F.
Prepare for Adjustment

 S 012-016
 (1)  
Open the access door 315A (AMM 06-09-05/201).

 S 862-017

 (2)  
Do this task: "Supply Electrical Power" (AMM 24-22-00/201).

 S 862-019

 (3)  
Make sure the elevator feel unit detent moves the elevator control system to the center.

 S 862-020
 CAUTION: DO NOT PRESSURIZE THE AUXILIARY PITOT SYSTEM TO MORE THAN 4.00
_______ PSIG (OR 395 KNOTS). MAKE SURE THE PRESSURE CHANGE IS LESS THAN 5000 FEET (OR 300 KNOTS IAS) FOR EACH MINUTE FOR THE PITOT SYSTEM. THOSE ARE TO PREVENT THE DAMAGE TO THE ELEVATOR FEEL COMPUTER WHICH IS A VERY EASILY DAMAGED INSTRUMENT.
 (4) Pressurize the auxiliary pitot static systems No. 1 and No. 2 to
 2.50 |0.10 psi (or 317 |10 knots IAS. Note: reference static pressure to ambient pressure.)(AMM 34-11-00/201).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-31-17
 ALL  ú ú 01 Page 207 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 862-021
 WARNING: MOVE ALL PERSONS AND EQUIPMENT AWAY FROM THE RUDDERS AND THE
_______ ELEVATORS BEFORE YOU PRESSURIZE THE HYDRAULIC SYSTEMS. THE RUDDERS AND THE ELEVATORS CAN MOVE QUICKLY AND CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (5)  
Pressurize the hydraulic systems No. 2 and No. 3 (AMM 29-11-00/201).

 G.
Adjust the Elevator Feel Unit

 S 492-022
 (1)
Install the rig pin E-2 at the bottom of the aft quadrant (5).

 (a)  
If you cannot install the rig pin E-2, adjust the control rod

 (4)
 until the holes align.

 S 832-023
 (2)  
Do the fine adjustment:

 (a)  
Loosen the checknuts.

 (b)  
Turn the sleeve as much as necessary.

 (c)  
Tighten the checknuts.

 S 832-024
 (3)  
Do the coarse adjustment:

 (a)  
Release the pressure in the hydraulic systems No. 2 and No. 3 (AMM 29-11-00/201).

 (b)  
Remove the bolt assembly (6) to connect the rod clevis to the aft quadrant bearing arm (3).

 (c)  
Install the rig pin E-2 in the bottom of the aft quadrant (5).

 (d)  
Loosen the checknuts if it is necessary.

 (e)  
Adjust the clevis on the sleeve, (or the sleeve in the tube, or the two of them) until the clevis aligns with the bearing in the bearing arm.

 NOTE: One turn of the clevis assembly in the sleeve changes
____ the length of the control rod by 0.042 inches. A maximum of 1 1/2 turns of the clevis assembly in the sleeve, or sleeve in the tube assembly is permitted.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-31-17
 ALL  ú ú 01 Page 208 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 (f)  
Remove the rig pin E-2 from the aft quadrant (5).

 (g)  
Apply a thin layer of grease on the clevis bolt assembly (6).

 (h)  
Install the clevis bolt assembly (6).

 (i)  
Turn the sleeve until you can install the rig pin easily by hand.

 (j)  
Tighten the two check nuts on the control rod and make sure the rig pin is still free.

 (k)  
Install the washer (10) and nut (7) on the outer bolt of clevis bolt assembly (6). 1) Tighten the nut (7) to 85-100 pound-inches.

 (l)  
Install the washer (9) and nut (8) on the inner bolt of clevis bolt assembly (6). 1) Tighten the nut (8) to 30-40 pound-inches.

 NOTE: Do not tighten the outer bolt nut (7) again after
____ you tightened the inner bolt nut (8).
 (m)  Do the fine adjustment, if it is necessary.
 S 432-025
 (4)  
Tighten the checknuts.

 S 222-026

 (5)  
Make sure the control rod sleeve and the clevis are not loosened more than the safety limits (Detail B, Fig. 201).
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(93)