90
260
100
190 170
180
S-M56-MM-01934-01-B
Addition of Vectors (Example) Figure 510
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-31-00
ALL ú ú C03 Page 547 ú Mar 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
WARNING: MAKE SURE THAT THE BRAKES ARE SUFFICIENT AND THAT THE
_______ ADDED EXHAUST (JET BLAST) WILL NOT CAUSE PROBLEMS. BRAKES THAT ARE NOT SUFFICIENT AND TOO MUCH EXHAUST CAN CAUSE DAMAGE TO EQUIPMENT AND INJURIES TO PERSONS.
CAUTION: MAKE SURE YOU OBEY THE WIND VELOCITY AND DIRECTION
_______ LIMITS. IF YOU DO NOT OBEY THE LIMITS, FAN TIP STALL CAN OCCUR.
1) Start the engine (AMM 71-00-00/201) and operate it at minimum power for 3 minutes until the engine is stable. 2) Increase the speed of the engine slowly, during a time of 20-30 seconds, until the speed is 80 |2 %N1 rpm.
3) Continue to operate the engine at a speed of 80 |2 %N1 rpm for a minimum of 5 minutes to make the temperature of the engine stable.
NOTE: The time to make the temperature stable can be
____ decreased to a minimum of 3 minutes if the engine was operated less than 15 minutes before this procedure. This 3 minute time is not necessary if the trim balance procedure is started less than 5 minutes after the engine was operated at high power and was not stopped.
4) If the analyzer equipment only has sensitivity switch positions of 20 and 100 pC/g, do the steps that follow. a) Initially, set the sensitivity selector to the 100 pC/g
position. b) If the vibration level indication is less than 4 mils
__________ DA (8 mils actual), change the position of the sensitivity switch to 20 pC/g.
NOTE: If the 20 pC/g position is used, the vibration
____ level indications above 20 mils DA are not
___________ satisfactorily accurate.
c) Multiply the indication that shows on the indicator by a number, as follows, to get the correct vibration level.
NOTE: The sensitivity switch for channel 1, which is
____ connected to the 50 pC/g TRF sensor, can only be set to 20 or 100 pC/g.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-31-00
ALL ú ú C05 Page 548 ú Mar 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
1. When the switch is set on 100 pC/g,
_ multiply the indication that shows by 2 to get the correct vibration level.
Mils DA, corrected = Mils DA shown x 2
2. When the switch is set on 20 pC/g,
_ multiply the indication that shows by 0.4 to get the correct vibration level.
Mils DA, corrected = Mils DA shown x 0.4
5) While you monitor the vibration indications for the No. 1 bearing (or FFCCV) and the TRF, increase the speed of the engine slowly to the correct takeoff target %N1.
6) When the engine becomes stable, write the vibration amplitudes (U) and phase angles (A) for each sensor, at the speeds that you used before, on the worksheet on Fig. 511.
7) Decrease the speed to minimum power. a) After 5 minutes, when the engine becomes stable, do the engine shutdown procedure (Ref 71-00-00/201).
(g) See if the vibration levels of the No. 1 bearing (or FFCCV) are not more than 3.5 mils DA and the levels of the TRF are not more than 4.0 mils DA. 1) If the vibration levels are not more than the limits, the
trim balance procedure is completed. a) Do this subsequent task: Put the Airplane Back to Its Usual Condition. 2) If the vibration imbalances are more than limits, do the subsequent Vector Analysis.
J. Do the Vector Analysis.
NOTE: Vector analysis is used when the "one shot" procedure does not
____ correct the imbalance problem. The "one shot" procedure can have phase lag and/or sensitivity values that are not accurate. A new value, from corrected phase lag and sensitivity values, that is calculated by vector analysis will usually give a better result.
S 975-011-C00
(1) Calculate phase lags and sensitivites, again, as follows:
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737-300 400 500 AMM 飞机维护手册 ENGINE 发动机 1(93)
