1
COMPASS COUPLER 1
3
CAPT ATT/COMP
STAB RELAY
LEG SWITCH, XTK, TKE, DA, NAV VALID TO A/P-F/D ROLL COMPUTER-B
2
COMPASS COUPLER 2
3
F/O ATT/COMP
STAB RELAY
LEG SWITCH, XTK, TKE, DA, NAV VALID TO A/P-F/D ROLL COMPUTER-C
INS Nav Data Simplified Switching Schematic Figure 14
1
3
CAPT INS TRANSFER RELAY
CAPT ALT
NOR-MAL
F/O ALT
INS TRANSFER SW
2
3
F/O INS TRANSFER RELAY INSTR SW ACCESS BOX
INSTR SW ACCESS BOX DIGITAL DATA AND GROUND SPEED VALID
DA DIST
VALID RAD
TRUE HDG VALID
G
G
NAV VALID
TO
CAPT 1 F/O 2 ANN MASTER
CAPT 3 DIM AND ALERT
F/O 2 ANN TEST MODULE
TO/FROM
CAPT 1
F/O 3 ANN XTK
TRUE HDG
TKE+DA
INS RADIO/NAV DATA CAPT RAD/INS
RELAY 28V DC ESS FLT INST BUS CAPT SELECTED
CAPT FLT INST SW RELAY - INS
28V DC FLT INST BUS NO. 2
F/O FLT INST SW RELAY - INS
P7 ELEX CB PNL
RAD F/O SELECTED RADIO/NAV DATA
INS
F/O RAD/INS RELAY
MILES GND SPEED
I N S
1 G
S
A
L
E
R
T
CAPT HSI
TR
E
MILES GND SPEED
I
N
S
2
A
L
E
R
T
F/O HSI
(SAME SIGNALS AS CAPT HSI)
EFFECTIVITY
AIRPLANES WITH LTN-72 INS CONFIG 2 799 Page 35/36
34-41-00
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THIS PAGE INTENTIONALLY LEFT BLANK
INS Attitude and Compass Stabilization Simplified Switching Schematic
Figure 15
EFFECTIVITY CONFIG 2AIRPLANES WITH LTN-72 INS
799 Page 37
34-41-00
Apr 25/86
T34614
F/O HSI
CAPT HSI
F/O ADI
INS 3
CAPT ADI
P126 OVERHEAD CIRCUIT BREAKER PANEL AC INS Power Distribution and Control Figure 16
EFFECTIVITY
CONFIG 2 AIRPLANES WITH LTN-72INS
799 Page 38
34-41-00
Apr 25/86
CAPT ALT
CAPT ATTITUDE/COMPASS
(INS 3)
E12 INS BATTERY SHELF DC INS Relay Control and Power Distribution Figure 17
EFFECTIVITYCONFIG 2AIRPLANES WITH LTN-72INS
799 Page 39
34-41-00
Apr 25/86
(5)
The PMS controls the airplanes flight plan using inertial velocities and present position data received from the INS. These data are averaged (by the PMS) with radio navigation data to compute refined present position. The refined (updated) present position is then transmitted from the PMS to the INU where reasonableness tests are applied. If the update is unreasonable, a malfunction code is displayed on the INS CDU and transmitted to the PMS.
(6)
If a PMS transmission failure is detected by the INS, it will issue a malfunction code and automatically revert to INS waypoint control. When the INS issues the malfunction code, it will search the flight plan for the next TO waypoint. If the waypoint is found, the INS FROM/TO display will show 0 in the left position and the TO waypoint in the right. The airplane will continue to fly the current track until a track change is made, at which time the INS will direct the airplane to the new desired track; the INS FROM/TO display will become the FROM and TO waypoint numbers. If the TO waypoint is not found, the airplane will continue to fly the current track, and the INS will issue another malfunction code. The INS ALERT annunciator will turn on approximately two minutes before the current TO waypoint is reached, and will flash as the waypoint is overflown, with the airplane continuing on the current track. A flight plan should be entered at the INS CDU, using INS waypoint entry procedures.
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本文鏈接地址：747飛機維護手冊AMM CHAPTER 34 - NAVIGATION 第34章導航2(118)
