C.  The wing center section and the wing front spar are bolted together at Sta 996. A similar integration of the mid spar and the wing center box occurs at Sta 1136. The rear spar and the wing center section are connected at Sta 1236.
 D.  The wing to fuselage attachment is reinforced by the landing gear beams connected to the fuselage at the body station 1350 bulkhead. The keel beam which extends from the front spar through the wheel wells provides longitudinal reinforcement to the fuselage, and provides a structural connection for the wing center section underside, rear spar, and landing gear beams.
 6.  Empennage
_________
 A.  The empennage comprises a dorsal fin, a vertical fin, an adjustable horizontal stabilizer, upper and lower rudders, inboard and outboard elevators, fuel tank in the horizontal stabilizer center section, and a surge at the outboard end of right horizontal stabilizer.
 B.  The horizontal stabilizer is attached to the body by hinge and actuator attachments. The stabilizer center section is made of stiffened aluminum skin panels. These panels are supported by rib and spar assemblies constructed of aluminum sheet and extrusions. The outboard portions of the stabilizers consist of removable leading edges; auxiliary, front, and rear spars with interconnecting ribs; a forward torque box consisting of thin skin and closely spaced ribs; an aft torque box of aluminum skin-stiffener and rib construction; and a fixed trailing edge consisting of bonded panels and hinge rib construction for connecting to the elevators.
 C.  The inboard and outboard elevators are composed of fiberglass honeycomb panels and aluminum rib and spar structure. The elevators are hinged from the stabilizer rear spar.
 D.  The vertical fin is constructed in a similar manner to the outboard horizontal stabilizers. The fin is attached to the body by bolt attachments in the aft torque box and the pinned link at the auxiliary spar.
 E.  The upper and lower rudders are hinged from the rear spar of the fin box. They are of fiberglass honeycomb panel and aluminum rib and spar construction.
 7.  Engine Nacelles - Pylons
________________________
 A.  The four engines are individually mounted in nacelles and attached by pylons to the wing. A forward and aft fairing installation is affixed to each pylon. These fairing installations are nonstructural and support local pressure load only. They are made of aluminum alloy.
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 51-00-00
 ALL  ú ú 01 Page 7 ú Jun 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 REDUCED VERTICAL SEPARATION MINIMUM (RVSM) - INSPECTION/CHECK
_____________________________________________________________
 1.  General
 A.  RVSM airspace is any airspace where airplanes are separated by 1000 feet (instead of the current 2000 feet) vertically between Flight Level 290 and Flight Level 410. RVSM may be used in a specific area, on a specific route, or by a specific operator. RVSM would effectively double the available route assignments and provide benefits to operators through more optimized route assignments and reduced schedule delays. RVSM may also facilitate increased use of direct routings at altitudes not currently available.
 B.  This procedure contains one task. The task is to examine the airplane skin for smoothness in the area of the pitot-static probes.
 TASK 51-10-00-216-001
 2.  Examine the Airplane Skin
_________________________
 A.  Equipment
 (1)  G51001-21 - Skin Waviness Tool
 MIT65B00007 - Alternate Skin Waviness Tool

 B.  Access
 (1)  Location Zone
 100 Fuselage - Lower Half
 200 Fuselage - Upper Half

 C.  Procedure
 S 826-003
 (1)  Calibrate the measuring tool (Fig. 601).
 NOTE: After ten airplanes have been measured, the measuring tool
____ should be calibrated as shown in this procedure.
 NOTE: The tool should be used at the same temperature as it was
____ when it was calibrated. The tool will change its shape in different temperatures adversly affecting the accuracy of the tool.
 (a)  
　
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