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Temporary Revision
RACC
DA 42 NG AMM
AIRCRAFT
TEMPORARY REVISION
%
AMM-TR-OÄM 42-193/b
%
supersedes AMM-TR-OÄM 42-193/a
Recirculating Air-Cabin Cooling
(RACC)
%
This Temporary Revision AMM-TR-OÄM 42-193/b is approved in conjunction with the Optional Design
%
Change Advisory OÄM 42-193/n and is valid in conjunction with the Airplane Maintenance Manual
(AMM) until this Temporary Revision has been incorporated into the AMM.
The limitations and information contained herein either supplement or, in the case of conflict, override
those in the AMM.
The technical information contained in this document has been approved under the authority of DOA
No. EASA.21J.052.
Doc. No.
7.02.15
Section
Affected Pages
05-28-50
24a, 24b
21-00-00
1a, 1aa
21-50-00
1a, 2a
21-51-00
1 through 4, 101, 102,
201 through 214
92-00-00
1a, 1aa
Instruction
) Print this document double-sided on yellow paper (odd pages and "a" pages on front sides,
even pages and "aa" pages on reverse sides).
) Insert this cover page as the first page of the AMM.
) Insert the other pages of this Temporary Revision in front of the corresponding AMM pages.
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COVER
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COVER
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DA 42 NG AMM
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AFFECTED CHAPTERS:
CHAPTER 05
TIME LIMITS AND MAINTENANCE CHECKS
Section 05-28
Maintenance Checklist DA 42 NG
Section 05-28-50
Maintenance Checklist Airframe
3. Interior of the Rear Fuselage
A. Interior Structure of the Rear Fuselage
Item 5 is amended to read:
100 hr items marked * apply to US registered airplanes only
Inspection Items, Interior Structure of the Rear
100 200 1000 2000 Time Initials
Fuselage
5.
X*
Examine the RACC air inlets and outlets (if
X
X
X
OÄM 42-193/c or earlier is carried out):
S One air inlet on the bottom.
S Check the air inlet filter for contamination.
S Two air outlets to the LH and RH side of the
upper fuselage.
Examine the RACC air inlets and outlets (if OÄM
42-193/d or later is carried out):
S One air outlet on the bottom.
S Check the RACC compartment ventilation filter
on the LH side fuselage for contamination.
S One air inlet on the LH side of fuselage.
S Check evaporator drain on the bottom for
blockage.
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The following items are added:
100 hr items marked * apply to US registered airplanes only
Inspection Items
5A.
Examine the RACC central unit (if OÄM 42-193 is
100 200 1000 2000 Time Initials
X*
X
X
X
X
X
carried out). Look specially for:
S Insecure attachment of hoses, shrouds and
cables.
S Leakage of hoses.
%
S Cleanness of drain tubes.
%
5B.
Examine the RACC central unit (if OÄM 42-193 is
carried out). Look specially for:
S Defective bonding of the side brackets.
S Incorrect attachment of the mounting panel.
S Lack of mechanical stability of the mounting
panel.
S Insecure attachment of RACC components to the
mounting panel.
S Insecure attachment of hoses, shrouds and
cables.
%
5C.
Perform a Leakage Test.
1 yr.
Item 6 is amended to read:
100 hr items marked * apply to US registered airplanes only
Inspection Items
6.
If OÄM 42-193/c or earlier is carried out:
100 200 1000 2000 Time Initials
X*
X
X
X
Check the compartment fan for incorrect operation.
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RACC
CHAPTER 21
AIR CONDITIONING, HEATING AND VENTILATION
1. General
The second Paragraph is amended to read:
If OÄM 42-193 is carried out, a recirculating air - cabin cooling (RACC) system is installed. Refer to
Section 21-50 (if OÄM 42-193/c or earlier is installed) or Section 21-51 (if OÄM 42-193/d or later is
installed) for more details about the RACC system.
2. Description and Operation
B. Cabin Ventilation/Cooling
The second Paragraph is amended to read:
Refer to Section 21-50 for more details about the RACC system (if OÄM 42-193/c or earlier is
installed).
The following is added:
Refer to Section 21-51 for more details about the RACC system (if OÄM 42-193/d or later is installed).
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The headline of Section 21-50 is amended to read:
Section 21-50-00
Cooling (OÄM 42-193/c or earlier installed)
1. General
The first Sentence is amended to read:
If OÄM 42-193/c or earlier is installed, a recirculating air - cabin cooling (RACC) system is installed.
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RACC
The Section is added:
Section 21-51-00
Cooling (OÄM 42-193/d or later installed)
1. General
If OÄM 42-193/d or later is installed, an improved recirculating air - cabin cooling (RACC) system is
installed. The RACC system is an independent subsystem of the airplane and is electrically powered.
It consists of the central unit (installed aft of baggage compartment) and a control panel (in the cabin,
center console).
2. Description
A. Central Unit
The central unit operates with a refrigerant R134a vapor cycle cooling circuit. The system requires
electrical power (28 V DC, max. 65 A) for operation, which is provided by an additional alternator.
The central unit is subdivided into the following components:
) Compressor assembly (part of refrigerant circuit).
) Condenser assembly (part of refrigerant circuit).
) Evaporator assembly (part of refrigerant circuit).
) Condenser radial fan.
) Evaporator radial fan.
) Electrical control system.
Refer to Figure 1 for a system schematic of the RACC system.
Note:
The refrigerant vapor cooling system is a hermetically sealed and
pressurized circuit and contains the refrigerant R134a.
WARNING:
ALL MAINTENANCE AND REPLENISHMENT WHICH REQUIRES TO
OPEN AND DEPRESSURIZE THE REFRIGERANT CIRCUIT MUST BE
CARRIED OUT BY AUTHORIZED PERSONNEL ACCORDING TO
NATIONAL AND INTERNATIONAL REGULATIONS FOR REFRIGERANT
SYSTEMS.
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DA 42 NG AMM
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Figure 1: RACC System Schematic (OÄM 42-193/d or later is installed)
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RACC
B. Control Panel
The control panel is situated on the center console in the cabin. It is electrically connected to the
RACC controller and provides all necessary elements to control the center unit. An integrated
display shows the preset air temperature.
Refer to Figure 2 for details about the RACC control panel.
Figure 2: RACC Control Panel (if OÄM 42-193/d or later is installed)
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DA 42 NG AMM
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3. Operation
If electrical power is provided to the RACC system, the power status LED on the control panel flashes.
The control panel of the RACC system in the center console allows the crew to control the fan speed
and the cabin temperature. A two digit display shows the preset cabin air temperature in °C. A
push-button is used to set the RACC system to ON (if short depressed; display is illuminated) and OFF
(if pressed and held for approximately one second).
During power-up the software version of the control panel is displayed.
The central unit is located aft of the baggage compartment. The RACC controller is located below the
condenser unit and controls the refrigerant circuit valves and the compressor with respect to the
control panel settings. With the control panel set to ON and a temperature preset lower than the
current cabin air temperature, the refrigerant cooling circuit is activated. An electrically powered
compressor takes the low-pressure low-temperature refrigerant gas and compresses it to a hightemperature gas. A pressure switch on the compressor assembly regulates the compressor discharge
pressure. The hot refrigerant gas is cooled down in the condenser and condenses to a high pressure
liquid. A radial condenser fan forces outside air through the condenser coils and vents the thus heated
air overboard. The drier / receiver bottle separates moisture from liquid and filters contaminations from
refrigerant. The expansion valve controls the amount of refrigerant liquid flowing to the evaporator.
The refrigerant boils in the evaporator and turns back into a low-pressure low-temperature gas while
cooling the coils of the evaporator. A radial evaporator fan forces cabin air through the cooling coils
and thus remove heat from the cabin air. The cool cabin air cannot hold the moisture and water
condensates on the evaporator cooling coils. The condensate is collected under the evaporator and
is drained overboard. The refrigerant gas returns to the compressor.
An inlet including a drip tray and an air filter enables ambient air to enter the RACC compartment
ensuring sufficient compartment ventilation.
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DA 42 NG AMM
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Trouble Shooting
1. General
The table below lists the defects you could have with the control panel in the center console. If you
have the trouble detailed in the Trouble column read across to the Possible Cause column. Then do
the repair given in the Repair column.
Trouble
The Power Status LED on
Possible Cause
Repair
RACC circuit breaker open.
Set.
Additional alternator defective.
Check RACC power supply of
control panel does not
illuminate.
the airplane.
Central unit does not power up.
Insufficient cooling.
Control panel defective.
Replace.
Electrical control unit defective.
Replace.
Hot air outlet on fuselage
Remove blockage.
bottom blocked.
Leak in refrigerant circuit.
Perform a leak test.
Repair leak.
Charge the system.
Condenser faulty.
Check condenser coils for dirt
accumulation and remove dirt.
Expansion valve faulty.
Replace expansion valve.
Compressor faulty.
Replace compressor.
Electrical power source
Check ground power source
insufficient.
respective RACC power supply
of airplane.
%
Filter/Dryer Assembly
%
inoperative.
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DA 42 NG AMM
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Maintenance Practices
1. Remove/ Install the Central Unit
A. Remove the Central Unit
Detail Steps/Work Items
Key Items/References
(1)
Remove the passenger seats.
Refer to Section 25-10.
(2)
Remove the seatbelt pulleys of the passenger
Refer to Section 25-10.
seats.
(3)
Remove the short baggage extension.
(4)
Remove the flexible air hoses from the RACC
Refer to Section 25-10.
central unit:
S Flexible cold air hose.
S Flexible hot air hose.
(5)
Remove the hot exhaust air duct from the RACC
central unit.
(6)
Unplug the electrical connections from the RACC
central unit to:
S 2 heavy connectors at the RACC central unit
terminal board (LH).
S 1 plug coming from the RACC control panel.
(7)
Remove the drain hoses from the RACC central
unit:
S Drip tray drain hose.
S Evaporator drain hose.
(8)
Remove the drip tray.
(9)
Remove the four bolts which connect the base
plate of the RACC central unit to the RACC
brackets on the LH and RH side of airplane.
(10)
Slide the RACC central unit forward.
(11)
Lift the RACC central unit clear of the airplane.
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Figure 3: RACC Central Unit Installation (if OÄM 42-193/d or later is installed)
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RACC
B. Install the Central Unit
Detail Steps/Work Items
Key Items/References
(1)
Lift the RACC central unit into the airplane.
(2)
Slide the RACC central unit backward. Make sure
to position the baseplate of the RACC central unit
above the RACC brackets and trailing edge of
the baseplate inside the C-profile.
(3)
Install four bolts which connect the baseplate of
the RACC central unit to the RACC brackets on
LH and RH side of airplane.
(4)
Install the drip tray.
(5)
Install the drain hoses to the RACC central unit:
S Drip tray drain hose.
S Evaporator drain hose.
(6)
Connect the electric cables to the RACC central
unit to:
S 2 heavy connectors of the RACC central unit
terminal board (LH).
S 1 plug coming from control panel.
(7)
Install the hot exhaust air duct to the RACC
central unit.
(8)
S Install the flexible air hoses to the RACC
central unit:
S Flexible cold air hose.
S Flexible hot air hose.
(9)
Install the short baggage extension.
Refer to Section 25-10.
(10)
Install the seatbelt pulleys of the passenger seats.
Refer to Section 25-10.
(11)
Install the passenger seats.
Refer to Section 25-10.
(12)
Perform a cooling test of the RACC system.
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Figure 4: Central Unit - Front and LH Side (if OÄM 42-193/d or later is installed)
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Figure 5: Central Unit Back and RH Side (if OÄM 42-193/d or later is installed)
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2. Remove/Install the Control Panel
A. Remove the Control Panel
Detail Steps/Work Items
(1)
Remove the center console.
(2)
Unplug the electrical connectors of the control
Key Items/References
Refer to Section 25-10.
panel.
(3)
Unclip the RACC control panel from the center
console.
B. Install the Control Panel
Detail Steps/Work Items
(1)
%
Key Items/References
Move the RACC control panel in position on the
center console.
(2)
Push the center console into the center console
until the clips hold the panel in place on the
center console.
(3)
Connect the electrical connectors to the control
panel.
(4)
Install the center console.
Refer to Section 25-10.
(5)
Perform a RACC - System test.
Refer to Paragraph 3.
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3. RACC - System Test Procedure
Detail Steps/Work Items
%
Key Items/References
(1)
Perform an engine ground test.
Refer to Section 71-00.
(2)
Set the engine to 1000 to 1200 RPM.
The test procedure may be alternatively
%
performed with power supplied by
%
engine or GPU.
(3)
Set the AUX POWER switch to ON.
The Power Status LED on the RACC
control panel must flash.
(4)
(5)
Push the ON/OFF button on the RACC control
The preset temperature display on the
panel once to switch the RACC system ON.
RACC control panel must illuminate.
Push the Preset Temperature DOWN button until
%
the preset temperature shows ‘LO’ and switch the
%
cabin fan speed to the highest stage (“3") .
%
(6)
Verify that the cabin air temperature at outlet is
%
significantly lower than the outside air
%
temperature. Perform test at ambient
%
temperature of (20-30°C) and relative humidity of
%
(20-90%). The cabin air temperature at outlet
%
must be 8-15°C less than the ambient
%
temperature.
(7)
(8)
Set the cabin air preset temperature to a
Use the preset temperature UP and
convenient temperature level.
DOWN buttons on the control panel.
Push the ON/OFF button on the RACC control
panel for approximately 1 second to switch the
RACC system to OFF.
(9)
Set the AUX POWER switch to OFF.
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4. Remove/Install Parts of the Refrigerant Circuit
Note:
The refrigerant vapor cooling system is a hermetically sealed and
pressurized circuit and contains the refrigerant R134a.
WARNING:
ALL MAINTENANCE AND REPLENISHMENT WHICH REQUIRES TO
OPEN AND DEPRESSURIZE THE REFRIGERANT CIRCUIT MUST BE
CARRIED OUT BY AUTHORIZED PERSONNEL ACCORDING TO
NATIONAL AND INTERNATIONAL REGULATIONS FOR REFRIGERANT
SYSTEMS.
Before you do any maintenance on parts of the refrigerant circuit you must remove the central unit from
the airplane. Refer to Paragraph 1.
Make sure to obey the regulations for handling the refrigerant.
%
If the refrigerant circuit is open for more than 30 min and the filter /dryer assy is not sealed, Diamond
%
Aircraft recommends to replace the filter/dryer assy by a new one.
A. Discharge/Charge the Refrigerant Circuit
(1) Equipment
One of the following automated discharge and charging stations or equivalent may be used:
Item
Quantity
Part Number
Silco CS 199
1
Commercial.
Silco CS 195
1
Commercial.
Silco CS 150
1
Commercial.
(2) Discharge the Refrigerant Circuit
Detail Steps/Work Items
Key Items/References
(1)
Remove the central unit from the airplane.
Refer to Paragraph 1.
(2)
Connect the RACC system to the discharge /
Follow the instructions of the
charging station.
discharge/charging station.
Discharge the refrigerant.
Follow the instructions of the
(3)
discharge/charging station.
(4)
Print the protocol of the discharge/charging station
Follow the instructions of the
and add it to the RACC system documentation.
discharge/charging station.
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(3) Charge the Refrigerant Circuit
Detail Steps/Work Items
(1)
Key Items/References
Make sure that all connectors of the refrigerant
circuit are tight.
%
(2)
Charge the refrigerant circuit with R134a
Follow the instructions of the
%
(500g±25 g if OÄM 42-193/d and subsequent or
discharge/charging station.
%
450±25 g if OÄM42-193/c and earlier is installed)
%
and add 15 ccm ± 5 ccm of oil (type PVE 68 cSt
%
acc. to ISO 68).
%
If refrigerant circuit and compressor was
%
completely discharged add a total of 290 ccm of
%
oil instead of the amount described above.
%
(3)
%
Perform a Leakage Test if not automatically
Refer to Paragraph 4.
performed by the discharge / charging station.
(4)
Print the protocol of the discharge/charging
Follow the instructions of the
station and add it to the RACC system
discharge/charging station.
documentation.
(5)
Disconnect the RACC system from the
Follow the instructions of the
discharge/charging station.
discharge/charging station.
(6)
Install the RACC central unit in the airplane.
Refer to Paragraph 1.
(7)
Perform a RACC System test.
Refer to Paragraph 3.
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%
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(4) Leakage Test of the Refrigerant Circuit
%
After every discharge/charge of the refrigerant system it must be checked for leakages.
%
Most of the charging stations run automatically a leakage check before charging the air condition
%
system. If the applied service station was equipped with this function, but does not automatically
%
perform a test, engage manually the check before charging the air condition system.
%
If leakage in the air condition system was detected or the air condition unit lost more than 150g/year
%
%
of refrigerant, then one of the below described checks must be performed:
%
%
Detail Steps/Work Items
(1)
Use a detection spray or soapy water at the
%
suspicious areas and watch for bubbles and foam.
%
If a leak is detected, repair the leakage.
%
To order spare parts contact DAI.
%
(2)
Key Items/References
Use an electronic leak detector suitable to detect
%
the R134a refrigerant with a minimum leakage
%
detection sensitivity of 5 g per year.
%
If a leak is detected, repair the leakage.
%
To order spare parts contact DAI.
%
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B. Remove/Install the Compressor
(1) Remove the Compressor
Detail Steps/Work Items
(1)
Discharge the refrigerant circuit.
(2)
Unplug the electrical connectors from the
Key Items/References
Refer to Paragraph 4A(2).
compressor.
(3)
Loosen the hose connections of the refrigerant
Use caps to plug the hose connectors.
circuit on the compressor.
(4)
Remove the three screws which attach the
compressor to the RACC mounting panel.
(5)
Move the compressor clear of the central unit.
(2) Install the Compressor
Detail Steps/Work Items
(1)
Key Items/References
Position the compressor on the RACC mounting
panel.
(2)
Use the three screws to attach the compressor to
the RACC mounting panel.
(3)
Connect the refrigerant circuit hoses to the
Remove the caps from the hose
compressor.
connectors and replace O-rings of
circuit-hoses.
(4)
Connect the electrical connectors to the
compressor.
%
(5)
Charge the refrigerant circuit.
Refer to Paragraph 4A/(3).
(6)
Perform a leakage check.
Refer to Paragraph 4A/(4).
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C. Remove/Install the Filter/Dryer Assembly
(1) Remove the Filter/Dryer Assembly
Detail Steps/Work Items
(1)
Discharge the refrigerant circuit.
(2)
Remove the electrical connectors from the
Key Items/References
Refer to Paragraph 4A/(2).
pressure sensor.
(3)
Loosen the hose connections of the refrigerant
Use caps to plug the hose connectors.
circuit on the filler/drier assembly.
(4)
Remove the two screws which attach the
filler/drier assembly to the central unit.
(5)
Move the filter/drier assembly clear of the central
unit.
(2) Install the Filter/Dryer Assembly
Detail Steps/Work Items
(1)
Key Items/References
Position the filter/drier assembly on the RACC
mounting panel.
(2)
Use the two screws to attach the filter/drier
assembly to the central unit.
(3)
Connect the refrigerant circuit hoses to the
Remove the caps from the hose
filter/drier assembly.
connectors and replace O-rings of
circuit-hoses.
(4)
Connect the electrical connectors to the pressure
sensor.
%
(5)
Charge the refrigerant circuit.
Refer to Paragraph 4A/(3).
(6)
Perform a leakage check.
Refer to Paragraph 4A/(4).
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D. Remove/Install Parts of the Refrigerant Circuit
(1) Remove the Expansion Valve
Detail Steps/Work Items
(1)
Discharge the refrigerant circuit.
(2)
Open latches of evaporator cover and remove
Key Items/References
Refer to Paragraph 4A(2).
cover.
(3)
Remove evaporator from fixing cover.
(4)
Loosen the hose connections of the refrigerant
Note and mark the correct position of
circuit to the expansion valve and remove
refrigerant hoses evaporator fixing plate
associated evaporator fixing plate.
on the expansion valve.
Remove two bolts from the expansion valve and
Note and mark correct position of the
the second evaporator fixing plate first and then
expansion valve.
(5)
remove the expansion valve from the evaporator.
(6)
Move the expansion valve clear of the central unit.
(2) Install the Expansion Valve
Detail Steps/Work Items
Key Items/References
(1)
Position the expansion valve on the evaporator.
Use new O-rings on evaporator-hoses.
(2)
Install the associated expansion valve fixing plate
Check for correct position.
with two bolts.
(3)
Connect the refrigerant circuit hoses and the
Use new O-rings on refrigerant-hoses
second evaporator fixing plate to the expansion
and check for correct position.
valve.
(4)
(5)
Install the evaporator inside fixing cover.
Install the evaporator cover and close the cover
latches.
%
(6)
Charge the refrigerant circuit.
Refer to Paragraph 4A/(3).
(7)
Perform a leakage check.
Refer to Paragraph 4A/(4).
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Temporary Revision
DA 42 NG AMM
RACC
AIRCRAFT
Intentionally left blank
Page 214
20 Feb 2014
21-51-00
Doc # 7.02.15
AMM-TR-OÄM 42-193/b
DA 42 NG AMM
AIRCRAFT
Temporary Revision
RACC
CHAPTER 92
WIRING DIAGRAMS
1. General
The following item is added to the table:
Title
Schematic, RACC Wiring (if OÄM 42-193/d or later
Drawing No.
Rev.
No. of
No.
Sheets
D64-9221-50-01
A
1
is installed)
Doc # 7.02.15
AMM-TR-OÄM 42-193/b
92-00-00
Page 1a
20 Feb 2014
Temporary Revision
DA 42 NG AMM
RACC
AIRCRAFT
Intentionally left blank
Page 1aa
20 Feb 2014
92-00-00
Doc # 7.02.15
AMM-TR-OÄM 42-193/b
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
8
CN2
5
2
6
PRESSURE SWITCHES
TEMP SENSOR
TEMP SENSOR
7
TEMPERATUR
SENSOR
21504A20
6
21504B20
9
CN2
21502B20
2
21502A20
2
CONDENSER
21506B20
6
21506A20
21503B20
21505B20
21500A22
21501A22N
21503A20
3
5
1
2
6
J2151
P2150
3
21505A20
21500B22
21501B22N
FAN LO
5
CN1
8
4
TB
FAN MED
FAN HI
A/C POWER
A/C GROUND
GL-F700
FUSELAGE
6
A/C DISP
3
21521A8
21520A8
21516A22
7
7
J2152
B
U
S
A
L
T
2
n
d
20
5
21511A14
21516B22
COND
20
EVAP
50
COMP
5
85
87
87A
85
87
87A
85
87
85
87
87A
L
PRESSURE
SWITCHES
H
86
30
85
87
87A
21509A16
9
2 DECIMAL
1DECIMAL
DECIMAL
ANGLE
RAD
4
u0,25
u0,5
u1
u1°
u0,5
DIMENSION TOLERANCES
A2
FINISH
IN
MICROMETER
3.2
5
6
DP-S-17-00001
IDENTIFICATION MARKINGS
NO
-
-
3
APPROVED:
SYSTEM:
TL
N/A
N/A
N/A
STRESS:
MANUF.:
N/A
QA:
CHECKED:
DRAWN
Airc raft
Indust ries GmbH
Diamond
21518A10N
21515D20
CONDENSER
DEPARTMENT
10
EVAP
FAN
HI
MED
LO
J2152
SOLID EDGE V18
D64-9221-50-01a.dft
FILENAME
SOFTWARE:
THIS DRAWING WAS PRODUCED USING
INTERCHANGEABLE PART
N ON E
CLASSIFICATION:
BLK
21511E14
OR
RD
YE
BLK
3
21515C20
THERMOSTAT
1
2
J2155
21511D14
21514B14N
red
black
J2154
1
2
3
4
COOLING
FAN
21508B16
21509B16
21510B16
21512B16N
21515B20
FORMAT
UNLESS OTHERWISE SPECIFIED
DIMENSIONS ARE IN MM
FIRST ANGLE PROJECTION
METRIC
8
J2152
21516D22
DIMENSIONS
21511C14
J2152
1
2
J2153
J2152
1
2
3
4
J2152
21515A20
21511B14
21516C22
COMPRESSOR RELAY
86
30
CONDENSER RELAY
86
30
87A
FAN LO RELAY
86
30
FAN MED RELAY
86
30
FAN HI RELAY
21512A10
REAR BAGGAGE COMPARTMENT
4
21508A16
21510A16
E
8
21513A22N
21512A16N
21517A22
3
F
Confidential
21514A14N
21507A16
ALL
ALL
ZONE
- GROUND
7 SPEED SET POINT
6 +5V
3 PWR ON/OFF
DESCRIPTION
SIGN
2
20.06.12
DATE
REVISION
DATE
1
J5
J4
J3
JP6
IN 1
OUT 2
SCALE
NTS
1
SH
01
01
"A"
Confidential
OF
N. A. Otto-Straße 5
A-2700 Wiener Neustadt
D64-9221-50-01
DWG.NO.
710197
DAIA
CODE
DA 42 N G
Schem atic, RACC
Wiring
DWG.ORIG.
TITLE
PROJECT
PHASE
C
PHASE
B
PHASE
A
TO TEMP.
SWITCH
REV
APPROVAL
OÄM 42-193
19.08.10 SEE TB
FIRST RELEASE
OÄM 42-193/d
20.06.12 SEE TB
Wire numbers analog to DA 40 NG updated,
cabin fan removed, connectors J2152,
J2153, J2154, J2155 amd terminal block
added.
Diamond Aircraft Industries
J2
01
A
+ DC IN
JP5
J1
01
-
ELECTRIC
COMPRESSOR
SH
REV
2
A
B
C
D
E
F