For two tank aircraft 20QJ, 21QJ, and 22QJ are replaced by dummy sensors 35QJ, 36QJ, and 37QJ. The sensors 23QJ1(2), 24QJ1(2), 25QJ1(2), 26QJ1(2), 27QJ1(2), and LOGIC 2 are not used.
Automatic FLSS BITE
After power-up the FQIC tests each Level Sensor Group in a predefined sequence as soon as all the applicable conditions for that group are met.
All groups require:
- the landing gear to be down
- the filght phase 1 (aircraft on the ground)
- a FQIC overall grade of 1, 2, or 3.
In addition to the above each group requires the power and fuel quantity conditions as shown below.
--------------------------------------------------------------------------| Group | Power Source | Fuel Quantity | |--------------------------------------------------------------------------| | 1 | Refuel Bus > 7 seconds | Both inner cells < 3000 kg (6610 lb) | |--------------------------------------------------------------------------| | 2 | Main power > 22 seconds | Center tank > 650 kg (1430 lb) | |--------------------------------------------------------------------------| | 3 | Main power > 22 seconds | Both inner cells > 1500 kg (3310 lb) | |--------------------------------------------------------------------------| | 4 | Main power > 7 seconds | Both inner cells < 3000 kg (6610 lb) | |--------------------------------------------------------------------------| | 5 | Main power > 7 seconds | Both inner cells > 3150 kg (6940 lb) | |--------------------------------------------------------------------------| | 6 | Main power > 7 seconds | Both inner cells < 1900 kg (3890 lb) | --------------------------------------------------------------------------
Where:
- > = more than
- < = less than.
NOTE : Group 2 has no fuel quantity condition for a two tank aircraft
____
(because dummy sensors are fitted).
NOTE : Group 6 and parts of group 4 and 5 are not tested for a
____ two-tank aircraft (because the sensors and Logic 2 are not installed).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page 319
201-299, 401-499, Aug 01/05 CES
(8) INPUT PARAMETERS There are three pages of input parameters that supply data. They are:
- (a) INPUT PARAMETERS, Page 1 - FQIS INPUT PARAMETERS
- (b) INPUT PARAMETERS, Page 2 - FQIS PROBE CAPACITANCES
- (c) INPUT PARAMETERS, Page 3 - FQIS DISCRETE INPUTS.
To observe the working of the Fuel System via the CFDS(FUEL), INPUT PARAMETER pages in real time the pages must be continually updated. Do this by cycling the pages using the NEXT PAGE control on the MCDU. If this procedure is not adopted the pages will remain as they were at the time of the page (menu option) selection.
(a) INPUT PARAMETERS, Page 1 - FQIS INPUT PARAMETERS (Ref. Fig. 304) This page shows:
- the permittivity calculated from the cadensicon
- the density calculated from the cadensicon
- the permittivity calculated from the CIC
- the fuel temperature in the inner and outer cells.
The page also shows the effective pitch and roll. The source of
this attitude data is identified as follows:
- A = Air Data Inertial Reference System (ADIRS)
- F = Fuel Quantity Indicating System (FQIS).
Any Input Parameter Values on this page (or page 2) that are failed or not available may be replaced by crosses (X) or have their decimal point (or C in the case of temperature) replaced by an asterisk (*), as defined below.
-----------------------------------------------------------------------------
| | Displayed Values |
| Parameter |--------------------------------------------------------------|
| | Actual Value | Value with * | XX.......X |
|--------------|--------------------|--------------------|--------------------|
| Cadensicon | Cadensicon covered | Cadensicon not | Kd not available |
| permitivity | and Kd range check | covered or Kd range| (due to failure of |
| (Kd) | not failed | check failed | a FQIC circuit or |
| | | | the K-cell |
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 FUEL 燃油4(18)
