27-61-00
ALL ú ú 01 Page 1 ú Mar 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
Spoiler Panel Identification
Figure 1
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27-61-00
ALL ú ú 01 Page 2 ú Oct 20/83
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
FLIGHT CONTROLS FLIGHT SPOILERS
HYDRAULIC MODULAR
PACKAGE - SYSTEM B
SPOILER CONTROL QUADRANT WHEEL WELL CEILING 6 7 WING REAR SPAR
CABIN FLOOR
SPOILER RATIO CHANGER AND MIXER
AILERON
CONTROL
FLIGHT SPOILERS CABLES - AB
AILERON
2 3 CONTROL
CABLES - AA
SPOILER ACTUATOR AILERON SPRING
ACTUATOR QUADRANT
CARTRIDGE FLIGHT CONTROLS
AILERON CAPTAIN'S AILERON TRANSFERHYDRAULIC MODULAR BUS DRUMS CONTROL WHEEL MECHANISMPACKAGE - SYSTEM A
WHEEL WELL
FIRST OFFICER'S
FORWARD
AILERON CONTROL
BULKHEAD
WHEEL
Spoiler Control System Component Location
Figure 2
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27-61-00
ALL ú ú 01 Page 3 ú Oct 20/83
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
D. An auxiliary set of control cables runs from a transfer mechanism at the base of the first officer's control column to a spoiler control quadrant which also drives the spoiler ratio changer. If a malfunction occurs to restrict operation of the aileron control system, the first officer may transmit lateral control signals to the ratio changer through these cables. When spoiler control is obtained in this manner, the first officer is required to override a spring in the transfer mechanism. If a malfunction occurs to restrict operation of the spoiler control system, the captain may override the spring in the transfer mechanism to provide aileron control. See 27-11-00, Aileron and Aileron Trim Control System, for a complete description of the transfer mechanism.
E. Each spoiler is operated by its own actuator. Hydraulic power to operate the spoilers is obtained from hydraulic system B for the outboard flight spoiler on each wing, and from hydraulic system A for the inboard flight spoiler on each wing. Maximum hinge moment on the spoilers is limited by a check valve in each actuator, permitting the spoiler panels to blow down if limiting speed is exceeded with spoilers up.
F. Electric motor-driven shutoff valves, located in the flight controls hydraulic modular packages, allow the flight crew to shut off spoiler hydraulic power from sysem A, system B, or both systems. The system A flight controls hydraulic modular package is in the left wheel well and the system B flight controls hydraulic modular package is in the right wheel well. Control switches for these two shutoff valves are on the pilots' overhead panel.
2. Flight Spoilers
_______________
A. The spoilers are constructed of graphite epoxy over a nomex honeycomb core for weight saving. A continuous phenolic rub strip is bonded to the lower surface at the trailing edge. Dacron covered silicone rubber seals are installed at each end and at the forward edge. The seals at each end are adjustable. The flight spoilers (No. 2, 3, 6, and 7) and the outboard ground spoilers (No. 0, 1, 8, and 9 are interchangeable among themselves.
B. Spoilers are attached to the wing structure by four hinge fittings equipped with self-aligning bearings (Fig. 3). The flight spoilers are located forward of the outboard flaps and are attached to wing structure aft of the rear spar. The four flight spoiler actuators are attached between the spoilers and wing structure at the spanwise center of each spoiler. Bonding jumpers provide an electrical bond between spoilers and wing structure. A blade seal along the bottom length of the spoiler acts as a dam to limit excessive air leakage through the flaps.
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