R. Test autopilot disconnect switch (AMM 22-11-411/501).
S. Perform Elevator and Tab Control System Power Made Operation Test (AMM 27-31-0/501).
T. Restore airplane to normal hydraulic configuration (AMM 27-31-0/201).
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27-31-51 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/00
G09371
501 Control Column Adjustment
May 01/99 Figure 402 27-31-51
Page 405
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ELEVATOR FORWARD CONTROL QUADRANT - REMOVAL/INSTALLATION
1. General
A. The following procedure describes the removal of the forward control quadrant without removing the control columns. Adequate support must be provided at each column to prevent it from falling. To remove a control column refer to 27-31-51 R/I.
2. Equipment and Materials
A. Control Column Protractor Assembly-4MIT65B80307-1 (Preferred) or F52485-500
(Optional) which is used with the following adapters:
(a)
Aileron Control Wheel Protractor Mount-F72790
(b)
Forward Thrust Lever Protractor Adapter-F72952-2
B. Tensiometer - 0- to 320-pound capacity
C. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
E-1 E-5 ST-1 -11 -11 -16 0.309-0.311 0.309-0.311 0.182-0.186 6.7 ±0.25 6.7 ±0.25 2.7 ±0.25 FWD CONTROL QUADRANT AFT CONTROL QUADRANT STABILIZER TRIM BRAKE ARM
D. Steel scale - 0 to 2 feet, graduated in inches and tenths of an inch
3. Remove Elevator Forward Control Quadrant
A. Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
B. Open autopilot pitch control channel, flight controls and spoiler circuit breakers on circuit breaker panel P6.
C. Open lower nose compartment access door 1103 and aft compartment access door 3701. Remove tail cone access door 3802.
D. Install rigging pin E-1 in left forward control quadrant and rigging pin E-5 in aft control quadrant (Fig. 401 and 402).
E. Release tension in elevator control cables at turnbuckles in aft unpressurized compartment. Do not disconnect turnbuckles.
F. Install clamps on elevator control cables to prevent cables running aft through bulkhead.
G. Remove cables EA and EB from forward control quadrants by removing retainer pin from each cable end. Tag cables.
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H. Remove screws securing cable support fairlead to each quadrant.
I. Disconnect pitch transducer (5) electrical cable at electrical connector.
J. Disconnect stabilizer trim brake pushrod (6) from fork on quadrant torque tube and disconnect forward end of brake release cable from arm on stabilizer trim brake.
K. Remove ring assembly (3) and dust seal (4) from the base of one control column (1).
NOTE: Control column connectors (13) and forward control quadrant shoulders may be lightly scribe marked to facilitate alignment of control column during quadrant installation.
L. Remove rigging pin E-1.
M. Release two inboard coupling bolts (9) from each inboard coupling (8). Remove couplings.
CAUTION: BOTH CONTROL COLUMNS AND FORWARD CONTROL QUADRANT MUST BE SUPPORTED TO PREVENT THEM FROM FALLING.
N. Slide control column outboard until teeth on connector (13) are disengaged from control quadrant (7).
O. Remove elevator forward control quadrant from airplane.
P. If new forward quadrant assembly is to be installed remove pitch transducer with electrical cable and clamps from each quadrant and install with new forward quadrant assembly.
4. Prepare to Install Forward Control Quadrant
A. If BAC27DCT135 marker is not installed on both quadrants, install marker as follows:
(1)
Locate marker for installation per location of marker on removed quadrant.
(2)
Install per applicable instructions in Chapter 20.
B. Remove elevator systems A and B hydraulic power. Refer to 27-31-0.
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27-31-61 Page 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
G09381 G09389
500 Elevator Forward Control Quadrant Installation
May 15/67 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-61 Page 403
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