(1)
AMM 24-22-00/201, Manual Control

 (2)
AMM 25-52-65/401, Cargo Compartment Ceiling Lining

 (3)
AMM 27-51-00/201, Trailing Edge Flap System

 (4)
AMM 27-51-87/501, Flap Limit Switches

 (5)
AMM 27-58-01/501, Trailing Edge Flap Position Indicating SystemAccess

 (1)  
Location Zone 101, 102 Control Cabin 202 Lower Nose Compartment 216, 217 Main Wheel Well 218 Aft Cargo Compartment 307, 407 Wing Trailing Edge Outboard Flap and Spoilers 309, 409 Wing Trailing Edge Inboard Flap and Spoilers

 (2)
Access Panels

 1103 Forward Access DoorPrepare to Adjust the Trailing Edge Flap System
 S 865-012
 (1) Supply the electrical power (AMM 24-22-00/201).
 S 865-013
 WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LE AND TE
_______ FLAPS AND FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAPS. THE FLAPS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
 CAUTION: CAREFULLY MONITOR THE FLAP MOVEMENT IF YOU HAVE DONE WORK ON
_______ THE FLAP CONTROL SYSTEM OR THE FLAP DRIVE SYSTEM. INCORRECTLY ADJUSTED COMPONENTS CAN CAUSE DAMAGE TO THE FLAP SYSTEM.
 (2) Retract the trailing edge flaps:
 WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL
_______ CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, TRAILING EDGE FLAPS, LEADING EDGE FLAPS AND SLATS, SPOILERS LANDING GEAR AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
 (a)
Supply the system B hydraulic power (AMM 27-51-00/201).

 (b)
Move the flap control lever to the UP detent.

 (c)
Stop for 2 minutes to make sure the flap movement stops.

 (d)
Remove the system B hydraulic power (AMM 27-51-00/201).Adjust the Flap Control Cables

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-00
 ALL  ú ú 02 Page 505 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

TEMP `F

1
5
6
117
152 90
110
108
140 70
100
130 50
 91
118 30
83
108 +10
74
 96 -10
65
 85-30
57
 74-40
52 68CABLE FUNCTION
CODE WFA
WING FLAPS UP
WFB
WING FLAPS DOWN
WFFA WING FOLLOW-UP FLAPS UP
WFFB WING FOLLOW-UP FLAPS DOWN
TABLE 3
ADJUSTMENT LOAD +10/-0 POUNDS 3/32 AND 1/8 INCH DIAMETER CABLES WFA AND WFB

ADJUSTMENT LOAD 3/32 INCH DIA CABLES WFFA AND WFFB +10/-0 POUNDS

71 65 60 55 49 44 38 33 30

TO MAKE SURE YOU GET THE CORRECT CABLE TENSION, PERMIT THE AIRFRAME TEMPERATURE TO STABILIZE (|5 DEGREES) FOR A MINIMUM OF ONE HOUR.
FOR THE NECESSARY PERIODIC CHECKS WITHOUT A SYSTEM DISCREPANCY REPORT, THE CABLE TENSIONS CAN BE +15/-30 POUNDS FROM THE VALUES IN THE TABLE 3. IF YOU DO A CHECK ON THE CABLE TENSION BECAUSE OF A SYSTEM DISCREPANCY REPORT, THE CABLE TENSIONS CAN BE |15 POUNDS FROM THE VALUES IN THE TABLE. WHEN YOU ADJUST THE CABLE TENSION, YOU MUST GET THE TENSION IN THE LIMITS SHOWN IN THE TABLE.
FOR THE NECESSARY PERIODIC CHECKS WITHOUT A SYSTEM DISCREPANCY REPORT, THE CABLE TENSIONS CAN BE |20 POUNDS FROM THE VALUES IN THE TABLE 3. IF YOU WILL CHECK THE CABLE TENSION BECAUSE OF A SYSTEM DISCREPANCY REPORT, THE CABLE TENSIONS CAN BE |15 POUNDS FROM THEVALUES IN THE TABLE. WHEN YOU ADJUST THE CABLE TENSION, YOU MUST GET THE TENSION IN THE LIMITS SHOWN IN THE TABLE.
THE FORWARD CABLES ARE 3/32 INCH DIAMETER. THE AFT CABLES ARE 1/8 INCH DIAMETER.
AIRPLANES WITH A TWO-PIECE WFA/WFB FLAP CONTROL CABLE.
AIRPLANES WITH A ONE-PIECE WFA/WFB-2 FLAP CONTROL CABLE.
Trailing Edge Flap System Adjustment
Figure 501 (Sheet 1)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-00
 ALL  ú
 ú  02  Page 506
 ú  Jul 15/91 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 S 825-014
 (1)  
Do a check of the adjustment of the flap control cables WFA and WFB (Fig. 501):
　
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