(2)
The mode selector units for all three systems are located on the pilots' overhead panel.
(3)
The three navigation units are located on a shelf (E2-6) in the main equipment center.
(4)
The three battery units are located on a separate shelf (E12) just forward of the main equipment center at body station 390 and buttock line 45R. Access to the battery units is through the main equipment center.
C. The INS continuously computes horizontal navigation data and senses airplane attitude displacements in pitch, roll, and yaw from a local-horizontal reference. Output signals from the INS are used to steer the airplane over a computed course to a preselected destination, to maintain the airplane and the weather radar display at a level attitude, to provide pitch data for the overrotation warning system, and to display navigation data and airplane attitude on navigation and flight instruments. Each INS furnishes a numerical display of its navigation data and operating status.
EFFECTIVITY AIRPLANES WITH LTN-72 INS
CONFIG 01 A Page 1 Apr 25/86
34-41-00
INS NO. 1 MODE SELECTOR UNIT INS NO. 3 MODE SELECTOR UNIT
INS NO. 2 MODE
SEE B
SELECTOR UNIT
SEE B SEE B SEE A SEE A
SEE C
SEE I
SEE D
SEE C SEE F SEE D
SEE G
SEE G
INS NO. 2 CONTROL/
DISPLAY UNIT
SEE E
VOR/ILS DISPLAY UNIT E INS NO. 1 CONTROL/ SEE SEE H SEE DISPLAY UNIT INS NO. 3 CONTROL/ E
INS
FLIGHT INSTRUMENT SWITCHING RELAY PANEL (P73)
RADIO/INS SWITCH
A
NO. 1 FWD
NO. 3
NO. 2
INS BATTERY
MAIN EQUIPMENT SHELF E-12
CENTER SHELF E2-6
NAVIGATION UNIT INSTALLATION BATTERY UNIT INSTALLATION
Inertial Navigation System Component Location Figure 1 (Sheet 1)
EFFECTIVITY
CONFIG 2
AIRPLANES WITH LTN-72 INS
799 Page 2
34-41-00
Apr 25/86
ALIGN STBY
NAV READY OFF
ATT NAV
REF DH
BATT 20 20
MODE SELECTOR UNIT
10 10 F
55
B
5 5
S 10 10 2020TR E
MILES GND SPEED
T
I N S
2
ATTITUDE DIRECTOR INDICATOR
C
A L E R T
INS AND ATTITUDE TRANSFER SWITCHES
ALERT BATT WARN
HORIZONTAL SITUATION INDICATOR W P 0 D I
D T TK CHG M 1 N 2 3
MAN
AUTO RMT W 4 5 6 E
INSERT
INS COMPASS ATT/COMP STAB
F/O 2 CAPT 1 F/O 2 CAPT 3 CAPT 1 F/O 2 F/O 2 CAPT 2 F/O 2 CAPT 1 F/O 2 CAPT 3 POS XTK/TKE WPT WIND DIS/TIME L 7 S 8 9 R
F/O 3 CAPT 1 F/O 1 CAPT 1 F/O 3 CAPT 1 HDG DA STS DSR TK HOLD 0 DTK CLEAR
TK TEST
GS
CONTROL/DISPLAY UNIT
F E
INS UPDATING
12
KVARS
ESS AC BUS STANDBY
POWER
NORMAL GEN 3 OFF
INS UPDATING ANNUNCIATOR ON
INS BAT PARALLEL GEN 2
G1
NORMAL GEN 1 ON OFF
INS-3 G/S-3 LOC-3 LRRA-3
MANUAL ON
ESS BUS NORMAL OFF
INS BATTERY XFR SWITCH INS NO. 3 ANNUNCIATOR
I
1 INOP ON AIRPLANES H WITHOUT PMS
Inertial Navigation System Component Location Figure 1 (Sheet 2)
EFFECTIVITY
AIRPLANES WITH LTN-72 INS CONFIG 2799 Page 3
34-41-00
Apr 25/86
D. The INS navigation unit contains a gyro stabilized gimbal assembly which senses all changes in airplane attitude and acceleration. Attitude stabilization signals are produced for airplane movement about its pitch, roll, and yaw axes. Instruments in the gimbal assembly sense all vertical and horizontal accelerations (velocity changes). The velocity change signals, central air data computer signals, and manually inserted position data are used by a digital computer in the navigation unit. The digital computer uses the input signals to continuously solve navigation equations, to produce output signals for automatic steering along the desired track, and for display of the computed data.
EFFECTIVITY AIRPLANES WITH LTN-72 INS
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本文鏈接地址：747飛機(jī)維護(hù)手冊(cè)AMM CHAPTER 34 - NAVIGATION 第34章導(dǎo)航2(106)
