C
Hydraulic Brake Assembly
Figure 3 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH DUNLOP CARBON BRAKES ú
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(5)
The approximate brake wear remaining is indicated by the amount the end face of pin protrudes through tube in the bracket when brake is applied.
(6)
A hydraulic hose disconnect fitting is attached at the top of the brake. The fitting provides a connection between the brake hydraulic hose and the brake. The disconnect fitting will automatically close the hydraulic line on both the hose and brake sides upon removal which will eliminate hydraulic line bleeding requirements after brake replacement.
(7)
A bleed plug is installed at the top of the brake assembly, adjacent to the disconnect fitting. The plug can be used to bleed air from the hydraulic brakes.
H.
GUN 051;
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Hydraulic Brake Assembly (BF Goodrich Steel Brake) (Fig. 3A)
__________________________________________________
(1)
The brake assembly is a conventional rotor-stator multiple disc unit. The brake housing is mounted on bushings which ride on main landing gear axle sleeves. A brake rod (torque arm) attaches between the lower brake housing, at a pin joint, and the yoke of the shock strut. The brake is thus allowed to rotate on the axle with corresponding landing gear truck position changes. Lubrication fittings are provided for brake rod and axle bearing joints.
(2)
Brake pressure is applied hydraulically through six pistons which push against a pressure plate. The pressure plate in turn slides axially against the stators and rotors to compress against the torque plate. When pressure is released, brake adjuster springs pull the pressure plate back from contact with the rotor-stator stack.
(3)
The six brake adjusters automatically maintain the offset of the pressure plate from the rotor-stator stack. As the brake disks wear, the adjustor compensates by allowing a pin and ball mechanism to deform a circular tube to automatically hold the required offset.
(4)
Two wear pins are installed in each brake assembly which indicate when brakes require replacement. The pins attach to the pressure plate and protrude through a brake housing bracket at grommet locations. The wear pins on new brakes initially protrudes 1 3/8 inch past the grommets with brakes applied and when brakes need replacing the protrusion will be zero.
I.
Indication (Fig. 4)
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(1)
A BRAKE SOURCE amber indication light (Detail A) is installed on the pilot's P1 panel. The BRAKE SOURCE indication illuminates when both the right (normal) hydraulic system and left (alternate) hydraulic system are approximately 48 percent or less of normal system pressure.
(2)
The RESERVE BRAKES panel (Detail A) includes a selector switch with a white ON indicator light. The ON light indicates when RESERVE BRAKES source is selected.
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FITTING QUICK DISCONNECT (3 LOCATIONS) STATOR SEGMENTED A CONNECTOR HYDRAULIC HOSE
BLEED PLUG
(LINED) PLATE TORQUE (6 LOCATIONS) PISTON
HOUSING
BRAKE
FWD AND SLEEVES AXLE BUSHINGS
SEE A
(12 LOCATIONS) BRAKE TIE BOLTS
FITTING DISCONNECT (4 LOCATIONS) ROTOR (LINED) PLATE PRESSURE SEGMENTED LINING A A (6 LOCATIONS) AUTOMATIC ADJUSTER POINT ATTATCHMENT BRAKE ROD
SEE B SEE B
PIN INDICATOR WEAR GROMMET
A-A PRESSURE PLATE BRACKET GUIDE
HOUSING PISTON
WEAR INDICATOR
B
Figure 3A Hydraulic Brake Assembly (BF Goodrich Steel Brake)
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本文鏈接地址：757 AMM 飛機維護手冊 起落架 CHAPTER 32 - LANDING GEAR 2(129)
