S 434-013
(5)
Install the cover on the thrust lever with the screws.
F. Test the Go-Around switches
S 864-014
(1)
Supply electrical power (Ref 24-22-00).
S 864-015
(2)
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P11 panel:
(a) 11E16, MODE CONT PNL LEFT
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(b) (c) (d) (e) (f) (g) (h) (i) (j) (k) 11E17, FLT CONT COMPUTER POWER LEFT11E18, FLT CONT COMPUTER SERVO LEFT11E20, FLIGHT CONT CMPTR PWR CENTER11E21, FLIGHT CONT CMPTR SERVO CENTER11E34, MODE CONT PNL RIGHT11E35, FLT CONT CMPTR PWR RIGHT11E36, FLT CONTR CMPTR SERVO RIGHT11F14, TMC AC11F15, TMC DC11F16, TMC SERVO
(3) S 724-016Do MCDP Ground Test 13-SW G/A (Ref 22-00-02). (a) Make sure no failure messages show during the test.
(4) S 864-017Set the MCDP to off.
(5) S 864-018Remove electrical power if it is not necessary (Ref 24-22-00).
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AUTOPILOT/FLIGHT DIRECTOR PITCH CHANNEL - DESCRIPTION AND OPERATION
___________________________________________________________________
1. General (Fig. 1)_______
A. The pitch channel consists of pitch mode switches on the AFCS mode control panel, pitch modes of the three Flight Control Computers (FCCs) three Autopilot Pitch Control Servos (APCS) and three elevator neutral shift transducers. Each servo and transducer is dedicated to a single flight control computer. Primary AFDS control modes are selected on the AFCS Mode Control Panel (MCP). Flight director and mode displays are on the Electronic Attitude Director Indicators (EADIs).
B. Each FCC generates commands for the Flight Director (F/D) and Autopilot (A/P). The FCC selected provides commands for either the A/P or F/D, but not both at the same time. The A/P and F/D modes are selected on the MCP. F/D displays are turned on by the F/D switches on the MCP. The FCC providing F/D displays is selected by the pilots FLT DIR source select switch.
(1)
Pitch axis control functions of the FCC provide pitch axis stability, manual pitch attitude control and programmed pitch attitude control of the airplane. The functions control the autopilot or provide flight director steering commands. The autopilot pitch control servos and elevator control system provide for pitch axis maneuvering. The automatic stabilizer trim system provides for the transfer of sustained elevator loads to the horizontal stabilizer. A Stabilizer trim and elevator Asymmetry limit Module (SAM) provides the interface between the FCC and the stabilizer trim system.
(2)
Pitch Axis Stability
(a) The attitude hold function of the FCC maintains airplane pitch attitude during turbulence with the autopilot engaged or provides F/D commands.
(3)
Manual Pitch Attitude Control
(a) AIRPLANES WITH CONTROL WHEEL STEERING; manual pitch attitude control is accomplished through control wheel steering when the autopilot is engaged in CWS. A force applied to the control column overrides the attitude hold mode. Pitch rate is then proportional to the force applied.
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MAINTENANCE MANUAL
Pitch Axis Control
Figure 1 (Sheet 1)
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