EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-31-00
ALL ú ú 01 Page 113 ú Jul 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
TROUBLE REMEDYISOLATION PROCEDUREPROBABLE CAUSE
Oversensitive pitch control in control wheel steering mode (Airplane over-reacts to column input)(Cont) Autopilot system fails Bite test Control cable following normal rig procedures tension repeat-edly checks low after flight (AMM 27-31-00/ (AMM 27-31-00/ Refer to AMM 22-11-00, Troubleshooting, for further auto-Elevator power control unit valves sticking Release tension in elevator control system cables. Check for roughness and binding at input cranks Replace elevator power control unit Replace feel and centering unit Check input crank for backlash Elevator feel and centering unit has excessive play NOTE____: Excessive cable Check control cable tension cable rig load is repeat-edly more than 15 pounds below value listed in cable tension chart, cable is worn, or requires rerigging Worn rivets in autopilot eleva-tor actuator lever assembly Hold lever assembly and attempt to rotate at shear Remove assembly and replace rivet area Rerig control pilot troubleshooting related to oversensitive pitch control in control wheel steering mode. tension relaxation (AMM 27-31-00/501). If 401) (AMM 27-31-14/ (AMM 27-31-64/ 401) rivets (OHM 27-09-05) cable as follows: Increase cable rig load listed 1. in cable tension 501) Cycle system 25 times while load 2. Reduce cable rig load listed 3. maintaining increased rig in cable tension chart 501)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-31-00
ALL ú ú 01 Page 114 ú Jul 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
TROUBLE PROBABLE CAUSE ISOLATION PROCEDURE REMEDY
Control cable 4. Cycle system
tension repeatedly 25 times while
checks low after maintaining
flight following normal rig load
normal rig (Step 3)
procedures (Cont)
601) broken wires (AMM 20-20-31/ Check control cable for 401). rig load cable to normal (AMM 20-10-91/ cable After approxi-mately 1 week of service rig Cycle system 25 times while maintaining normal rig load Replace control cable rig load to relax below rig load established 5. (Step 3) (Step 3) 6. NOTE Do not allow ____ in step 3.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-31-00
ALL ú ú 01 Page 115 ú Jul 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
TROUBLE PROBABLE CAUSE ISOLATION PROCEDURE REMEDY
other. and not the rate of climb of Porpoising on 4.5 pounds ments less than force measure-static friction Autopilot (1) both A and B A or B autopilot Occurs on either than 25 seconds. Porpoising; During cruise with autopilot engaged, while flying straight and level, oscillation in more than 250 feet per minute and Stabilizer Trim Wheel movement occurs at intervals less Elevator System Friction Related to Autopilot System Use a force gage to apply inboard aft section of the a vertical force to the Torque Tube. Disconnect the Elevator input rod at the input Feel and Centering Unit Refer to Chapter 22.
the index mark. trailing edge aligned with force with the elevator Measure the static friction applied. where the force is being elevator at the point 0.01 inch movement of necessary to start friction, the minimum force measure system static and B hydraulic systems, With power applied to A inboard side. side and 1 inch from elevator 1 inch from aft
H56174
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-31-00
ALL ú ú 01.1 Page 116 ú Jul 12/02
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(95)
