9)
Tighten the clamps.
(10)
Remove the rigging pin from the control stick.
(11)
Install the front seat which was removed.
(12)
Install the pitch servo.
Page 210
01 Jun 2009
22-11-00
Refer to Section 25-10 in the AMM to
give access for the rigging pin.
Doc. # 7.02.15-O03
Rev. 0
System O03
DA 42 NG
Supplemental AMM
9.
Remove/Install the Pitch Trim Servo
A.
Remove the Pitch Trim Servo
(1)
Remove the co-pilot's seat.
(2)
Dis-connect the connector from the servo.
(3)
(4)
B.
Hold the servo.
Install the Pitch Trim Servo
(1)
(2)
Install the 2 screws which attach the servo to
the mounting plate and clutch.
(3)
(4)
The upper forward screw also holds the
chain adjuster. Ensure proper chain
tension.
− Set ELECT MASTER switch to ON.
− Set AVIONICS MASTER switch to ON.
computer.
is operative.
− Set AVIONICS MASTER switch to OFF.
− Set ELECT MASTER switch to OFF.
(5)
Install the co-pilot's seat.
Doc. # 7.02.15-O03
Rev. 0
22-11-00
Page 211
01 Jun 2009
System O03
DA 42 NG
Supplemental AMM
10. Remove/Install the Pitch Trim Servo Clutch
A.
Remove the Pitch Trim Servo Clutch
CAUTION:
DO NOT APPLY STRONG FORCES TO THE CARDAN SHAFT. THE
UPPER CARDAN JOINT CONNECTS TO A PART WHICH IS WEAK BY
DESIGN TO GIVE OCCUPANT PROTECTION IN AN EMERGENCY
LANDING.
(1)
Remove the pitch trim servo.
(2)
Remove the screw which holds the cap to the
capstan.
(3)
Remove the cap from the capstan.
(4)
Release chain tension with chain adjuster.
(5)
Remove the chain from the chain gear.
(6)
Remove the 2 screws which attach the clutch
and the chain adjuster to the mounting plate.
B.
On the chain gear next to the servo.
Hold the clutch and the chain adjuster.
Install the Pitch Trim Servo Clutch
(1)
Put the clutch and the chain adjuster in place on
the mounting plate.
(2)
Install the 2 screws which attach the clutch and
the chain adjuster to the mounting plate.
(3)
Install the chain to the chain gear.
(4)
Put the cap in place on the capstan.
(5)
Install the screw which holds the cap to the
capstan.
(6)
Install the pitch trim servo.
Page 212
01 Jun 2009
22-11-00
Doc. # 7.02.15-O03
Rev. 0
System O03
DA 42 NG
Supplemental AMM
11. Adjust the Bridle Cable Tension
A.
Equipment
Item
B.
Quantity
Part Number
1
Commercial.
Adjustment Procedure
(1)
Loosen the bolts in the clamps which connect
the bridle cable to the pushrod.
Do not remove the bolts. Loosen just
enough so that the next step can be
done.
(2)
along the pushrod to adjust the bridle cable
tension.
Adjust tension to 89 ±22 N (20 ±5 lbf).
tension gauge.
(3)
Tighten the bolts in the clamps which connect
the bridle cable to the pushrod.
Doc. # 7.02.15-O03
Rev. 0
22-11-00
Page 213
01 Jun 2009
System O03
DA 42 NG
Supplemental AMM
12. Adjust the Servo Clutch Torques
A.
Equipment
Item
Goodrich slip clutch test stand.
B.
Quantity
Part Number
1
20-9855-03.
Adjustment Procedure
(1)
Remove the clutch from the airplane.
Refer to this Section.
(2)
Install the clutch assembly on the slip clutch test
stand.
Refer to the equipment manufacturers'
documentation.
(3)
Measure clockwise (CW) and counterclockwise
(CCW) clutch torque, adjust if necessary.
Refer to the equipment manufacturers'
documentation.
The correct clutch torques are:
(4)
Remove the clutch assembly from the slip
clutch test stand.
(5)
Install the clutch to the airplane.
Page 214
01 Jun 2009
22-11-00
Roll servo
2.03 ±0.23 Nm
(18 ±2 lbf.in.)
Pitch servo
3.39 ±0.34 Nm
(30 ±3 lbf.in.)
Pitch trim servo
4.07 ± 0.45 Nm
(36 ±4 lbf.in.)
Doc. # 7.02.15-O03
Rev. 0
System O03
DA 42 NG
Supplemental AMM
13. Mechanical Test of the Autopilot System
Do this check at the intervals given in Section 05-10.
(1)
Check bridle cable tension for the roll servo,
adjust if necessary.
(2)
Check bridle cable tension for the pitch servo,
adjust if necessary.
(3)
Check the clutch torque settings for the roll
servo, adjust if necessary.
(4)
Check the clutch torque settings for the pitch
servo, adjust if necessary.
(5)
Check the clutch torque settings for the pitch
trim servo, adjust if necessary.
(6)
Perform Pitot and static system leak tests.
Doc. # 7.02.15-O03
Rev. 0
22-11-00
Page 215
01 Jun 2009
System O03
DA 42 NG
Supplemental AMM
Page 216
01 Jun 2009
22-11-00
Doc. # 7.02.15-O03
Rev. 0
System O03
DA 42 NG
Supplemental AMM
CHAPTER 31 – INDICATING SYSTEMS
Section 31-10 – Instrument and Control Panels
2.
Instrument Panel Description
The landing gear and flap control switches are located on each side of the autopilot control panel, if
the KAP 140 autopilot is installed.
Doc. # 7.02.15-O03
Rev. 0
31-10-00
Page 1
01 Jun 2009
System O03
DA 42 NG
Supplemental AMM
Page 2
01 Jun 2009
31-10-00
Doc. # 7.02.15-O03
Rev. 0
System O03
DA 42 NG
Supplemental AMM
CHAPTER 52 – DOORS
Section 52-10 – Canopy and Passenger Door
2.
Canopy Description and Operation
Figure 1 shows the canopy locking mechanism if MÄM 42-097 is not carried out.
A handle on the left of the canopy operates two locking bolts. The handle has a spring assisted
over-center lock which holds the handle in the closed position. The locking bolts are at the bottom
rear corners of the canopy.
The handle has two parts. The inner handle is black and has a double lever. The outer handle is
red and attaches to the inner handle with two roll pins. A connecting rod attaches to the rear of the
double lever. The other end of the connecting rod attaches to the inside of the left locking bolt.
A teleflex cable attaches to the front of the double lever. The teleflex cable goes inside the front of
the canopy frame to the right locking bolt. If you pull the canopy handle away from the canopy
frame, these things happen:
− The double lever turns to pull the connecting rod and the teleflex cable.
− The connecting rod pulls the left locking bolt forward.
− The teleflex cable pulls the right locking bolt forward. The forward movement of the locking
bolt operates the door unlocked warning micro-switch in the left side fuselage shell.
The canopy can be pushed up and forward to open.
With the canopy fully closed, push the canopy handle towards the canopy frame. This engages the
locking bolts in the fuselage holes. The spring assisted over-center lock holds the handle in the
closed position. The right locking bolt operates the micro-switch for the DOOR warning caption.
When the handle is flush with the canopy frame, the canopy is locked. Push up on the rear of the
canopy frame to make sure that it is locked. A key operated lock can be used to secure the canopy
in the closed position when the airplane is parked.
Doc. # 7.02.15-O03
Rev. 0
52-10-00
Page 1
01 Jun 2009
System O03
DA 42 NG
Supplemental AMM
Figure 1: Canopy Locking Mechanism, MÄM 42-097 Not Carried Out
Page 2
01 Jun 2009
52-10-00
Doc. # 7.02.15-O03
Rev. 0
System O03
DA 42 NG
Supplemental AMM
3.
Passenger Door Description and Operation
Figure 2 shows the passenger door installation and locking mechanism if MÄM 42-097 is not
carried out.
The passenger door is a CFRP molding with inner and outer frames. The frames bond together
with thickened resin. Each part of the frame has layers of carbon cloth and one layer of glass cloth.
Areas of high stress have extra layers of carbon cloth. Mounting bushes for the handle and locking
bolts bond to the inside of the frame with thickened resin.
The door has a acrylic glass window. A special flexible adhesive bonds the window to the door
frame. A flexible filler seals the small gap between the edge of the window and the frame.
Two hinges attach the door to the top of the fuselage near the center-line. The hinges bolt to the
door frame. The front hinge can be removed from inside of the cabin in an emergency. With the
front hinge removed, the passenger door can be forced open from the top. A gas strut attaches to a
bracket at the rear of the door and to the fuselage. The gas strut holds the door open. A door
unlocked warning caption on the ICS display operates when the door is unlocked.
A handle on the left of the door operates two locking bolts. The locking bolts are at the bottom front
and rear corners of the door.
The handle has two parts. The inner handle is black and has a double lever. The outer handle is
red and attaches to the inner handle with two roll pins. A long connecting rod attaches to the rear of
the double lever. The other end of the long connecting rod attaches to the inside of the rear locking
bolt. A safety lock is fitted to prevent accidental movement of the handle.
You must lift the safety handle before you can operate the black handle from inside the passenger
compartment. To operate the red handle from the outside you must push the button next to the red
handle to lift the inner safety lock.
A short connecting rod attaches to the front of the double lever. The short connecting rod goes to
the front locking bolt. If you pull the canopy handle away from the canopy frame, these things
happen:
− The double lever turns to pull the both of the connecting rods.
− The long connecting rod pulls the rear locking bolt forward.
− The short connecting bolt pulls the front locking bolt aft. The aft movement of the locking bolt
operates a micro switch for the warning caption located on the ICS.
The door can be pushed up and out to open.
Doc. # 7.02.15-O03
Rev. 0
52-10-00
Page 3
01 Jun 2009
System O03
DA 42 NG
Supplemental AMM
With the door fully closed, push the door handle towards the door frame. This engages the locking
bolts in the fuselage holes. The forward locking bolt operates the door unlocked micro switch.
When the handle is flush with the door frame, the door is locked. Push outwards on the bottom of
the door frame to make sure that it is locked. A key operated lock can be used to secure the door in
the closed position when the airplane is parked.
Page 4
01 Jun 2009
52-10-00
Doc. # 7.02.15-O03
Rev. 0
System O03
DA 42 NG
Supplemental AMM
Figure 2: Passenger Door, MÄM 42-097 Not Carried Out
Doc. # 7.02.15-O03
Rev. 0
52-10-00
Page 5
01 Jun 2009
System O03
DA 42 NG
Supplemental AMM
Page 6
01 Jun 2009
52-10-00
Doc. # 7.02.15-O03
Rev. 0
System O03
DA 42 NG
Supplemental AMM
CHAPTER 92 – WIRING DIAGRAMS
1.
General
Title
Drawing No.
Rev.
No.
No. of
Sheets
Schematic, KAP 140 Wiring
D64-9222-10-01
-
1
Schematic, G 1000
D64-9231-60-02
-
6
Schematic, LH ECU
D64-9277-40-02x01
-
2
Schematic, RH ECU
D64-9277-40-03x01
-
2
Doc. # 7.02.15-O03
Rev. 0
92-00-00
Page 1
01 Jun 2009
System O03
DA 42 NG
Supplemental AMM
Page 2
01 Jun 2009
92-00-00
Doc. # 7.02.15-O03
Rev. 0
ALL RIGHTS RESERVED FOR THIS DOCUMENT WHICH MAY NOT BE REPRODUCED
OR DISCLOSED TO THIRD PARTIES WITHOUT THE PRIOR WRITTEN CONSENT OF
DIAMOND AIRCRAFT INDUSTRIES
A
B
C
D
E
F
8
P1401
11
27
2
COMPASS VALID
HDG/CRS REF
HDG DATUM
N/C
BARO SET 16
TRANSPONDER REF. 35
8
N/C
22060B22
22061B22
22062B22
A1 11
A4 14
N/C
N/C
37
BP 1
CHASIS GROUND 15
BP 4
22010A22N
47
48
BARO REF SUPPLY
22106A22WH
22106A22BL
22107A22WH
22107A22BL
6
23
TACH +
TACH -
22101A22WH
22101A22BL
22307A22WH
22307A22BL
TRIM SENSE +
TRIM SENSE -
22065B22
22066B22
22067B22
B2 34
B4 20
C1 21
3
5
C2
C4
22068B22
22063B22
22064B22
B1 33
A2 13
P2414
REF D60-9231-60-02
J2414
P2414
26
35
36
37
38
39
40
57
56
55
54
27
28
29
30
31
32
33
34
DIMENSIONS
REF D60-9231-60-02
METRIC
22012A22WH
22012A22OR
22012A22BL
22014A22N
22015A22
34 MIDDLE MARKER SENSE
20 AURAL ALERT AUDIO
POWER GROUND
DC POWER IN
SP
IP GS10
IP GS11
IP GS11
IP GS12
GS IP 11
22030A22
22018A22
REF D60-9231-60-01 (GMA 1347)
22000A20
22014A22N
22002A20N
22015A22
22022A22WH
22022A22BL
22023A22N
IDENTIFICATION MARKINGS
ROLL RATE +
ROLL RATE RATE VALID
B
A
TURN COORDINATOR
C
E
D
J3492
5
4
DATA JACK
AVIONICS BUS
J2414
53
52
51
50
49
48
47
46
45
7
6
2 DECIMAL
1DECIMAL
DECIMAL
ANGLE
RAD
u0,25
u0,5
u1
u1°
u0,5
DIMENSION TOLERANCES
FINISH
IN
MICROMETER
3.2
A3
FORMAT
UNLESS OTHERWISE SPECIFIED
DIMENSIONS ARE IN MM
FIRST ANGLE PROJECTION
SOLID EDGE V18
5
D64-9222-10-01.dft
FILENAME
SOFTWARE:
THIS DRAWING WAS PRODUCED USING
INTERCHANGEABLE PART
NO
CLASSIFICATION:
NONE
DE-S-10-00003
IP GS9
22306A22N
22305A20N
22107A22WH
22107A22BL
22103A22N
22102A20N
22106A22WH
22106A22BL
22101A22WH
22101A22BL
22104A22
22105A22
22307A22WH
22307A22BL
APPROVED:
SYSTEM:
MANUF.:
STRESS:
QA:
CHECKED:
DRAWN
Aircraft
Zeillinger
N/A
N/A
N/A
N/A
Kowarsch
Moise
Industries GmbH
Diamond
P2403
22028B22
22030B22N
22027B22
22026B22
22029B22N
22025B22
22016D20
22071A20
22205B22N
22204B20N
22200B20
54
36
34
35
26
16
25
29
30
39
37
38
40
41
3
2
1
2
ROLL SERVO CMD REF
ROLL CLUTCH
ROLL SERVO CMD
ROLL SERVO VALID
ROLL SERVO
KS 271C
3
4
J2210
white
green
black
2
3
SIGN
DATE
18.05.09
PITCH SERVO
KS 270C
TRIM VOLTAGE +
TRIM VOLTAGE -
TRIM SENSE TRIM SENSE +
P TACH A TACH +
N SIGNAL GROUND
C POWER GROUND
R
J
H SERVO AMP POWER
E SERVO CLUTCH POWER
D SERVO CMD REF
L PITCH SERVO CMD
K PITCH SERVO VALID
F PITCH CLUTCH
R
J
A TRIM DISABLE
M TRIM CLUTCH
L TRIM SERVO CMD
D SERVO CMD REF
H SERVO AMP POWER
E SERVO CLUTCH POWER
N SIGNAL GROUND
C POWER GROUND
2
SCALE
NTS
SH
D64-9222-10-01
DWG.NO.
710197
DAIA
CODE
DA 42 NG
1
01
01
Confidential
OF
-
REV
APPROVAL
N. A. Otto-Straße 5
A-2700 Wiener Neustadt
MANUAL
ELECTRIC
TRIM SW
CWS SW
TRIM
INTERUPT
AP DISC SW
1
18.05.09 SEE TB
DATE
Schematic,
KAP 140 Wiring
DWG.ORIG.
TITLE
PROJECT
DN
ARM
PITCH TRIM SERVO
KS 272C
red
J2230
J2205
UP
SERVO AMP POWER
SERVO CLUTCH POWER
AP DISC SW
COPILOT´S STICK
E
H
N SIGNAL GROUND
C POWER GROUND
1
6
5
7
8
P2205
K
F
J2220
D
L
REVISION
DESCRIPTION
OÄM 42-171
FIRST RELEASE
P2207
22072A20
J2207
ALL
ZONE
2
Diamond Aircraft Industries
22107B22WH
22107B22BL
22103B22N
22102B20N
22106B22WH
22106B22BL
22101B22WH
22101B22BL
22104B22
22105B22
22100B20
22307B22WH
22307B22BL
22304B22BL
22301B22
22303B22
22304B22WH
22306B22N
22305B20N
16
15
12
13
14
19
20
21
01
SH
22201B22
22202B22
22203B22WH
22203B22BL
3
8
4
1
22302B20
25
26
27
22027A22
22028A22
22030A22N
P2406
P2403
-
REV
BACK PLATE VIEWED FROM REAR
3
7
24
DEPARTMENT
4
J2403
4
9
22025A22
22026A22
22029A22N
22032A20
28
1
22032B20
J2406
50
49
53
17
15
42
43
44
J2403
22016C20
22205A22N
22204A20N
22203A22WH
22203A22BL
22201A22
22202A22
5A
AUTOPILOT
AP.WRN.
RH MAIN BUS
2A
GS IP 12
4
3
2
1
22301A22
22303A22
22104A22
22105A22
4
2
SONALERT
22012A22WH
22012A22OR
22012A22BL
3 CFG ENABLE
4 CFG CLOCK
5 CFG DATA
CFG +5V
1
2 GROUND
P1001
KCM 100
J3472
GMA 1347
22304A22WH
22304A22BL
+
22008A22
22009A22
6
J3471
22304A22WH
22304A22BL
REF D60-9231-60-01
-
7
22026A22
22027A22
22028A22
22051B22
22301A22
22303A22
PITCH SERVO CMD 7
SERVO CMD REF 24
PITCH SERVO VALID 28
PITCH CLUTCH 8
BP 1
TRIM VOLTAGE +
TRIM VOLTAGE -
TRIM FAIL ANNUN 44
TRIM CLUTCH
1
TRIM SERVO CMD 32
SERVO CMD REF 36
TRIM UP
TRIM DOWN
ARM
MIDDLE MARKER GAIN
22
27
25
22009A22
38
26
22052B22
22058B24WH
22058B22BL
31
12
G/S FLAG +
G/S FLAG -
GPS SELECT
BP 1
22057B24WH
22057B24BL
17
9
10
22069B24OR
22069B24BL
22069B24WH
22056B22
22053B22
CRS DATUM
G/S + UP
G/S + DN
J1402
22055B24WH
22055B24BL
24
25
NAV DEV + LT
NAV DEV + RT
BP 3
22054B24WH
22054B24BL
7
22
23
ILS ENERGIZE
NAV + FLAG
NAV - FLAG
22203A22BL
9
26
5
1
18
19
22031A22
22018A22
33011A22
22000A20
22032A20
22025A22
22201A22
22202A22
22203A22WH
22012A22WH
22012A22OR
22012A22BL
22020A22WH
22020A22OR
22020A22BL
22019A22
22021A22N
22008A22
22022A22WH
22022A22BL
22023A22N
22002A2ON
22040A22N
22041A22N
22042A22N
AP DISC
CWS
ROLL SERVO VALID
CLUTCH LO
ROLL SERVO CMD
ROLL SERVO CMD REF
BP 2
SONALERT DRIVE 20
AP ALERT POWER 14
PANEL LIGHT HI 12
AP PRIMARY POWER 16
CHASIS GROUND 15
ROLL RATE + 21
ROLL RATE - 3
RATE VALID 10
BP 3
TXD RS 232 28
RXD RS 232 29
BP 2
AURAL ALERT AUDIO 6
CFG ENABLE 13
CFG CLOCK 30
CFG DATA 8
CONFIG +5 VOLT 4
BP 2
BP 2
STRAP 1 31
STRAP 2 32
STRAP 5 17
BP 3
POWER GROUND 35
KAP 140
AP CONTROLLER
Confidential
A
B
C
D
E
F
A
B
C
D
E
F
Confidential
7
6
AIRCRAFT GROUND
COAXIAL CABLE
WIRE SPLICE CONNECTION
GARMIN (SHIELD BLOCK) GROUND
REFER TO DOC. 190-00313-09
N/C = NO CONNECTION
S
TWISTED SHIELDED 4 CONDUCTOR
SHIELD FLOATS
SHIELD TERMINATED TO GROUND
P/N
E10422 (22 GAUGE)
E10424 (24 GAUGE)
392404 (24 GAUGE)
DRAWING NUMBER
190-00313-00
190-00313-04
190-00313-02
190-00313-01
8
REV 2 PIN
35
29
7
REV 2 UNITS HAVE SERIAL NUMBERS LESS THAN 46901600
REV 3 UNITS HAVE SERIAL NUMBERS OF 46901600 OR GREATER
PIN NAME
CAN BUS 1 TERMINATION
CAN BUS 2 HI
REV 3 PIN
34
32
21. NOTE THE FOLLOWING PIN DIFFERENCES IN REV 2 AND REV 3 GIA P603:
DIMENSIONS
6
2 DECIMAL
1DECIMAL
DECIMAL
ANGLE
RAD
u0,25
u0,5
u1
u1°
u0,5
FINISH
IN
MICROMETER
3.2
A3
FORMAT
METRIC
21. FOR GROUNDING PROCEDURE REFER TO GARMIN DOCUMENTS 190-00313-00 AND 190-00313-04.
ADDITIONAL FOR IFR OPERATION, REFER TO GARMIN DOCUMENT 190-00313-09.
19. RELATED DOCUMENTS
190-00295-27 UNIT INTERCONNECT SUMMARY.
190-00295-28 UNIT POWER.
190-00295-29 INTERCONNECT.
10. FOR TRIM FAIL OUTPUT: GROUND = ACTIVE = TRIM FAIL, OPEN = INACTIVE = TRIM OK
9. FOR FAN FAIL OUTPUT: OPEN = ACTIVE = FAN FAIL, GROUND = INACTIVE = FAN OK
DESCRIPTION
INSTR SHEET, OAT PROBE
INSTR SHEET, GMU44
INSTR SHEET, CONFIG MODULE
INSTR SHEET, THERMOCOUPLE
8. INSTALLATION INSTRUCTIONS FOR OAT PROBE, GMU44, GND HARNESS, CONFIGURATION MODULES, AND THERMOCOUPLES.
MANUFACTURER
PIC WIRE AND CABLE
PIC WIRE AND CABLE
ELECTRONIC CABLE SPECIALIST
7. USE AIRCRAFT GRADE CATEGORY 5 ETHERNET CABLE.
5. UNLESS OTHERWISE NOTED, ALL SHIELD GROUNDS MUST BE MADE TO THE RESPECTIVE UNIT BACKSHELLS.
ALL OTHER GROUNDS SHOULD BE TERMINATED TO AIRCRAFT GROUND AS CLOSE TO THE RESPECTIVE UNIT AS POSSIBLE.
SHIELD FLOATS
TWISTED SHIELDED PAIR
SHIELD FLOATS
TWISTED SHIELDED PAIR
TWISTED SHIELDED SINGLE CONDUCTOR
SHIELD FLOATS
TWISTED SHIELDED SINGLE CONDUCTOR
4. SYMBOL DESIGNATIONS
3. UNLESS OTHERWISE NOTED, ALL WIRES ARE 24 GAUGE MINIMUM.
2. UNLESS OTHERWISE NOTED, ALL SHIELDED WIRE MUST CONFORM TO MIL-C-27500 OR EQUIVALENT
1. UNLESS OTHERWISE NOTED, ALL STRANDED WIRE MUST CONFORM TO MIL-W-22759/16 OR EQUIVALENT
NOTES:
8
SOLID EDGE V18
5
D64-9231-60-02.dft
FILENAME
SOFTWARE:
NO
CLASSIFICATION:
NONE
DE-S-10-00003
5
4
APPROVED:
SYSTEM:
MANUF.:
STRESS:
QA:
CHECKED:
DRAWN
Aircraft
Zeillinger
N/A
N/A
N/A
N/A
Kowarsch
Moise
Industries GmbH
Diamond
DEPARTMENT
4
-
REV
ZONE
ALL ALL
SH
3
SIGN
DATE
15.05.09
OÄM 42-171
FIRST RELEASE
2
SCALE
1:1
SH
1
01
06
Confidential
OF
-
REV
APPROVAL
D64-9231-60-02
DWG.NO.
710197
DAIA
CODE
DA 42 NG
1
15.05.09 SEE TB
DATE
Schematic, G1000
DWG.ORIG.
TITLE
PROJECT
REVISION
DESCRIPTION
2
3
A
B
C
D
E
F
A
B
C
D
E
F
Confidential
8
8
23017A22
J2413
34102B24BL
69
38
39
RS 232 OUT 2
RS 232 IN 2
7
34102B24WH
68
AIRCRAFT GROUND
S
S
5A
J2414
34102A24BL
Industries GmbH
5
24
Aircraft
34100B22
34101B22N
23
34100A22
GS AVB
3.2
23013A24BL
18
19
23013A24WH
17
34101A22N
23013B24BL
23013B24WH
34102A24WH
11
9
23301B20N
16
23301A20N
10
23300B20
DA 42 NG
23302A24BL
7
8
23302A24WH
TITLE
53V
0.499 Ω 20W
34100E22
P2301
1
2
S
S
S
S
S
S
J2301
MARKER
ANTENNA
34000E22
S
AIRCRAFT POWER 1
AIRCRAFT POWER 1
POWER GROUND
31
29
76
2P605
62
59
2P603
61
59
POWER GROUND
AIRCRAFT POWER 1
MAIN RS 232 OUT 7
MAIN RS 232 IN 7
SIGNAL GROUND
VOR/LOC DIGI AUDIO OUT
AIRCRAFT POWER 1
2P602
AIRCRAFT POWER 1
POWER GROUND
19
30
COM DIGITAL AUDIO OUT
COM MIC DIGITAL AUDIO IN
NO. 2 GIA63
INTEGRATED AVIONICS
SPEAKER
VOICE ALERT DIGITAL AUDIO OUT
MAIN RS 232 OUT 7
MAIN RS 232 IN 7
SIGNAL GROUND
VOR/LOC DIGI AUDIO OUT
POWER GROUND
AIRCRAFT POWER 1
COM DIGITAL AUDIO OUT
COM MIC DIGITAL AUDIO IN
17
13
14
2P601
69
62
59
1P603
61
59
1P602
76
29
1P605
13
14
POWER GROUND
POWER GROUND
30
31
17
COM MIC AUDIO IN LO
COM AUDIO OUT LO
COM AUDIO OUT HI
COM MIC KEY
COM MIC AUDIO IN HI
NO. 1 GIA63
INTEGRATED AVIONICS
MIDDLE MARKER GAIN
AURAL ALERT AUDIO
HONEYWELL
KC 140
19
8
10
9
4
7
1P601
38
P1402
6
P1401
3
4
3
Schematic, G1000
23008B24BL
6
P2414
23008B24WH
44
45
43
23008A24BL
P2404
53V
0.499 Ω 20W
SEE SHEET 6
4
23008A24WH
J2404
J3482
15
Diamond
6
34890B400
P3482
23211A24
23300A20
PROJECT
P3481
GS IP-16
AVIONICS
BUS
GPS/NAV 2
GS IP-12
5A
CROSS SIDE NAV DIGI AUDIO IN
COM 2
23302B24BL
AVIONICS
BUS
48
CROSS SIDE COM DIGI AUDIO IN
S
23302B24WH
23008A24BL
47
23008A24WH
J3481
49
50
20
23012A24BL
19
23012B24BL
23211B24
23012A24WH
18
23012B24WH
CROSS SIDE COM MIC DIGI AUD OUT
S
34890A400
GS IP-7
34002A24BL
23011A22N
34002A24WH
16
17
15
34002B24BL
38
34002B24WH
34000B22
34001B22N
37
34000A22
34001A22N
GS AVB
23210A24BL
3.2
23210A24WH
53
54
52
41
59
5A
GS IP-2
LH MAIN
BUS
GPS/NAV 1
23200B20
23201B20N
23210B24BL
27
26
23210B24WH
23201A20N
23200A20
23203A24BL
46
23203A24WH
42
78
MKR ANTENNA HI
MKR ANTENNA LO
S
S
5A
GS IP-2
LH MAIN
BUS
COM 1
SPKR AUDIO OUT HI
29
VOICE ALERT DIGITAL AUDIO IN
S
S
S
45
23203B24BL
8
44
23203B24WH
SPKR AUDIO OUT LO
7
71
AIRCRAFT GROUND
6
28
ON SIDE NAV DIGI AUDIO IN
RS 232 IN 1
9
ON SIDE COM DIGI AUDIO IN
RS 232 OUT 1
8
ON SIDE COM MIC DIGI AUDIO OUT
14
53
POWER GROUND
34
POWER
P3472
7
8
MIDDLE MARKER SENSE
ON SIDE COM AUDIO LO
ON SIDE COM AUDIO IN HI
23202A24WH
23202A24BL
7
P2413
6
23202B24BL
27
ON SIDE COM MIC
S
100 Ω 10W
26
23018A22
23010A22
ON SIDE COM MIC AUDIO OUT HI
22009A22
22009A22
+28 V ANR TIP POWER
23202B24WH
22008A22
22008A22
AUDIO
AVIONICS
5A
BUS
5
20
P3471
6
UNSWITCHED AUDIO IN 2 HI
GMA1347
AUDIO PANEL
7
CODE
2
SCALE
1:1
SH
D64-9231-60-02
DWG.NO.
710197
DAIA
DWG.ORIG.
2
1
02
1
06
Confidential
OF
-
REV
A
B
C
D
E
F
A
B
C
D
E
F
Confidential
8
8
15
16
19
39
DME AUDIO IN HI
DME AUDIO IN LO
UNSWITCHED AUDIO IN 1 HI
UNSWITCHED AUDIO IN LO
7
35
36
PROJECT
17
18
37
MUSIC IN 1 LEFT
MUSIC IN 1 RIGHT
MUSIC IN 1 LO
ADF AUDIO IN HI
ADF AUDIO IN LO
23025B24WH
23025B24OR
23025B24BL
56
57
76
MUSIC IN 2 LEFT
MUSIC IN 2 RIGHT
MUSIC IN 2 LO
S
S
S
5A
Aircraft
Industries GmbH
Diamond
34430A24WH
34430A24BL
34300A24WH
34300A24BL
34206A24WH
34206A24BL
GS IP-6
23400A22
23403A22N
23016A24WH
23016A24OR
23016A24BL
J2414
6
DATA LINK
AVIONICS
BUS
S
S
S
23002A24WH
23002A24BL
23002A24OR
23007A24WH
23007A24OR
23007A24BL
23005A24WH
23005A24OR
23005A24BL
23006A24WH
23006A24BL
23004A24WH
23004A24BL
J2413
27
23003A24WH
23003A24OR
23003A24BL
69
70
71
COPILOT PHONE AUDIO LT OUT HI
COPILOT PHONE AUDIO RT OUT HI
COPILOT PHONE AUDIO OUT LO
J2403
8
40
9
10
23015A24WH
23015A24BL
50
COPILOT MIC KEY IN
S
49
51
COPILOT MIC AUDIO IN HI
COPILOT MIC AUDIO IN LO
+28 V ANR
S
S
67
68
48
PASS PHONE L OUT HI
PASS PHONE R OUT HI
PASS PHONE AUDIO LO OUT
S
65
66
PASS 2 MIC AUDIO IN HI
PASS 2 MIC AUDIO IN LO
S
46
47
23014A24WH
23014A24BL
23001A24WH
23001A24OR
23001A24BL
42
43
44
36
47
51
23
29
30
1
3
45
47
46
48
26
28
29
48
53
54
14
13
12
11
18
50
19
20
24
51
25
33
21
22
23
17
15
16
5
49
6
7
57
55
56
4
PASS 1 MIC AUDIO IN HI
PASS 1 MIC AUDIO IN LO
1
2
3
9
10
11
S
J2405
51
PILOT PHONE AUDIO LT HI OUT
PILOT PHONE AUDIO RT HI OUT
PILOT PHONE AUDIO LO OUT
S
PILOT
HAND
MIC
J2403
29
23000A24WH
23000A24BL
23000A24OR
23026A24WH
23026A24BL
23026A24OR
34411B22
PILOT MIC KEY IN
S
CR 900
28
30
P3471
+28 V ANR TIP POWER
34412A22
34413A22
6
PILOT MIC AUDIO IN HI
PILOT MIC AUDIO IN LO
GMA1347
AUDIO PANEL
7
34430B24WH
34430B24BL
34300B24WH
34300B24BL
34206B24WH
34206B24BL
23400B22
23403B22N
23016B24WH
23016B24OR
23016B24BL
23025B24WH
23025B24OR
23025B24BL
23003B24WH
23003B24OR
23003B24BL
23015B24WH
23015B24BL
23002B24WH
23002B24BL
23002B24OR
23007B24WH
23007B24OR
23007B24BL
23005B24WH
23005B24OR
23005B24BL
23006B24WH
23006B24BL
23004B24WH
23004B24BL
23001B24WH
23001B24OR
23001B24BL
23014B24WH
23014B24BL
23000B24WH
23000B24BL
23000B24OR
34411A22
5
DA 42 NG
P2414
P2413
P2403
P2405
P2403
5
TITLE
4
3
P1
N
C
P631
2
3
P2
35
20
19
18
17
P691
P692
22
P2
OPTIONAL
AVIDYNE
9900BX
TAS
AUDIO
AUDIO GROUND
OPTIONAL
HONEYWELL
KN 63
DME
AUDIO HI
AUDIO LO
AUDIO OUT HI
AUDIO OUT LO
OPTIONAL
BECKER
RA 3502-(01)
ADF RECEIVER
REF D60-9234-50-01
AIRCRAFT POWER
POWER GROUND
AUDIO LEFT
AUDIO RIGHT
AUDIO OUT LO
GDL 69
DATA LINK
OPTIONAL
CO-PILOT
PHONE
CO-PILOT
MIC
PASS #2
PHONE
PASS #1
PHONE
PASS #2
MIC
PASS #1
MIC
PILOT
PHONE
PILOT
MIC
OPTIONAL
GOODRICH
WX-500
STORMSCOPE
ANTENNA
INHIBIT
3
4
3
Schematic, G1000
CO-PILOT PTT
VHF - 6T
(AAE)
1
2
1
2
PILOT PTT
4
CODE
2
SCALE
SH
D64-9231-60-02
DWG.NO.
710197
DAIA
DWG.ORIG.
2
1
03
1
06
Confidential
OF
-
REV
A
B
C
D
E
F
A
B
C
D
E
F
8
7
8
RS 485 2 A
RS 485 2 B
11
16
74
75
77
76
+12V TRANSDUCER POWER
DIGITAL IN 1A
DIGITAL IN 2A
DIGITAL IN 4A
DIGITAL IN 3A
74
46
47
62
63
14
ANALOG IN 10 HI
ANALOG IN 5 HI
ANALOG IN 5 LO
ANALOG IN 6 HI
ANALOG IN 6 LO
+10V TRANSDUCER POWER
45
12
ANALOG IN 4 LO
TRANSDUCER LO (GND)
24332B24BL
36
24332A24BL
30112A22
30114A22
30115A22N
SIGNAL GROUND 32
30111A22N
30110A22
24332B24WH
35
24332A24WH
31270A22
27307A22N
43
DISCRETE IN* 20
SIGNAL GROUND 78
8
30422A20
13
TRANSDUCER POWER OUT LO
44
30117A22BL
47
ANALOG / CURR MON IN 1A HI
30117A22WH
ANALOG/CURR MON IN 2 A HI 46
ANALOG/CURR MON IN 2 A LO
7
REF D60-9227-30-01
J2418
30117B22WH
30117B22BL
19
20
18
REF D60-9231-00-02
38
24332B24OR
37
24332A24OR
P2418
31
33
24331B24BL
30
24331A24BL
24331B24OR
24331B24WH
32
24331A24OR
24331A24WH
31031A22BL
31031A22WH
31030A22BL
31030A22WH
30113A22N
S
GS IP-1
3A
HI
GS IP-1
GS IP-1
HEATER
Aircraft
Industries GmbH
Diamond
DE- ICE POWER
1,5 - 192 OHMS
DE-ICE FLUID LEVEL
OUT LO
OUT HI
V+
RH ALT AMPS SENSOR
OUT LO
OUT HI
V+
LH ALT AMPS SENSOR
RH BUS VOLTS
LH BUS VOLTS
GS IP-18
PROJECT
NOT POWERED
28V (POWERED)
REF D60-9230-30-01
HEATER
STALL WARNING HEATER
AMPS SENSOR
GS IP-18
3A
3A
REF D60-9230-30-01
28004D22WH
28004D22OR
28004D22BL
28002D22WH
28002D22OR
28002D22BL
28003D22WH
28003D22OR
28003D22BL
28001D22WH
28001D22OR
28001D22BL
74002D22
74000D22
PITOT HEAT AMPS
SENSOR
37
34
P2401
P2400
P2420
P2419
6
2
P3024
BLK
3
1
WHT
2
BLK
3
P7751
RED
WHT
2
1
P7750
RED
1
GS IP-1
3A
HI
28004C22WH
28
31
35
36
28
28004C22BL
28004C22OR
25
27
30
14
26
37
34
29
28002C22OR
28002C22WH
16
3A
P2415
3A
J2401
8
36
35
17
28002C22BL
30013A22
DISCRETE IN* 3 76
P702
P2422
15
3A
DISCRETE IN* 2 71
4
J2422
30012A22
SIGNAL GROUND 19
SIGNAL GROUND
DISCRETE IN *1 70
44
11
TRANSDUCER LO (GND)
ANALOG IN 4 HI
42
43
ANALOG IN 3 HI
ANALOG IN 3 LO
S
S
S
72
ANALOG IN 9 HI
S
51
31014A22BL
31014A22WH
50
31015A22BL
31015A22WH
ENGINE TEMP ANALOG IN 8 HI
S
J2415
28004A22WH
30011A22
28004B22WH
28
31
28004B22BL
28004B22OR
30
28002B22WH
29
28002A22WH
17
14
28004A22BL
28002B22OR
16
28002A22OR
28004A22OR
28002B22BL
15
28002A22BL
ENGINE TEMP ANALOG IN 8 LO
ANALOG IN 7 HI
P2404
26
28003B22WH
26
28003A22WH
28003C22WH
28
29
27
29
28003C22BL
28003C22OR
17
28003B22BL
28003B22OR
5
7
28001C22OR
28001C22WH
6
28001C22BL
28
14
28001B22WH
J2400
24 GEA RS 485 1 B
23 GEA RS 485 1 A
27
16
28001B22OR
P2421
6
6
NO. 2 GIA63
INTEGRATED AVIONICS
24 GEA RS 485 1 B
2P603
J2420
J2419
NO. 1 GIA63
INTEGRATED AVIONICS
6
23 GEA RS 485 1 A
1P603
74002C22
74000C22
17
15
28001B22BL
GS IP-16
P2422
P2421
28003A22BL
14
J2421
77011C24BL
56
57
77011C24WH
55
P2402
77010C24BL
5A
77010C24WH
28
32
50
ENG INST LH MAIN
BUS
J2422
J2421
12
74002B22
74000B22
11
P2413
P2404
P2402
7
28003A22OR
28001A22WH
16
28001A22OR
J2404
J2402
15
30010A22
S
S
S
S
S
32
50
J2413
J2404
J2402
28001A22BL
REF D60-9231-00-01
77011A24BL
77011A24WH
64
49
48
ENGINE TEMP ANALOG IN 7 HI
ENGINE TEMP ANALOG IN 7 LO
66
ANALOG IN 8 HI
P701
37
42
SIGNAL GROUND
TRANSDUCER PWR OUT LO
DISCRETE IN 19A
6
RS 485 1 B
S
5
RS 485 1 A
P702
77010A24BL
20
POWER GROUND
S
77010A24WH
35
AIRCRAFT POWER 1
77015A22
77016A22N
37
AIRCRAFT POWER 1
74002A22
74000A22
24
22
P701
ANALOG IN 2 HI
ANALOG IN 1 HI
GEA71
ENGINE/AIRFRAME
Confidential
5
28V (STARTER POWERED)
3A
4
2
1
3
J2804
1
2
3
J2802
4
2
1
3
1
2
3
J2806
1
2
3
J2805
FUEL LEVEL LEFT
LONG RANGE
GROUND
OUT HI
EXCITATION
5
TITLE
FUEL LEVEL RIGHT
LONG RANGE
GROUND
OUT HI
EXCITATION
DA 42 NG
28V
28V
28004E22WH
28004E22OR
28004E22BL
OUT HI
EXCITATION
FUEL LEVEL RIGHT
GROUND
28003E22WH
28003E22OR
28003E22BL
OUT HI
1
J2803
EXCITATION
FUEL LEVEL LEFT
GROUND
STARTER NOT POWERED
28V (STARTER POWERED)
STARTER NOT POWERED
2
3
J2801
RH START INITIATE
LH START INITIATE
49
31027A22N
5
1
TEST
J2415
32033A22N
26104A22N
43
41
42
40
41
10
22
33
25
24
40
6
5
37
38
39
51
52
43
5
20
25
32
12
11
37
38
39
P2415
P2404
4
3
31027B22N
31026B22
31025B22N
31038B22
77404B22
26103B22
26101B22
31022B22
31006B22
31037B22
31034B22
31017B22N
31016B22
31200B22WH
31200B22BL
77403B22
26102B22
26100B22
31002B22
31004B22
31036B22
31032B22
31019B22N
31018B22
31300B22WH
31300B22BL
Schematic, G1000
SIGNAL GROUND 34
31026A22
31038A22
77404A22
REF LH
4
REF D60-9232-00-01
2
26103A22
26101A22
31022A22
31006A22
31037A22
GS IP-11
31035A22N
31034A22
GS IP-xx
31009A22N
31025A22N
DISCRETE IN 4 A 63
J2404
32033A22N
26104A22N
REF
31007A22
D64-9227-40-03x01
31017A22N
31016A22
31200A22WH
31200A22BL
5
1
TEST
DISCRETE IN 3 A 62
41
30
28
58
S
77403A22
REF RH
4
REF D60-9232-00-01
2
26102A22
26100A22
31002A22
31004A22
31036A22
GS IP-10
31033A22N
31032A22
GS IP-xx
31008A22N
REF
31005A22
D64-9227-40-02x01
31019A22N
31018A22
31300A22WH
31300A22BL
SIGNAL GROUND 33
DISCRETE IN 18 A
DISCRETE IN 16 A
DISCRETE IN 14 A
ANALOG IN 4 A HI
71
36
SIGNAL GND
DISCRETE IN 8 A
65
51
DISCRETE IN 6 A
CURR MON IN 4 A LO
50
32
CURR MON IN 4 A HI
61
SIGNAL GND
39
DISCRETE IN 2 A
54
55
SIGNAL GROUND
40
29
27
56
66
35
ANALOG IN 2A HI
ANALOG IN 2A LO
DISCRETE IN 17 A
DISCRETE IN 15 A
DISCRETE IN 13 A
ANALOG IN 3 A HI
DISCRETE IN 7 A
SIGNAL GND
64
CURR MON IN 3 A LO
DISCRETE IN 5 A
48
31
60
52
53
38
CURR MON IN 3 A HI
SIGNAL GND
DISCRETE IN 1 A
ANALOG IN 1A HI
ANALOG IN 1A LO
SIGNAL GROUND
S
3
P2402
J2402
4
ENGINE / AIRFRAME P702
GEA71
J2811
J2810
J2422
J2421
37
38
1
2
1
2
41
4
22
33
25
24
40
6
5
39
37
38
51
4
43
5
20
25
32
12
11
39
J2419
J2420
31038C22
31027C22N
31026C22
31025C22N
CODE
10
9
23
24
25
10
9
11
12
13
8
4
26
9
P2401
P2419
J2420
8
4
26
9
31037D22
77404D22
26103D22
26101D22
31022D22
ON
SCALE
LOW
REF D60-9228-11-01
SH
1
04
LOW
28V
28V
RELAY NOT
POWERED
Confidential
06
-
REV
RELAY NOT
POWERED
28V (POWERED)
OF
RH ENGINE WATER
OK
FIRE
RH ENGINE FIRE
OK
RH START REQUEST
FAIL
RH ALT WARNING
OK
RH AUX FUEL XFER
(MOTOR)
TO AUX FUEL
VALVE
REF D60-9228-11-01
OK
AUX FUEL LEVEL RIGHT
LOW
LOW
28V
28V
28V (POWERED)
MAIN FUEL LEVEL RIGHT
OK
RIGHT FUEL
TEMP SENSOR
LOW
LH ENGINE WATER
OK
FIRE
LH ENGINE FIRE
OK
LH START REQUEST
FAIL
LH ALT WARNING
OK
LH AUX FUEL XFER
(MOTOR)
TO AUX FUEL
VALVE
REF D60-9228-10-01
OK
AUX FUEL LEVEL LEFT
LOW
D64-9231-60-02
RH FUEL XFR SWITCH
OFF
OFF
1
LEFT FUEL
TEMP SENSOR
1
MAIN FUEL LEVEL LEFT
OK
REF D60-9228-10-01
2
2
1
J3102
31016D22
31017D22N
28011A20
ON
1
J3110
31200D22WH
31200D22BL
77403D22
26102D22
26100D22
31002D22
28010A20
2
2
J3109
1
31019D22N
J3101
31018D22
31300D22WH
31300D22BL
LH FUEL XFR SWITCH
P2420
28015B22
TO AUX FUEL
RELAY
REF D60-9228-11-01
P2420
J2401
J2419
31036D22
TO AUX FUEL
RELAY
REF D60-9228-10-01
DWG.NO.
2
P2400
28012B22
P2419
J2400
710197
DAIA
DWG.ORIG.
P2811
P2810
77404C22
26103C22
26101C22
31022C22
31006C22
31037C22
5
10
31017C22N
31016C22
31200C22WH
31200C22BL
31034C22
28015C22
REF D60-9228-10-01
P2422
77403C22
26102C22
26100C22
31002C22
31004C22
31036C22
5
2
10
31019C22N
31018C22
31300C22WH
31300C22BL
31032C22
28012C22
REF D60-9228-10-01
P2421
3A
3A
A
B
C
D
E
F
A
B
C
D
E
F
25
39
10
9
40
14
29
26
41
11
13
28
21
35
6
15
30
RS 485 IN A
RS 485 IN B
RS 232 OUT 2
MAGNETOMETER POWER OUT
MAGNETOMETER GROUND
ARINC 429 OUT 1 A
ARINC 429 OUT 1 B
RS 232 OUT 1
SIGNAL GROUND
RS 232 IN 1
ARINC 429 OUT 2 A
ARINC 429 OUT 2 B
RS 232 OUT 4
SIGNAL GROUND
RS 232 IN 4
ARINC 429 IN 1 A
ARINC 429 IN 1 B
17
29
30
11
12
10
1
21
40
60
POWER GROUND
ARINC 429 OUT 2 A
ARINC 429 OUT 2 B
RS 232 OUT 1
AIRCRAFT GROUND
RS 232 IN 1
CONFIG MODULE GROUND
CONFIG MODULE POWER
CONFIG MODULE DATA
CONFIG MODULE CLOCK
8
55
AIRCRAFT POWER 1
2
3
4
26
27
ARINC 429 OUT 1 A
ARINC 429 OUT 1 B
TEMP PROBE POWER OUT
TEMP PROBE IN HI
TEMP PROBE IN LO
42
41
ARINC 429 OUT 1 B
ARINC 429 OUT 1 A
P741
22
POWER GROUND
GDC74
AIR DATA
18
AIRCRAFT POWER 1
P771
1
17
16
31
GRS77
AHRS
8
CONFIG MODULE POWER
CONFIG MODULE DATA
CONFIG MODULE CLOCK
Confidential
BLK
RED
YEL
WHT
S
S
S
S
S
S
S
S
S
S
S
S
34902E22
BLK
RED
YEL
WHT
34902B22
34900A22
31203C24WH
31203C24BL
31203C24OR
34909B24WH
34909B24BL
34908B24BL
34908B24WH
34908A24WH
34908A24BL
34907A24OR
34907A24BL
34907A24WH
34906A24WH
34906A24BL
34905A24WH
34905A24BL
34905A24OR
34904A24WH
34904A24BL
1
4
3
2
GND
VCC
DATA
CLK
7
34911B24OR
34911B24BL
34911B24WH
34910B24WH
34910B24BL
GS IP-3
51
48
49
50
33
31
32
6
4
5
J2403
0,5Ω, 25W
J2404
J2413
P2403
GS AVB
3.2
34700E24WH
34700E24OR
34700E24BL
34901A22N
GND
VCC
DATA
CLK
34903A22N
34701E24WH
34701E24BL
53V
0.499 Ω 20W
1
4
3
2
7
8
9
14
P2403
LH MAIN
BUS
34911A24OR
34911A24BL
34911A24WH
34910A24WH
34910A24BL
5A
ADC
31203B24WH
31203B24BL
31203B24OR
34909A24WH
34909A24BL
4
1
2
3
Industries GmbH
Aircraft
J3122
34700C24WH
34700C24OR
34700C24BL
34701C24WH
34701C24BL
8
9
6
15
21
16
5
23
17
22
MAIN ARINC 429 IN 5 A
MAIN ARINC 429 IN 5 B
12
13
PROJECT
MAIN RS 232 IN 6
SIGNAL GROUND
MAIN RS 232 OUT 6
P2401
POWER
SENSE
LOW
34700A24WH
34700A24OR
34700A24BL
34701A24WH
34701A24BL
3
8
9
6
1
4
2
5
P441
GTP 59
OAT PROBE
J441
DA 42 NG
NO. 2 GIA63
INTEGRATED AVIONICS
31203A24WH
31203A24BL
31203A24OR
MAIN RS 232 IN 1
SIGNAL GROUND
MAIN RS 232 OUT 1
MAIN RS 232 IN 6
SIGNAL GROUND
MAIN RS 232 OUT 6
56
57
58
14
15
2P603
12
13
41
42
43
56
57
58
14
15
34700B24WH
34700B24OR
34700B24BL
34701B24WH
34701B24BL
J2401
5
NO. 1 GIA63
INTEGRATED AVIONICS
P2428
LH MAIN
BUS
1P603
7
4
6
3
12
P3122
J2428
Diamond
P2416
5A
AHRS
7
4
6
3
34700D24WH
34700D24OR
34700D24BL
34701D24WH
34701C24BL
J2416
11
13
12
CONFIG MODULE
012-00605-00
24
23
22
21
20
18
19
34902A22
34903B22N
GS IP-3
12
J2403
9
7
8
28
27
34900B22
P2404
P2413
J2403
P2403
CONFIG MODULE
012-00605-00
6
TITLE
FAN FAIL
2
SAFE 128
MFD FAN
FAN FAIL
GDL69
DATA LINK
ETHERNET IN A
ETHERNET IN B
ETHERNET OUT A
ETHERNET OUT B
OPTIONAL
NO. 2 GIA63
INTEGRATED AVIONICS
ETHERNET OUT A
ETHERNET OUT B
ETHERNET IN A
ETHERNET IN B
REVERSIONARY MODE 2
REV MOD COMMON 2
GMA1347
AUDIO PANEL
ARINC 429 OUT 3 A
ARINC 429 OUT 3 B
ARINC 429 OUT 3 A
ARINC 429 OUT 3 B
GRS77
AHRS
ARINC 429 OUT 3 A
ARINC 429 OUT 3 B
GDC74
AIR DATA
ARINC 429 OUT 3 A
ARINC 429 OUT 3 B
NO. 1 GIA63
INTEGRATED AVIONICS
ETHERNET IN B
ETHERNET IN A
ETHERNET OUT B
ETHERNET OUT A
2
23
22
25
24
P691
2
3
76
77
2P603
56
57
P3472
33
19
12
27
P771
47
48
32
33
P741
77
76
3
2
1P603
GMA1347
P3472
AUDIO PANEL
REVERSIONARY MODE 1 36
REV MOD COMMON 1 37
SAFE 128
PFD FAN
3
4
3
Schematic, G1000
RS 232 IN
+12VDC POWER
POWER GROUND
RS 485 OUT B
GMU44
MAGNETOMETER
RS 485 OUT A
RS 485 OUT B
4
S
S
S
S
S
S
S
S
S
LH MAIN
BUS
21006A22
5A
2
1
4
3
5
P2413
J2403
40
39
42
41
43
0,5Ω, 25W
710197
2
21006A22
31158B24WH
31158B24OR
31158B24GR
31158B24BL
31155A22
31156A22N
GS IP-10
31150B24WH
31150B24OR
31150B24GR
31150B24BL
33002B22
31153A24WH
31153A24BL
1
4
3
2
31102A24WH
31102A24OR
31102A24GR
31102A24BL
31102A24BL
31102A24GR
31102A24OR
31102A24WH
S
S
S
S
S
S
ETHERNET OUT 1 B
ETHERNET OUT 1 A
ETHERNET IN 1 B
ETHERNET IN 1 A
CONFIG MODULE POWER
CONFIG MODULE DATA
CONFIG MODULE CLOCK
ETHERNET OUT 2 A
ETHERNET OUT 2 B
ETHERNET IN 2 A
ETHERNET IN 2 B
ETHERNET OUT 2 B
ETHERNET OUT 2 A
ETHERNET IN 2 B
ETHERNET IN 2 A
ETHERNET IN 1 A
ETHERNET IN 1 B
ETHERNET OUT 1 A
ETHERNET OUT 1 B
ETHERNET OUT 3 A
ETHERNET OUT 3 B
ETHERNET IN 3 A
ETHERNET IN 3 B
SCALE
SH
1
05
06
-
REV
Confidential
OF
14 FAN MONITOR VALID
10
11
12
13
35 AIRCRAFT POWER 1
27 POWER GROUND
4
5
2
3
57 CDU ID PROG 3
59 LIGHTING BUS HI
58 REVERSIONARY MODE SEL 1
38 AIRCRAFT GROUND
17 ARINC 429 IN 2 B
16 ARINC 429 IN 2 A
7
6
9
8
18 ARINC 429 IN 1 A
19 ARINC 429 IN 1 B
NO. 2 GDU1040 MFD
18 ARINC 429 IN 1 A
19 ARINC 429 IN 1 B
6
7
8
9
17 ARINC 429 IN 2 B
16 ARINC 429 IN 2 A
1
23
22
43
35 AIRCRAFT POWER 1
27 POWER GROUND
59 LIGHTING BUS HI
3
2
5
4
58 REVERSIONARY MODE SEL 1
38 AIRCRAFT GROUND
2P10001
S
S
S
BLK
RED
YEL
WHT
S
S
NO. 1 GDU1040 PFD
1
14 FAN MONITOR VALID
1P10001
D64-9231-60-02
DWG.NO.
J2413
2
1
4
3
5
J2414
REF D60-9233-10-07
31152A24BL
21
22
31151A24WH
31151A24BL
31152A24WH
31104B24WH
31104B24BL
31103A24WH
31103A24BL
CONFIG MODULE
012-00605-00
GND
VCC
DATA
CLK
31105A22
31106A22N
33000B22
31100B24WH
31100B24OR
31100B24GR
31100B24BL
31101A24WH
31101A24BL
21007A22
20
J2414
56
57
55
31155B22
P2414
P2414
P2403
REF D60-9233-10-07
DAIA
CODE
J2413
0,5Ω, 25W
P2413
DWG.ORIG.
31158A24WH
31158A24OR
31158A24GR
31158A24BL
RH MAIN
BUS
31150A24WH
31150A24OR
31150A24GR
31150A24BL
31153A24WH
31153A24BL
31152A24WH
31152A24BL
31104A24WH
31104A24BL
31151A24WH
31151A24BL
MFD
GS IP-8
31105B22
31103A24WH
31103A24BL
5A
PFD
31100A24WH
31100A24OR
31100A24GR
31100A24BL
31101A24WH
31101A24BL
21007A22
2
A
B
C
D
E
F
A
B
C
D
E
F
Confidential
8
8
23
24
25
26
MAIN VERT DEV +UP
MAIN VERT DEV +DN
MAIN VERTICAL +FLAG
MAIN VERTICAL -FLAG
62
MAIN KING SERIAL DME REQ
ANNUNCIATE* 15
NO. 1 GIA63
INTEGRATED AVIONICS
ANNUNCIATE* 15
71
70
MAIN ARINC 429 OUT 1 A
MAIN ARINC 429 OUT 1 B
38
1P604
38
2P604
42
10
11
27
28
RS 485/422 IN A
RS 485/422 IN B
SIGNAL GROUND
36
37
RS 485/422 OUT A
RS 485/422 OUT B
2P603
59
60
10
11
12
ADF X / COS
ADF Y / COS
ADF Z (GROUND)
MAIN KING SERIAL DME CLK
48
46
47
49
COURSE DATUM HI
HEADING DATUM HI
HEADING DATUM LO
COURSE DATUM LO
MAIN KING SERIAL DME DATA
67
68
69
70
71
72
73
74
75
DISCRETE OUT *1B
DISCRETE OUT *2B
DISCRETE OUT *3B
DISCRETE OUT *4B
DISCRETE OUT *5B
DISCRETE OUT *6B
DISCRETE OUT *7B
DISCRETE OUT *8B
DISCRETE OUT *9B
2P606
68
DISCRETE OUT *2A
19
20
17
18
MAIN LATERAL +FLAG
MAIN LATERAL -FLAG
2P605
7
27
25
2P604
MAIN LATERAL DEV +LEFT
MAIN LATERAL DEV +RIGHT
DISCRETE IN *1
ANNUNCIATE *4
ANNUNCIATE *2
NO. 2 GIA63
INTEGRATED AVIONICS
S
S
S
S
S
S
S
S
S
34426A22
P1
ANTENNA
AVIDYNE
9900BX
OPTIONAL
7
REMOTE MUTE
34302B22
P1
34390A142
34303B22N
Industries GmbH
Aircraft
34414A142
6
5
DA 42 NG
REF GTX 33 XPDR (COUPLER)
AVIONICS
BUS
GS IP
3A
TAS
BOTTOM ANTENNA
TOP ANTENNA
REF D60-9232-00-01
REF D60-9230-30-01
PROJECT
34410A142
34412A142
J4
34413A142
J2
34411A142
J3
34427A22
34428A22
34420A22
34421A22N
2
10
34420B22
J2403
AVIONICS
BUS
GS IP-11
3A
DME
5
34421B22N
P2403
34302A22
34303A22N
13
J2413
BP 4
A1
A2
A4
B1
B2
B4
C1
C2
C4
CRS DATUM
2 HDG DATUM
27 HDG/CRS REF
P1401
11
13
14
33
34
20
21
3
5
17
38 MIDDLE MARKER GAIN
9 G/S +UP
10 G/S +DN
BP 1
31 G/S +FLAG
12 G/S -FLAG
J1
Diamond
COUPLER
11 COMPASS VALID
P1402
14
P2413
ILS ENERGIZE
22 NAV +FLAG
23 NAV -FLAG
BP 3
24 NAV +LEFT
25 NAV +RIGHT
7
P1401
44 TRIM FAIL ANNUN
26 GPS SELECT
HONEYWELL
KAP 140 AFCS
P1402
REF D60-9222-10-01
RS-232 RX 2
RS-232 TX 2
RS-232 GROUND 2
5
19
17
18
34425A22
429 RX 1+
429 RX 1SUPPRESSION
22 AWG
N/C
P632
2
3
1
A
P1
REF SHEET 2
TAS +28 VDC POWER 1
RS-232 RX 3
RS-232 TX 3
+28 VDC POWER 2
RS-232 GROUND 3
POWER GROUND 14
POWER GROUND 15
RS-232 RX 4
POWER SWITCH 16
RS-232 TX 4
J1
RS-232 GROUND 4
NO RYAN DISPLAY 15
429 TX+
GEAR POSITION 11
429 TXWEIGHT ON WHEELS 14
7
2.2kΩ, 0.25W
25
23
24
8
9
N/C
N/C
10
11
22
20
21
22 AWG
N/C
P1
12 TX-A
31 TX-B
27 GROUND
P1
BECKER
RA 3502-(01)
ADF RECEIVER
REF D60-9234-50-01
13 RX-A
14 RX-B
OPTIONAL
11 DME ON
34424A22
REF KN 63 DME
34423A24OR
34423A24WH
34423A24BL
34422A24OR
34422A24WH
34422A24BL
34201A24WH
34201A24BL
34200A24WH
34200A24BL
34424A22
REF 9900BX TAS
34305A24
REF GTX 33 XPDR
34512A22
34307A24
34306A24
HONEYWELL
KN 63
P1
DME
A/C POWER
6 DATA BUS
A/C POWER
F CLOCK BUS
A/C GROUND
A/C GROUND
D DME REQUEST
12 GROUND
K SUPPRESSION
17 ADF COS
16 ADF SIN
OPTIONAL
BECKER
AC 3504-(1)
RMI CONVERTER
REF D60-9234-50-01
22069B24WH
22069B24BL
22069B24OR
54
55
56
57
22069A24WH
22069A24BL
22069A24OR
22058B24WH
22058B24BL
22060B22
22061B22
22062B22
22063B22
22064B22
22065B22
22066B22
22067B22
22068B22
22058A24WH
22058A24BL
45
46
47
48
49
50
51
52
53
22056B22
33
34
22056A22
22060A22
22061A22
22062A22
22063A22
22064A22
22065A22
22066A22
22067A22
22068A22
22055B24WH
22055B24BL
31
32
22055A24WH
22055A24BL
22057B24WH
22057B24BL
22054B24WH
22054B24BL
28
29
30
22054A24WH
22054A24BL
35
36
37
38
39
40
22053B22
27
22053A22
REF D60-9222-10-01
22051B22
22052B22
J2414
25
26
P2414
22051A22
22052A22
6
22057A24WH
22057A24BL
34202A22
34203A22
7
G/S ANTENNA
NAV ANTENNA
DISCRETE IN* 12
CAN BUS 2 LO
CAN BUS 2 HI
24
22
2P604
47
49
48
2P603
1P611
2P612
53
55
54
32
30
34
22
20
2P603
2P613
2P614
1P614
1P613
24
1P604
39
30
32
21005A22
S
S
S
77401E22WH
77401E22BL
Wx 500
21008A22
25
24
48
REF D60-9221-20-01
34404A24WH
34404A24BL
34404A24OR
33
31
32
J2413
J2414
J2403
34503A24WH
34503A24BL
34503A24OR
P2413
34400B20WH
34400B20BL
34402A20N
GS IP-2
77405E22WH
77405E22BL
77409A22WH
77409A22BL
77408A22BL
77408A22WH
34691B142
12
13
14
P2414
34502A24WH
34502A24BL
34502A24OR
REF D60-9221-20-01
77409A22BL
77409A22WH
77408A22WH
77408A22BL
23390A400
34190A400
34191A400
34091A400
34090A400
S
S
S
AVIONICS
3A
BUS
S
S
34690B142
23290A400
3
4
3
Schematic, G1000
DISCRETE IN* 12
GIA SYS ID PROGRAM 1
MAIN RS 232 IN 3
MAIN RS 232 OUT 3
SIGNAL GROUND
GPS ANTENNA
COM ANTENNA
MAIN RS 232 IN 5
MAIN RS 232 OUT 5
SIGNAL GROUND
CAN BUS 2 HI
CAN BUS 2 LO
CAN BUS 1 LO
CAN BUS 1 HI
NAV ANTENNA
G/S ANTENNA
NO. 2 GIA63
INTEGRATED AVIONICS
TITLE
53
55
54
1P603
1P611
2P612
CAN BUS 1 HI 20
CAN BUS 1 LO 22
MAIN RS 232 IN 5
MAIN RS 232 OUT 5
SIGNAL GROUND
GPS ANTENNA
COM ANTENNA
NO. 1 GIA63
INTEGRATED AVIONICS
4
P2403
REF. SHEET 3
1
5
OPTIONAL
GOODRICH WX-500
STORMSCOPE
CODE
2
34500A22
34501A22N
ORANGE
RED
BROWN
BLACK
YELLOW
GREEN
BLUE
DRAIN
S
S
SCALE
SH
A
H
G
F
J
B
D
C
J3441
1
06
25 RS 232 OUT 2
24 RS 232 IN 2
58 SIGNAL GROUND
AIRCRAFT POWER 1
POWER GROUND
21
SUPPRESSION
27
31
1
GTX33
MODE S XPDR
ANTENNA
23 RS 232 OUT 1
22 RS 232 IN 1
51 SIGNAL GROUND
P3301
P3302
D64-9231-60-02
34503A24WH
34503A24BL
34503A24OR
P2413
34512A22
34502A24WH
34502A24BL
34502A24OR
OPTIONAL
XPDR
COUPLER
DWG.NO.
3
16
17
2
15
4
14
1
J2
34
35
710197
DAIA
DWG.ORIG.
6 CONFIG. GROUND
5 RS 232 GROUND
22 INHIBIT
J2
X LOOP
+12V
SENSE
ANT REF
-12V
Y LOOP
ANT TEST
ANT COM
AIRCRAFT POWER
AIRCRAFT GROUND
20 RS 232 TX
8 RS 232 RX
3 TOP ANT.
J3
J1
J2413
REF KN 63 DME
34500B22
34501B22N
GS IP-11
REF D64-9277-40-03x01
5A
XPDR
REF D64-9277-40-02x01
LH MAIN
BUS
34400A20WH
34400A20BL
77405C22WH
77405C22BL
77401C22WH
77401C22BL
34410A142
REF 9900BX TAS
34590A142
2
06
Confidential
OF
-
REV
A
B
C
D
E
F
A
B
C
D
E
F
Confidential
8
8
20
120Ω
7
DIAGNOSTIC
2
7
10
7
12
9
ON
OFF
77401CC22BL
77401CC22WH
77401C22BL
77401C22WH
REF D64-9231-60-02
24300A14
24360A20
ENGINE MASTER LH
22 AWG
11
8
VOTER LH
22 AWG
INSTRUMENT PANEL
7
REF D64-9231-60-02
B
U
S
E
C
U
L
H ECU A
ECU
TEST LH
5A
2A
2
1
3
DIMENSIONS
J2402
2
5
1
4
2
6
3
5
6
2 DECIMAL
1DECIMAL
DECIMAL
ANGLE
RAD
u0,25
u0,5
u1
u1°
u0,5
FINISH
IN
MICROMETER
3.2
A3
FORMAT
METRIC
77401B22BL
77401B22WH
31005B22
24300B14
24361B22
24362B22
74010B22
24321B22WH
24321B22BL
1
1
4
2
6
3
5
2
1
3
GS-RP
GS-RP
CLASSIFICATION:
5
4
APPROVED:
SYSTEM:
MANUF.:
STRESS:
QA:
CHECKED:
DRAWN
Aircraft
Zeillinger
N/A
N/A
N/A
N/A
Kowarsch
Moise
Industries GmbH
Diamond
4.7kΩ
74011A16
74012A16
74013A16
74014A16
24342A20N
24343A20N
24344A20N
24345A20N
4.7kΩ
31005C22
24327A20
24328A20
24329A20
24361C22
24362C22
74010C22
32050B22
DEPARTMENT
74016A22N
77401A22BL
77401A22WH
50A
GS-RP
74015A22N
1
24321C22WH
24321C22BL
77402A22OR
77402A22WH
77402A22BL
77420A22OR
77420A22WH
77420A22BL
SOLID EDGE V18
D64-9277-40-02e.dft
FILENAME
SOFTWARE:
NO
DE-S-10-00003
NONE
4
ENGINE NACELLE
REF D64-9224-30-01 24004B4
GS-RP
24300C14
J2421
2
5
10
12
14
6
7
8
J2427
J3205
J2423
5
REF D64-9230-30-01
32050A22
77402B22OR
77402B22WH
77402B22BL
77420B22OR
77420B22WH
77420B22BL
FUSELAGE
31005A22
REF D64-9261-20-01
2A
24361A22
24362A22
74010A22
6
7
8
10
12
14
J2417
POWER
LEVER
SENSOR
ECU A
REF D64-9261-20-01
24321A22WH
24321A22BL
6
2
4
3
2
4
3
12
23
24
23
24
3
SIGN
DATE
13.05.09
13.05.09
CPC 1
GPC Caution Lamp
CAN Low
CAN High
GPC Power Supply
GPC Power Supply
GPC Power Supply
GPC Power Supply
ECU A GND
ECU A GND
ECU A GND
ECU A GND
GPC Annun. Lamp
ECU A Power Supply
ECU A Power Supply
ECU A Power Supply
Engine Master
Engine Master
Glow Enable
Selftest Signal
Selftest GND
A/C on Ground
A/C on Ground
Sensor Supply
Sensor Signal
Sensor GND
Sensor Supply
Sensor Signal
Sensor GND
ENGINE HARNESS
OÄM 42-171
FIRST RELEASE
2
SCALE
NTS
SH
1
01
Confidential
OF
-
REV
02
D64-9277-40-02X01
DWG.NO.
710197
DAIA
DWG.ORIG.
CODE
DA 42 NG
APPROVAL
13.05.09 SEE TB
DATE
1
Schematic, LH ECU
PROJECT
TITLE
REVISION
DESCRIPTION
2
32
8
32
7
28
28
8
27
27
7
26
26
25
22
22
25
21
21
29
19
29
18
19
17
18
17
31
11
31
12
14
13
30
11
14
13
30
20
6
20
5
6
1
ZONE
ALL ALL
SH
EMI FILTER
(OPTIONAL WITH ADF)
-
REV
5
1
CPC 1
3
A
B
C
D
E
F
A
B
C
D
E
F
Confidential
8
8
B
U
S
E
C
U
L
H
7.5
FUEL
PUMP B
7.5
FUEL
PUMP A
20
ECU B
7
4
1
6
3
GS-IP
GS-IP-22
7
GS-IP-3
OFF
ON
ON
OFF
FUEL PUMPS LH
28036A22N
28032A20
GS-IP-17
28030A20
24301A14
24363A20
ENGINE MASTER LH
24325A22BL
24325A22WH
24322A22WH
24322A22BL
INSTRUMENT PANEL
VOTER LH
5
2
22 AWG
5A
Aircraft
Industries GmbH
Diamond
4
27
28
21
22
9
16
17
PROJECT
28037B22
28032B20
28030B20
24301B14
24364B22
24365B22
24325B22BL
24325B22WH
24322B22WH
24322B22BL
77410B22OR
77410B22WH
77410B22BL
77421B22OR
77421B22WH
77421B22BL
FUSELAGE
6
4
27
28
21
22
9
16
17
23
24
25
29
30
31
J2427
8
12
9
14
10
13
J2423
28037A22
REF D64-9261-20-01
2A
24364A22
24365A22
2A
REF D64-9261-20-01
1
4
2
6
3
5
23
24
25
29
30
31
J2417
POWER
LEVER
SENSOR
ECU B
6
GS-RP
28037C22
28032C20
28030C20
GS-RP
5
85
86
30
TITLE
85
87
FUEL PUMP B
RELAY LH
87A
86
87
FUEL PUMP A
RELAY LH
87A
24346A20N
24347A20N
24348A20N
24349A20N
24301C14
51801A10
24364C22
24365C22
24325C22BL
24325C22WH
24322C22WH
24322C22BL
30
4
2
GS-RP
28033B20
28035B20N
1
28033A20
28035A20N
J2806
2
GS-RP
28031B20
28034B20N
1
J2805
28039A22
28038A22
24333A20
24334A20
24335A20
28034A20N
2
51802A20
28031A20
5A
3
LH FUEL
PUMP B
LH FUEL
PUMP A
4
3
Schematic, LH ECU
ENGINE NACELLE
77410A22OR
77410A22WH
77410A22BL
77421A22OR
77421A22WH
77421A22BL
DA 42 NG
5
DWG.ORIG.
CODE
2
CPC 2
Fuel Pump Output B
Fuel Pump Output A
ECU B GND
ECU B GND
ECU B GND
ECU B GND
ECU B Power Supply
ECU B Power Supply
ECU B Power Supply
Engine Master
Engine Master
ECU A
ECU B
Voter
Signal Input
Sensor Supply
Sensor Signal
Sensor GND
Sensor Supply
Sensor Signal
Sensor GND
ENGINE HARNESS
1
SCALE
1:1
SH
1
02
02
-
REV
Confidential
OF
D64-9277-40-02X01
710197
DAIA
2
DWG.NO.
3
2
30
3
30
28
29
27
29
28
25
24
23
27
25
24
23
18
14
14
17
13
13
18
16
17
15
16
9
9
15
8
10
8
10
12
12
7
11
CPC 2
11
7
EMI FILTER
(OPTIONAL WITH ADF)
2
A
B
C
D
E
F
A
B
C
D
E
F
Confidential
8
8
20
ECU A
24302A14
120Ω
7
DIAGNOSTIC
2
7
10
7
12
9
ON
OFF
77405CC22BL
77405CC22WH
77405C22BL
77405C22WH
REF D64-9231-60-02
24370A20
ENGINE MASTER RH
22 AWG
11
8
VOTER RH
22 AWG
INSTRUMENT PANEL
7
REF D64-9231-60-01
B
U
S
E
C
U
R
H
ECU
TEST RH
5A
2A
2
1
3
DIMENSIONS
J2404
2
1
26
32
33
1
4
2
6
3
5
6
2 DECIMAL
1DECIMAL
DECIMAL
ANGLE
RAD
u0,25
u0,5
u1
u1°
u0,5
FINISH
IN
MICROMETER
3.2
A3
FORMAT
METRIC
77405B22BL
77405B22WH
31007B22
24302B14
24371B22
24372B22
74020B22
24323B22WH
24323B22BL
1
2
1
3
1
4
2
6
3
5
GS-RP
GS-RP
CLASSIFICATION:
SOLID EDGE V18
5
4
APPROVED:
SYSTEM:
MANUF.:
STRESS:
QA:
CHECKED:
DRAWN
Aircraft
Zeillinger
N/A
N/A
N/A
N/A
Kowarsch
Moise
Industries GmbH
Diamond
4.7kΩ
74021A16
74022A16
74023A16
74024A16
24350A20N
24351A20N
24352A20N
24353A20N
31007C22
24336A20
24337A20
24338A20
24371C22
24372C22
74020C22
32051B22
DEPARTMENT
74026A22N
77405A22BL
77405A22WH
50A
GS-RP
74025A22N
1
24323C22WH
24323C22BL
77406A22OR
77406A22WH
77406A22BL
77422A22OR
77422A22WH
77422A22BL
D64-9277-40-03X01.dft
FILENAME
SOFTWARE:
NO
DE-S-10-00003
NONE
4
ENGINE NACELLE
REF D64-9224-30-01 24004B4
GS-RP
24302C14
J2422
2
1
26
32
33
34
35
36
J2428
J3206
P2425
5
REF D64-9230-30-01
32051A22
77406B22OR
77406B22WH
77406B22BL
77422B22OR
77422B22WH
77422B22BL
FUSELAGE
31007A22
REF D64-9261-20-01
2A
24371A22
24372A22
74020A22
34
35
36
J2416
POWER
LEVER
SENSOR
ECU A
REF D64-9261-20-01
24323A22WH
24323A22BL
6
2
4
3
2
4
3
31
23
24
23
24
3
SIGN
DATE
13.05.09
CPC 1
GPC Caution Lamp
CAN Low
CAN High
GPC Power Supply
GPC Power Supply
GPC Power Supply
GPC Power Supply
ECU A GND
ECU A GND
ECU A GND
ECU A GND
GPC Annun. Lamp
ECU A Power Supply
ECU A Power Supply
ECU A Power Supply
Engine Master
Engine Master
Glow Enable
Selftest Signal
Selftest GND
A/C on Ground
A/C on Ground
Sensor Supply
Sensor Signal
Sensor GND
Sensor Supply
Sensor Signal
Sensor GND
ENGINE HARNESS
OÄM 42-171
FIRST RELEASE
2
SCALE
1:1
SH
1
01
Confidential
OF
-
REV
02
D64-9277-40-03X01
DWG.NO.
710197
DAIA
DWG.ORIG.
CODE
DA 42 NG
APPROVAL
13.05.09 SEE TB
DATE
1
Schematic, RH ECU
PROJECT
TITLE
REVISION
DESCRIPTION
2
32
8
32
7
28
28
8
27
27
7
26
26
25
22
22
25
21
21
29
19
19
29
18
18
17
12
31
17
11
12
14
13
30
11
14
13
30
20
6
20
5
6
1
ZONE
ALL ALL
SH
EMI FILTER
(OPTIONAL WITH ADF)
-
REV
5
1
CPC 1
3
A
B
C
D
E
F
A
B
C
D
E
F
Confidential
8
8
B
U
S
E
C
U
R
H
4
1
6
3
7.5
FUEL
PUMP B
7.5
FUEL
PUMP A
20
ECU B
VOTER RH
5
2
22 AWG
5A
GS-IP
GS-IP-1
OFF
ON
ON
OFF
7
FUEL PUMPS RH
28046A22N
GS-IP-22
28042A20
GS-IP-11
28040A20
24303A14
24373A20
ENGINE MASTER RH
24326A22BL
24326A22WH
24324A22WH
24324A22BL
INSTRUMENT PANEL
7
28047A22
20
27
28
21
22
14
16
17
Aircraft
Industries GmbH
Diamond
28047B22
28042B20
28040B20
24303B14
24374B22
24375B22
24326B22BL
24326B22WH
24324B22WH
24324B22BL
77407B22OR
77407B22WH
77407B22BL
77423B22OR
77423B22WH
77423B22BL
FUSELAGE
PROJECT
20
27
28
21
22
14
16
17
23
24
25
29
30
31
J2428
P2425
8
12
9
14
10
13
6
REF D64-9261-20-01
2A
24374A22
24375A22
2A
REF D64-9261-20-01
23
24
25
29
30
31
J2416
POWER
LEVER
SENSOR
ECU B
1
4
2
6
3
5
6
GS-RP
5
85
87
86
30
85
87
87A
FUEL PUMP B
RELAY RH
86
87A
FUEL PUMP A
RELAY RH
24354A20N
24355A20N
24356A20N
24357A20N
24303C14
51803A10
24374C22
24375C22
24326C22BL
24326C22WH
24324C22WH
24324C22BL
77407A22OR
77407A22WH
77407A22BL
77423A22OR
77423A22WH
77423A22BL
30
4
TITLE
2
GS-RP
28043B20
28045B20N
1
28043A20
J2808
28045A20N
GS-RP
28041B20
28044B20N
2
28041A20
J2807
28049A22
28048A22
24339A20
24340A20
24341A20
28044A20N
2
51804A20
1
5A
RH FUEL
PUMP B
RH FUEL
PUMP A
3
4
3
Schematic, RH ECU
ENGINE NACELLE
DA 42 NG
28047C22
28042C20
28040C20
GS-RP
5
DWG.ORIG.
13
CODE
2
Fuel Pump Output B
Fuel Pump Output A
ECU B GND
ECU B GND
ECU B GND
ECU B GND
ECU B Power Supply
ECU B Power Supply
ECU B Power Supply
Engine Master
Engine Master
ECU A
ECU B
Voter
Signal Input
Sensor Supply
Sensor Signal
Sensor GND
Sensor Supply
Sensor Signal
Sensor GND
ENGINE HARNESS
1
SCALE
1:1
SH
1
02
02
-
REV
Confidential
OF
D64-9277-40-03X01
710197
DAIA
2
CPC 2
DWG.NO.
3
2
30
3
29
30
28
29
27
28
25
25
27
24
24
23
18
18
23
17
17
14
16
13
14
15
16
9
15
8
10
9
12
10
11
8
12
7
11
7
EMI FILTER
(OPTIONAL WITH ADF)
CPC 2
2
A
B
C
D
E
F

SUPPLEMENTAL AIRPLANE MAINTENANCE

Transcription

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