ELEVATOR AFT CONTROL QUADRANT - INSPECTION/CHECK
1. General
A. This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to component removal/installation for this information.
2. Elevator Aft Control Quadrant Wear Limits
551 Elevator Aft Control Quadrant Wear Limits
Nov 01/75 Figure 601 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-71 Page 601
Elevator Aft Control Quadrant Wear Limits 501
27-31-71 Page 602 Figure 601 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/75
G44612
500 Elevator AFt Control Quadrant Wear Limits
May 15/68 Figure 601 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-71 Page 603
ELEVATOR INDEX PLATES - REMOVAL/INSTALLATION
1. General
A. The following procedure must be performed whenever the tail cone is removed and replaced with a new or different tail cone.
2. Removal/Installation Index Plates
A. Equipment and Materials
(1)
Trammel Bar Assembly, Stabilizer Trim Actuator F80055-1
(2)
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
(3)
Elevator Index Plate Rigging Beam - F80230-1 (Preferred)(Ref 27-09-700)
B. Remove Index Plates
(1)
Remove tail cone from airplane (Ref Chapter 53, Tail Cone - R/I).
(2)
Break lockwire and remove two nuts, washers and screws from each index plate. Remove index plates from tail cone (Fig. 403).
C. Prepare for Installation
(1)
Install replacement tail cone on airplane (Ref Chapter 53, Tail Cone - R/I).
(2)
Open aft compartment access door 3701 and remove tail cone access panel 3802 (Ref Chapter 12, Access Doors and Panels).
(3)
Set horizontal stabilizer B dimension at 41.57 +0.04 inches, using trammel bar (Fig. 401).
(4)
Set mach trim actuator at fully extended position per 27-31-0 - MP.
(5)
Remove elevator systems A and B hydraulic power (Ref 27-31-0, - MP).
(6)
Tag control columns to prevent injury to personnel by unexpected movement of elevator surfaces.
(7)
If using elevator and tab travel protractor:
(a)
Remove screws A thru D from underside of right stabilizer and screws E and F from underside of right elevator. Screws C and D are first and third screws inboard of seam in stabilizer leading edge (Fig. 402).
(b)
Attach protractor to underside of right stabilizer using screw holes vacated in previous step.
500
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-81 Page 401
G09547
Stabilizer Trim Jackscrew Setting 500
27-31-81 Figure 501 Nov 15/67
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(c) Position elevator trailing edge 4.00 + 0.05 degrees down as indicated on protractor.
NOTE: With horizontal stabilizer B dimension set at 41.57 + 0.04 inches and elevator trailing edge at 4.00 + 0.05 degrees down, elevator is in neutral position.
As shown on MIT65-73715-1, protractor zero graduation is elevator zero degree position with elevator trailing edge lying in horizontal stabilizer chord plane.
(8) If using elevator index plate rigging beam: (Fig. 402)
(a)
Use a trammel bar or scale to set the horizontal stabilizer at the “B” dimension of
41.57 +0.01 inches (Ref 27-41-0/501).
(b)
Hold the rigging beam on the bottom side of the stabilizer.
(c)
Set the index slot, located on the front of the rigging beam, to 6.80 inches inboard of the aligned point Q on the stabilizer.
NOTE: At this position, the index slot of the rigging beam will align with the mark on the stabilizer.
(d)
Move the rigging beam forward or aft until the scale of the rigging beam touches the aft edge of the elevator trailing edge.
(e)
Make sure that the scale on the rigging beam in 2.25 inches inboard of the inboard end of the elevator tab.
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