747-400 AMM 飞机维护手册 大气 AIR 1(25)

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 NOTE:____ The cure time is for a temperature conditions of 77 |5°F (25 |3°C) and 50 |5% relative humidity. The cure time can be decreased if you increase the temperature of the sealant (temperature not to be more than 120°F [50°C]) or the structure.
 (4)  S 374-022-N00Use a brush or a spray gun to apply the enamel on the bare metal surfaces.
 NOTE:____ The surfaces became bare when you removed the old sealant and cleaned them.
 (5)  S 434-013-N00Remove the covers that prevent contamination from the electrical connector and the receptacle on the barometric switch.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 434-014-N00
 (6)  Connect the electrical connector to the receptacle on the barometric switch. Refer to the table that follows for the correct equipment numbers.
 ~...................................... | | Equipment Number | | Strut ............................ | | Switch | Connector | ........................................
 |  1  |  S1622  |  DS1622  |
 |  2  |  S1623  |  DS1623  |
 |  3  |  S1624  |  DS1624  |
 |  4  |  S1625  |  DS1625  |

 2...........….............…............1
 S 944-015-N00
 CAUTION: DO NOT PERMIT TOOLS, LOOSE MATERIAL, AND BROKEN PIECES TO STAY
_______ IN THE INTERNAL AREA OF THE STRUT. THEY CAN CAUSE A BLOCKAGE IN THE DRAIN SYSTEM AND CAUSE IT TO NOT OPERATE CORRECTLY.
 (7)  
Make sure that tools, loose material, and broken pieces are not in the internal area of the strut.

 S 414-016-N00

 (8)  
Do this task: "Close the Nacelle and Engine-to-Wing Fairing Access Doors and Panels" (AMM 06-09-09/201). Refer to the table that follows for the correct access door:

 ~............................................................ | Strut | Access Door | Name of the Access Door | .............................................................. | 1 | 451AR | TAI Valve Access Door | | 2 | 461AR | TAI Valve Access Door | | 3 | 471AR | TAI Valve Access Door | | 4 | 481AR | TAI Valve Access Door | 2...........….................…..............................1
 S 864-017-N00
 (9)  
For the applicable engine, remove the DO-NOT-CLOSE tag and close the circuit breaker as follows:

 (a)  
P6 Main Power Distribution Panel 1) 6F14 Eng 1 EEAC 2) 6E14 ENG 2 EEAC 3) 6D14 ENG 3 EEAC 4) 6C14 ENG 4 EEAC

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
TURBINE COOLING SYSTEM - DESCRIPTION AND OPERATION
__________________________________________________
 1.  General
_______
 A.  The turbine cooling system includes the turbine case cooling, and turbine vane and blade cooling for a higher engine efficiency.
 B.  The turbine case cooling (TCC) system includes the shutoff valves for the high pressure turbine (HPT) and low pressure turbine (LPT) case cooling air, HPT and LPT case cooling collectors, HPT and LPT case cooling manifolds, control cable for the TCC air valve, TCC air valve actuator, and the necessary duct to supply fan discharge air to the TCC air inlet duct.
 C.  ENGINES WITHOUT PHASE 3;
 The turbine vane and blade cooling system includes the turbine vane and
 blade cooling air (TVBCA) valves, position switch for the TVBCA valve,
 PS3 air filter (TVBCA valve filter), TVBCA ducts, and TVBCA valve
 solenoid.

 D.  ENGINES WITH PHASE 3;
 The turbine vane and blade cooling system includes the turbine vane and
 blade cooling air (TVBCA) valves, the turbine vane cooling air (TVCA)
 valve, PS3 air filters, TVBCA ducts, TVBCA valve solenoids, and TVCA
 valve solenoid.

 E.  The HPT and LPT cases are externally cooled by fan discharge air during
　
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