52-34-01
 ALL  ú ú 04 Page 422 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 5)  Put the adapter tube on the rotary actuator input shaft.
 NOTE: The direction of the rotation of the rotary
____ actuator input shaft is opposite to the direction of the actuator arm movement.
 6)  Install the adapter tube on the drive torque tube attachment bolt.
 I.  Cargo Door - Adjustment
 S 034-026
 (1)  
Loosen the forward and aft midspan latch pin fittings.

 S 014-042

 (2)  
Remove all eight lower latch pins.

 S 824-027

 (3)  
Adjust the door centering rollers (Fig. 405).

 (a)  
Turn the manual drive for the lift actuator to move the door until the thickest part of the ramp is above the roller.

 (b)  
Make sure the clearance from the ramp to the roller is correct. 1) If the airplane is on jacks, the correct distance is 0.04 +/- 0.01 inch on the two doors.

 2)  If the airplane is not on jacks, use the distances as follows: a) CLEARANCE 0.04 +/- 0.01 inch at both rollers on the
 forward door b) CLEARANCE 0.15 +/- 0.01 inch at the aft roller on the aft cargo door c) OVERLAP 0.07 +/- 0.01 inch at the forward roller of the aft door.
 (c)  Do these steps if it is necessary to get the correct clearance at the guide roller: 1) Remove the roller fitting 2) Change the thickness of the shim below the roller fitting 3) Install the roller fitting.
 S 824-051
 (4)  
You must connect the lift mechanism and adjust the forward cargo door with the airplane on its gear with the operating weight empty or leveled on jacks.

 S 824-028

 (5)  
Trim the door skin, if it is necessary, to get the clearances between the door and the body skin (Fig. 406).

 S 824-029

 (6)  
Adjust the hook pin fittings as follows (View B-B, Fig. 405):

 (a)  
Manually close the door until the hooks engage the hook pins, but the latch cams stay fully open.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 52-34-01
 ALL  ú ú 04 Page 423 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

+0.06 INCH -0.04
SPLICE
+0.06
INCH
-0.04
-0.12
SPLICE  SPLICE
+0.00
FWDINCH
-0.12

AFT DOOR SHOWN (EXAMPLE FOR FORWARD DOOR
NOTE:TRIM DOOR SKIN, IF REQUIRED, TO OBTAIN SPECIFIED CLEARANCES.
POSITIVE TOLERANCE INDICATES DOOR IS OUTSIDE BODY SKIN CONTOUR.
NEGATIVE TOLERANCE INDICATES DOOR IS INSIDE BODY SKIN CONTOUR.
FLUSHNESS TOLERANCES DO NOT APPLY TO SKIN LAP SPLICE AND RUNOUT AREA
(SHOWN CROSS-HATCHED).

20% OF THE TRAILING EDGE AREA MAY EXCEED SPECIFIED TOLERANCE BY +0.02 INCH 20% OF THE LEADING EDGE AREA MAY EXCEED SPECIFIED TOLERANCE BY -0.02 INCH 8% OF THE LEADING EDGE AREA MAY EXCEED SPECIFIED TOLERANCE BY +0.02 INCH 10 INCHES MAXIMUM OF THE TRAILING EDGE AREA MAY EXCEED SPECIFIED TOLERANCE BY -0.06 INCH IF YOU CANNOT GET THIS DIMENSION CORRECT WHEN THE OTHER CONTOURS ALIGN CORRECTLY,
IGNORE THIS DIMENSION.
Cargo Door Fair Tolerances and Door Skin Gaps
Figure 406 (Sheet 1)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 52-34-01
 ALL  ú ú 05 Page 424 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

747-400
MAINTENANCE MANUAL

UPPER TANGENT POINT

+0.06
0.18 INCH
-0.02 (AT UPPER FORWARD CORNER)

+0.06
+0.06
0.18 INCH0.18 INCH -0.02

-0.02
(ALONG LEFT-HAND SIDE STRAIGHT LINE BETWEEN AND LOWER EDGE) DIMENSIONS AT UPPER
AND LOWER TANGENT POINT

+0.06
0.29 INCH
-0.02
(AT LOWER AFT CORNER)
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 艙門 DOORS 3(47)