(d)  
While you hold the nut (3) with the wrench A71034, tighten the bolt (6) to 7500-9700 pound-inches (847.4-1075.9 newton-meters).

 (e)  
Align the link and install the link pivot pin (10) through the clevis boss for the engine mount and the link.

 (f)  
Install the bolt (11), nut (8) and washer (9) with the bolt head on the forward side of the engine mount.

 (g)  
Tighten the nut (8) to 220-410 pound-inches (24.9-46.3 newton-meters).

 (h)  
Install the bolt retainer (12) with the bolt (1) and washer (2).

 S 434-020-N00
 (3)  
Install the turbine exhaust sleeve (AMM 78-11-01/401).

 (4)  
Install the power plant (AMM 71-00-02/401).

 S 414-024-N00
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 71-21-02
 ALL  ú ú N01 Page 404 ú Jun 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
ENGINE WIRE HARNESS - ADJUSTMENT/TEST
_____________________________________
 1.  General
_______
 A.  This procedure gives the steps to do two tests. These tests are for the electrical harnesses on the power plant which do not have cables with the external braid. One test is the circuit continuity test. The other test is the wire insulation test. This follows with steps to connect the connectors.
 B.  If the engine wire harness is damaged, repair the harness
 (AMM 71-50-00/801).

 TASK 71-50-00-845-020-N00
 2.  Engine Wire Harness - Adjustment/Test
_____________________________________
 A.  Equipment
 (1)  
Ohmmeter - Simpson 260 (or equivalent); Simpson Electric Co., 853 Dundee Ave., Elgin, IL 60120-3090, USA

 (2)  
Wrench - Glenair TG-70 (or equivalent); Glenair Inc., 1211 Air Way, Glendale, CA 91201, USA

 (3)  
Wrench, Strap - Daniels BT-BS-611 (or equivalent); Daniels Manufacturing Corp., 6103 Anno Ave., Orlando, FL 32809-5033, USA

 (4)  
Pliers, Connector Soft Jaw - Glenair TG-69 (or equivalent); Glenair Inc., 1211 Air Way, Glendale, CA 91201, USA

 B.  
Consumable Materials

 (1)  
Lockwire - MS20995N20

 C.  
References

 (1)  
AMM 24-22-00/201, Electrical Power - Control

 (2)  
AMM 71-11-04/201, Fan Cowl Panels

 (3)  
AMM 71-11-06/201, Core Cowl Panels

 (4)  
AMM 71-50-00/801, Wire Harness Repair

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

 D.  
Access

 (1)  
Location Zones
 412 Engine 1
 422 Engine 2
 432 Engine 3
 442 Engine 4

 (2)  
Access Panels 416 and 417 Thrust Reverser Halves - Engine 1 426 and 427 Thrust Reverser Halves - Engine 2 436 and 437 Thrust Reverser Halves - Engine 3 446 and 447 Thrust Reverser Halves - Engine 4

 E.  
Prepare to Do the Engine Wire Harness - Adjustment/Test

 (1)  
Open the fan cowl panels (AMM 71-11-04/201).

 S 015-021-N00
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 71-50-00
 ALL  ú ú N01 Page 501 ú Jun 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 045-022-N00
 WARNING: DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
_______
 OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
 THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO
 EQUIPMENT.

 (2)  
Do this procedure: Thrust Reverser Deactivation for Ground
 Maintenance (AMM 78-31-00/201).

 S 015-023-N00

 (3)  
Open the core cowl panels (AMM 71-11-06/201).

 S 015-024-N00
 WARNING: DO THE PROCEDURE IN 78-31-00/201 TO OPEN THE THRUST REVERSERS.
_______
 IF YOU DO NOT USE THIS PROCEDURE, YOU CAN CAUSE INJURY TO
 PERSONS OR DAMAGE TO EQUIPMENT.
　
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