(2)
AMM 27-81-00/201, Leading Edge Flap System
(3)
AMM 71-00-00/501, Power Plant
(4)
AMM 71-00-03/201, Power Plant
(5)
AMM 71-00-09/201, Power Plant
(6)
AMM 71-11-04/201, Fan Cowl Panels
(7)
AMM 71-11-04/401, Fan Cowl Panels
(8)
AMM 71-11-06/201, Core Cowl Panels
(9)
AMM 71-11-06/401, Core Cowl Panels
(10)
AMM 71-11-07/501, Core Cowl Panel Latch
(11)
AMM 78-31-00/201, Thrust Reverser System
(12)
AMM 78-31-04/401, Thrust Reverser
(13)
AMM 78-31-01/601, Thrust Reverser
(14)
AMM 78-31-02/501, Latch Bands
(15)
AMM 78-31-04/501, Tension Latches
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
71-00-02
ALL ú ú N05 Page 480P ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
E. Access
(1)
Location Zone
412 Engine 1
422 Engine 2
432 Engine 3
442 Engine 4
452 Strut No. 1 - Torque Box
462 Strut No. 2 - Torque Box
472 Strut No. 3 - Torque Box
482 Strut No. 4 - Torque Box
(2)
Access Panel
452JL Core Cowl Skirt Mid Fairing - Strut 1, Left Side
452JR Core Cowl Skirt Mid Fairing - Strut 1, Right Side
462JL Core Cowl Skirt Mid Fairing - Strut 2, Left Side
462JR Core Cowl Skirt Mid Fairing - Strut 2, Right Side
472JL Core Cowl Skirt Mid Fairing - Strut 3, Left Side
472JR Core Cowl Skirt Mid Fairing - Strut 3, Right Side
482JL Core Cowl Skirt Mid Fairing - Strut 4, Left Side
482JR Core Cowl Skirt Mid Fairing - Strut 4, Right Side
F.
Procedure
S 414-156-N00
(1)
If they are installed, close the core cowl panels
(AMM 71-11-06/201).
S 414-002-N00
(2)
Install the mid-fairing of the core cowl skirt (2) 452JL and 452JR, 462JL and 462JR, 472JL and 472JR, or 482JL and 482JR on each side of the strut on the aft engine mount (Fig. 401).
(a) Attach the mid-fairing (2) to the strut with the bolts (1).
S 434-017-N00
(3)
Install the pneumatic hose (5) to the precooler (Fig. 407, View A).
S 434-016-N00
(4)
Install the precooler inlet duct (15) with the steps that follow
(Fig. 407, View C):
(a)
Remove the caps from the precooler inlet duct (15).
(b)
Install the precooler inlet duct (15) with the seal (17) and clamp (16).
(c)
Tighten the clamp (16) to 110-125 pound-inches (12.4-14.1 newton-meters).
S 434-069-N00
(5) Install the thermal anti-ice (TAI) duct (24) of the inlet cowl with
the steps that follow (Fig. 407, view D):
(a) Remove the protection covers from the TAI duct (24).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
71-00-02
ALL ú ú N04 Page 480Q ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
(b) Install the TAI duct (24) on the engine.
1) Install the V-clamps (19) with the seals (18).
(c) Install the bolt (22), washers (21 and 23), and nut (20) on the
fan case bracket.
(d) Tighten the clamp nuts (19) to 85-100 pound-inches (9.6-11.3
newton-meters).
NOTE:____ Make sure the lock bolt does not extend above the top of
the TAI duct into the fan cowl panel.
S 424-155-N00
CAUTION: DO NOT LUBRICATE THE STATIC PRESSURE HOSE THAT CONNECTS TO THE
_______ EEC. THIS CAN CAUSE CONTAMINATION IN THE EEC.
(6)
Install the static pressure hose (29) for the EEC (Fig. 407, view F).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 动力装置 POWER PLANT 2(23)
