Elevator Feel and Centering Unit Wear Limits 500
27-31-151 Figure 601 (Sheet 2) May 15/68
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Elevator Feel and Centering Unit Wear Limits
May 15/68 Figure 601 (Sheet 3) 27-31-151
Page 603
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Elevator Feel and Centering Unit Wear Limits 500
27-31-151 Figure 601 (Sheet 4) May 15/68
Page 604
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
INDEX NO. PART NAME DIM DESIGN LIMITS WEAR LIMTS REPLACE WORN PART REPAIR WORN PART REPAIR INSTR.
DIAMETER MAX WEAR DIM. MAX DIAM CLEAR-ANCE
MIN MAX
1 BEARING ID 0.1895 0.1900 0.1930 0.0035 X
BOLT OD 0.1885 0.1895 0.1881 X
2 BEARING ID 0.3120 0.3125 0.3155 0.0037 X
BOLT OD 0.3108 0.3118 0.3104 X
3 BEARING ID 0.3120 0.3125 0.3155 0.0035 X
BOLT OD 0.3110 0.3120 0.3106 X
4 ROD CLEVIS ID 0.3120 0.3130 0.3160 0.0040 X 1
BOLT OD 0.3110 0.3120 0.3106 X
5 BEARING ID 0.3745 0.3750 0.3780 0.0035 X
BOLT OD 0.3735 0.3745 0.3731 X
6 CLEVIS BUSHING ID 0.3750 0.3765 0.3795 0.0050 X 2
BOLT OD 0.3735 0.3745 0.3732 X
7 HOUSING ID 1.9375 1.9385 1.9415 0.0040 X
BEARING OD 1.9365 1.9375 1.9360 X
8 BEARING ID 0.9990 1.0000 1.0025 0.0035 X
CRANK SHAFT OD 0.9985 0.9990 0.9965 X
OBTAIN BUSHING. BORE HOLE TO ATTAIN -0.0002 TO 0.0013 INCH INTERFERENCE FIT (0.4379 INCH MAXIMUM). REAM BUSHING TO 0.3120/0.3130 INCH DIAMETER.
REPLACE WORN BUSHING. FEEL ACTUATOR - REMOVAL/INSTALLATION
500 Elevator Feel and Centering Unit Wear Limits
May 15/68 Figure 601 (Sheet 5) 27-31-151
Page 605
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1. General
A. Further disassembly of the feel actuator should be accomplished using procedures given in the Overhaul Manual.
2. Equipment and Materials
A. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
E-5 -11 0.309-0.311 6.7 ±0.25 Aft Control Quadrant
B. Trammel Bar - F80055-1
C. Masking Tape (AMM 20-30-51/201)
D. Air Pressure Regulator - F72928-53 (Preferred), or -52 (Optional)
3. Remove Feel Actuator
A. Remove elevator systems A and B hydraulic power (AMM 27-31-0/201).
B. Remove tail cone access door 3802.
C. Install rigging pin E-5 in aft control quadrant.
D. Disconnect four flexible hydraulic lines from the feel actuator (Fig. 401). Cap and plug open ports and hydraulic lines.
CAUTION: HYDRAULIC PRESSURE OF 70 PSI MAY BE PRESENT IN SYSTEM A AND SYSTEM B PRESSURE AND RETURN LINES. WHEN DISCONNECTING HYDRAULIC LINES, RELEASE CONNECTION SLOWLY AND ALLOW SYSTEM PRESSURE TO BLEED OFF BEFORE COMPLETE REMOVAL.
E. Detach feel actuator forward and aft mounting bolts and remove feel actuator from airplane.
4. Install Feel Actuator
A. Remove elevator systems A and B hydraulic power (AMM 27-31-0/201).
B. Check that rigging pin E-5 is installed in aft control quadrant.
C. Install feel actuator forward and aft mounting bolts as follows:
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