(11)
Turn off applicable forward and aft fuel pump switches.
(12)
Remove adapter from P&D valve filter pad and reinstall fuel filter and cover using a new O-ring.
7. Engine Prestart Procedure
A. Prepare check sheet to record engine data during start and ground running operation.
B. Check position of following switches on forward overhead panel:
(1)
Ground Power Switch - ON, if ground power is being used.
(2)
AC Meter Switch - GND POWER or APU GEN depending on power source.
(3)
Battery Switch - ON.
(4)
Engine Bleed Air Switches - ON.
(5)
Left and Right Pack Switches - OFF.
(6)
Fuel Pumps - OFF.
(7)
Fuel Heat Switches - OFF.
(8)
Hydraulic System A Engine Pump for Appropriate Engine - ON.
(9)
Hydraulic System B Electric Pumps - OFF.
(10)
Wing and engine inlet anti-ice switches - OFF.
(11)
Gravel Runway Switch - ON.
C. Push (close) Engine Start Ignition circuit breakers and Low Energy Ignition circuit breakers (total of four) on P6 panel.
511
71-09-100 Page 214 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/69
8. Engine Starting and Operating Limitations
CAUTION: GROUND RUNNING OF THE ENGINE AT TAKEOFF POWER SHALL BE RESTRICTED TO FIVE MINUTES. THIS WILL PREVENT CERTAIN ENGINE COMPONENTS FROM EXCEEDING THEIR TEMPERATURE LIMITATION.
A. In addition to monitoring engine starting and operating limitations, it is also necessary to monitor ignition system and air turbine starter limitations. Refer to Chapter 74, Ignition for ignition system limitations. The pneumatic starter duty cycle limitations are as follows:
(1)
For normal starting, the duty cycle is thirty seconds (maximum) on and sixty seconds off.
(2)
For a slow starting engine, the duty cycle can be extended to a maximum at 60 seconds on, at speeds up to starter cutout speed (35 to 40% N2 rpm), and sixty seconds off. The extended duty cycle can be repeated once and then a five-minute cooling period must be observed between extended duty cycle starts.
(3)
For motoring the engine, the duty cycle is two minutes on and five minutes off.
(4)
The starter re-engagement limits are as follows:
(a)
Starter re-engagement is recommended at 0% N2 rpm.
(b)
Starter re-engagement is not permitted above 20% N2 rpm.
NOTE: If possible let the engine come to a complete stop before you re-engage the starter.
CAUTION: YOU MUST NOT ENGAGE THE STARTER AT 20% OR MORE. IF YOU DO ENGAGE THE STARTER, YOU CAN CAUSE DAMAGE TO THE STARTER OR GEARBOX.
(c) Starter re-engagement up to 20% is permitted to clear a fire or after an EGT exceedance condition.
B. Recommended engine operating conditions and limitations are outlined in Fig. 205. The ratings listed in Fig. 205 are defined below and are obtained by positioning the thrust lever to a predetermined EPR.
(1)
TAKE-OFF - This is the maximum thrust that can be used without overboosting the engine and is limited to a five minute time period. This rating is to be used for take-off only.
(2)
MAX CONTINUOUS OR NORMAL RATED - This rating is the maximum thrust which may be used continuously and is also the maximum thrust approved for normal climb.
(3)
MAX CRUISE - This is the maximum thrust approved for cruising.
(4)
IDLE - This is not a thrust rating, but a thrust lever position suitable for minimum thrust operation on the ground or in flight. It is obtained by fully retarding the thrust lever.
500
May 01/98 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 71-09-100 Page 215
C. The maximum allowable compressor rotor speeds are 102.4% (8800 rpm) for the N1 rotor and 100% (12,250 rpm) for the N2 rotor. Engines which are oversped to speeds between 8800 to 8980 (104.5% N1) or 12,250 to 12,550 (102.4% N2) must be given a thorough visual inspection, the rotors checked for free rotation and the cause of overspeed determined and corrected prior to continuing the engine in service. Engines which are oversped above 8980 (104.5% N1) or 12,550 (102.4% N2) must be sent to overhaul for complete inspection.
D. Conditions of over temperature may be anticipated by excessively rapid increase in fuel flow, high-pressure compressor rpm and/or temperature. When an over temperature condition is anticipated or has occurred, the engine should be shut down in accordance with the caution steps outlined in the Start Engine procedure, step A.(8). The engine should not be restarted until the cause of the over temperature is corrected and inspection shows that both compressors will rotate normally.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 动力装置 POWER PLANT(29)
