(a)  
Remove the protective covers from the electrical connectors.

 (b)  
Find the air valve actuator for the TCC at the 2 o'clock position.

 (c)  
Connect the W4P16 connector to the air valve actuator for the TCC.

 S 424-106-N00
 (8)  
Adjust the W4 harness to get the necessary clearances.

 S 424-105-N00

 (9)  
Install the clamps on the harness at the tape marker locations.

 (a)  
Make sure you can see the tape marker on both sides of the clamp.

 (b)  
Make sure the tracer cord is pointed outboard.

 (10)
 Install the clamps at all the clamp locations.

 (11)
 Lubricate threads for the nuts and bolts with engine oil.

 S 424-104-N00
 S 424-103-N00
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 73-21-07
 ALL  ú ú N01A Page 433 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 424-102-N00
 (12)
 Loosely install the bolts and nuts to the clamps for the W4 wiring
 harness.

 S 424-101-N00

 (13)
 Make sure the wiring harnesses are not pulled too tightely between
 any two clamps.

 S 424-100-N00

 (14)
 Make sure the wiring harness does not touch any engine parts.

 S 424-099-N00

 (15)
 Make sure the wiring harness is not pulled too tightly where the
 wiring harness attaches to the connectors.

 S 424-098-N00

 (16)
 Tighten all the nuts and bolts for the clamps on the harness to
 36-40 pound-inches (4.067-4.519 newton-meters).

 F.
Put the Airplane Back to its Usual Condition

 S 414-122-N00
 WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
_______
 THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,
 INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.

 (1)  
Close the right thrust reverser (AMM 78-31-00/201).

 S 414-120-N00

 (2)  
Close the right core cowl panel (AMM 71-11-06/201).

 S 414-119-N00

 (3)  
Close the right fan cowl panel (AMM 71-11-04/201).

 S 444-118-N00

 (4)  
Do the activation procedure for the thrust reverser
 (AMM 78-31-00/201).

 S 864-117-N00

 (5)  
For the applicable engine, remove the DO-NOT-CLOSE tags and close
 these circuit breakers as follows:

 S 864-116-N00

 (6)  
AIRPLANES WITH THE AUTOMATIC ENGINE START;
 For the applicable engine, remove the DO-NOT-CLOSE tags and close
 these circuit breakers as follows:

 (a)  
P6 Main Power Distribution Panel
 1) 6G15 SCU ALT PWR ENG 1
 2) 6G23 ENG SCU 1

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 73-21-07
 ALL  ú ú N01A Page 434 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
3) 6G16 SCU ALT PWR ENG 2
 4) 6G24 ENG SCU 2
 5) 6G17 SCU ALT PWR ENG 3
 6) 6G25 ENG SCU 3
 7) 6G18 SCU ALT PWR ENG 4
 8) 6G26 ENG SCU 4

 S 714-115-N00
 (7)  Do the Test No. 6 - Electronic Engine Control (EEC) Idle Test and No. 7 - EEC Static Test (AMM 71-00-00/501).
 TASK 73-21-07-004-123-N00
 6.  Remove the EEC Wiring Harness W5________________________________
 A. Equipment
 (1)  
Strap Wrench TG-70

 (2)  
Torque Adapter PWA 85749 (optional)

 ~..................................................................... | HARNESS CONNECTORS WHERE THE TORQUE ADAPTER (PWA 85749) CAN BE USED | ....................................................................... | CONNECTOR | COMPONENT | ....................................................................... | W5P6 | EEC Alternator (N2 Transducer) | ....................................................................... | W5P11 | 2.9 Bleed Valve Solenoid | 2............…........................................................1
　
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