曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

 D.  The precooler exhaust duct and gearbox breather duct are installed on the left core cowl panel.
 E.  A hold-open rod, installed on the inner side of each core cowl panel, holds the core cowl panel in the open position. The hold-open rod is released from the stowed position and the top end is turned down to attach to a bracket on the engine flange. The hold-open rod must be fully extended to stay locked in the open position.
 F.  A port through the lower access door on the left core cowl panel gives access to the manual override for the starter control valve without the cowling or access doors opened.
LEFT FAN COWL PANEL
NOMEXADJUSTMENT(LEFT AND RIGHT COWLS)
COMPOSITE A-A B-B PANEL

Fan Cowl Panels Figure 3
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 71-11-00
 ALL  ú ú N01 Page 4 ú Feb 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.

FIRE
PRECOOLER EXHAUST (LEFT COWL ONLY)
HOLD-OPEN ROD (STOWED, ONE FOR EACH CORE COWL PANEL)
GEARBOX
BREATHER
DUCT (LEFT
COWL ONLY)
Core Cowl Panels
Figure 4

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 71-11-00
 ALL  ú
 ú  N01  Page 5
 ú  Feb 10/93 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
ENGINE COWLING - MAINTENANCE PRACTICES (AERODYNAMIC SMOOTHNESS)
_______________________________________________________________
 1.  General
_______
 A.  This procedure gives the task to adjust the engine cowling to the specified tolerances.
 B.  The access doors and panels on the engine cowling are very important areas for aerodynamic smoothness. After a removal or an installation, you must adjust the access doors and panels to the specified tolerances.
 TASK 71-11-00-822-001-N00
 2.  Adjustment - Engine Cowling Surfaces
____________________________________
 A.  Access
 (1)  
Location Zone
 412 Engine 1
 422 Engine 2
 432 Engine 3
 442 Engine 4

 B.  
Procedure

 S 822-002-N00
 (1)  Adjust for aerodynamic smoothness of the surfaces shown in Fig. 201 at or less than the specified tolerances given in Table 201.
 NOTE: In Table 201, use the tolerances given for all airplanes as
____ shown by the Airplane Effectivity "ALL" unless expanded tolerances for a specific airplane are shown.
 NOTE: All dimensions are shown in inches.
____
 (a)  If it is necessary, cut or bend the surfaces, or install the shims to adjust the access doors and panels for aerodynamic smoothness.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 71-11-00
 ALL  ú ú N01 Page 201 ú Oct 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
~...........-...-....-......-..........-......-................................. | TABLE 201 | ................................................................................. | AIRPLANE |REF|FIG.| VIEW | LIMITS | AVG. | LIMIT DEVIATIONS | |EFFECTIVITY|NO.|201 | | | MAX | | ................................................................................. | ALL | 1 | 3 | B.B | 0.14 | | | | | | | | 0.02 | | | ................................................................................. | ALL | 2 | 3 | C.C | +0.025 | | | | | | | | .0.035 | | | ................................................................................. | ALL | 3 | 4 | E-E | 0.14 | | | | | | | | 0.02 | | | ................................................................................. | ALL | 4 | 4 | F.F | +0.015 | | | | | | | | -0.025 | | | ................................................................................. | ALL | 5 | 4 | H.H | 0.10 | | | | | | | | 0.02 | | | ................................................................................. | ALL | 6 | 4 | H-H | 0.13 | | | | | | | | 0.07 | | | ................................................................................. | ALL | 7 | 4 | I.I | +0.000 | | | | | | | | -0.010 | | | ................................................................................. | ALL | 8 | 5 | J.J | 0.09 | | | | | | | | 0.03 | | | ................................................................................. | ALL | 9 | 5 | J-J | 0.09 | | | | | | | | 0.03 | | | ................................................................................. | ALL | 10| 5 | K.K | +0.03 | | | | | | | | -0.03 | | | ................................................................................. | ALL | 11| 5 | L.L | +0.02 | | | | | | | | -0.02 | | | ................................................................................. | ALL | 12| 5 | M-M | 0.90 | | | | | | | | 0.84 | | | ................................................................................. | ALL | 13| 5 | M.M | +0.030 | | | | | | | | -0.030 | | | ................................................................................. | ALL | 14| 5 | M.M | 0.050 | | | | | | | | 0.030 | | | ................................................................................. | ALL | 15| 5 | N-N | 0.15 | | | | | | | | 0.05 | | | .................................................................................
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 動力裝置 POWER PLANT 2(51)