G04037
Tab Control Rods 528
27-11-151Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/69
C. Lift aileron to align aft balance panel hinge, install hinge pin and hinge retainer bolt (Ref 27-11-11 R/I).
D. Install balance panel hinge seal, retaining strip, and bolts.
E. Connect tab control rods to forward fittings by installing two attach bolts, washers, and nuts.
F. Install hinge access panel on aileron and aileron access panels on lower wing surface adjacent to aileron.
G. Install forward portion of tab fairing.
H. Operate aileron control wheel through full travel and check that tab moves without binding.
I. With index mark on aileron aligned with index mark on wing within 0.03 inch, check mismatch between aileron trailing edge and aileron tab trailing edge. Using straightedge or aileron tab alignment protractor, measure mismatch from trailing edge of tab to theoretical extension of aileron bottom surface at 1/2 inch in from inboard end of tab. Check that tab trailing edge aligns with aileron bottom surface within 0.07 +0.07 inch.
J. Perform a flight test to determine and correct asymmetrical flight control forces (Ref 27-11-0 A/T).
521
Oct 20/87 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-151 Page 403
AILERON TAB CONTROL RODS -INSPECTION/CHECK
1. General
A. This data consists of illustration and wear limits charts. No procedure is given for gaining access to permit inspection. For this information, refer to component removal/installation.
2. Aileron Tab Control rods Wear Limits
INDEX PART DESIGN LIMITS WEAR LIMTS REPLACE WORN REPAIR WORN REPAIR
DIAMETER MAX WEAR MAX DIAM CLEAR-
NO. NAME DIM MIN MAX DIM. ANCE PART PART INSTR.
1 Rod End ID *[1] X
Bolt OD X
*[1] REPLACE WHEN RADIAL PLAY OF BEARING EXCEEDS 0.0020 INCH.
521 Aug 15/73 Tab Control Rods Wear Limits Figure 601 B
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27-11-151 Page 601
G09981
RUDDER AND RUDDER TRIM CONTROL SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
AIRPLANES PRE-SB 27-1252
1. General
A. Yaw control of the airplane is provided by a single conventional rudder without tab. There are two separate hydraulic systems powering one main power control unit. Rudder control backup is provided by a standby power unit, which is driven by a third hydraulic system. Any one of the three hydraulic systems will provide effective rudder control. Rudder trim is accomplished by operating a trim control wheel which repositions the rudder.
B. The rudder control system is pedal operated by the captain or the first officer. (See figure 1.) Pedal movement rotates the forward quadrants, which are cable connected to the aft quadrant. Rotation of the aft quadrant moves a control rod which is connected to a torque tube. Rotation of the torque tube moves a crank connected to the rudder power control unit linkage. This in turn admits hydraulic fluid to the actuating cylinder, which moves the rudder.
C. Rudder trim is initiated by rotation of the trim wheel located on the aisle stand. (See figure 3.) The trim wheel is attached to the forward cable drum, which is connected by cables to the trim actuator located in the vertical fin. Extension or retraction of the trim actuator jackscrew causes the feel unit housing to rotate. This moves linkages which rotate the torque tube, causing rudder power control unit input.
D. Rudder feel is provided by a rudder feel unit. The feel unit is connected to the rudder control torque tube, which connects through linkage and cables to the rudder pedals. (See figure 3.)
E. The rudder is fully power operated through its entire travel. The rudder power control unit is hydraulically operated by hydraulic systems A and B simultaneously. The A and B systems can be independently activated by switches located on the overhead panel. Either of the A and B switches can be used to activate the standby hydraulic system and supply pressure to the standby actuator.
May 01/03 27-21-0 Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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