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 A.  This procedure gives a task to do an operational test of the engine starting system.
 B.  The operational test makes sure the engine starting system operates correctly. It is necessary to dry motor the engine to do this test.
 TASK 80-11-00-705-001-N00
 2.  Operational Test - Engine Starting System (Fig. 501)
_________________________________________
 A.  General
 (1)  The limits of the starter duty cycle for the motoring of the engine are as follows:
 (a)  
0 to 5 minutes ON, Let the N2 decrease to zero before you engage the starter again

 (b)  
5 to 10 minutes ON, Let the starter cool for 20 minutes before you motor the engine again.

 (c)  
10 to 15 minutes ON, Let the starter cool for 30 minutes before you motor the engine again.

 B.  References
 (1)  
AMM 12-13-06/301, Engine Starter - Servicing

 (2)  
AMM 24-22-00/201, Manual Control

 (3)  
AMM 31-61-00/501, Integrated Display System

 (4)  
AMM 36-00-00/201, Pneumatic Power

 (5)  
AMM 78-31-00/201, Thrust Reverser System

 (6)  
AIPC 80-11-01 Fig 1, AIPC 80-11-02 Fig. 1

 (7)  
WDM 80-11-11, 80-11-21, 80-11-31, 80-11-41

 (8)  
SSM 80-11-01, 80-11-02, 80-11-03, 80-11-04

 C.  Access
 (1)  
Location Zone 221 Control Cabin, LH 222 Control Cabin, RH 412 Engine 1 - Main Gearbox Aft Face 5 o'clock 422 Engine 2 - Main Gearbox Aft Face 5 o'clock 432 Engine 3 - Main Gearbox Aft Face 5 o'clock 442 Engine 4 - Main Gearbox Aft Face 5 o'clock

 (2)  
Access Panel
 416 Right Thrust Reverser Half - Engine 1
 426 Right Thrust Reverser Half - Engine 2
 436 Right Thrust Reverser Half - Engine 3
 446 Right Thrust Reverser Half - Engine 4

 

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 80-11-00
 ALL  ú ú N01 Page 501 ú Jun 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
FWD
SEEA
QUICK ATTACH-DETACH (QAD) ADAPTER
MAIN START VALVE
GEARBOX
SEE C SEE B A
STARTER
FLIGHT COMPARTMENT

ENGINE IGNITION CONTROL MODULE EEC PANEL ASSEMBLY BC
Engine Starting System - Component Location
Figure 501

C79660
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
 80-11-00
 ALL  ú ú N07 Page 502 ú Oct 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
D. Preconditions
 S 865-015-N00
 (1)  These conditions are necessary for this task:
 (a)  Electrical Power on (AMM 24-22-00/201).
 (b)  Integrated Display System (IDS) serviceable (AMM 31-61-00/501).
 (c)  Pneumatic power available (AMM 36-00-00/201).
 E. Prepare for the Test
 S 015-013-N00
 (1)  Open the thrust reverser halves (Ref 78-31-00/201).
 S 615-002-N00
 (2)  Lubricate the starter (Ref 12-13-06/301).
 S 865-003-N00
 (3)  Apply electrical power (Ref 24-22-00/201).
 S 865-004-N00
 (4)  Open these circuit breakers for the applicable engine and attach
 DO-NOT-CLOSE tags:

 (a)  P6 Main Power Supply Panel
 1) 6F1 IGN 1 ENG 1
 2) 6F2 IGN 1 ENG 2
 3) 6F3 IGN 1 ENG 3
 4) 6F4 IGN 1 ENG 4
 5) 6G1 FUEL SHUTOFF VALVE ENG 1
 6) 6G2 FUEL SHUTOFF VALVE ENG 2
 7) 6G3 FUEL SHUTOFF VALVE ENG 3
 8) 6G4 FUEL SHUTOFF VALVE ENG 4
 9) 6G19 STBY IGN ENG 1
 10) 6G20 STBY IGN ENG 2
 11) 6G21 STBY IGN ENG 3
 12) 6G22 STBY IGN ENG 4
 13) 6K19 IGN 2 ENG 1
 14) 6K20 IGN 2 ENG 2
 15) 6K21 IGN 2 ENG 3
 16) 6K22 IGN 2 ENG 4
 17) 6L10 FUEL CONT VALVE ENG 1
 18) 6L11 FUEL CONT VALVE ENG 2
 19) 6L12 FUEL CONT VALVE ENG 3
 20) 6L13 FUEL CONT VALVE ENG 4
　
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