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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
~...........-...-....-......-..........-......-................................. | TABLE 201 | ................................................................................. | AIRPLANE |REF|FIG.| VIEW | LIMITS | AVG. | LIMIT DEVIATIONS | |EFFECTIVITY|NO.|201 | | | MAX | | ................................................................................. 2...........…...…....…......…..........…......….................................1
 TASK 71-11-00-822-003-N00
 3. Adjustment - Outer Surface of the Engine Cowling
________________________________________________
 A. Access
 (1)  
Location Zone
 412 Engine 1
 422 Engine 2
 432 Engine 3
 442 Engine 4

 B.
Procedure

 S 212-004-N00
 (1)  Make sure that the outer surfaces are free from dents, scratches or other damage.
 NOTE: Damage of this type can cause the cowling to come loose
____
 during a flight.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
PROBE ACCESS DOOR
AE-AE Y-Y
W-W  T-T 
V 
A  X  Z  AA 
V  X  Z  AA  AB  AC  AD  FAIRING AFT STRUT 
R-R  BB-BB  AB  AG 
24.4 INTERNAL INCHES  AL AK-AK  AL  AM  AGAF AF AC AQ AQ AQ AM  AD  AH  AH  THROAT 5 INCHES FROM END 
CRITICAL  BA  AM  AM  15 INCHES INTERNAL CRITICAL AREA 
AREA  AY  AY  AO  AQ  AJ  AJ  PRIMARY NOZZLE 
BA  AO 
10 INCHES INSIDE 
A  AR  AR  CRITICAL AREA 

FAN COWL AP-AP
INLET COWL
THRUST REVERSER
AIRFLOW  AIRFLOW
1
(+) POSITIVE STEP  (-) NEGATIVE STEP
Aerodynamic Smoothness Figure 201 (Sheet 1)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
OUTSIDE BODY SKIN SURFACE (EXAMPLE FOR STRAIGHT OR CURVED AREA)

FWD
CONCAVE OR CONVEX
SKIN SMOOTHNESS
THE SKIN SMOOTHNESS IN CRITICAL AND NON-CRITICAL AREAS ALONG CONTINUOUS SKIN SHOULD AGREE WITH THE
WAVE DEPTH -INCHES

LIMITS SHOWN AT RIGHT. (EXAMPLE FOR STRAIGHT OR CURVED AREAS).
WAVE LENGTH - INCHES

(AREAS NOT INCLUDED ARE SHOWN IN SECTION VIEWS) AERODYNAMIC SMOOTHNESS TOLERANCES 
CONDITION  LOCATION  CRITICAL  NON-CRITICAL 
1  WAVE DEPTH TO LENGTH RATIO  ALL SKINS  0.0025  SEE GRAPH 
WAVE DEPTH TO LENGTH RATIO 1.0 MAX DIA. DISHING AT FASTENERS  AT FASTENERS  0.0050  0.0100 
GAPS 
2  LONGITUDINAL (STREAMWISE) BUTT JOINT-MAX. GAPS  REMOVABLE PANELS  0.060  0.060 
HINGED PANELS  0.080  0.080 
FIXED SKINS  0.040  0.040 
3  BUTT JOINT GAPS TRANSVERSE (NORMAL TO AIRSTREAM)  FIXED SKINS  0.00 TO 0.03  0.00 TO +0.06 
REMOVABLE & HINGED PANELS  0.01 TO 0.07  +0.01 TO +0.07 
FLUSHNESS
4  LONGITUDINAL JOINT FLUSHNESS  FIXED SKINS  0.00 TO 0.03  0.00 TO +0.03
REMOVABLE & HINGED PANELS  0.00 TO 0.03  0.00 TO +0.03 
5  TRANSVERSE JOINT FLUSHNESS  FIXED SKINS  -0.02 TO 0.00  -0.03 TO +0.02 
REMOVABLE & HINGED PANELS  -0.035 TO +0.025  -0.04 TO +0.02 
　
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