(5)
TORQUE the clamp (4) to between 10 and 16 lbf.in (0.11 and 0.18 m.daN).
(6)
TORQUE the tube connector (8) to between 135 and 150 lbf.in (1.52 and
1.69 m.daN).
(7)
Install the duct (1) with the clamp (2).
(8)
TORQUE the clamp (2) to between 10 and 16 lbf.in (0.11 and 0.18 m.daN).
(9)
Position the duct (1) on the outlet duct (9).
(10)
Install the clamp (4) loosely.
(11)
Lightly lubricate the bolts (5) with engine oil.
(12)
Install the bolts (5).
(13)
Torque the clamp (4) to between 10 and 16 lbf.in (0.11 and 0.18 m.daN).
(14)
Torque the bolts (5) to 40 lbf.in (0.45 m.daN). Subtask 49-52-54-865-052
C.
Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1KD, 2KD
Subtask 49-52-54-710-050
D. Test.
(1)
Start and operate the APU (Ref. TASK 49-00-00-860-005).
(2)
Select bleed air to ON and check cooling valve closes.
(3)
Select bleed air OFF and check cooling valve opens.
(4)
Stop the APU (Ref. TASK 49-00-00-860-006).
5. Close-up
________ Subtask 49-52-54-410-050
A. Close Access
(1)
Make sure that the work area is clean and clear of tool(s) and other items.
(2)
Set the LIGHT control switch 11LJ to the off position.
(3)
Close the APU access doors 315AL, 316AR (Ref. TASK 52-41-00-410-001).
(4)
Remove the access platform(s).
(5)
Remove the warning notice(s).
Subtask 49-52-54-860-052
B. Aircraft Maintenance Configuration
(1) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
ENGINE CONTROLS - DESCRIPTION AND OPERATION
___________________________________________
R **ON A/C 001-003, 051-099, 401-499,
1.
General
_______ In order to start, control its performance and to shut off the auxiliary power system, manual and automatic controls are provided. Manual control of the APU is possible through the crew interfaces in the cockpit. Automatic control is accomplished through the Electronic Control Box (ECB) 59KD.
2.
System Description
__________________
A. Control and Monitoring A Full Authority Digital Electronic Control system is contained in the ECB 59KD. The ECB 59KD provides control for the operation and monitoring of the Auxiliary Power Unit (APU). It also provides the communication to the aircrafts other systems. The ECB gives:
-
the control for the automatic operation of the APU,
-
the control for the APU at a constant speed,
-
the protection of the APU if a failure or an overload occurs,
-
the supply of pneumatic and shaft power,
-
the monitoring of the Line Replaceable Units (LRUs),
-
the tests on the APU system.
B. APU Emergency Shutdown The APU emergency shutdown-system stops the APU if an emergency occurs. The system is automatically activated on the ground if the APU fire and overheat detection system finds an overtemperature in the APU compartment (Ref. 26-13-00). You can also stop the APU manually from:
-
the cockpit,
-
the external power control panel on the nose landing gear (only when the aircraft is on the ground).
ENGINE CONTROLS - DESCRIPTION AND OPERATION
___________________________________________
1.
General
_______ In order to start, control its performance and to shut off the auxiliary power system, manual and automatic controls are provided. Manual control of the APU is possible through the crew interfaces in the cockpit. Automatic control is accomplished through the Electronic Control Box (ECB) 59KD.
2.
System Description
__________________
A. Control and Monitoring A Full Authority Digital Electronic Control system is contained in the ECB 59KD. The ECB 59KD provides control for the operation and monitoring of the Auxiliary Power Unit (APU). It also provides the communication to the aircrafts other systems. The ECB gives:
-
the control for the automatic operation of the APU,
-
the control for the APU at a governed speed,
-
the protection of the APU if a failure or an overload occurs,
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