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(IF THE AIRPLANE HAS BEEN ADJUSTEDTHE LEFT AND THE RIGHT TAB TOTALS WILL BE EQUAL FOR LATERAL TRIM, THE OUTBOARD FLAPSIN 0.15 INCH (3.81 mm) OR LESS.
MIGHT NOT BE SYMMETRICAL.) THE CLEARANCE BETWEEN THE DEFLECTION CONTROL 3. (+) SHOWS CONTROL SURFACE ABOVE TE. RAMP AND THE ROLLER AT THE OUTBOARD END OF THE (-) SHOWS CONTROL SURFACE MIDFLAP. BELOW TE (LINEAR DIMENSIONS ARE INCHES AND MILLIMETERS ARE IN
AT THE INBOARD ACTUATOR OF NUMBER 4 AND 5 SPOILERS
PARENTHESIS).
SHOWN FOR AN AIRPLANE ON THE GEAR WITH FUEL: 4. SEE THE APPLICABLE MAINTENANCE . FOR AN AIRPLANE ON THE GEAR WITH NO FUEL USE MANUAL SECTIONS TO GET THE0.08 TO 0.18 INCH (2.03 TO 4.572 mm) CHART DIMENSIONS.
. FOR AN AIRPLANE ON JACKS WITH NO FUEL USE
0.03 TO 0.13 INCH (0.76 TO 3.30 mm).
IF THE AIRPLANE HAS BEEN ADJUSTED FOR LATERAL TRIM, AIRPLANE CONFIGURATION
THE FLAP-TO-WING CHORD DIMENSION MIGHT BE MORE THAN WHEN INSPECTED
0.001-0.25 INCH (0.0254 TO 6.35 mm).
IF THE AIRPLANE HAS BEEN ADJUSTED FOR LATERAL TRIM, THE FLAP SCREW STOPS SETTING MIGHT BE MORE THAN
ON JACKS 170`-190`F (77`-88`C).
ON LANDING GEAR, NO FUEL
ON LANDING GEAR, WITH FUEL
DATA SHEET 

 

 

 

 

 

 

 

 

AIRPLANE NO.

AIRPLANES WITH ALUMINUM TAB CONTROL RODS
AIRPLANES WITH TITANIUM TAB
CONTROL RODS
____ USE THE DATA SHEET TO WRITE OTHER INFORMATION
NOTE: THAT YOU THINK IS IMPORTANT.
Flight Controls Surface Mismatch Record Figure 501 (Sheet 2)
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 27-09-71
 ALL  ú
 ú  01  Page 506
 ú  Nov 12/01 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
RUDDER FLAP AILERON TRIM TRIM
4.5`  4.5`
0 CRUISE
0
250K

CONTROL

6`3` 0 3`6` WHEEL FLIGHT
(TRIM
(1.0) (0.5)  (0.5) (1.0)
UNITS) LEFT WHEEL RIGHT WHEEL
FLAP SETTING.
1
15
40
PILOT REPORTED TRIM POINTS. MAKE A RECORD OF THE RUDDER TRIM.
MAKE A RECORD BELOW OF OTHER RELATED PILOT COMMENT
(FEEL FORCE, CENTERING, VIBRATION, ROUGHNESS, ETC.)

Trim Correction Graphic Aid
Figure 501A

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 27-09-71
 ALL  ú ú 02.1 Page 507 ú Jul 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
 C.

D.
E.
A
737-300/400/500MAINTENANCE MANUAL
Access
 (1)  
Location Zone 307 Wing Trailing Edge Outboard Flap and Spoilers, LH 407 Wing Trailing Edge Outboard Flap and Spoilers, RH

 (2)  
Access Panel 8207 Outboard TE Flap Access Panel, LH 8208 Outboard TE flap Access Panel, LH 8707 Outboard TE Flap Access Panel, RH 8708 Outboard TE Flap Access Panel, RH

Prepare for Adjustment
 S 865-021
 (1)  
Pressurize hydraulic system B (AMM 27-51-00/201).

 S 865-022

 (2)  
Move the flap control lever to the 40-unit detent.

 S 865-023

 (3)  
Release pressure from hydraulic system B (AMM 27-51-00/201).

 S 015-024

 (4)  
Remove access panels from the top surface of the midflap to get

 access to each carriage bearing support.Adjust the Outboard Trailing Edge Flaps
 S 865-065
 (1)  Do these steps if trim correction is necessary:
 CAUTION: MAKE SURE TO REMOVE ONLY ONE CARRIAGE BEARING SUPPORT AT A
_______ TIME FROM EACH FLAP. THIS IS TO PREVENT THE FLAPS FROM DAMAGE.
 (a)  
Remove the bolts that attach the left and right wing carriage bearing supports (Fig. 502).

 (b)  
Measure the total shim thickness below the left and right carriage bearing supports.

 (c)  
Make a record of the total shim thickness.

 (d)  
Find the change in the shim thickness for the FLAP UP trim correction (Fig. 503).

 NOTE: The recommended total shim thickness is 0.20 inch
____ maximum. The permitted total shim thickness will not be more than 0.23 inch. The total shim thickness includes the shims installed during the assembly and installation plus the shims added for a trim correction. If you made trim correction, the dimension between the trailing edge flap and the wing chord plane can be more than 0.00 to
　
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