(2)
SSM 27-32-01
(3)
WDM 27-32-11
C.
Access
(1)
Location Zones 221 Control Cabin, L - Captain's Control Column 222 Control Cabin, R - First Officer's Control Column
D.
Installation Procedure
S 424-019
(1)
Hold the shaker (7) in position at the strap (2).
(a)
Install the shims (5), spacers (4), bolts (1), and nuts (3).
S 824-008
(2) Adjust the assembly so that there is 8.10 |0.03 (20.57cm |0.076cm) inches between the center of the strap and the top of the clamp (the clamp is at the base of the control column)(Fig. 401).
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S 434-009
(3)
Tighten the bolts (1) to 20-25 pound-inches (2.25-2.82
Newton-Meters).
(a)
Add or remove shims (5) if necessary so that there is a tight fit.
S 434-010
(4)
Connect the electrical connector (6) to the shaker (7).
E.
Shaker Operational Test
S 864-011
(1)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a)
P7, Overhead Circuit Breaker Panel
1) 7D5, STICK SHAKER L
2) 7D19, STICK SHAKER R
S 864-012
(2)
Supply electrical power (AMM 24-22-00/201)
S 864-021
(3)
Set the IRS L, C, and R switches on the IRS mode select unit (P5 panel) to ATT or NAV.
(a)
Make sure that the ATT flag does not show on the captain's or the first officer's PFD.
S 864-020
(4)
Set the IRS L, C, and R switches on the IRS mode select unit (P5 panel) to ATT or NAV.
(a)
Make sure that the ATT flag does not show on the captain's or the first officer's PFD.
S 744-014
(5)
Do a stall warning system confidence test with the CMC:
(a)
Get CONFIDENCE TESTS from the CMC main menu.
(b)
Push and release the STALL LEFT or STALL RIGHT line select key on the CMC confidence test menu. 1) Make sure the control column shakers operate. 2) Make sure the control column shakers stop after
approximately 10 seconds.
S 864-017
(6)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a)
P414, Left Power Distribution Panel
1) 414D8, CAPT PWR SEAT
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(b) P415, Right Power Distribution Panel 1) 415H32, F-O PWR SEAT
S 864-016
(7) Remove electrical power (AMM 24-22-00/201).
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ELEVATOR POSITION INDICATING SYSTEM - DESCRIPTION AND OPERATION
_______________________________________________________________
General (Fig. 1)
_______
A. The elevator position indicating system provides visual indication on the flight deck of outboard elevator angular displacement. The elevator position indicators appear on the EICAS status page as part of the EICAS surface position display.
B. Components used by the elevator position indicating system are the four elevator position transmitters, the rudder/elevator aft surface position digitizer circuit card, and the EIU's and EICAS display. The system is powered by 28 volts dc from the 28 vdc bus 3 and by 28 volts ac from the 28 vac bus 3 through circuit breakers on the P6 panel.
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本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(106)
