(2)
Install the new packing (3) on the drain valve (2).
(3)
Install the drain valve (2) in the combustion chamber elbow (4). NOTE : Make sure that the drain valve is installed with the embossed
____ arrow pointed overboard to the drain tube connector.
(4)
TORQUE the drain valve (2) to between 70 and 100 lbf.in (0.79 and
1.13 m.daN).
(5)
Connect the drain tube (1) to the drain valve (2). NOTE : When you torque the drain tube nut, hold the drain valve
____ firmly with a wrench to prevent torque transfer.
(6)
TORQUE the drain tube nut (1) to between 270 and 300 lbf.in (3.05 and
3.39 m.daN).
5. Close-up
________ Subtask 49-32-51-865-052
A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1KD, 2KD
Subtask 49-32-51-410-050
B. Close Access
(1)
Close the APU access doors 315AL, 316AR (Ref. TASK 52-41-00-410-001).
(2)
Remove the access platform(s).
(3)
Remove the warning notice(s).
IGNITION AND STARTING - DESCRIPTION AND OPERATION
_________________________________________________
R **ON A/C 001-003, 051-099, 401-499,
1.
General
_______ (Ref. Fig. 001) The ignition and starting systems are necessary to start the APU. They operate electrically and are supplied from the aircraft electrical system. The two aircraft batteries are assisted by the APU Transformer Rectifier Unit (TRU) if powered through the external power or if the main engine generator supplies sufficient power to start the APU. The two aircraft batteries are installed in the avionics compartment, below the cockpit. A starter cable supplies electrical current to the starter motor. This cable is routed through the aircraft, along the ceiling of the cabin. The APU has an inflight restart capability within an established altitude and airspeed envelope. In this case, the aircraft's batteries or the TRUs rectifier supply electrical power to the starter motor
2.
System Description
__________________
A. Ignition System The ignition system gives the constant high-energy ignition which ignites the fuel/air mixture in the combustion chamber. It operates during the start sequence when the APU speed is between 7 % and 95 %. The Electronic Control Box (ECB) controls the ignition system fully automatically.
B. Starting System The starting system rotates and accelerates the rotor of the APU to 50 % of the APU's usual speed. You can operate the starting system from the APU panel in the cockpit. The Electronic Control Box (ECB) 59KD controls the start sequence of the APU. Three consecutive start attempts are permitted without cooldown. After the third start attempt the starter motor must cool down for at least 60 minutes.
Ignition and Starting - Component Location
Figure 001
CES IGNITION AND STARTING - DESCRIPTION AND OPERATION
_________________________________________________
1.
General
_______ The ignition and starting systems are necessary to start the APU. They operate electrically and are supplied from the aircraft electrical system. The two aircraft batteries are used to supply power through the system to the starter moter. When external power or main-engine generator-power is used the batteries are assisted by the APU Transformer Rectifier Unit (TRU). The two aircraft batteries are installed in the avionics compartment, below the cockpit. A cable passes electrical power to the starter motor. This cable is routed through the aircraft, along the ceiling of the cabin. The APU has an inflight restart capability within an established altitude and airspeed envelope. The aircraft's batteries or the TRU rectified electrical power is used to start the APU in flight.
2.
System Description
__________________
(Ref. Fig. 001)
A. Ignition System The ignition system gives the constant high-energy ignition which ignites the fuel/air mixture in the combustion chamber. It operates during the start sequence when the APU speed is between 7 % and 60 %. The Electronic Control Box (ECB) controls the ignition system fully automatically. When the APU speed is below 95% the ECB energizes the ignition system to ensure a stable combustion.
B. Starting System The starting system rotates and accelerates the rotor of the APU to 50 % or in high altitude (P2 < 6.76PSIA) up to 58% of the APU's usual speed. You can operate the starting system from the APU panel in the cockpit. The Electronic Control Box (ECB) 59KD controls the start sequence of the APU. Three consecutive start attempts are permitted without cooldown. After the third start attempt the starter motor must cool down for at least 60 minutes.
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