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(15) Leave the power lever at
IDLE.
Make sure that there are no
warning lights on.
(16) Monitor the oil pressure. The oil pressure must rise to
1 bar minimum, within 3
seconds of starting the
engine. If it does not, then
you must shut-down the
engine.
(17) Let the engine idle at 890
RPM for 2 minutes.
Monitor the engine
instruments for unusual
indications.
(18) Set the power lever to give
1400 RPM.
Until the oil temperature
rises to at least 50 ºC and
the coolant temperature
rises to at least 60 °C.
AIRCRAFT
Power Plant DA 40 Series
AMM
Page 218
20 Sep 2007 71-01-00 Doc # 6.02.01
Rev. 5
D. ECU Test, Propeller Control Test and ECU Swap Test
Do these tests with the engine warm (see Paragraph C, above).
Note: The engine drives the propeller through a speed-reducing gear. All RPM's are
shown as propeller RPM's.
WARNING: DO NOT CONTINUE WITH THE TEST IF THE ECU CAUTION LIGHTS DO
NOT GO ON AND OFF WHEN REQUIRED, OR IF A CAUTION LIGHT
STARTS FLASHING. STOP THE GROUND TEST AND FIND THE FAULT.
WARNING: DO NOT OPERATE THE AIRPLANE IF THE ENGINE STOPS DURING THE
TEST.
Detail Steps/Work Items Key Items/References Results/Comments
(1) Set the power lever to IDLE. The RPM must be 890 ± 50.
Both ECU caution lights
must be off.
Note: If the ECU TEST button is released before the test is over, then the ECU will
immediately switch back to normal operation.
(2) Press and hold ECU TEST
button.
Both ECU caution lights
must go on.
Note: During the change-over from one ECU to the other, a single light vibration of the
engine may occur. This is normal.
WARNING: DO NOT OPERATE THE AIRPLANE IF THE VIBRATION CONTINUES.
STOP THE GROUND TEST AND FIND THE FAULT.
(3) After two seconds, the
system changes over to
ECU B.
The ECU A caution light
must be off.
The ECU B caution light
must be on.
(4) The propeller control is
activated.
The RPM increases to 1100
and then returns to 890.
(5) The system changes back
to ECU A.
The ECU A caution light
must be on.
The ECU B caution light
must be off.
AIRCRAFT
DA 40 Series
AMM
Power Plant
Detail Steps/Work Items Key Items/References Results/Comments
Doc # 6.02.01
Rev. 5 71-01-00 Page 219
20 Sep 2007
(6) The propeller control is
activated.
The RPM increases to 1100
and then returns to 890.
(7) The system returns to
normal operation.
Both ECU caution lights
must be off.
(8) When both ECU caution
lights are off and the powerplant
has reached idle RPM:
SRelease the ECU TEST
button.
(9) Do an ECU swap test:
S Set the ECU SWAP
switch from
AUTOMATIC to ECU B
and immediately back to
AUTOMATIC.
Re-activate ECU A:
S Set the power lever to
IDLE.
S Push ECU TEST button
until both ECU caution
lights are off.
AIRCRAFT
Power Plant DA 40 Series
AMM
Page 220
20 Sep 2007 71-01-00 Doc # 6.02.01
Rev. 5
E. Performance Check
CAUTION: THE ENGINE PARAMETERS MUST BE IN THE GREEN RANGE FOR
THIS CHECK. DO THE PERFORMANCE CHECK IMMEDIATELY AFTER
WARM-UP AND ECU TESTS (SEE PARAGRAPHS C AND D, ABOVE).
Note: The engine has a full authority digital engine control (FADEC) system. The
performance check is therefore different from the usual aircraft engines. If the
values are within the limits shown below, no caution or warning light is illuminated
% and the 'ECU Operator' software reports no failures, the engine works properly. If
% the performance check is not passed successfully, refer to the Trouble shooting
% Section of this chapter or to the Engine Maintenance Manuals.
Detail Steps/Work Items Key Items/References Results/Comments
(1) Allow gearbox temperature
to rise to at least 65 °C.
(2) Check engine and propeller
control:
S Quickly move the power
lever to MAX.
S Check RPM.
S Check LOAD.
The RPM must increase
smoothly and steadily.
The CED must indicate
2250 to 2350 RPM.
The CED must indicate
90 % or more. Factors
which generally reduce the
attainable LOAD are:
S Low ambient pressures.
S Airbox temperatures
above 45 °C (indicated
by the "ECU Operator"
software).
AIRCRAFT
DA 40 Series
AMM
Power Plant
Detail Steps/Work Items Key Items/References Results/Comments
Doc # 6.02.01
Rev. 5 71-01-00 Page 221
20 Sep 2007
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钻石40系列AMM 3(34)
