(b)
Install bearing bar and attach bolts in hinge No. 2. Use new hardware (Fig. 201) to attach bearing bar. Do not tighten attach bolts. Install rudder hinge bolt using previously removed hardware. Do not tighten rudder hinge bolt.
(c)
Tighten bearing bar attach bolts 95 to 110 pound-inches. Shim hinge to control gap
(0.005 maximum) between rudder hinge segment and bearing bar. Tighten hinge bolt 95 to 110 pound-inches.
(d)
Remove rudder sling.
(e)
Install vertical fin hinge segments at rudder hinges No. 4 and 5. Do not tighten attach bolts.
(f)
Install No. 4 and 5 hinge bolts using previously remove attaching hardware. Tighten 60 to 85 pound-inches. Tighten No. 4 and 5 hinge segment bolts 70 to 80 pound-inches.
(g)
Install a new upper balance weight cover (Ref Drawing 65-48245).
(h)
Install a new lower balance weight seal (Ref Drawing 65-48244).
(i)
Install a new trailing edge beam seal (Ref Drawing 65-524290).
(j)
Install a new lower fin air dam seal (Ref Drawing 65C25990).
(k)
Install a new upper fin air dam seal (Ref Drawing 65-54807).
(l)
Restore airplane to normal (Ref 27-21-12, para. 6).
500
Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-09-800 Page 203
Rudder Installation Aluminum to Graphite 500
27-09-800 Figure 201 (Sheet 2) Oct 20/85
Page 204
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
3. Elevator Interchangeability
A. Aluminum Elevator to Graphite Elevator
(1)
Remove aluminum elevator (Ref 27-31-11).
NOTE: Point of interchangeability is the interface of the balance panel and aft balance panel hinge. The hinge is detached from the balance panel and retained with the replaced elevator. A new hinge must be fitted to the replacement elevator prior to installation of the elevator.
(2)
Retain nuts and bolts for subsequent installation, discard all washers.
(3)
Install aft balance panel hinge on elevator nose and install graphite elevator (Ref 27-31-12) with existing hardware except all washers, bonding jumpers, and bonding jumper hardware should be replaced with new hardware.
(4)
Adjust and test elevator and tab per 27-31-0 A/T.
B. Graphite Elevator to Aluminum Elevator
(1)
Remove graphite elevator (Ref 27-31-12).
NOTE: Point of interchangeability is the interface of the balance panel and aft balance panel hinge. The hinge is detached from the balance panel and retained with the replaced elevator. A new hinge must be fitted to the replacement elevator prior to installation of the elevator.
(2)
Retain hardware for subsequent installation.
(3)
Install aft balance panel hinge on elevator nose and install aluminum elevator (Ref 27-31-11) with existing hardware except delete shims from No. 1 hinge bearing bolt.
(4)
Adjust and test elevator and tab per 27-31-0 A/T.
4. Elevator Tab Interchangeability
A. General
(1) The elevator tabs are balanced into the elevator system by adding or removing tab adjust weights on the elevator nose in balance bay No. 1. The number of adjust weights required is a function of tab part number and tab weight. The data plate on each tab is stamped with the tab weight and the number of adjustment weights required. When replacing an elevator tab, the number of tab weights installed on the elevator nose must agree with the number called for on the tab data plate. If data plate is missing or if tab weight is changed (due to structural changes or repainting), see chapter 51 of the structural repair manual for tab adjust weight requirement.
B. Equipment and Materials
(1)
Rigging Pin E-5 - 0.309/0.311-inch diameter, 6.7 +0.25 inches long (MS20392-4)
NOTE: Rigging Pin is part of kit F70207-3, -52, -61, or -84.
(2)
Sealant - BMS 5-95 (Ref 20-30-11)
500
Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-09-800 Page 205
C. Prepare For Removal
(1)
Open or remove the following access panels: tail cone access door 3802, tab pushrod access panel (Fig. 202), and tab lock mechanism upper and lower access panels. (Panels are located at elevator inboard leading edge.)
(2)
Remove elevator systems A and B hydraulic power (Ref 27-31-0, MP).
(3)
Install rigging pin E-5 in aft control quadrant.
中國(guó)航空網(wǎng) m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 1(47)
