747-400 AMM 飞机维护手册滑油 OIL(125)_航空信息_民用航空_通用航空

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B. The thermocouple probe senses the engine oil temperature at the main gearbox and sends two independant signals to Channel A and Channel B of the EEC. A corresponding signal is then sent to the EIU's for display.
C. Refer to AMM 73-21-00/001, Fuel Control System, for more data on the thermocouple probe for the EEC oil temperature.
3. No. 3 Bearing Oil Temperature Thermocouple Probe (Fig. 1)
________________________________________________
A. The thermocouple probe for the No. 3 bearing oil temperature includes two thermocouples, and is installed on the oil scavenge line for the No. 3 bearing just before the lubrication and scavenge oil pump.
B. The thermocouple probe senses the scavenge oil temperature of the No. 3 bearing and sends two independant signals to Channel A and Channel B of the EEC.
4. Oil Temperature Indication (Fig. 2)
__________________________
A. The oil temperature indication is installed on the auxiliary EICAS display. For more data on oil temperature indicating system, refer to Integrated Display System, AMM 31-61-00/001.
B. The display shows the temperature of oil in °C on a verticle scale with triangular analog pointers and digital readouts. The digital readouts and pointers change from white to amber when the oil temperature increases to more than 163°C or decreases to less than 50°C. When the oil temperature is more than 177°C, the digital readouts and pointers turn to red.
C. The differential oil temperature, adjacent to the title of DOT, is shown on the EPCS maintenance page.
5. Operation
_________
A. Functional Description
(1) The thermocouple probes for the EEC oil temperature and No. 3 bearing oil temperature find the oil temperature at their respective positions and send related signals to the EEC.
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ALL ú ú N01 Page 1 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
SEE A
EEC OIL
TEMPERATURE
MAIN THERMOCOUPLE
GEARBOX PROBE
(REF) FWD
A
N0. 3 BEARING
SCAVENGE OIL TUBE
NO. 3 BEARING
OIL TEMPERATURE
THERMOCOUPLE PROBE

FWD
MAIN GEARBOX (REF)
LUBRICATION AND SCAVENGE OIL PUMP (REF)
B
Oil Temperature Indicating System Component Location Figure 1
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79-34-00
ALL ú ú N02 Page 2 ú Jun 10/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
78 21 81
N2 X-BLD
17.6 17.6 FF 0.0 18.3
OIL P 65
65 12 66
OIL T 105
105 103 107
15 15 OIL Q 19 15 N2
N2 N2 N2
1.2
1.2 VIB 0.5
1.2
SEE B
SEE A
AUXILIARY EICAS DISPLAY A
TAT +21c D-T0 1 +23c CABIN ALTITUDE EPCS MAN
AUTOTHROT DISC

1.83 1.83 REV 1.83
OUTFLOW VLV L

AA BA
1.62 1.62 1.00 1.65
54.3 54.3 TRA 54.3 54.3 EPR
(11 LINES) 12.4 12.4 SVA 12.4 12.4
102 102 BVA 102 102 CON IGNITION
N C
72.3 72.3 2 72.3 72.3
SEATBELTS RECALL STATUS PG 1 T
75.6 75.6 N1 15.2 83.7 12 12212 12
TAI FL 250 246-324 KTS

P
10.5 10.5 S 10.5 10.5
587 587 EGT 97 535 623
P

12.3 12.3 2 12.3 12.3
XB
N UP GEAR UP
78 78 2 21 15 81
101.5 101.5 RP 101.5 101.5
108 108 SCAV 108 108 65 65 OIL P 12 66
17.6 17.6 FF 0.0 18.3 DN DN
16.3 16.3 P5 16.3 16.3
F L
105 105 OIL T 103 107
5
15 15 OIL Q 19 15
A
60 60AOC 60 60 N21.2 N21.2 VIB N20.5 N21.2
P S
70 70TCC 70 70 12 DUCT PRESS 12 CAB ALT 7500 RATE +250 TOTAL FUEL345.0LBS X
1000 DATE02SEP90 GMT 18:54:04LDG ALT 200AUTO ~P 5.6 TEMP +10c
COMPACTED EICAS DISPLAY ELECTRONIC PROPULSION CONTROL SYSTEM (EPCS) MAINTENANCE PAGE
AOR B A
Oil Temperature Indication
Figure 2