S 415-197-N00
WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
_______ THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(27)
Close the thrust reversers (AMM 78-31-00/201).
S 415-198-N00
(28)
Close the core cowl panels (AMM 71-11-06/201).
S 415-199-N00
(29)
Close the fan cowl panels (AMM 71-11-04/201).
S 445-200-N00
(30)
Do the activation procedure for the thrust reversers (AMM 78-31-00/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
71-00-00
ALL ú ú N03 Page 581 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
TEST NO. 13 - ENGINE MAIN OIL PRESSURE
______________________________________
TASK 71-00-00-705-041-N00
15. Test No. 13 - Engine Main Oil Pressure______________________________________
A. General
(1)
This test is used to monitor and adjust the main oil pressure of the engine.
(2)
The permitted limits of the main oil pressure at high rotor speeds (N2) are given in this test.
(3)
If the main oil pressure is not in the limits, you must replace the metering tube nipple of the external oil tube with one of a different type.
B.
Special Tools and Equipment
(1)
Use this table to identify the metering tube nipple:
~......................................................... | TABLE 505 | | TUBE METERING NIPPLE CLASS SELECTION | ........................................................... | PART NUMBER | ORIFICE DIAMETER | ........................................................... | 52T955 CL1 | 0.099-0.101 inch (2.515-2.565 mm) | ........................................................... | 52T955 CL2 | 0.104-0.106 inch (2.642-2.692 mm) | ........................................................... | 52T955 CL3 | 0.109-0.111 inch (2.769-2.819 mm) | ........................................................... | 52T955 CL4 | 0.114-0.116 inch (2.896-2.946 mm) | | 52T955 CL5 | 0.119-0.121 inch (3.023-3.073 mm) | ........................................................... | 52T955 CL7 | 0.123-0.125 inch (3.124-3.175 mm) | ........................................................... | 52T955 CL8 | 0.125-0.127 inch (3.175-3.226 mm) | ........................................................... | 52T955 CL9 | 0.127-0.129 inch (3.226-3.277 mm) |
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
71-00-00
ALL ú ú N03 Page 582 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
TEST NO. 13 - ENGINE MAIN OIL PRESSURE
______________________________________
| 52T955 CL10 | 0.129-0.131 inch (3.276-3.327 mm) | ........................................................... | 52T955 CL11 | 0.131-0.133 inch (3.328-3.378 mm) | ........................................................... | 52T955 CL13 | 0.135-0.137 inch (3.429-3.480 mm) | ........................................................... | 52T955 CL17 | 0.143-0.145 inch (3.632-3.683 mm) | | 52T955 CL20 | 0.149-0.151 inch (3.785-3.835 mm) | ........................................................... | 52T955 CL24 | 0.157-0.159 inch (3.988-4.039 mm) | ........................................................... | 52T955 CL27 | 0.163-0.165 inch (4.140-4.191 mm) | ........................................................... | 52T955 CL30 | 0.169-0.171 inch (4.293-4.343 mm) | | 52T955 CL33 | 0.175-0.177 inch (4.445-4.496 mm) | ........................................................... | 52T955 CL36 | 0.181-0.183 inch (4.597-4.648 mm) | ........................................................... | 52T955 CL39 | 0.187-0.189 inch (4.750-4.801 mm) | ........................................................... | 52T955 CL42 | 0.193-0.195 inch (4.902-4.953 mm) | ........................................................... | 52T955 CL45 | 0.199-0.201 inch (5.055-5.105 mm) | ........................................................... | 52T955 CL48 | 0.205-0.207 inch (5.207-5.258 mm) | 2...............….........................................1
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(90)
