(e)
Place RRCM test switch from TEST to NORMAL. 1) Check ratio changer actuator fully retracts. 2) Check that IN TEST light remains on for 15 seconds. 3) Check PCA and TEST FAIL faultballs do not set.
(f)
Repeat BITE test for remaining RRCM.
(g)
Remove hydraulic power.
(h)
Remove electrical power if no longer required.
C.
Control
_______
(1) Provide electrical power (AMM 24-22-00/201).
WARNING: TO PREVENT INJURY OR DAMAGE, KEEP PERSONNEL AND EQUIPMENT CLEAR
_______ OF ALL CONTROL SURFACES BEFORE PROVIDING HYDRAULIC POWER. AILERONS, ELEVATORS, RUDDER, TRAILING EDGE FLAPS, LEADING EDGE SLATS, AND SPOILERS ARE FULLY POWERED.
(2) Provide left, center, and right hydraulic systems power
(AMM 29-11-00/201).
NOTE: Hydraulic power from only one system is required to operate
____
rudder.
(3)
Rudder Pedals Control
(a)
Push right pedal for right rudder, push left pedal for left rudder.
(b)
Remove foot pressure on pedals to return rudder to neutral or trimmed position.
(4)
Rudder Trim Control
(a)
Rotate trim knob right for right trim, left for left trim.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-21-00
ALL ú ú 05 Page 38 ú Sep 20/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
(5) (6) (b) Rotate trim knob until trim indicator reads zero units to return rudder to neutral.Remove hydraulic power.Remove electrical power if no longer needed.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-21-00
ALL ú ú 06 Page 39 ú Sep 20/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
FAULT ISOLATION/MAINT MANUAL
RUDDER AND RUDDER TRIM CONTROL SYSTEM
COMPONENT SHT 102 FIG. QTY ACCESS/AREA AMM REFERENCE
ACTUATOR - RUDDER TRIM, M515 3 1 324AL, RUDDER FEEL, CENTERING, 27-21-06
AND TRIM MECHANISM
ACTUATOR (PCA) - RUDDER POWER CONTROL 4 3 324CL, MID VERT FIN 27-21-20
ACTUATOR (RRCA) - RUDDER RATIO CHANGER, M626 4 1 324BL, LWR VERT FIN 27-21-13
ASSEMBLY - AFT QUADRANT 3 1 324AL, RUDDER FEEL, CENTERING, 27-21-06
AND TRIM MECHANISM
ASSEMBLY - RUDDER FORWARD QUADRANT AND 2 2 113AL, FWD EQUIP COMPT 27-21-05
JACKSHAFT
ASSEMBLY - RUDDER PEDAL 2 2 FLT COMPT AND 113AL, FWD EQUIP 27-21-02
COMPT
ASSEMBLY - YAW DAMPER SUMMING LEVER 4 1 324BL, LWR VERT FIN 27-21-17
CABLE - (AMM 27-00-01/201)
RUDDER CONTROL
CIRCUIT BREAKER - 1 FLT COMPT, P11
ELEVATOR LIMIT, C4032 1 11J12 *
FLT CONT ELEC 1L AC, C1538 1 11C6 *
FLT CONT ELEC 1L DC, C1534 1 11C7 *
FLT CONT ELEC 1R AC, C1536 1 11G17 *
FLT CONT ELEC 1R DC, C1531 1 11G18 *
FLT CONT ELEC 2L AC, C1537 1 11C8 *
FLT CONT ELEC 2L DC, C1533 1 11C9 *
FLT CONT ELEC 2R AC, C1535 1 11G27 *
FLT CONT ELEC 2R DC, C1532 1 11G28 *
FLT CONT SHUTOFF TAIL LEFT, C4033 1 11H17 *
PCU MON SENSOR, C4283 1 11J10 *
PCU MON MOD, C4270 1 11J11 *
RUDDER POS, C1005 1 11J16 *
RUD RATIO, C1031 1 11G10 OR 11D18 *
RUD TRIM, C1033 1 11C10 *
RUDDER TRIM POS, C1034 1 11J17 *
STAB TRIM CONT L, C1017 1 11H11 OR 11C5 *
STAB TRIM CONT R, C1018 1 11H20 *
COMPUTER - (FIM 31-41-00/101)
L EICAS, M10181
R EICAS, M10182
CRANK - RUDDER PEDAL ADJUSTMENT 1 2 FLT COMPT AND 113AL, FWD EQUIP 27-21-03
COMPT
FILTER - RRCA 1 324BL, RRCA M626 27-21-13
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：757 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 1(141)
