SPECIAL WASHER
PIN
BOLT
NUT
WASHER
BUSHING BUSHING
B-B
0.10 TO 0.15 INCH
(0.25 TO 0.38 cm) MIDFLAP
1  ACTUATOR ROD
COMPRESS 10-60%
WASHER
SEAL  WASHER
SEAL
RETAINER BOLT
NUT0.00 |0.06 INCH
(0.00 |0.15 cm)
AFTFLAP
0.40 TO 0.60 INCH
EDGE OF LE JOGGLE
(1.02 TO 1.52 cm) AFTFLAP AFTFLAP FITTING 6.35 TO 6.15 INCH FITTING
(16.1 TO 15.6 cm) BUSHING
C-C
D-D
Inboard Flap Adjustment Figure 503 (Sheet 2)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
SPOILER
3
FOREFLAP
4
SEAL RETAINER
ADJUSTABLE MIDFLAP TIE ROD SEAL
2
WING TRAILING EDGE  SEE TABLE I 
E-E 
SPRINGS 
BOLT 
(6 LOCATIONS) 
A 
SHIM  7 
PUSHROD 
ROLLER  MIDFLAP 
MIDFLAP  6  AFT ROLLER 
SUPPORT 
5 

CRANK
STRUCTURE ACTUATOR
WASHER
ROD
DEFLECTION CONTROL TRACK
F-F
D
1  WITH THE MOVABLE FAIRINGS INSTALLED 6 45.91 INCHES (116.6 cm) ON NUMBER 4 AND 5 AND THE SEALS COMPRESSED FLAP TRACKS
2 THE RODS MAY BE ADJUSTABLE AT ONE OF 7 THE REQUIRED CLEARANCE WILL CHANGE THE TWO ENDS DEPENDING ON WING LOAD AND AIRPLANES CONDITION AS FOLLOWS:
3  THE FOREFLAP TO MIDFLAP CLEARANCE IS
0.15 INCH (0.38 cm) MAXIMUM  0.45-0.55 INCH (1.14-1.40 cm) (WING IN JIGGED POSITION)
4
THE SPOILER HAS A 0.50 INCH (1.3 cm) PRELOAD AGAINST THE MIDFLAP 0.35-0.50 INCH (0.89-1.27 cm) (AIRPLANE ON GEAR, FUEL TANKS EMPTY)
5
45.08 INCHES (114.5 cm)
ON NUMBER 3 AND 6 FLAP TRACKS  0.17-0.27 INCH (0.43-0.69 cm) (AIRPALNE ON GEAR, FUEL TANKS FULL)
Inboard Flap Adjustment Figure 503 (Sheet 3)
C83785
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 ~............................................................................... | | Lower Trailing Edge Panel Seal-To-Inboard Midflap | | | Leading Edge Clearance (Inches) or | | | Seal Compressed Condition (%) for Retracted Flaps | | ...........................................................
 |  |  |Between Flap  |  |
 |  |  |Tracks (Center |  |
 |  |  |Panel)(Inboard |  |
 |  |  |Panel Outboard | At Midflap  |
 |  | At Midflap Inboard  |End)(Outboard  | Outboard End  |
 |  Airplane Load  | End (Inboard Panel  |Panel Inboard  | (Outboard Panel  |
 |  Condition  | Inboard End)  |End)  | Outboard End)  |

 ................................................................................. | Wing In Jig Position| 80 to 20% | 80 to 20% | 80 to 20% | | On Jacks I thru VIII| Compressed | Compressed | Compressed | ................................................................................. | On Jacks I, II & |60 to 0.0% | 78 to 18% | 80 to 20% | | III |Compressed *[2] |Compressed *[2]| Compressed *[2] | ................................................................................. | On Gear, Main Wing | +0.02 to +0.42 Inch | 76 to 16% | 78 to 18% | | Fuel Tanks Empty | (+0.51 to +10.67 mm)| Compressed | Compressed | | *[1] | Clearance *[2] | *[2] | *[2] | ................................................................................. | On Gear, Main Wing |+0.64 to +1.04 Inch | 74 to 14% | 95 to 35% | | Fuel Tanks Full |(+16.26 to +26.42 mm)| Compressed | Compressed | | *[1] |Clearance *[2] | *[2] | *[2] | 2.....................….....................…...............…...................1
 *[1]  USE LINEAR INTERPOLATION TO CALCULATE THE PANEL SEAL CONDITION FOR FUEL LOADS OTHER THAN THOSE SHOWN.
 *[2]  USE LINEAR INTERPOLATION TO CALCULATE THE PANEL SEAL CONDITION LIMITS AT LOCATIONS OTHER THAN THOSE SHOWN.
　
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