S 212-077-N00
(3)
On the primary EICAS, make sure the left or right DUCT PRESS is between 32 and 47 psig.
S 862-122-N00
(4)
If you use the autostart, do the steps that follow (Fig. 208 and Fig. 209):
(a)
Put the AUTOSTART switch to the ON position
(b)
Pull out the applicable START button.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
71-00-00
ALL ú ú N03A Page 243 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
CAUTION: DO NOT MANUALLY STOP THE START PROCEDURE (EMERGENCY
_______ CONDITION NOT INCLUDED) UNTIL YOU GET 50% N2 RPM. IF YOU STOP THE START PROCEDURE BEFORE YOU GET 50% N2, HOT STARTS CAN OCCUR WITH SUBSEQUENT ENGINE DAMAGE.
(c) Put the applicable FUEL CONTROL switch to the RUN position and make sure the START switch goes on.
NOTE: When the FUEL CONTROL switch is put to the RUN position,
____ the starter will engage and start to turn the engine. It is possible the EICAS will not show N2, N1, or the correct EGT value until the N2 gets to approximately 8% rpm. The N1 will show at approximately 15% N2 rpm.
(d) Examine the EICAS for indications when the engine lights up and increases in speed to idle.
NOTE: With the autostart, the system will automatically stop
____ the start if the engine does not light up, if the engine stalls, or if there is an overtemperature condition. If the engine does not light up, the autostart system will automatically dry-motor the engine after the start is stopped and then try to start the engine a second time.
1) N1 and N2 increase (you must have an N1 rpm of approximately 24% when N2 rpm is 65% during the start cycle).
2) Lightup (EGT increase) occurs in approximately 20 seconds
after the FUEL CONTROL switch is put to the RUN position. 3) Fuel flow is approximately 227 kgs/hr before light up. 4) Indication of the engine oil pressure increases. 5) EICAS advisory message, HYD PRESS ENG (1, 2, 3, or 4), goes
off as the hydraulic pressure increases more than 1400 psi.
(e) Make sure the START button releases to the off position and the light goes off when the N2 rpm gets to 50%. 1) Make sure the EICAS caution message, STARTER CUTOUT (1, 2,
3 or 4), does not show. 2) If the START button does not release at 50% N2, manually push the START button to the off position.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
71-00-00
ALL ú ú N03A Page 244 ú Oct 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
CAUTION: IF THE EICAS CAUTION MESSAGE, "STARTER CUTOUT (1, 2,
_______ 3, OR 4)", SHOWS AFTER THE START BUTTON RELEASES TO THE OFF POSITION, YOU MUST IMMEDIATELY DO THE ENGINE SHUTDOWN PROCEDURE. IF YOU DO NOT DO THE ENGINE SHUTDOWN PROCEDURE IMMEDIATELY, YOU CAN CAUSE DAMAGE TO THE STARTER.
3) If the EICAS caution message, STARTER CUTOUT (1, 2, 3, or 4), shows with the START switch in the off position, do the steps that follow: a) Move the FUEL CONTROL switch to the CUTOFF position. b) Find and correct the cause of the EICAS message (FIM
71-EICAS Messages).
(f) Let the engine increase in speed to idle.
1) If the engine is not at minimum idle in 120 seconds from fuel-on, it is the flight crew's decision whether to continue with the start procedure.
S 862-141-N00
(5) If you do not use the autostart, do the steps that follow (Fig. 208 and Fig. 209):
(a)
Make sure the AUTOSTART switch is in the OFF position.
(b)
Pull out the applicable START button.
NOTE: When you pull out the START button, the starter will
____ engage and start to turn the engine. It is possible the EICAS will not show N2, N1, or the correct EGT value until N2 is approximately 8% rpm. N1 will show at approximately 15% N2 rpm.
CAUTION: DO NOT PUT THE APPLICABLE FUEL CONTROL SWITCH TO THE
_______ RUN POSITION UNTIL THE PERSONS ON THE GROUND SEES THE N1 ROTOR TURN IN THE FORWARD DIRECTION (CLOCKWISE FROM THE REAR). IF YOU DO NOT OBEY THIS INSTRUCTION, A HOT START CAN OCCUR WITH SUBSEQUENT ENGINE DAMAGE.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 动力装置 POWER PLANT 1(28)
