71-11-00
ALL ú ú C01 Page 6 ú Feb 25/86
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ENGINE COWLING - MAINTENANCE PRACTICES (AERODYNAMIC SMOOTHNESS)
_______________________________________________________________
1. General
_______
A. The access doors and panels of the engine cowling are in areas where aerodynamic smoothness is important.
B. Minimum clearances for gaps around doors and panels, and skin flushness at joints will minimize the aerodynamic drag.
C. If doors and panels are lost and replaced, it may be necessary to adjust the new panels and doors to get the correct clearances for aerodynamic smoothness.
D. All the dimensions shown are in inches.
E. Aerodynamic Smoothness Specifications
(1)
The table of clearances for aerodynamic smoothness are the general clearances for the engine nacelle.
(2)
Figure 201 gives general information to define the critical and non-critical areas of the engine nacelle, the definition of skin smoothness, and the smooth alignment of skin joints.
(3)
The section views in Figure 202 to 205 show the areas that have different clearances than the general clearances in the table.
(a)
Aerodynamic Smoothness for the Nose Cowl (Fig. 202).
(b)
Aerodynamic Smoothness for the Fan Cowl and the Forward Fairing (Fig. 203).
(c)
Aerodynamic Smoothness for the Thrust Reverser (Fig. 204).
(d)
Aerodynamic Smoothness for the Exhaust (Fig. 205).
TASK 71-11-00-202-001-C00
2. Aerodynamic Smoothness
______________________
A. Access
(1)
Location Zones
410 Left Power Plant
420 Right Power Plant
B.
Procedure
S 222-002-C00
(1) Examine the aerodynamic smoothness of the access doors, panels and the skin surfaces around the doors and panels.
(a)
Compare the clearances from the general clearances table and the section views in Figure 202 with what you see and measure around the skin joints, or access doors and panels.
(b)
If it is necessary, trim, shim or change the shape of the surfaces.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
71-11-00
ALL ú ú C01 Page 201 ú Mar 15/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
~............................................................................... | NECESSARY CLEARANCES FOR AERODYNAMIC SMOOTHNESS [1] [INCHES] | ................................................................................. | CONDITION | LOCATION | CRITICAL | NON-CRITICAL | ................................................................................. | WAVE DEPTH TO | ALL SKINS | 0.0025 | SEE THE SKIN | | LENGTH RATIO | | | SMOOTHNESS GRAPH | | | | | (FIGURE 201) | .................................................................................
| WAVE DEPTH TO | AT FASTENERS | 0.0025 | 0.0050 |
| LENGTH RATIO, | | | |
| 1.0 MAX DIAMETER | | | |
| DISHING AT | | | |
| FASTENERS | | | |
....................…..................…..................…...................... | GAPS | ................................................................................. | CONDITION | LOCATION | CRITICAL | NON-CRITICAL | ................................................................................. | LONGITUDINAL | REMOVABLE PANELS | 0.060 | 0.060 | | (STREAMWISE) ............................................................. | BUTT JOINT | HINGED PANELS | 0.07 [2] | 0.07 [2] | | MAX. GAPS ............................................................. | | FIXED SKINS | 0.030 | 0.040 | ................................................................................. | TRANSVERSE | FIXED SKINS | 0.00 TO +0.03 | 0.00 TO +0.06 [3] | | (NORMAL TO THE ............................................................. | AIRSTREAM) | REMOVABLE AND | +0.01 TO +0.06 | +0.01 TO +0.07 | | BUTT JOINT GAPS | HINGED PANELS | [2] | | ....................…..................…..................…...................... | FLUSHNESS | ................................................................................. | CONDITION | LOCATION | CRITICAL | NON-CRITICAL | ................................................................................. | LONGITUDINAL | FIXED SKINS | [2] | -0.03 TO +0.03 | | JOINT FLUSHNESS ............................................................. | | REMOVABLE AND | -0.02 TO +0.02 | -0.03 TO +0.03 | | | HINGED PANELS | | | ................................................................................. | TRANSVERSE | FIXED SKINS | [2] | -0.03 TO +0.03 | | JOINT FLUSHNESS ............................................................. | | REMOVABLE AND | -0.02 TO +0.02 | -0.03 TO +0.03 | | | HINGED PANELS | | | 2...................…..................…..................….....................1 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 動力裝置 POWER PLANT 2(103)
