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Indication system - Identification and location of components
Figure 1A -SIN 731 - 9999
AFAB
Validity : S / N 275 - 968, 970 - 1184, 1186 - 1213,
1215 - 1477, 1479 - 1505, 1509 - 1512 28-40-00Page 4
(DA) SEP 02
INDICATION SYSTEM
DESCRIPTION AND OPERATION
1. GENERAL (Figure 2)
The main function of the indication system is to provide the pilot with information about fuel pressure and quantity.
The indication system includes :
- gages,
- fuel pressure switch,
- microswitch of selector valve indicator light,
- gaging conditioner,
- tank indicators fitted into engine monitoring cluster - refer to 31-10-00,
- pressure indicator light of the electric pump on advisory panel - refer to 31-50-00,
- tank selector valve indicator light on advisory panel - refer to 31-50-00,
- fuel flow indicator - refer to 73-30-00,
- fuel flow totalizer - refer to 73-30-00 (option).
Option Pre-MOD. 151, Standard Post-MOD. 151
- low level detector,
- low level indicator light on advisory panel - refer to 31-50-00.
Post-MOD. 171
- low level detector,
- low-level double indicator light.
I 2. LOCATION (Figure 1)
COMPONENT QTY AREA ACCESS DOOR REFERENCE
Gage 4 510 /610 512,513,514,516,
519 / 612,613,614,
616,619 28-40-01
Fuel pressure switch 1 100 121,131 28-40-03
Microswitch of selector valve indicator light 1 210 / 28-40-00
Gaging conditioner 1 210 218 28-40-02
Low level detector 2 510 / 610 511,513 /611,613 28-40-04
Engine monitoring cluster 1 251C / 31-10-00
Advisory panel 1 251L / 31-50-00
COMPONENT QTY AREA ACCESS DOOR REFERENCE
Fuel flow indicator 1 251 R / 73-30-00
Fuel flow totalizer (option) 1 250 / 73-30-00
Post-MOD. 171 1 251 L / 28-40-00
Low-level double indicator light
3. DESCRIPTION
A. Gages
The gages, two on each wing, are capacity gage type and are attached to the rear of the tanks on the wing spar.
The level is measured by a capacitor made of two concentric tubes which form the frames. The sensor capacity value varies proportionally with the level.
The oscillator, located on each sensor, changes the capacitor value in frequencies which are proportional to the level.
The sensor transmits the numerical signal into the conditioner.
B. Gaging conditioner
The conditioner which is supplied by the aircraft network, generates the auxiliary power supplies (+ 9 V and +5
The electric signals which come from the sensors, are converted and commuted before the micro-controller is in charge of them.
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本文链接地址：TB20 MAINTENANCE MANUAL 28 FUEL TB20飞机维护手册 燃油(37)
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