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 05-51-43
 ALL  ú ú 02 Page 201 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 
747-400 
MAINTENANCE MANUAL
 (g) (h)  Disconnect the track from the lever. Make sure that the track rolls in and out of the mid flap without binding on the flight load rollers or the dead weight rollers. Clean the fore flap cavity of the mid flap if/as necessary to prevent dirt and grit from contaminating the rollers. Refer to 747-400 AMM 27-51-02/401 for track disconnect instructions. Refer to 747 AMM 27-51-01/601 for wear limits.Connect the track to the lever. Refer to 747 AMM 27-51-02/401 for track connect instructions.
 (i)  Do a detailed external visual inspection of the main inboard flap tracks at WBL 235 and WBL 353. Look for gouges or scoring in the center cam surface. Look for cracks or deformation of
 (j)  the flap track. (747-400 AMM 27-51-22/601 and AMM 27-51-25/601).Do a detailed external visual inspection of the Fore Flap leading edge. Look for dents and gouges. Refer to 747-400 SRM 57-53-01 for wear limits.
 (k)  Do a detailed external visual inspection of the mid flap upper panel. Examine the area surrounding the flore flap track cavity for damage. Look for dents and gouges. Refer to 747-400
 SRM 57-53-01 for wear limits.
 (l) (m) (n) (o) (p) (q)  Do a detailed external visual inspection of the flap drive torque tubes. Look for damage (AMM 27-51-20/601).Do a detailed external visual inspection of the fixed trailing edge structure. Look for damage to the aileron hinge rib and systems braketry.Pressurize the hydraulic systems No.1 and 4 (AMM 29-11-00/201).Put the flap control lever in the UP detent to retract the trailing edge flaps.Remove pressure from the hydraulic systems No.1 and 4 (AMM 29-11-00/201).Put the Airplane Back to Its Usual Condition.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 05-51-43
 ALL  ú ú 01 Page 202 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 LANDING WITH DEFLATED NOSE GEAR SHOCK STRUT CONDITION
_____________________________________________________ (CONDITIONAL INSPECTION) - MAINTENANCE PRACTICES
________________________________________________
 1.  General
_______
 A.  One task is supplied in this procedure. The task is landing with deflated nose gear shock strut conditional inspection.
 B.  This examination is to make sure the nose landing gear shock strut is servicable and to find the cause for the nose landing gear shock strut to be deflated.
 C.  If an airplane lands with a deflated shock strut, and the procedures examination in this procedure finds damage, deformation, cracks, buckling, etc, make an inspection for hard landing of the specific landing gear with the deflated shock strut and the area of the airplane adjacent to the deflated shock strut per:
 (1)  The Phase I and Phase II examination of the nose landing gear and the adjacent structure (AMM 05-51-05/201).
 TASK 05-51-55-202-001
 2.  Landing with Deflated Nose Gear Shock Strut Conditional Inspection
__________________________________________________________________
 A.  References
 (1)  
AMM 07-11-02/201, Jacking Airplane Nose

 (2)  
AMM 12-15-05/301, Nose Landing Gear Shock Strut

 (3)  
AMM 29-11-00/201, Main Hydraulic Supply System

 (4)  
AMM 32-21-02/301, Nose Gear Shock Strut

 (5)  
FIM 32-51-00/101, Nose Wheel Steering System

 B.  Examine the Airplane Structure.
 S 212-002
 (1)
Examine the nose gear tires for cuts, bruises or signs of damage.

 S 212-003

 (2)  
Examine the nose gear wheels for cracks or deformation.

 S 212-004

 (3)  
Examine these items of the nose gear for distortion, cracks, and/or flaking paint:

 (a)  
Nose Gear Outer Cylinder

 (b)  
Nose Gear Inner Cylinder

 (c)  
Nose Gear Drag Strut

 (d)  
Nosa Gear Side Struts
　
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