(b)
Push the LSK that is adjacent to START TEST>.
(c)
Make sure that there is no failure indication shows on the CDU.
(d)
Continue with the instructions on the CDU until the POSITIVE LIMIT and NEGATIVE LIMIT page is shown.
(e)
Push the LSK adjacent to <POSITIVE LIMIT for the positive surface limit positions.
(f)
Write down the values for the aileron surface position:
L ______ , C ______ , R ______ .
(g)
Make sure that the values for the left, center, and right channels are +16.0 degrees (minimum).
(h)
Make sure that the control columns stay at the positive limit and the AUTOPILOT DISC does not show on the main EICAS display.
(i)
Push the LSK adjacent to <CONTINUE on the CDU to go back to the POSITIVE LIMIT and NEGATIVE LIMIT page.
(j)
Push the LSK adjacent to <NEGATIVE LIMIT for the negative surface limit positions.
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(k)
Write down the values for the aileron surface position:
L ______ , C ______ , R ______ .
(l)
Make sure that the values for the left, center, and right channels are -16.0 degrees (minimum).
(m)
Make sure that the control columns stay at the negative limit and the AUTOPILOT DISC does not show on the main EICAS display.
(n)
Push the LSK adjacent to <CONTINUE on the CDU to go back to the POSITIVE LIMIT and NEGATIVE LIMIT page.
(o)
Push the LSK adjacent to <ADVANCE to complete the test.
NOTE: An autopilot disconnect warning will occur at the end of
____ this test which is permitted.
(p) Push the captain's or first officer's autopilot disconnect switch two times.
G. Put the Airplane in Its Usual Condition
S 865-420
(1)
Remove hydraulic power if it is not necessary (AMM 29-11-00/201).
S 865-317
(2)
Remove the electrical power if it is not necessary
(AMM 24-22-00/201).
TASK 22-10-00-745-294
19. Ground Test - Elevator Surface Limit
____________________________________
A. General
(1) This test is for a check of the elevator surface limit. During this test, the elevator servos move the elevator surface to its limits in the two directions and show the final surface position.
B. References
(1)
AMM 22-11-01/401, Flight Control Computer
(2)
AMM 24-22-00/201, Manual Control
(3)
AMM 29-11-00/201, Main Hydraulic Supply System
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MAINTENANCE MANUAL
(4)
AMM 34-61-00/501, Flight Management Computer System
(5)
AMM 34-61-02/401, Control Display Unit
(6)
AMM 45-10-00/501, Central Maintenance Computer System
C. Access
(1) Location Zones
221 Control Cabin, LH
222 Control Cabin, RH
D. Preconditions
S 865-461
(1) These conditions are necessary for this task:
(a)
Electrical Power On (AMM 24-22-00/201).
(b)
Central Maintenance Computer (CMC), serviceable (AMM 45-10-00/501).
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