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the engine shock-mounts.
C. Electrical Harness
Electrical cables go through the firewall to connect to the engine. They give electrical supply to the
engine sensors. Electrical cables from the main battery and from the generator supply electrical
power to the airplane electrical system.
AIRCRAFT
Power Plant DA 40 Series
AMM
Page 4
20 Sep 2007 71-01-00 Doc # 6.02.01
Rev. 5
D. Air Intakes
The top cowling has these air intakes:
) The intake on the top left of the top cowling supplies cooling air for the engine cooling system
radiator.
) The intake on the top right of the top cowling supplies air to the intercooler.
The bottom cowling has these intakes:
) Combined engine air intake and cabin heating intake. This intake is located in the right side of
the cowling and supplies air to the engine air filter and the cabin heat heat-exchanger.
) The intake at the bottom of the bottom cowling supplies air to the oil radiator.
AIRCRAFT
DA 40 Series
AMM
Power Plant
Doc # 6.02.01
Rev. 5 71-01-00 Page 5
20 Sep 2007
3. Engine Specification
Note: The engine drives the propeller through a speed-reducing gear. All RPM's are
shown as propeller RPM's.
TAE 125-01 Engine Specification
Engine manufacturer. Thielert Aircraft Engines.
Engine model. TAE 125-01
Engine operating limits:
S Maximum take-off power.
S Maximum continuous power.
S Maximum RPM.
99 kW (135 DIN-hp) at 2300 ± 50 RPM
99 kW (135 DIN-hp) at 2300 ± 50 RPM
2500 RPM
Oil pressure (indicated values are corrected for
pressure altitude):
S Minimum.
S Normal.
S Maximum.
1.0 bar (14.5 psi)
2.3 to 5.2 bar (33.4 to 75.4 psi)
6.5 bar (94.3 psi)
Oil temperature:
S Minimum for engine start.
S Normal.
S Maximum.
-30 ºC (-22 °F)
60 to 125 °C (140 to 257 °F)
140 ºC (284 °F)
Oil consumption:
S Maximum. 0.1 liters/hr. (0.11 US qts/hr.)
Oil quantity:
S Minimum.
S Maximum.
4.5 liters (4.8 US qts)
6 liters (6.3 US qts)
Coolant temperature:
S Minimum for engine start.
S Normal.
S Maximum.
-30 °C (-22 °F)
60 to 96 ºC (140 to 205 ºF)
105 ºC (221 ºF)
AIRCRAFT
Power Plant DA 40 Series
AMM
TAE 125-01 Engine Specification
Page 6
20 Sep 2007 71-01-00 Doc # 6.02.01
Rev. 5
Fuel consumption:
S Maximum 28 l/h (7.4 US gal/h)
Gearbox oil capacity: 1 liter (1.06 US qts)
Engine weight, bare: 134 kg (295.4 lb)
Fuel grade: Refer to Airplane Flight Manual.
Oil specification: Refer to Airplane Flight Manual.
Coolant: Refer to Airplane Flight Manual.
Gearbox oil: Refer to Airplane Flight Manual.
AIRCRAFT
DA 40 Series
AMM
Power Plant
Doc # 6.02.01
Rev. 5 71-01-00 Page 101
20 Sep 2007
Trouble-Shooting
1. General
The table below lists the defects you could have with the power plant. It does not give trouble shooting
data for the engine or the engine systems. Refer to the TAE 125-01 Operator's Manual for engine and
engine system trouble-shooting.
WARNING: YOU MUST BE CAREFUL WHEN YOU DO POWER PLANT TROUBLE
SHOOTING. OPERATION OF A DAMAGED ENGINE CAN CAUSE MORE
DAMAGE TO THE ENGINE. THIS CAN CAUSE INJURY TO PERSONNEL.
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 Possible Cause Repair
Engine vibration. Damaged shock mounts.
Propeller unbalance.
Engine operates with only 3
fuel injectors.
Replace the shock mounts.
Balance the propeller.
Refer to the engine
manufacturer.
Engine does not produce full
power.
Engine air inlet blocked. Examine the air inlet.
Air filter blocked. Examine/Replace the air filter.
Sensor signal out of limits. Read TAE engine data with
laptop computer via CAN
interface. Refer to Section
72-01.
Defective sensor. Read TAE engine data with
laptop computer via CAN
interface. Refer to Section
72-01.
AIRCRAFT
Power Plant DA 40 Series
AMM
Page 102
20 Sep 2007 71-01-00 Doc # 6.02.01
Rev. 5
Intentionally left blank
AIRCRAFT
DA 40 Series
AMM
Power Plant
Doc # 6.02.01
Rev. 5 71-01-00 Page 201
20 Sep 2007
Maintenance Practices
1. General
These maintenance practices tell you how to remove/install the engine.
WARNING: DO NOT STAND WITHIN THE DANGER AREA OF THE PROPELLER. IF
THE ENGINE STARTS, THE PROPELLER CAN CAUSE DEATH OR
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