(3)
Rigging Pins Kit - F70207-3, -52, -61, or -84:
(4)
Deleted.
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
E-1 E-2 E-3 E-4 E-5 -11 -66 -66 -11 -11 0.309-0.311 0.4937-0.4945 0.4937-0.4945 0.309-0.311 0.309-0.311 6.7 士0.25 3.7 士0.25 3.7 士0.25 6.7 士0.25 6.7 士0.25 FWD Control Quadrant FWD Control Quadrant FWD Control Quadrant Feel Computer Input Arm Aft Control Quadrant
Aug 01/94 27-31-0 Page 503
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(5)
Spring scale - 0- to 30-pound capability, graduated in 1-pound increments
(6)
Trammel Bar - F80055-1
(7)
Elevator Rigging and Restraining Tool - F80063-501 (Preferred) or F80063-500 (Optional)
(8)
Grease - MIL-G-23827 (Ref 20-30-21)
(9)
Rigging Fixture, Elevator Tab - C27028 (preferred) (airplanes with metal-fiberglass or composite elevators)
(10)
Rigging Fixture, Elevator Tab - F80248-8 (Preferred) or F80248-1 (Optional) (airplanes with metal-fiberglass or composite elevators)
(11)
Rigging Fixture, Elevator Tab, Inboard Locations - TE27T-31001-15 (airplanes with composite elevators).
(12)
Rigging Fixture, Elevator Tab, Outboard Locations - TE27T-31001-17 (airplanes with composite elevators).
C. Adjust Elevator and Tab Control System
(1) Adjust elevator control cables EA and EB and pitch force transducers.
(a)
Set horizontal stabilizer B dimension at 41.57 士0.05 inches, using trammel bar (Fig. 502).
(b)
Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
(c)
Ensure that mach trim actuator is in null position (Ref 27-31-0 MP).
(d)
Insert rigging pin E-5 in elevator right aft quadrant and ensure that rigging pin is easily movable. If holes do not align, move elevator surface by hand, up or down, until they align. Elevator surface should stay in this position.
(e)
Insert rigging pin E-1 in elevator left forward quadrant. Check that Rigging pin fits easily.
(f)
Remove shoulder bolt from both column quadrants and check that rigging pins E-2 and E-3 fit easily through shoulder bolt installation holes. See Fig. 503 for locations.
(g)
Check that tension in cables EAR, EBR, EAL, and EBL is within value required for ambient temperature per table on Fig. 501.
(h)
If new cables are installed:
542
27-31-0 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
1) Adjust turnbuckles on the EA and EB cables to 300 士20 pounds to prestretch
cables.
2) Adjust all seals during rigging to eliminate bending of cables.
3) Remove rigging pins E-1 and E-5.
4) Cycle control column 25 times through full travel.
5) Accomplish steps (d) thru (g).
(i)
If the conditions of steps (d), (e), (f), or (g) are not met or if step (h) was accomplished, remove bolts from adjustable ends of pitch force transducer and use turnbuckles to adjust cable tension to value for ambient temperature per table on Fig.
501.
(j)
Rigging pins E-1, E-2, E-3, and E-5 must all be easily movable after final adjustment.
(k)
If steps (h) or (i) were accomplished, adjust and connect pitch force transducers per Chapter 22, Pitch Control Wheel Steering Force Transducer - A/T.
(l)
Remove rigging pins E-2 and E-3 and install shoulder bolts.
(m)
Install locking clips on all turnbuckles.
(n)
Remove rigging pins E-1 and E-5.
500
Feb 20/91 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-0 Page 505
Stabilizer Trim Jackscrew Setting 500
27-31-0 Figure 502 Jun 20/84
Page 506
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Forward Control Quadrant and Pitch Transducer Rigging Pin Locations
May 01/99 Figure 503 27-31-0
Page 507
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Aft Control Quadrant Rigging Pin Location 500
27-31-0 Figure 504 Jun 20/84
Page 508
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(2) Adjust Elevator Control Pushrods
(a) Check that elevators are synchronized at neutral as follows: 1) Remove elevator systems A and B hydraulic power (Ref 27-31-0, MP).
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