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all airplanes)  Position flap handle to  Do test 
does not come on  40 units. Hold flap load  AMM 27-51-89/501 
(158 knots for  limiter test switch in  to determine if 
737-300, 737-500  SYSTEM TEST. Check that  airspeed switch 
with ARINC 429  flaps retract. Release  is bad or do test 
receiver, or 162  switch and check that flaps  AMM 27-51-00/501 
knots for  extend. Check that flap  to determine if 
737-400)  LOAD LIMITER TEST light comes on  bad component is bad. Replace ARINC 429 receiver or power supply PC board 
Flap position  Faulty flap  Perform flap asymmetry  Replace flap 
indicator  position indi- shutoff test  position indi-
pointers left and  cator  (AMM 27-51-00/501)  cator 
right are split and at the same time the primary flap drive system continues to  relay, R123 Faulty flap asymmetry shutoff  relay, R123 asymmetry shutoff Replace flap 401) (AMM 27-58-41/ 
operate. 
Flaps do not  Faulty flap load  Replace valve 
retract auto- limiter solenoid 
matically, but  valve (V94) 
FLAP LOAD RELIEF 
light (not on all 
airplanes) does 
come on 
Flaps retract  Faulty FLAP LOAD  Press-to-test FLAP LOAD  Replace faulty 
automatically,  RELIEF light  RELIEF light (not on all  light bulbs 
but FLAP LOAD  (not on all  airplanes). Check that 
RELIEF light (not  airplanes)  light comes on 
on all airplanes) 
does not come on 

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 27-51-00
 ALL  ú ú 01 Page 110 ú Jul 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
maintain level is required to or aileron trim additional rudder approach, During takeoff/ flight  mid-flap spindle broken flap carriage Outboard T.E.  ____NOTE: If L or R aileron suspect carriage side first for inspect opposite trim was required, for a fracture of the carriage spindle Check the tapered section then outboard panel carriage. Remove inboard to gain access to the Remove access panels from upper surface of midflap  (AMM 27-51-44/ 401) carriage Replace flap 

M25785
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 27-51-00
 ALL  ú ú 01 Page 111 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 TRAILING EDGE FLAP SYSTEM - MAINTENANCE PRACTICES
_________________________________________________
 1.  General
_______
 A.  There are two tasks in this procedure: There is one task for the deactivation and one task for the activation of the trailing edge flap system.
 B.  It is necessary to do the deactivation procedure for the trailing edge flap system before you do the work on the system. This is to prevent injury to persons and damage to equipment by the accidental operation of the trailing edge flaps. Make sure you put all equipment out of the limits of the travel of the trailing edge flaps.
 C.  The operation of the leading edge flaps and slats is related to the trailing edge flaps. Make sure to locate all equipment farther than the limits of travel of the leading edge flaps and slats.
 D.  To pressurize or depressurize hydraulic systems A and B refer to 29-15-00/201.
 TASK 27-51-00-042-001
 2.  Trailing Edge Flap System Deactivation
______________________________________
 A.  Special Tools and Equipment
 (1)
F80049-2, Lock Assembly

 B.  
References

 (1)
27-11-00/201, Aileron and Aileron Trim Control System

 (2)
27-61-00/201, Flight Spoiler Control System

 (3)
27-62-00/201, Speed Brake Control System

 (4)
27-81-00/201, Leading Edge Flap and Slat Control System

 C.  
Access

 (1)  
　
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