27-00-01
ALL ú ú 02 Page 15 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
CABLE REF REQ NO. 21 (TO NEAREST TENTH LENGTH INCH) 6FITTINGS
1 2
SBB-3 SBA-3 SBB-2 SBA-2 SBB-1 SBA-1 1 1 932.9 922.2 245.5 270.0 75.8 63.0 MS21260L4LH MS21260L4LH MS21260L4RH MS21260L4LH MS21260L4RH MS21260L4LH MS21260L4RH BACT14A4 BACT14A4 MS21260L4RH BACT14A4 BACT14A4
MATERIAL:
CABLE - CARBON STEEL PER BMS 7-265, TYPE I, COMPOSITION A (TIN OVER ZINC)
FITTINGS: CORROSION RESISTANT STEEL PER MIL-T-781
CABLE SIZE - 1/8 7 X 19
REFERENCE ONLY. FOR SPECIFIC PART NUMBER, EFER TO CURRENT IPC MEASURE LENGTH OF CABLE WHILE APPLYING 37- TO 43-POUND TENSION LOAD
SBA, SBB, -1, -3
SBA, SBB, -2
Speed Brake Control Cables
Figure 6 (Sheet 3)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-00-01
ALL ú
ú 02 Page 16
ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
B. Adjust all seals during rigging to prevent any bending of cables. Control cables must not be bent by fairleads, rub strips, or groomets after rigging at normal operating positions. The minimum clearance between all control cables and adjacent structure or other installations including but not limited to hydraulic tubes, wire bundles and control brackets must be 0.20 inch except for fairleads, rub strips, or grommets. For pulley brackets and structure within 10 inches of the cable break point the minimum cable clearance must be 0.10 inch. Exceptions to the above: The cables can be deflected by wing bending or installation tolerances on wing cable runs where grommets in non-adjustable mountings, cable guard and guard blocks are installed. AA and AB cables can sag to lower surface of grommets at RBL 103.70 and RBL 106.25, WL 197.5, between STATIONS 660 and 1250.
NOTE: You can mix zinc-only and tin-zinc coated cables but opposite
____ cable segments in the same cable loop must be of the same type (for example, in figure 2, cables AA-3 and AB-3 must be replaced together with both new cables either zinc-only or tin-zinc). This will prevent asymetric cable stretch that can make cable rigging bad.
C. Control cables in the flight control system transmit the pilots' control inputs to the corresponding control surface actuators. A typical control cable system terminates at a drum or quadrant by means of swaged terminals and has turnbuckles to allow tensioning the cable to the proper rigging load. Long cable runs are supported by idler pulleys. Air seals are used to reduce pressure loss when cables are routed through pressure bulkheads.
D. Control cables for aileron, spoiler and speed brake control systems are routed under flight control compartment, above main deck compartment ceiling (spoiler and speed brake cables) and through lower cargo compartment ceiling (aileron cables), and down through air pressure seals in rear spar canted bulkhead of aileron quadrants, spoiler differential mechanism and speed brake quadrants mounted on center section rear spar. Control cables for ailerons and spoilers are routed from center section rear spar to aileron and spoiler power control packages attached to outboard wing rear spars. Speed brake cables terminate at quadrants in wheel well rear spars.
E. The control cables for the elevator system is routed under the flight control compartment, above the main deck compartment ceiling, through air seals at the aft pressure bulkhead to the empennage. The elevator cables are routed under the stabilizer truss.
F. Control cable runs are identified by coded letter designations. The cable codes identify cable function. Markers showing proper cable routing utilize the codes (Fig. 1). The markers are mounted to structure above the main deck compartment ceiling.
G. Clad cables should not be replaced with nonclad cables, or vice versa.
H. Dies for the next larger size AN standard terminals are required for swaging all BACT14A terminals.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-00-01
ALL ú ú 02 Page 17 ú Feb 18/02
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 1(21)
