(b)
11C13, STAB TRIM SHUTOFF RIGHT
(c)
11E17, FLT CONT COMPUTER POWER LEFT
(d)
11E18, FLT CONT COMPUTER SERVO LEFT
(e)
11E20, FLIGHT CONT CMPTR PWR CENTER
(f)
11E21, FLIGHT CONT CMPTR SERVO CENTER
(g)
11E35, FLT CONT CMPTR PWR RIGHT
(h)
11E36, FLT CONT CMPTR SERVO RIGHT
(i)
11H17, FLT CONT SHUTOFF LEFT
(j)
11H18, FLT CONT SHUTOFF CENTER
(k)
11H28, FLT CONT SHUTOFF RIGHT
S 864-059
(2)
Remove the DO-NOT-OPERATE tags and set the L, C, and R FLT CONTROL SHUTOFF switches on the panel P61 to the ON position.
S 864-060
(3)
Remove the DO-NOT-OPERATE tags and set the two STAB TRIM switches on the P10 panel to the NORM position.
S 864-061
(4)
Set the stabilizer at two units of trim so dimension B=22.24 |0.01 inches (Fig. 402).
S 864-062
(5)
Pressurize the elevator feel pitot system to 350 knots
(Ref 34-11-00).
(6)
Pressurize the L, C, and R main hydraulic systems (Ref 29-11-00).
(7)
Start MCDP Ground Test 66-XDCR OUTPUTS (Ref 22-00-02).
S 984-065
(8)
Push the YES/ADV switch until the message 66 FEEL POS DEG |X.XX |X.XX |X.XX shows.
S 214-066
(9)
Make sure the three values that show are 0.00 |0.1 degree with the control column released. Make sure the maximum difference between the channels is 0.1 degree.
S 864-063
S 714-064
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757 MAINTENANCE MANUAL
S 214-067
(10)
Write the values that show.
S 864-068
(11)
Set the stabilizer to six units of trim as measured on the
indicator.
S 214-069
(12)
Make sure the three values that show are still 0.00 |0.1 degree with the control column released.
S 214-070
(13)
Make sure the difference between the FEEL POS DEG values at 2 units of trim and at six units of trim is 0.05 degree or less for each channel. Adjust the elevator feel unit upper arm (MM 27-31-00) if the difference is more than 0.05 degree.
S 864-071
(14)
Remove pressure from the elevator feel pitot system.
S 714-072
(15)
Do MCDP Ground Test 08-SERVO ELEV (Ref 22-00-02).
(a) Make sure no fault messages show during the test.
I. Put the Airplane Back to Its Usual Condition
S 864-073
(1)
Set the MCDP to off.
(2)
Remove hydraulic power if it is not necessary (Ref 29-11-00).
(3)
Remove electrical power if it is not necessary (Ref 24-22-00).
(4)
Close the service access panel 313AL.
S 864-074
S 864-075
S 864-076
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757
MAINTENANCE MANUAL
AUTOPILOT/FLIGHT DIRECTOR ROLL AND YAW CHANNEL - DESCRIPTION AND OPERATION
__________________________________________________________________________
1. General (Fig. 1)
_______
A. The roll and yaw channels consist of three flight control computers (FCCs), three autopilot lateral control servos (ALCSs) and three autopilot rollout guidance servos (ARGSs). Each servo is dedicated to a single FCC. Primary control of the A/P is through selections made on the AFCS Mode Control Panel (MCP). Mode and Flight Director (F/D) displays are presented on the Electronic Attitude Director Indicators (EADIs) of the Electronic Flight Instrument System (EFIS).
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