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 B.  The flaps consist of one group of five segments and one group of six segments for each outboard wing. The segments are identified in numerical sequence beginning with the outboard segment of the left outboard wing and progressing to the right outboard wing outboard segment. Segments No. 1E thru 5 and No. 22 thru 26E are located outboard of the outboard nacelles on the left and right outboard wings respectively. Segments No. 6 thru 10 and No. 17 thru 21 are located between the engine nacelles of the left and right outboard wings respectively. Each segment is supported by two linkages which extend and contour the flap and extend the folding nose section.
 C.  The structural framework of the variable camber flaps consists of spanwise stringers supporting a flexible skin panel, linkage support fittings, and a folding nose assembly.
 D.  The stringers are installed spanwise on the skin panels along the fore and aft edges and in the center. The forward stringer (flaps retracted) is a modified J-section member machined from an aluminum extrusion for flap segments No. 6 thru 10 (and opposites), and an aluminum sheet formed member for segments No. 1A thru 5 (and opposites). The center stringers are extruded hat-section members of aluminum alloy. The aft stringers are basically tubular-type members fabricated from extruded rectangular tubes or mated channel sections of aluminum alloy.
 E.  The flexible skin panels are of laminated fiberglass construction. Actuator linkage hinge fittings are installed at two places on each stringer near the ends of each segment. Up-stop fittings are installed adjacent to the hinge fittings on the center stringers. The hinge and up-stop fittings are machined from aluminum alloy.
 F.  The folding nose section structure utilizes a spanwise spar and chordwise nose and tail ribs. The spar is a Z-section member formed from aluminum alloy sheet. Flanged lightening holes are incorporated in the nose rib web. The ribs are formed from aluminum alloy sheet and are attached to the spar. The folding nose section skin is a contoured aluminum alloy sheet. The folding nose assembly is attached to the main section of each flap by means of hinge fittings fastened to the Z-spar near the ends of the nose section. Two additional lugs on each hinge fitting provide attachments for the folding nose actuation linkages. The hinge fittings are machined from aluminum forgings. Seals are provided to improve the aerodynamic efficiency of the leading edge variable camber flaps in the faired position by eliminating gaps between flaps and adjacent structure.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 747-400 MAINTENANCE MANUAL 
SEE  B 
SEE  C  SEE  A 
NOSE FOLDING  (2 LOCATIONS) ACTUATOR LINKAGE HINGE FITTING  SPAR SPANWISE NOSE RIB SEAL TAIL RIB  A-A 
NOSE RIB 
FWD 
(EXAMPLE) A FLAP NO. 1E THRU 5 LEFT, NO. 22 THRU 26E RIGHT (3 LOCATIONS) STRINGER  SKIN PANEL FLEXIBLE 
Figure 1 (Sheet 1) Variable Camber Leading Edge Flaps Structure 

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

FOLDING NOSE
(2 PLACES) HINGE FITTING LINKAGE ACTUATOR 
LH AND NO. 21 RH TYPICAL FLAP NO. 6 
B  (3 PLACES) STRINGER 
(2 PLACES) HINGE FITTING LINKAGE ACTUATOR  A NOSE RIB  SKIN PANEL FLEXIBLE 

A
FOLDING NOSE
C AND NO. 17 THRU 20 RH TYPICAL FLAP NO. 7 THRU NO. 10 LH  SKIN PANEL FLEXIBLE 
(3 PLACES) STRINGER 
Figure 1 (Sheet 2) Variable Camber Leading Edge Flaps Structure

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
 1.

　
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