(b)  
Install a new packing (31), lubricated with engine oil, on the forward flange groove on the deoiler outlet tube (32).

 (c)  
Put the deoiler outlet tube (32) on the doiler outlet port on the rear of the main gearbox.

 (d)  
Put the brackets (23, 30) on the flange of the deoiler outlet tube (32).

 (e)  
Install the three bolts (22), threads lubricated with engine oil, which attach the deoiler outlet tube (32) to the rear of the main gearbox. 1) Tighten the three bolts (22) with your hand.

 (f)  
Install the bolts (24, 27), nuts (25), and clamps (26) which attach the deoiler outlet tube (32) to the M and N flanges. 1) Tighten the clamp bolts (24, 27) to 36-40 pound-inches

 (4.1-4.5 newton-meters).

 (g)  
Tighten the three bolts (22), which attach the deoiler outlet tube (32) to the main gearbox, to 62-72 pound-inches (7.0-8.1 newton-meters).

 (h)  
Tighten the clamp (28) which attaches the main filter oil tube (29) to the front flange of the deoiler outlet tube (32) to 36-40 pound-inches (4.1-4.5 newton-meters).

 (i)  
Connect the stator cables (17) to the clips on the bracket (23) that is attached to the flange of the deoiler outlet tube (32).

 S 414-047-N00
 (22)
 Install the starter (AMM 80-11-01/401).

 G.
Put the Airplane Back to Its Usual Condition

 S 414-083-N00
 WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00 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 thrust reversers (AMM 78-31-00/201).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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S 414-084-N00
 (2)  Close the core cowl panels (AMM 71-11-06/201).
 S 414-085-N00
 (3)  Close the fan cowl panels (AMM 71-11-04/201).
 S 444-086-N00
 (4)  Do the activation procedure for the thrust reverser (AMM 78-31-00/201).
 S 864-049-N00
 (5)  For the applicable engine, remove the DO-NOT-CLOSE tags and close this circuit breaker on the P6 panel:
 (a)  6K19 IGN 2 ENG 1
 (b)  6K20 IGN 2 ENG 2
 (c)  6K21 IGN 2 ENG 3
 (d)  6K22 IGN 2 ENG 4
 (e)  6G19 STBY IGN ENG 1
 (f)  6G20 STBY IGN ENG 2
 (g)  6G21 STBY IGN ENG 3
 (h)  6G22 STBY IGN ENG 4
 (i)  6G15 SCU ALT PWR ENG 1
 (j)  6G16 SCU ALT PWR ENG 2
 (k)  6G17 SCU ALT PWR ENG 3
 (l)  6G18 SCU ALT PWR ENG 4
 (m)  6G23 ENG SCU 1
 (n)  6G24 ENG SCU 2
 (o)  6G25 ENG SCU 3
 (p)  6G26 ENG SCU 4
 S 714-050-N00
 (6)  Do the test of the EEC alternator (N2 Transducer) that is shown in the Power Plant Test Reference Table (AMM 71-00-00/501).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
EEC SPEED TRANSDUCER (N1) - REMOVAL/INSTALLATION
________________________________________________
 1.  General
_______
 A.  This procedure removes and installs the EEC speed transducer (N1).
 B.  The EEC speed transducer (N1) is installed on the engine intermediate case at the 5 o'clock position.
 C.  You can get access to the EEC speed transducer (N1) through the right thrust reverser half. You must also remove the fan exit liner at the No. 3 position.
 TASK 73-21-06-004-001-N00
 2.  Remove the EEC Speed Transducer (N1) (Fig. 401)
____________________________________
 A.  References
 (1)  
AMM 71-11-04/201, Fan Cowl Panels

 (2)  
AMM 71-11-06/201, Core Cowl Panels

 (3)  
AMM 72-34-03/401, Fan Exit Liner Segment

 (4)  
AMM 78-31-00/201, Thrust Reverser System

 B.  
　
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