W DOC AIRBUS | TSM A320F

QUANTITY INDICATING - TASK SUPPORTING DATA

** ON A/C NOT FOR ALL
1. Introduction to the FQIS
(Smiths Industries - Intertechnique) with FQIC Software Standard 07.
Part Number Changes.

After upgrading to 07 standard, the FQIC and the OBRM part numbers will change as follows:
FQIC/OBRM
  • SIC5059-03-0106/0206 becomes SIC5059-03-0107/0207
  • SIC5059-11-0106/0206 becomes SIC5059-11-0107/0207
OBRM
  • SIC6175-01-06 becomes SIC6175-01-07
  • SIC6175-02-06 becomes SIC6175-02-07

(Simmonds Precision - Sextant Avionique) with FQIC Software Standard 06.

Part Number

After upgrading the FQIC/OBRM part number will change as follows:
  • B539 AA M 02 04 becomes B539 AA M 02 06.

This shows:
  • the computer hardware remains unchanged at 02 standard
  • the program software is now at 06 standard.

The update introduces no new menus or options but is designed to correct some outstanding problems.

The software changes are summarised as follows.

The wing tank model has been revised to improve gauging accuracy.

It is now possible to preselect small increments of fuel, ie. 200 kg (440 lb).

There will now be no wing imbalance when refuel is complete if refuel had started with a wing inbalance.

If two (2) temperature sensors in the same wing are failed the failure is now a class 1 and not a class 3.

There is a longer confirm time before the ultracomp will show a class 1 failure (was seventeen (17) seconds now five (5) minutes).

If a failure of two probes cause a cockpit affect (degraded or failed) a new class 1 message reporting a double probe failure is produced.

Common FQIC supplied by UTAS with Hardware Part Number P/N 30320-0201 and software Standard S/W S01545-030101 R0102.
The software changes are summarized as follows:

  • Runs on the common fuel gauging fuel computer designed for all single Aisle Family Aircrafts and incorporating the latest digital signal processing hardware.

  • Has an additional FLSS Bite function.

  • Provides more extensive FLSS trouble shooting pages.

  • Uses probe substitution for wing tank probes 1 to 4 if out of range failures are detected.

  • To process the temperature inputs from 3 wires Resistance Temperature Devices (RTD's) used for all fuel temperature monitoring.

Introduction (Refer to AMM 22-82-00, 28-42-00, and 31-32-00 for more data).

The options/facilities are shown and controlled from the menu on the MCDU (part of the CFDS). To see the menu, make sure the MCDU and FQIC is supplied with power. Select CFDS MENU, SYSTEM REPORT/TEST, then FUEL.
The FUEL main menu page is now shown. When the data has more than one page the more-to-come symbol (an arrow) will be shown in the top right corner.

Introduction (Refer to AMM 22-82-00, 28-42-00, and 31-32-00 for more data).

The 07 software has improved performance and introduces a new menu option COMMAND FLSS BITE. The FQIC fault diagnosis/trouble-shooting page has been fully revised. Although it is for use in the workshop it can be used as an aid to trouble-shooting on the aircraft.
These facilities are shown and controlled from the menu on the MCDU (part of the CFDS). To see the menu, make sure the MCDU is supplied with power. Select CFDS MENU, SYSTEM REPORT/TEST, then FUEL.
The FUEL main menu page is now shown. When the data has more than one page the more-to-come symbol (an arrow) will be shown in the top right corner.

Introduction (Refer to AMM 22-82-00, 28-42-00, and 31-32-00 for more data).

The main menu consists of a single page displayed in large and small characters. (Font sizes used for legacy A321 MENU).
The options/facilities are shown and controlled from the menu on the MCDU (part of the CFDS). To see the menu, make sure the MCDU and FQIC is supplied with power. Select the key 6L < RETURN to go back to Normal mode. The MENU is not appropriate for printing and so PRINT> option is not displayed. The PRINT> option is only displayed when a printer is fitted. Select CFDS MENU, SYSTEM REPORT/TEST, then FUEL.
The heading FUEL is displayed in large characters on line 1 of each page. When a menu consists of more than one page, the more-to-come symbol (< or >) will be shown on line 1 column 24 of every page.

To see the next page press the NEXT PAGE key on the MCDU. To select any menu option press the line-function key adjacent to the < or > symbol adjacent to the applicable option. The Fuel Quantity Indicating Computer (FQIC) has two channels identified as channel 1 and channel 2. The menu shown and related data initially come from the better channel (or from channel 1 when the two are equally good) of the FQIC. The channel used to supply the data is shown in the top left corner of the MCDU.

A. Menu Options

The menu options are:
  • (1) LAST LEG REPORT
  • (2) PREVIOUS LEGS REPORT
  • (3) LRU IDENTIFICATION
  • (4) CLASS 3 FAULTS
  • (5) Not applicable
  • (6) FQIS STATUS
  • (7) FLSS STATUS
  • (8) INPUT PARAMETERS VALUES
  • (9) COMMAND FLSS BITE.
NOTE: All the menu options (1) to (9) are shown on one page. This is called the Main Menu.


The menu options available with the 07 software are:
  • (1) LAST LEG REPORT
  • (2) PREVIOUS LEGS REPORT
  • (3) LRU IDENTIFICATION
  • (4) CLASS 3 FAULTS
  • (5) SELECT CHANNEL
  • (6) FQIS STATUS
  • (7) FLSS STATUS
  • (8) INPUT PARAMETERS VALUES
  • (9) COMMAND FLSS BITE.
NOTE: The options (1) to (5) are shown on page 1 of the MAIN MENU. Press the NEXT PAGE key of the MCDU to see the options (6) to (9) on page 2.


The menu options consist of a single page. The left hand side of the screen displays the following menu:
  • (1L) LAST LEG REPORT
  • (2L) PREVIOUS LEGS REPORT
  • (3L) CLASS 3 FAULTS
  • (4L) INPUT PARAMETERS VALUES
  • (5L) COMMAND FLSS BITE
  • (6L) RETURN.
    The right side of the screen displays the folloing menu:
  • (1R) FQIS STATUS
  • (2R) FLSS STATUS
  • (3R) LRU IDENT

NOTE: The FQI channel in communication with CFDS is displayed as either CH1 or CH2.

(1) LAST LEG REPORT
The LAST LEG REPORT gives all the class 1 and 2 LRUs which have been found unserviceable during the last flight leg, or on the ground before the last flight leg for defects detectable on the ground only (e.g. FLSS BITE detected defects). Each LRU is identified by:
  • description
  • FIN
  • Time (GMT/UTC) at which the failure was first detected
  • ATA number.
The FQIC channel(s) responsible for detecting and issuing the failure message are also identified.
NOTE: No failures are currently Class 2.
Trouble-shooting data can be accessed by use of the line function key to the right of the ATA number of the LRU.
(2) LAST LEG REPORT
The LAST LEG REPORT gives all the class 1 and 2 LRUs which have been found unserviceable during the last flight leg, or on the ground before the last flight leg for defects detectable on the ground only (e.g. FLSS BITE detected defects). Each LRU is identified by:
  • description
  • FIN
  • Time (GMT/UTC) at which the failure was first detected
  • ATA number.
NOTE: No failures are currently Class 2 when 07 FQIC software standard is installed.

If the FQIC has been found unserviceable, computer trouble-shooting data for internal faults can be accessed by use of the line function key to the right of the LRU. This causes an alpha-numeric grid to be shown.

The FQIC trouble shooting data can also be accessed from:
  • PREVIOUS LEGS REPORT
  • FQIS STATUS.

The FLSCU trouble-shooting data can also be accessed from:
  • PREVIOUS LEGS REPORT
  • FLSS STATUS.

NOTE: Cadensicon trouble-shooting data for internal faults can be accessed from:
  • CLASS 3 FAULTS
  • FQIS STATUS.

(3) LAST LEG REPORT
The LAST LEG REPORT gives all the class 1 and 2 Fault Maintenance Codes (FMC) during the last flight leg, or on the ground before the last flight leg for defects detectable on the ground only as follows:
  • FMCs detected during MAINT PHASE
  • FMCs detected during FQIC PBIT and/or FLSS PBIT.

    Each LRU is identified by:
  • Description
  • The aircraft tail number
  • Time (GMT) at which the failure was first detected
  • ATA number.

NOTE: For all failures detected on the ground prior to transition to MAIN PHASE the FQIS will transfer all failures to the non-volatile Flight Memory immediately.

Each failure message is separated by a line; this allows three failure messages to be displayed on each page of the MCDU.

The FQIC trouble-shooting data can also be accessed from:
  • PREVIOUS LEGS REPORT
  • FQIS STATUS.

Failures associated with the FQIS and FLSS produce troubleshooting data.

(4) PREVIOUS LEGS REPORT
The PREVIOUS LEGS REPORT identifies all the class 1 and 2 LRUs which have been detected as unserviceable during the previous flight legs, up to a maximum of 63 flight legs. The parameters used to identify each LRU are as follows:
  • description
  • FIN
  • flight leg
  • date
  • time (GMT/UTC) of the first detection of the failure for each flight leg
  • ATA number.

The FQIC channel(s) responsible for detecting and issuing the failure message are also identified.
If the FQIC has been installed in more than one aircraft. Each page is identified by the aircraft tail number.
The most recent flight leg is identified by -01, the flight before by -02 etc., the most recent failures being shown first.
Trouble-shooting data can be accessed by use of the line function key to the right of the ATA number of the LRU.
(5) PREVIOUS LEGS REPORT
The PREVIOUS LEGS REPORT identifies all the class 1 and 2 LRUs which have been detected as unserviceable during the previous flight legs, up to a maximum of 63 flight legs. The parameters used to identify each LRU are as follows:
  • description
  • FIN
  • flight leg
  • date
  • time (GMT/UTC) of the first detection of the failure for each flight leg
  • ATA number.
    If the FQIC has been installed in more than one aircraft. Each page is identified by the aircraft tail number.
    The most recent flight leg is identified by -01, the flight before by -02 etc., the most recent failures being shown first.
    Where the FQIC or either FLSCU has been found unserviceable, internal trouble-shooting data can be accessed and decoded in the same way as for the LAST LEG REPORT.

(6) PREVIOUS LEGS REPORT
The PREVIOUS LEGS REPORT identifies all the class 1 and 2 LRUs which have been detected as unserviceable during the previous flight legs, up to a maximum of 63 flight legs. The parameters used to identify each LRU are as follows:
  • Title
  • The LRU and its associated FIN
  • Date
  • Time (GMT) of the first detection of the failure for each flight.
  • The aircrafts tail number
  • ATA reference number

NOTE: For all failures detected on the ground prior to transition to MAIN PHASE the FQIS will transfer all failures to the non-volatile Flight Memory immediately.
Each Failure is allocated two lines on the MCDU.
If the FQIC has been installed in more than one aircraft. A new page shall be displayed for each aircraft. Each page is identified by the aircraft tail number.
The most recent flight leg is identified by -01, the flight before by -02 etc., the most recent failures being shown first.
Trouble-shooting data can be accessed by use of the line function key to the right of the ATA number of the LRU (only available for FQIC 3QT, FLSCU 1 and FLSCU 2).
(7) LRU IDENTIFICATION
This menu option shows the part number of the FQIC.

FQIC CH1 B539AAM XXYY *

FQIC CH2 B539AAM XXYY

* Where:
XX = computer hardware standard
YY = software standard

The part numbers shown must be the part numbers of the FQIC and OBRM which are currently installed in the aircraft.

The aircraft tail number, date, and time are also shown.
(8) LRU IDENTIFICATION
The selection of this option will show the FQIC and the OBRM combined part number. The part number shown must agree with the part number of that LRU installed in the aircraft.
EXAMPLE
FQIC SIC 5095-HH-00-SS
Where:
  • HH is the computer hardware standard (e.g. 03, 11)
  • 00 is the OBRM hardware standard (e.g. 01, 02)
  • SS is the software standard (07).

For 07 Software, and current in service units, one of the part numbers that follow will be shown:
  • SIC 5059-03-01-07
  • SIC 5059-03-02-07
  • SIC 5059-11-01-07
  • SIC 5059-11-02-07.
(9) LRU IDENTIFICATION
This menu option shows the part number of the FQIC.
The general display shows the channel number, title, date, time (GMT) at the time the page was selected, A/C tail number.

FQIC CH1 P/N 30320 0201

FQIC CH2 S/W S01545 - 0301R****

Where '****':
is the revision of the released S01545-030101 software standard.


The part numbers shown must be the part numbers of the FQIC currently installed in the aircraft.

(10) CLASS 3 FAULTS
This option shows the Class 3 faults (up to a maximum of 63 flight legs) known to the FQIC. Each LRU is identified by the same parameters as those on the PREVIOUS LEGS REPORT.
Trouble-shooting data can be accessed by use of the line function key to the right of the ATA number of the LRU.
(11) CLASS 3 FAULTS
This option shows the Class 3 faults (up to a maximum of 63 flight legs) known to the FQIC. Each LRU is identified by the same parameters as those on the PREVIOUS LEGS REPORT. Where any cadensicon has been found as unserviceable, internal trouble-shooting can be accessed and decoded in the same way as for the FQIC and FLSCU. See LAST LEG REPORT.
(12) CLASS 3 FAULTS
This option shows the Class 3 faults that have been identified during the last and previous flight legs (up to a maximum of 63 flight legs) known to the FQIC. Each failed LRU is identified by the same parameters as those on the PREVIOUS LEGS REPORT.
Trouble-shooting data can be accessed by use of the line function key to the right of the ATA number of the LRU.
(13) Not applicable.
(14) SELECT CHANNEL
Each menu mode transmission can be called from the other channel by use of the SELECT CHANNEL option. The channel with the best grade will get control when Normal Mode is re-entered. To get back to Normal Mode select RETURN on the MCDU. The CFDS will then send a logoff command to the FQIC, which must then go back to Normal Mode.

(15) FQIS STATUS
This option permits access to channel 1 or channel 2 BITE memory, as set on channel selection (see para., (5) above).
A list is made of every FQIS LRU known or thought to be defective currently, or at the last power-on BITE test. All failure classes are reported and where the FQIC or a cadensicon is defective, trouble-shooting data can be accessed by the same procedure as for the LAST LEG REPORT.

The operating grade number for each channel is also shown and is decoded as follows:

----------------------------------------------------------------------------
! GRADE ! System Operational Effect !
!-------!--------------------------------------------------------------------!
! 1 ! Correct operation. !
! ! In this grade the FQIS can be fully serviceable or contain the !
! ! failures as follows: !
! ! - a single probe failure in any tank (does not include 34QT1(2) !
! ! probe failures which are Grade 3) !
! ! - density out of range !
! ! - cadensicon permittivity out of range !
! ! - the A value out of range (calculated from density and !
! ! permittivity) !
! ! !
! ! (The A value is a fuel characteristic dependent on density and !
! ! permittivity) !
! ! !
! ! (A probe/cadensicon is said to have failed if for longer than !
! ! 30 seconds: !
! ! - its output is outside its normal working range !
! ! - an open circuit is found at the probe input !
! ! - a short circuit is found at the probe input). !
! ! !
! 2 ! Not used. !
! ! !
! 3 ! Degraded operation, less accurate (accuracy within 2.5 times the !
! ! specified accuracy). !
! ! The two least significant digits of the ECAM FQI indications are !
! ! forced to zero with an amber line across. !
! ! Can be caused by: !
! ! - more than 2 probe failures in any tank driven by the same !
! ! oscillator !
! ! - 34QT1(2) probe failures. !
! ! !
! 4 ! Worse than degraded operation - the FQI indications show XX. !
! ! Can be caused by: !
! ! - more than 2 probe failures in any tank driven by from different !
! ! oscillators !
! ! - the failure of cadensicon and compensator permittivity, !
! ! (the cadensicon is counted as failed if D, Kd or A has failed) !
! ! - Analog to Digital Converter gain failure !
! * ! - Analog to Digital Converter offset failure !
! * ! - volume or mass out of range. !
! ! Where: !
! ! - D = cadensicon density !
! ! - Kd = cadensicon permittivity !
! ! !
! ! The causes shown with an asterisk (*) are FQIC hardware failures. !
! ! !
! 5 ! FQIC output disabled, no computed data (NCD), Xs shown. !
! ! Can be caused by: !
! ! - the OBRM test failure !
! * ! - the RAM test failure !
! * ! - the dual port RAM test failure !
! * ! - the ARINC wrap-around test failure. !
! ! !
! ! Where: !
! ! - OBRM = on board replaceable memory module !
! ! - RAM = random access memory !
! ! - ARINC = Aeronautical Radio Inc., (429 type digital bus). !
! ! !
! X ! Master/better channel unable to show the grade of the other !
! ! channel. A cross communication, between channels failure. !
! ! !
----------------------------------------------------------------------------

Each failed LRU is identified by its:
  • description
  • FIN
  • time (GMT/UTC) at which the failure was first detected
  • ATA number.

Where the FQIC or any cadensicon has been found unserviceable, internal trouble-shooting data can be accessed and decoded in the same way as for the LAST LEG REPORT.
(16) FQIS STATUS
This option gives access to a list which is produced of every FQIS LRU detected as being currently failed. All failure classes are reported.

Each page includes the current aircraft tail number, the date, and the time GMT/UTC. The time shown is the time at which the page was selected.
Trouble-shooting data can be accessed by use of the line function key to the right of the ATA number of the LRU.

A number to show each channels health is given alongside the page title in brackets, FQIS STATUS (GRADES=A:B). A is the grade of channel 1, and B is the grade of channel 2.
The grades that can occur are:
GRADE 1 = Normal Fuel Grade
GRADE 3 = Degraded Fuel Grade
GRADE 4 = Failed Fuel Grade.
The grade number is decoded as follows:

----------------------------------------------------------------------------
! GRADE ! System Operational Effect !
!-------!--------------------------------------------------------------------!
! 1 ! Normal Fuel Grade. (Accuracy better than 3 times the specified !
! ! accuracy). !
! ! Normal or satisfactory operation. !
! ! In this grade the FQIS can be fully serviceable or contain up to !
! ! 20 probe failures (excluding double probe failures). !
! ! The FQIS will also continue in this grade if one source of fuel !
! ! permittivity is available. !
! ! !
! ! (A probe is said to have failed if for longer than 30 seconds: !
! ! - its output is outside its normal working range !
! ! - an open circuit is found at the probe input !
! ! - a short circuit is found at the probe input). !
! ! !
! 2 ! Not used. !
! ! !
! 3 ! Degraded Fuel Grade. (Accuracy between 3 and 5 times the specified !
! ! accuracy). !
! ! The two least significant digits of the ECAM FQI indications are !
! ! forced to zero with an amber line across. !
! ! !
! ! Data reference GRADE 3 logic can be found at the end of this table.!
! ! !
! 4 ! Failed Fuel Grade. (Accuracy worse than 5 times the specified !
! ! accuracy). !
! ! The ECAM FQI indications show XX. !
! ! !
! ! Data reference GRADE 4 logic can be found at the end of this table.!
! ! !
! X ! Master/better channel unable to show the grade of the other !
! ! channel. A cross communication, between channels failure. !
! ! Could be caused by: !
! ! - a channel not powered !
! ! - a channel failure. !
! ! !
----------------------------------------------------------------------------

GRADE 3 and 4 Logic

Double Probe Failure
The probes in all the cells are divided into pairs. If the capacitance of both probes in any of the pairs is invalid, then the accuracy mode for that cell is set to either degraded or failed. The probe pairs are as shown in the table below.
--------------------------------------------------------------
! ! Probe Pairs ! !
! !-----------------------! !
! Fuel Cell ! Probe 1 ! Probe 2 ! Accuracy Mode !
!-----------------!-----------!-----------!--------------------!
! Left Wing ! 4 ! 5 ! Degraded !
! ! 5 ! 6 ! Degraded !
! ! 6 ! 7 ! Degraded !
! ! 7 ! 8 ! Failed !
! ! 8 ! 9 ! Degraded !
! ! 9 ! 10 ! Failed !
! ! 10 ! 11 ! Failed !
! ! 11 ! 12 ! Failed !
! ! 12 ! 13 ! Degraded !
! ! 13 ! 14 ! Degraded !
! ! ! ! !
! Left Collector ! 1 ! 2 ! Failed !
! ! ! ! !
! Right Collector ! 1 ! 2 ! Failed !
! ! ! ! !
! Right Wing ! 4 ! 5 ! Degraded !
! ! 5 ! 6 ! Degraded !
! ! 6 ! 7 ! Degraded !
! ! 7 ! 8 ! Failed !
! ! 8 ! 9 ! Degraded !
! ! 9 ! 10 ! Failed !
! ! 10 ! 11 ! Failed !
! ! 11 ! 12 ! Failed !
! ! 12 ! 13 ! Degraded !
! ! 13 ! 14 ! Degraded !
! ! ! ! !
! Center ! 1 ! 2 ! Degraded !
! ! 1 ! 3 ! Degraded !
! ! 3 ! 5 ! Failed !
! ! 4 ! 5 ! Failed !
! ! ! ! !
! ACT 1 ! 1 ! 2 ! Failed !
--------------------------------------------------------------

For any cell, if there are greater than 2 pairs of probes with an invalid capacitance (except for pairs 2-4 and 3-4 in the center tank), then that cell shall be set to failed.

FQIC Signal Conditioner Failure
If there are greater than 20 probes with an invalid capacitance in all cells, then the Signal Conditioner that these connect to is considered to have failed. The failure status is set to Degraded.

Fuel Offset Errors
NOTE: The fuel offset value (A) is a fuel characteristic dependent on density and permittivity.
If the cell fractional volume is greater than 15% then the calculated Fuel Offset will be given a status which will be dependent on the Dielectric Computation status and the Fuel Offset status. The Fuel Offset status is determined as shown in the table that follows:
--------------------------------------------------------------
! Fuel Offset Status !
!--------------------------------------------------------------!
! Status Inputs ! Output Status !
!-----------------------------------------!--------------------!
! Fuel Offset(1) ! Dielectric Computation ! Fuel Offset Status !
!----------------!------------------------!--------------------!
! Measured ! High ! Normal !
! Measured ! Inferred ! Normal !
! Measured ! Default ! Normal !
! Default ! High ! Normal !
! Default ! Inferred ! Normal !
! Default ! Default ! Degraded !
! ! ! !
--------------------------------------------------------------

NOTE: The Fuel Dielectric Grades are as follows:
  • High - at least one value measured and validated
  • Inferred - measured values not validated, value computed from measured temperature
  • Default - cannot be determined, set to a default value.

If the cell fractional volume is less than 15% then the Fuel Offset Status is set to Normal

Final Tank Grades
The grades for the Left, Right, and Center tanks are calculated as follows:
  • the grade for each tank will be updated to Degraded if the Signal Conditioner failure Status is Degraded or if the Fuel Offset Status is Degraded when a tank was previously at Normal, otherwise no change is made
  • the grade obtained from the Double Probe Failure calculation overrides the others when it is the lowest.

The total fuel grade is set to the lowest grade of any tank (cell) fitted.
(17) FQIS STATUS
This option gives access to a list which is produced of every FQIS LRU detected as being currently failed. All failure classes are reported.

Each page includes the current channel number, title, the date, and the time (GMT) at which the page was selected, aircraft tail number.
Trouble-shooting data can be accessed by use of the line function key to the right of the ATA number of the LRU.

A number to show each channels health is given on line 4 of each page.
The grades that can occur are:
GRADE 1 = Normal operation
GRADE 2 = Not used
GRADE 3 = Normal operation with reduced accuracy, shown as dash
GRADE 4 = Outside normal operation, shown as cross
GRADE X = Grade unknown, computing channel is not operational.
The grade number is decoded as follows:

----------------------------------------------------------------------------
! GRADE ! System Operational Effect !
!-------!--------------------------------------------------------------------!
! 1 ! Normal Operation. (Accuracy within 3 times the specified FQIS !
! ! accuracy). !
! ! Normal or satisfactory operation. !
! ! In this grade the FQIS can be fully serviceable or contain up to !
! ! 20 probe failures (excluding double probe failures). !
! ! The FQIS will also continue in this grade if one source of fuel !
! ! permittivity is available. !
! ! !
! ! (A probe is said to have failed if for longer than 30 seconds: !
! ! - Its output is outside its normal working range !
! ! - An open circuit is found at the probe input !
! ! - A short circuit is found at the probe input). !
! ! !
! 2 ! Not used. !
! ! !
! 3 ! Normal operation with reduced accuracy. !
! ! (Accuracy between 3 and 5 times the specified FQIS accuracy. !
! ! The two least significant digits of the ECAM FQI indications are !
! ! forced to zero with an amber line across. !
! ! !
! ! Data reference GRADE 3 logic can be found at the end of this table.!
! ! !
! 4 ! Outside Normal operation (Accuracy outside 5 times the specified !
! ! FQIS accuracy). !
! ! The ECAM FQI indications show XX. !
! ! !
! ! Data reference GRADE 4 logic can be found at the end of this table.!
! ! !
! X ! Master/better channel unable to show the grade of the other !
! ! channel. A cross communication, between channels failure. !
! ! Could be caused by: !
! ! - A channel not powered !
! ! - A channel failure. !
! ! !
----------------------------------------------------------------------------

GRADE 3 and 4 Logic

FQI Operation Under Single and Double Probe Failures:
The cFQIC fuel gauging architecture has been designed to be tolerant to any single detected failure.
In the wing tanks the probes at the greatest risk of water contamination are tank units 1 and 2.
If a range fail is detected with these units, tank units 3 and 4 are used.
When there are two detected failures, the effect on the individual tank and FOB are dependent on the nature of the two failures.

Single Failures - Tank Unit 1 or Tank Unit 2:
When wing tank unit 1 is detected as failed, the fractional immersion of the neighbouring wing tank unit 3 is substituted onto tank unit 1 and the wing tank and FOB gauging accuracy mode will be set to ''Normal''.
When wing tank unit 2 is detected as failed, the fractional immersion of the neighbouring wing tank unit 4 is substituted on to tank unit 2 and the wing tankand FOB gauging accuracy mode will be set to ''Normal''.
Single Failures of tank units 3 or 4 have no effect on tank accuracy.

Single Probe Failures - Other Tank Units
When a single failure is detected, the wing tank and FOB gauging accuracy mode will be set to ''Normal''.

Double Probe Failures
When an even numbered (>=6 and <=12) and an odd numbered (>=5 and <=11) wing tank unit, that is one sensor from each group are detected as failed, then the wing tank and FOB gauging accuracy mode will be set to ''Failed''.
When 2 probes from the same group fails, the gauging display will be normal.

Probe Group Failures
FOB display in the wing tanks remains normal if any number of probes from the same group fail (even numbered probes or odd numbered probes). The wing tank quantity display will also remain normal if an entire FQI channel is failed.

Outer Wing Cell Single Failures
When outer wing tank unit 14 is detected as failed, the wing tank and FOB gauging accuracy mode will be set to ''Degraded''.
When outer wing tank unit 13 is detected as failed, there is no effect gauging display will be normal.

Centre Tank Probe Failures:
In the centre tank, 3 probes are connected to FQI CH1 and 2 probes connected to CH2 and hence the asysmmetric degraded and failures in the centre tank.

Centre Tank Single Probe Failures:
If FQI CH1 is detected as failed, the centre tank and FOB gauging accuracy mode will be set to ''Degraded''.
If FQI CH2 is detected as failed, the center tank and FOB gauging accuracy mode will be set to ''Normal''.

Centre Tank Double Probe Failures:
When any even and any odd centre tank unit are detected as failed, the centre tank and FOB gauging accuracy mode will be set to ''Failed''./
When two probes failed from the same group, then the accuracy is set to ''Degraded'' or ''Normal'' depending on the probe fail combination.

ACT Single Probe Failures:
When an ACT tank unit 1 or ACT tank unit 2 is detected as failed, the ACT and FOB gauging accuracy mode will be set to ''Degraded''.

ACT Double Probe Failures:
When an ACT tank unit 1 or ACT tank unit 2 is detected as failed, the ACT and FOB gauging accuracy mode will be set to ''Failed''.
--------------------------------------------------------------
! ! Probe Pairs ! !
! !-----------------------! !
! Fuel Cell ! Probe 1 ! Probe 2 ! Accuracy Mode !
!-----------------!-----------!-----------!--------------------!
! Left Wing ! 6 ! 5 ! Failed !
! ! 8 ! 7 ! Failed !
! ! 10 ! 9 ! Failed !
! ! 12 ! 11 ! Failed !
! ! 6 ! 8 ! Normal !
! ! 8 ! 10 ! Normal !
! ! 10 ! 12 ! Normal !
! ! 5 ! 7 ! Normal !
! ! 7 ! 9 ! Normal !
! ! 9 ! 11 ! Normal !
! ! ! ! !
! Right Wing ! 6 ! 5 ! Failed !
! ! 8 ! 7 ! Failed !
! ! 10 ! 9 ! Failed !
! ! 12 ! 11 ! Failed !
! ! 6 ! 8 ! Normal !
! ! 8 ! 10 ! Normal !
! ! 10 ! 12 ! Normal !
! ! 5 ! 7 ! Normal !
! ! 7 ! 9 ! Normal !
! ! 9 ! 11 ! Normal !
! ! ! ! !
! Centre ! 1 ! 1 ! Normal/Degraded !
! ! 1 ! 2 ! Failed !
! ! 2 ! 2 ! Normal/Degraded !
! ! 2 ! 3 ! Failed !
--------------------------------------------------------------

(18) FLSS STATUS
The selection of the FLSS STATUS gives the results of the last FLSS BITE test. See
F FLSS Status - BITE Test Results and Group Test Identification Cross Reference ** ON A/C NOT FOR ALL
Each part of the BITE test has three possible results:
  • P = PASSED
  • F = FAILED
  • * = PREVIOUS RESULT. This part of the BITE test was not carried out as the correct conditions did not exsist. The result given is that from a previous BITE when the conditions for that part of the BITE were correct and the test was performed.
If any of the BITE tests has FAILED, then the more-to-come symbol (an arrow) will be shown. Selection of the NEXT PAGE will cause a list of defective FLSS LRUs to be shown. See
F FLSS Status - Failures Detected ** ON A/C NOT FOR ALL

All FLSS LRUs failure classes are reported.

Each failed LRU is identified by its:
  • description
  • FIN
  • time (GMT/UTC at which the failure was first detected)
  • ATA number
  • identification as to which FQIC channel (1 or 2) issued the failure message.
    FLSS BITE

    The FLSS BITE is run automatically, by the FQIC master channel:
  • a small time after a power-up
  • after a manual command from the MCDU via the CFDS.

The FLSS BITE consists of 16 test groups as shown below.

-------------------------------------------------------------
! Test Group ! Sensor Circuit Tested ! FQIC to FLSCU !
! ! ! BITE Line Used !
!------------!-------------------------------!----------------!
! 1AL ! Left Wing High Level ! 1 !
! 1AR ! Right Wing High Level ! 1 !
! 1AC ! Center Tank High Level ! 1 !
! 1BL ! Left Surge Tank High Level ! 1 !
! 1BR ! Right Surge Tank High Level ! 1 !
! ! ! !
! 2AL ! Left Wing Low Level ! 2 !
! 2AR ! Right Wing Low Level ! 2 !
! 2AC ! Center Tank Low Level ! 2 !
! ! ! !
! 3L ! Left Wing Low Level ! 3 !
! 3R ! Right Wing Low Level ! 3 !
! ! ! !
! 4AL ! Left Wing Logic Circuits ! 4 !
! 4AR ! Right Wing Logic Circuits ! 4 !
! 4BL ! Left Wing Full/Underfull A ! 4 !
! 4BR ! Right Wing Full/Underfull A ! 4 !
! 4CL ! Left Wing Full/Underfull B/C ! 4 !
! 4CR ! Right Wing Full/Underfull B/C ! 4 !
! ! ! !
-------------------------------------------------------------

Not every part of the BITE test is always done. The tests done will depend on the power conditions and the fuel levels.

Automatic FLSS BITE

After power-up the FQIC initiates the FLSS BITE tests provided the conditions that follow are met:
  • the FQIC power-up BIT is complete
  • at least 35 seconds have passed since power was applied to the FQIC
  • the flight phase is 2 or less or not available
  • the Ground/Flight input discrete (Gnd/Flt) indicates ground
  • this is the MASTER channel.

In addition to the above each group requires the power and fuel quantity conditions as shown below.
-----------------------------------------------------------------------------
! Test ! Group Test Conditions ! Sensor(s)/!
! Group ! ! System !
! ! ! Tested !
!-------!---------------------------------------------------------!-----------!
! 1AL ! Left Wing Fuel Quantity less than or equal to 5300kg ! 17QJ1 !
! ! Refuel Bus Power is ON for last 7s minimum ! !
! ! High Level Test is OFF for last 5s minimum ! !
! ! ! !
! 1AR ! Right Wing Fuel Quantity less than or equal to 5300kg ! 17QJ2 !
! ! Refuel Bus Power is ON for last 7s minimum ! !
! ! High Level Test is OFF for last 5s minimum ! !
! ! ! !
! 1AC ! Center Tank Fuel Quantity less than or equal to 5700kg ! 6QJ !
! ! Refuel Bus Power is ON for last 7s minimum ! 20QJ !
! ! High Level Test is OFF for last 5s minimum ! !
! ! ! !
! 1BL ! Left Wing Fuel Quantity less than or equal to 5300kg ! 28QJ1 !
! ! Main/Battery Discrete at Main ! !
! ! High Level Test is OFF for last 5s minimum ! !
! ! ! !
! 1BR ! Right Wing Fuel Quantity less than or equal to 5300kg ! 28QJ2 !
! ! Main/Battery Discrete at Main ! !
! ! High Level Test is OFF for last 5s minimum ! !
! ! ! !
! 2AL ! Left Wing Fuel Quantity greater than or equal to 1900kg,! 16QJ1 !
! ! or at 0kg (tank empty/sensor dry) ! 40QJ1 !
! ! Main/Battery Discrete at Main ! !
! ! ! !
! 2AR ! Right Wing Fuel Quantity greater than or equal to ! 16QJ2 !
! ! 1900kg, or at 0kg (tank empty/sensor dry) ! 40QJ2 !
! ! Main/Battery Discrete at Main ! !
! ! ! !
! 2BC ! Center Tank Fuel Quantity greater than or equal to ! 21QJ !
! ! 650kg ! 22QJ !
! ! Main/Battery Discrete at Main ! !
! ! ! !
! 3L ! Left Wing Fuel Quantity greater than or equal to ! 15QJ1 !
! ! 1900kg, or at 0kg (tank empty/sensor dry) ! 39QJ1 !
! ! Main/Battery Discrete at Main ! !
! ! ! !
! 3R ! Right Wing Fuel Quantity greater than or equal to ! 15QJ2 !
! ! 1900kg, or at 0kg (tank empty/sensor dry) ! 39QJ2 !
! ! Main/Battery Discrete at Main ! !
! ! ! !
! 4AL ! Left Wing Fuel Quantity greater than or equal to 450kg, ! 38QJ1 !
! ! or at 0kg (tank empty/sensor dry) ! 29QJ1 !
! ! Main/Battery Discrete at Main !41QJ D/Load!
! ! !7QJ Logic 1!
! ! !7QJ Logic 2!
! ! ! !
! 4AR ! Right Wing Fuel Quantity greater than or equal to 450kg,! 38QJ2 !
! ! or at 0kg (tank empty/sensor dry) ! 29QJ2 !
! ! Main/Battery Discrete at Main !42QJ D/Load!
! ! !9QJ Logic 1!
! ! !9QJ Logic 2!
! ! ! !
! 4BL ! Left Wing Fuel Quantity greater than or equal to ! 23QJ1 !
! ! 5000kg, or at 0kg (tank empty/sensor dry) ! 24QJ1 !
! ! Main/Battery Discrete at Main ! !
! ! ! !
! 4BR ! Right Wing Fuel Quantity greater than or equal to ! 23QJ2 !
! ! 5000kg, or at 0kg (tank empty/sensor dry) ! 24QJ2 !
! ! Main/Battery Discrete at Main ! !
! ! ! !
! 4CL ! Left Wing Fuel Quantity less than or equal to 4500kg ! 25QJ1 !
! ! Main/Battery Discrete at Main ! 26QJ1 !
! ! ! 27QJ1 !
! ! ! !
! 4CR ! Right Wing Fuel Quantity less than or equal to 4500kg ! 25QJ2 !
! ! Main/Battery Discrete at Main ! 26QJ2 !
! ! ! 27QJ2 !
! ! ! !
-----------------------------------------------------------------------------

(19) FLSS STATUS
The selection of this option on the master channel will cause a list to be made of any FLSS or Inter Cell Transfer Valve (ICTV) failures detected since power-on. The list is updated by the last automatic FLSS BITE or COMMAND FLSS BITE tests. The last results are shown overwriting any previous test results. The selection of this option on the slave channel will cause the message FLSS NOT AVAILABLE ON THIS CHANNEL to be shown. The option to change to the master channel is also given.

All failure classes are reported.

Each failed LRU is identified by its:
  • description
  • FIN
  • time (GMT/UTC) at which the failure was first detected
  • ATA number.

Where one of the two FLSCUs is reported defective, trouble-shooting data can be accessed by the same procedure as for the LAST LEG REPORT.

FLSS BITE

For the function of the FLSS BITE the sensors are divided into six groups, (see below). Which group or combination of groups is tested is controlled by:
  • the type of test
  • the electrical power conditions
  • the fuel quantity conditions.
-----------------------------------------------------------------------------
! Group ! Description ! Sensors (FINS) ! BITE !
!---------------------------!-------------------------------------------------!
! 1 ! High Levels ! 17QJ1(2), 20QJ, 6QJ ! 1 !
!---------------------------!-------------------------------------------------!
! 2 ! Center low levels ! 21QJ, 22QJ ! 2 !
!-----------------------------------------------------------------------------!
! 3 ! Wing low levels ! 15QJ1(2), 16QJ1(2), 39QJ1(2) ! 2 & 3 !
!-----------------------------------------------------------------------------!
! 4 ! Surges, control ! 28QJ1(2), 27QJ1(2), 25QJ1(2), 26QJ1(2) ! 1 & 4 !
! ! ! 29QJ1(2), 30QJ1(2), LOGIC 1, LOGIC 2 ! !
!-----------------------------------------------------------------------------!
! 5 ! Control ! 38QJ1(2), 24QJ1(2) ! 4 !
!-----------------------------------------------------------------------------!
! 6 ! Control ! 23QJ1(2) ! 4 !
-----------------------------------------------------------------------------

The control sensors include Fulls, Underfulls, Logic Controls and Temperature sensors, all of which are used to control the fuel transfers (intercell).

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).
(20) FLSS STATUS
The selection of the FLSS STATUS gives the results of the last FLSS BITE test. See
F FLSS Status - BITE Test Results (No Failures Detected and FQI CH Fault) ** ON A/C NOT FOR ALL
Each part of the BITE test has three possible results:
  • NO FAULTS
  • FAILED LRU
  • TEST NOT AVAILABLE.
    A list of failed FLSS LRU, including ICTVs (but excluding ACTs), detected during the last power-up FLSS BITE or during a CFDS commanded FLSS BITE, is shown on this page.
    On transition to flight, all class 1 and 2 failures on this page are transferred to the Last Leg Report for permanent storage.
    All class 3 failures are transferred to the class 3 report for permanent storage.
    If FQIC CH1 is not available, the subsequent loss of refreshed FLSS data from FLSCU 1 to the FQIC will result in the CFDS displaying last known FLSCU 1 data.
    If FQIC CH2 is not available, the subsequent loss of refreshed FLSS data fromFLSCU 2 and FLSCU 3 to the FQIC will result in the CFDS displaying last known FLSCU 2 and FLSCU 3 data.
    Where FLSCU 1,2 or 3 has been detected as failed, coded troubleshooting data (stored in non-volatile RAM) may be accessed by pressing the line function key to the right of the ATA number of the LRU for the applicable sensors.
Selection of the NEXT PAGE will cause a list of defective FLSS LRUs to be shown. See
F FLSS Status - Failures Detected ** ON A/C NOT FOR ALL

All FLSS LRUs failure classes are reported.

Each failed LRU is identified by its:
  • Description
  • FIN
  • Time (GMT/UTC at which the failure was first detected)
  • ATA number
  • Identification as to which FQIC channel (1 or 2) issued the failure message.
    FLSS BITE

    For the function of the FLSS BITE the sensors are divided into six groups, (see below). Which group or combination of groups is tested is controlled by:
  • The type of test
  • The electrical power conditions
  • The fuel quantity conditions.
-----------------------------------------------------------------------------
! Group ! Description ! Sensors (FINS) ! BITE !
!---------------------------!-------------------------------------------------!
! 1 ! High Levels ! 17QJ1(2), 20QJ, 6QJ ! 1 !
!---------------------------!-------------------------------------------------!
! 2 ! Center low levels ! 21QJ, 22QJ ! 2 !
!-----------------------------------------------------------------------------!
! 3 ! Wing low levels ! 15QJ1(2), 16QJ1(2), 39QJ1(2) ! 2 & 3 !
!-----------------------------------------------------------------------------!
! 4 ! Surges, control ! 28QJ1(2), 27QJ1(2), 25QJ1(2), 26QJ1(2) ! 1 & 4 !
! ! ! 29QJ1(2), 30QJ1(2), LOGIC 1, LOGIC 2 ! !
!-----------------------------------------------------------------------------!
! 5 ! Control ! 38QJ1(2), 24QJ1(2) ! 4 !
!-----------------------------------------------------------------------------!
! 6 ! Control ! 23QJ1(2) ! 4 !
-----------------------------------------------------------------------------

The control sensors include Fulls, Underfulls, Logic Controls and Temperature sensors, all of which are used to control the fuel transfers (intercell).

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).
(21) 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
F CFDS(FUEL) - INPUT PARAMETERS, Page 1 (FQIS INPUT PARAMETERS) ** ON A/C NOT FOR ALL
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 !
! ! ! ! capacitance) !
! ! ! ! !
!--------------!--------------------!--------------------!--------------------!
! Cadensicon ! Cadensicon covered ! Cadensicon not ! Cadensicon density !
! density (D) ! and density range ! covered or density ! not available (due !
! ! check not failed ! range check failed ! to a failure of a !
! ! ! ! FQIC circuit) !
! ! ! ! !
!--------------!--------------------!--------------------!--------------------!
! CIC ! CIC covered and ! CIC not covered or ! Kt not available !
! permittivity ! Kt range check ! Kt range check ! (due to a failure !
! (Kt) ! not failed ! failed ! of a FQIC circuit !
! ! ! ! or the CIC !
! ! ! ! capacitance) !
! ! ! ! !
!--------------!--------------------!--------------------!--------------------!
! Temperature ! Diode Mode data ! Diode Mode data ! Diode Mode data !
! ! available and ! available and ! not available (due !
! ! Temperature check ! Temperature check ! to a failure of a !
! ! not failed ! failed ! FQIC circuit or a !
! ! ! ! probe diode) !
! ! ! ! !
!--------------!--------------------!--------------------!--------------------!
! Effective ! Value from ADIRS ! Probe value F ! (ADIRS is not !
! Attitude ! A if available ! with asterisk if ! available or !
! ! and not failed, ! (ADIRS is not ! failed) and probe !
! ! or ! available or ! data is not !
! ! Value from probes ! failed) and (probe ! available !
! ! F if (ADIRS is not ! data is available ! !
! ! available or ! but out of range) ! !
! ! failed) and (probe ! ! !
! ! data is available ! ! !
! ! and good) ! ! !
! ! ! ! !
!--------------!--------------------!--------------------!--------------------!
! Probe ! Probe available and! Probe available and! Probe not available!
! Capacitance ! capacitance range ! capacitance range ! (due to a failure !
! ! check not failed ! check failed ! of a FQIC circuit) !
! ! ! ! !
-----------------------------------------------------------------------------

If the aircraft does not have a center tank, the related data on the CFDS will not be shown.

(b) INPUT PARAMETERS, Page 2 - FQIS PROBE CAPACITANCES
F CFDS(FUEL) - INPUT PARAMETERS, Page 2 (FQIS PROBE CAPACITANCES) ** ON A/C NOT FOR ALL
This page gives the values (in picofarads) for all the capacitance devices in the tanks. That is for:
  • the probes
  • the CICs
  • the cadensicons K cell.

From the example of this page, the values can be read across to the applicable devices cross reference to obtain the tank and probe/sensor number.

In the example, left probe No. 10 is é42.9è pF, and the center tank probe No. 4 is <82.1> pF.

The probe numbers can be related to FINs by reference to Table 301.

If an out of range input parameter is detected, the applicable value will be shown with the decimal point (or the C in the case of temperature),replaced by an asterisk (*).
If a parameter is not available (eg. due to a FQIC failure) the applicable value will be replaced by Xs.
NOTE: See INPUT PARAMETERS Page 1 for a full description of the types of failure as above.
Nominal values are given in the Figure reference.
Reference to the FQIS STATUS will show which device and/or wiring to do trouble-shooting.

If the aircraft does not have a center tank, the related data on the CFDS will not be shown.
---------------------------------------------------
! FIN ! FUNCTIONAL DESIGNATION !
!---------!-----------------------------------------!
! 19QT1 ! SENSOR-CADENSICON L INNER CELL !
! 19QT2 ! SENSOR-CADENSICON R INNER CELL !
! 20QT ! SENSOR-CADENSICON CTR TANK !
! 21QT1 ! PROBE-FUEL QTY, L INNER CELL No. 1 !
! 21QT2 ! PROBE-FUEL QTY, R INNER CELL No. 1 !
! 22QT1 ! PROBE-FUEL QTY, L INNER CELL No. 2 !
! 22QT2 ! PROBE-FUEL QTY, R INNER CELL No. 2 !
! 23QT1 ! PROBE-FUEL QTY, L INNER CELL No. 3 !
! 23QT2 ! PROBE-FUEL QTY, R INNER CELL No. 3 !
! 24QT1 ! PROBE-COMPENSATOR, L INNER CELL No. 4 !
! 24QT2 ! PROBE-COMPENSATOR, R INNER CELL No. 4 !
! 25QT1 ! PROBE-FUEL QTY, L INNER CELL No. 5 !
! 25QT2 ! PROBE-FUEL QTY, R INNER CELL No. 5 !
! 26QT1 ! PROBE-FUEL QTY, L INNER CELL No. 6 !
! 26QT2 ! PROBE-FUEL QTY, R INNER CELL No. 6 !
! 27QT1 ! PROBE-FUEL QTY, L INNER CELL No. 7 !
! 27QT2 ! PROBE-FUEL QTY, R INNER CELL No. 7 !
! 28QT1 ! PROBE-FUEL QTY, L INNER CELL No. 8 !
! 28QT2 ! PROBE-FUEL QTY, R INNER CELL No. 8 !
! 29QT1 ! PROBE-FUEL QTY, L INNER CELL No. 9 !
! 29QT2 ! PROBE-FUEL QTY, R INNER CELL No. 9 !
! 30QT1 ! PROBE-FUEL QTY, L INNER CELL No. 10 !
! 30QT2 ! PROBE-FUEL QTY, R INNER CELL No. 10 !
! 31QT1 ! PROBE-FUEL QTY, L INNER CELL No. 11 !
! 31QT2 ! PROBE-FUEL QTY, R INNER CELL No. 11 !
! 32QT1 ! PROBE-FUEL QTY, L INNER CELL No. 12 !
! 32QT2 ! PROBE-FUEL QTY, R INNER CELL No. 12 !
! 33QT1 ! PROBE-FUEL QTY, L OUTER CELL No. 13 !
! 33QT2 ! PROBE-FUEL QTY, R OUTER CELL No. 13 !
! 34QT1 ! PROBE-FUEL QTY, L OUTER CELL No. 14 !
! 34QT2 ! PROBE-FUEL QTY, R OUTER CELL No. 14 !
! 35QT ! PROBE-FUEL QTY, CTR TANK No. 1 !
! 36QT ! PROBE-FUEL QTY, CTR TANK No. 2 !
! 37QT ! PROBE-FUEL QTY, CTR TANK No. 3 !
! 38QT ! PROBE-FUEL QTY, CTR TANK No. 4 !
! 39QT ! PROBE-FUEL QTY, CTR TANK No. 5 !
---------------------------------------------------

(c) INPUT PARAMETERS, Page 3 - FQIS DISCRETE INPUTS
F CFDS(FUEL) - INPUT PARAMETERS, Page 3 (FQIS DISCRETE INPUTS) ** ON A/C NOT FOR ALL
This page shows the states of all the discrete inputs to the FQIC. This includes the FLSS, the Refuel System, and ICTV inputs that are monitored by the FQIC.
NOTE: The date, time, and aircraft tail number are now included on the third line of this page.
The DISCRETE INPUTS can be interpreted by reference to Table 302.
NOTE: A 1 shows the active state.
In the example given, the bit location R3 is a 0 and shows the Refuel Door is not open. The bit location B4 is a 1 and shows that the Left FWD Intercell Transfer Valve is shut.

Table 302 - FQIS DISCRETE INPUTS Bit Position Cross Reference
---------------------------------------------------------------------
! BIT ! BIT INDICATION ! FQIC PIN !
! POSITION ! (ACTIVE STATE) ! ALLOCATION !
!--------------!--------------------------------------!---------------!
! A1 ! NOT USED ! !
! B1 ! EEPROM READY DISCRETE LINE ! INTERNAL !
! C1 ! NOT USED ! !
! D1 ! OWN FAIL RETURN ! INTERNAL !
! E1 ! NOT USED ! !
! F1 ! NOT USED ! !
! G1 ! NOT USED ! !
! H1 ! OTHER FAIL ! INTERNAL !
! J1 ! LOGIC 1 (IDG) FLSCU2 9QJ OPEN ! B-14J !
! K1 ! BITE 4 LANE 2 RETURN ! INTERNAL !
! L1 ! LS7 FLSCU2 6QJ DRY ! B-12H !
! M1 ! LS10 FLSCU1 38QJ1 WET ! B-3K !
! N1 ! LS15 FLSCU1 26QJ1 WET ! B-5H !
! P1 ! NOT USED ! !
! Q1 ! DELATCH LANE B RETURN ! INTERNAL !
! R1 ! BATTERY POWER ! B-6D !
! A2 ! ARINC OUTPUT READY 1 ! INTERNAL !
! B2 ! ARINC OUTPUT READY 2 ! INTERNAL !
! C2 ! ARINC OUTPUT READY 3 ! INTERNAL !
! D2 ! OTHER LANE 5 V PRESENT ! INTERNAL !
! E2 ! ARINC INPUT READY 1 ! INTERNAL !
! F2 ! ARINC INPUT READY 2 ! INTERNAL !
! G2 ! ARINC INPUT READY 3 ! INTERNAL !
! H2 ! NOT USED ! !
! J2 ! T1 FLSCU2 29QJ2 HIGH ! B-15J !
! K2 ! BITE 3 LANE 2 RETURN ! INTERNAL !
! L2 ! LS12 FLSCU2 27QJ2 WET ! B-13H !
! M2 ! LS14 FLSCU1 25QJ1 WET ! B-4K !
! N2 ! FLSCU1 SENSOR FAILURE ! B-6H !
! P2 ! NOT USED ! !
! Q2 ! DELATCH LANE B RETURN ! INTERNAL !
! R2 ! COCKPIT PRESELECTOR TX FAULT/ ! !
! ! NOT POWERED ! B-12G !
! A3 ! ARINC MULTIPLEXOR 1 ! INTERNAL !
! B3 ! ARINC MULTIPLEXOR 2 ! INTERNAL !
! C3 ! ARINC MULTIPLEXOR 3 ! INTERNAL !
! D3 ! NOT USED ! !
! E3 ! NOT USED ! !
! F3 ! 15 V FAULT ! INTERNAL !
! G3 ! NOT USED ! !
! H3 ! NOT USED ! !
! J3 ! LS3 FLSCU2 17QJ2 DRY ! B-11H !
! K3 ! BITE 2 LANE 2 RETURN ! INTERNAL !
! L3 ! LS15 FLSCU2 26QJ2 WET ! B-14H !
! M3 ! T2 FLSCU1 30QJ1 HIGH ! B-5K !
! N3 ! LS3 FLSCU1 17QJ1 DRY ! B-6G !
! P3 ! LS1 FLSCU1 16QJ1 WET ! B-2J !
! Q3 ! CROSSFEED VALVE FAULT ! B-2G !
! R3 ! REFUEL DOOR OPEN ! B-7D !
! A4 ! LEFT FWD ICT VALVE OPEN ! B-5E !
! B4 ! LEFT FWD ICT VALVE SHUT ! B-6E !
! C4 ! RIGHT FWD ICT VALVE OPEN ! B-7E !
! D4 ! RIGHT FED ICT VALVE SHUT ! B-8E !
! E4 ! LEFT REAR ICT VALVE OPEN ! B-11B !
! F4 ! LEFT REAR ICT VALVE SHUT ! B-12B !
! G4 ! RIGHT REAR ICT VALVE OPEN ! B-13B !
! H4 ! RIGHT REAR ICT VALVE SHUT ! B-14B !
! J4 ! LS6 FLSCU2 22QJ/36QJ DRY ! B-11K !
! K4 ! BITE 1 LANE 2 RETURN ! INTERNAL !
! L4 ! FLSCU2 SENSOR FAILURE ! B-15H !
! M4 ! LOGIC2(CTR TK PUMP 1) FLSCU1 7QJ OFF! B-6K !
! N4 ! LS7 FLSCU1 20QJ/37QJ DRY ! B-7G !
! P4 ! LS5 FLSCU1 16QJ2 WET ! B-5G !
! Q4 ! COCKPIT REFUEL SELECTED ! B-8G !
! R4 ! AIRCRAFT ON GROUND ! B-8D !
! A5 ! RIGHT REFUEL VALVE RETURN ! INTERNAL !
! B5 ! LEFT REFUEL VALVE RETURN ! INTERNAL !
! C5 ! CENTER REFUEL VALVE RETUTN ! INTERNAL !
! D5 ! NOT USED ! !
! E5 ! NOT USED ! !
! F5 ! NOT USED ! !
! G5 ! NOT USED ! !
! H5 ! NOT USED ! !
! J5 ! LS11 FLSCU2 23QJ2 WET ! B-12K !
! K5 ! BITE 4 LANE 2 RETURN ! INTERNAL !
! L5 ! LS2 FLSCU2 (39QJ1) WET ! B-10J !
! M5 ! NOT USED ! !
! N5 ! LS13 FLSCU1 24QJ1 WET ! B-4J !
! P5 ! LS11 FLSCU1 23QJ WET ! B-3J !
! Q5 ! COCKPIT PRESELECTOR DECREMENT ! B-11G !
! R5 ! REFUEL PRESELECTOR TX FAULT/NOT ! !
! ! POWERED ! B-10D !
! A6 ! NOT USED ! !
! B6 ! REFUEL SELECTED ! B-6C !
! C6 ! DEFUEL SELECTED ! B-7C !
! D6 ! NOT USED ! !
! E6 ! NOT USED ! !
! F6 ! NOT USED ! !
! G6 ! NOT USED ! !
! H6 ! NOT USED ! !
! J6 ! LS14 FLSCU2 25QJ2 WET ! B-13K !
! K6 ! BITE 3 LANE 1 RETURN ! INTERNAL !
! L6 ! LS5 FLSCU2 15QJ1 WET ! B-11J !
! M6 ! NOT USED ! !
! N6 ! T1 FLSCU1 29QJ1 HIGH ! B-5J !
! P6 ! LS2 FLSCU1 (39QJ2) WET ! B-4G !
! Q6 ! COCKPIT PRESELECTOR INCREMENT ! B-9G !
! R6 ! INDICATOR TX FAULT/NOT POWERED ! B-11D !
! A7 ! 4th TANK FITTED ! B-10C !
! B7 ! CENTER TANK FITTED ! B-12C !
! C7 ! LW RIBS 5-6 ONLY DRY BAYS ! B-15C !
! D7 ! LW 7 RW RIBS 5-6, 6-6B DRY BAYS ! B-13C !
! E7 ! NOT USED ! !
! F7 ! 72 TONNE ! B-15D !
! G7 ! CPU IS LANE A (1) ! INTERNAL !
! H7 ! SHORT INTERRUPT FROM PSU ! INTERNAL !
! J7 ! LOGIC2(CTR TK PUMP 2) FLSCU2 9QJ OFF! B-14K !
! K7 ! BITE 2 LANE 1 RETURN ! INTERNAL !
! L7 ! LS10 FLSCU2 38QJ2 WET ! B-12J !
! M7 ! LS1 FLSCU2 15QJ2 WET ! B-9K !
! N7 ! LOGIC1 (IDG) FLSCU1 7QJ OPEN ! B-6J !
! P7 ! LS6 FLSCU1 21QJ/35QJ DRY ! B-3H !
! Q7 ! REFUEL PRESELECTOR DECREMENT ! B-4E !
! R7 ! REFUEL BUS POWERED ! B-9D !
! A8 ! NOT USED ! !
! B8 ! NOT USED ! !
! C8 ! CPU IS LANE A (2) ! INTERNAL !
! D8 ! SERIAL FITTED ! INTERNAL !
! E8 ! RIGHT REFUEL VALVE SUPPLIED ! B-2C !
! F8 ! LEFT REFUEL VALVE SUPPLIED ! B-3C !
! G8 ! CENTER REFUEL VALVE SUPPLIED ! B-4C !
! H8 ! NOT USED ! !
! J8 ! T2 FLSCU2 30QJ2 HIGH ! B-15K !
! K8 ! BITE 1 LANE 1 RETURN ! INTERNAL !
! L8 ! LS13 FLSCU2 24QJ2 WET ! B-13J !
! M8 ! LS4 FLSCU2 28QJ2 DRY ! B-10K !
! N8 ! LS4 FLSCU1 28QJ1 DRY ! B-2K !
! P8 ! LS12 FLSCU1 27QJ1 WET ! B-4K !
! Q8 ! REFUEL PRESELECTOR INCREMENT ! B-2E !
! R8 ! MANUAL HIGH LEVEL TEST ! B-8J !
! ! ! !
---------------------------------------------------------------------

(22) 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.

The INPUT PARAMETER pages (only) are automatically updated, without request from the CFDS, once every 5.5 seconds.
(a) INPUT PARAMETERS, Page 1 - FQIS INPUT PARAMETERS
F CFDS(FUEL) - INPUT PARAMETERS, Page 1 (FQIS INPUT PARAMETERS) ** ON A/C NOT FOR ALL
This page shows:
  • the permittivity from the Ultracomp (center and right tanks)
  • the temperature from the Ultracomp (center and right tanks)
  • the velocity from Ultracomp (center and right tanks)
  • the permittivity one from Dualcomp (left tank)
  • the permittivity two from Dualcomp (left tank)
  • the density calculated for each tank
  • the fuel temperature from Probe 2 temperature sensors
  • the effective pitch
  • the effective roll.

The measured values from the Ultracomp of the fuel permittivity (K), temperature(T), and velocity (V) are shown on this page. These values are used to calculate the density shown which must be the density calculated for that tank.

The measured fuel permittivities from the Dualcomp (A) and (B) respectively, are shown on this page, as is the measured value of fuel temperature from the Probe 2 locations.

The pitch and roll shown is that used by the FQIC for gauging.

There are three methods of obtaining of attitude data, they are:
  • from the longitudinal, lateral, and normal accelerations supplied by ADIRS
  • from the capacitive probe data (FQIS)
  • from default data held by the FQIC/OBRM.

The method used is dependant on the availability of valid input data.
The hierarchy/priority of use is as shown in the above list.

The Input Parameter values will be shown as long as they are measured, (even if out of valid range). A dash is shown if the parameter is not measured (due to a detected circuit failure).
Out-of-range values exceding the display capacity are shown with the display at maximum magnitude and a + or - indicating the direction of the excursion, where applicable.
(b) INPUT PARAMETERS, Page 2 - FQIS PROBE CAPACITANCES
F CFDS(FUEL) - INPUT PARAMETERS, Page 2 (FQIS PROBE CAPACITANCES) ** ON A/C NOT FOR ALL
This page gives the values (in picofarads) for all the capacitance devices in the tanks. That is for:
  • the probes
  • the Dualcomps
  • the Ultracomps.

From the example of this page, the values can be read across to the applicable devices cross reference to obtain the tank and probe/sensor number.

In the example, the left probe No. 10 is 48.0 pF, and the center tank probe No. 4 is 40.1 pF.

The probe numbers can be related to FINs by reference to Table 301A.

The values will be shown as long as they are measured, (even if out of valid range). A dash is shown if the parameter is not measured (due to a detected circuit failure).
Out-of-range values exceding the display capacity are shown with the display at maximum magnitude and a + or - indicating the direction of the excursion, where applicable.

If the aircraft does not have an Additional Center Tank (ACT) installed the related data on the CFDS will not be shown.
-----------------------------------------------------------
! FIN ! FUNCTIONAL DESIGNATION !
!---------!-------------------------------------------------!
! 21QT1 ! PROBE-FUEL QTY No. 1, L WING TANK !
! 21QT2 ! PROBE-FUEL QTY No. 1, R WING TANK !
! 54QT1 ! PROBE-FUEL QTY No. 2, AND TEMP., L WING TANK !
! 54QT2 ! PROBE-FUEL QTY No. 2, AND TEMP., R WING TANK !
! 23QT1 ! PROBE-FUEL QTY No. 3, L WING TANK !
! 23QT2 ! PROBE-FUEL QTY No. 3, R WING TANK !
! 56QT1 ! PROBE-FUEL QTY No. 4, L WING TANK !
! 56QT2 ! PROBE-FUEL QTY No. 4, R WING TANK !
! 25QT1 ! PROBE-FUEL QTY No. 5, L WING TANK !
! 25QT2 ! PROBE-FUEL QTY No. 5, R WING TANK !
! 26QT1 ! PROBE-FUEL QTY No. 6, L WING TANK !
! 26QT2 ! PROBE-FUEL QTY No. 6, R WING TANK !
! 27QT1 ! PROBE-FUEL QTY No. 7, L WING TANK !
! 27QT2 ! PROBE-FUEL QTY No. 7, R WING TANK !
! 28QT1 ! PROBE-FUEL QTY No. 8, L WING TANK !
! 28QT2 ! PROBE-FUEL QTY No. 8, R WING TANK !
! 29QT1 ! PROBE-FUEL QTY No. 9, L WING TANK !
! 29QT2 ! PROBE-FUEL QTY No. 9, R WING TANK !
! 30QT1 ! PROBE-FUEL QTY No. 10, L WING TANK !
! 30QT2 ! PROBE-FUEL QTY No. 10, R WING TANK !
! 59QT1 ! PROBE-FUEL QTY No. 11, L WING TANK !
! 59QT2 ! PROBE-FUEL QTY No. 11, R WING TANK !
! 60QT1 ! PROBE-FUEL QTY No. 12, L WING TANK !
! 60QT2 ! PROBE-FUEL QTY No. 12, R WING TANK !
! 61QT1 ! PROBE-FUEL QTY No. 13, L WING TANK !
! 61QT2 ! PROBE-FUEL QTY No. 13, R WING TANK !
! 34QT1 ! PROBE-FUEL QTY No. 14, L WING TANK !
! 34QT2 ! PROBE-FUEL QTY No. 14, R WING TANK !
! 35QT ! PROBE-FUEL QTY No. 1, CTR TANK !
! 36QT ! PROBE-FUEL QTY No. 2, CTR TANK !
! 37QT ! PROBE-FUEL QTY No. 3, CTR TANK !
! 38QT ! PROBE-FUEL QTY No. 4, CTR TANK !
! 51QT ! PROBE-FUEL QTY No. 5, CTR TANK !
! 50QT ! ULTRACOMP, CTR TANK !
! 52QT ! ULTRACOMP, RIGHT WING TANK !
! 53QT ! DUALCOMP, LEFT WING TANK !
! 65QT1 ! PROBE-FUEL QTY No. 1, ACT 1 !
! 66QT1 ! PROBE-FUEL QTY No. 2, ACT 1 !
-----------------------------------------------------------

(c) INPUT PARAMETERS, Page 3 - FQIS DISCRETE INPUTS
F CFDS(FUEL) - INPUT PARAMETERS, Page 3 (FQIS DISCRETE INPUTS) ** ON A/C NOT FOR ALL
This page shows the states of all the discrete inputs to the FQIC. This includes the FLSS, and Refuel System inputs that are monitored by the FQIC.

The DISCRETE INPUTS can be interpreted by reference to Table 302A.
NOTE: A 1 shows the active state.
In the example given, the bit location H2 is a 0 and shows the Refuel Door is NOT OPEN. The bit location E2 is a 1 and shows that REFUEL is SELECTED.

Table 302A - FQIS DISCRETE INPUTS Bit Position Cross Reference
-----------------------------------------------------------------------------
! BIT ! SIGNAL DESCRIPTION ! STATE 0 ! STATE 1 ! FQIC PIN !
! POSITION ! ! ! ! ALLOCATION !
!----------!----------------------------!------------!-----------!------------!
! ! PROGRAM PINS ! ! ! !
! A1 ! ACT 1 FITTED ! NOT FITTED ! FITTED ! C06D !
! B1 ! SPARE 2 ! NOT SET ! SET ! C06C !
! C1 ! LH & RH RIBS DRY (SPARE) ! NOT SET ! SET ! C06H !
! D1 ! LH RIBS DRY (SPARE) ! NOT SET ! SET ! C06G !
! E1 ! ACT 1 FITTED ! NOT FITTED ! FITTED ! C05F !
! F1 ! ACT 2 FITTED (SPARE) ! NOT FITTED ! FITTED ! C06F !
! G1 ! LB/KG ! KG ! LBS ! C06E !
! H1 ! A321/A320 A ! A320 ! A321 ! C05E !
! J1 ! A321/A320 B (SPARE) ! A320 ! A321 ! C05H !
! K1 ! PROGRAM PIN PARITY ! NOT SET ! SET ! C05G !
! L1 ! NOT USED ! ! ! !
! M1 ! NOT USED ! ! ! !
! N1 ! NOT USED ! ! ! !
! P1 ! NOT USED ! ! ! !
! Q1 ! NOT USED ! ! ! !
! R1 ! NOT USED ! ! ! !
! ! DISCRETE INPUTS ! ! ! !
! A2 ! COCKPIT REFUEL PRIORITY ! OFF ! ON ! C07E !
! B2 ! DEFUEL SELECTED ! NO DEFUEL ! DEFUEL ! C09F !
! C2 ! HIGH LEVEL TEST ! OFF ! ON ! C10G !
! D2 ! REFUEL BUS POWERED ! NO ! YES ! C09E !
! E2 ! REFUEL SELECTED ! NOT SELECT ! SELECTED ! C08E !
! F2 ! CROSSFEED VALVE MONITOR ! OK ! FAIL ! C08F !
! G2 ! SURGE WET W/L- BATT REFUEL ! DRY ! WET ! C07F !
! H2 ! REFUEL PANEL DOOR OPEN ! NOT OPEN ! OPEN ! C08C !
! J2 ! BATTERY/MAIN REFUEL ! MAIN ! BAT ! C08H !
! K2 ! COCKPIT PRESELECTOR FAULT ! OK ! FAIL ! C07C !
! L2 ! REFUEL PANEL PRESEL FAULT ! OK ! FAIL ! C07H !
! M2 ! REFUEL INDICATOR FAULT ! OK ! FAIL ! C07G !
! ! PRESELECTOR INCREMENT AND DECREMENT ! ! !
! N2 ! COCKPIT INCREMENT ! NOT INC ! INC ! C05D !
! P2 ! COCKPIT DECREMENT ! NOT DEC ! DEC ! C05C !
! Q2 ! REFUEL PANEL INCREMENT ! NOT INC ! INC ! C04K !
! R2 ! REFUEL PANEL DECREMENT ! NOT DEC ! DEC ! C04J !
! A3 ! FLSCU1 LS1 L/WING LO LEVEL ! DRY ! WET ! C04D !
! B3 ! FLSCU1 LS2 R/WING LO LEVEL ! DRY ! WET ! C04C !
! C3 ! FLSCU1 LS3 L/WING HI LEVEL ! WET ! DRY ! C04H !
! D3 ! FLSCU1 LS4 L/SURGE HI LEVEL! WET ! DRY ! C04H !
! E3 ! FLSCU1 LS5 R/WING LO LEVEL ! DRY ! WET ! C03B !
! F3 ! FLSCU1 LS6 CENTER LO LEVEL ! WET ! DRY ! C03A !
! G3 ! FLSCU1 LS7 CENTER HI LEVEL ! WET ! DRY ! C01K !
! H3 ! FLSCU1 LS8 L/WING LO LEVEL ! DRY ! WET ! C03J !
! J3 ! FLSCU1 LS10 L/WING LO LEVEL! WET ! DRY ! C03D !
! K3 ! FLSCU1 LS11 L/WING FULL A ! WET ! DRY ! C03C !
! L3 ! FLSCU1 LS12 L/WING FULL B ! WET ! DRY ! C03H !
! M3 ! FLSCU1 LS13 L/W UND/FULL A ! WET ! DRY ! C03G !
! N3 ! FLSCU1 LS14 L/W UND/FULL B ! WET ! DRY ! C02B !
! P3 ! FLSCU1 LS15 L/W UND/FULL C ! WET ! DRY ! C02A !
! Q3 ! NOT USED ! ! ! !
! R3 ! NOT USED ! ! ! !
! A4 ! FLSCU2 LS1 R/WING LO LEVEL ! DRY ! WET ! C02G !
! B4 ! FLSCU2 LS2 L/WING LO LEVEL ! DRY ! WET ! C01B !
! C4 ! FLSCU2 LS3 R/WING HI LEVEL ! WET ! DRY ! C01A !
! D4 ! FLSCU2 LS4 R/SURGE HI LEVEL! WET ! DRY ! C01K !
! E4 ! FLSCU2 LS5 L/WING LO LEVEL ! DRY ! WET ! C01J !
! F4 ! FLSCU2 LS6 CENTER LO LEVEL ! WET ! DRY ! C01D !
! G4 ! FLSCU2 LS7 CENT/HI/LV/DUMMY! WET ! DRY ! C01C !
! H4 ! FLSCU2 LS8 R/WING LO LEVEL ! DRY ! WET ! C01H !
! J4 ! FLSCU2 LS10 R/WING LO LEVEL! WET ! DRY ! C01G !
! K4 ! FLSCU2 LS11 R/WING FULL A ! WET ! DRY ! C02E !
! L4 ! FLSCU2 LS12 R/WING FULL B ! WET ! DRY ! C01E !
! M4 ! FLSCU2 LS13 R/W UND/FULL A ! WET ! DRY ! C01F !
! N4 ! FLSCU2 LS14 R/W UND/FULL B ! WET ! DRY ! C02F !
! P4 ! FLSCU2 LS15 R/W UND/FULL C ! WET ! DRY ! C04F !
! Q4 ! NOT USED ! ! ! !
! R4 ! NOT USED ! ! ! !
! A5 ! FLSCU1 LOG 1 L/IDG COOLING ! SHUT ! OPEN ! C04B !
! B5 ! FLSCU1 LOG 2 C/TK PUMP CONT! ON ! OFF ! C04A !
! C5 ! FLSCU1 SENS FAILURE MONITOR! OK ! FAIL ! C02K !
! D5 ! FLSCU1 T1 LEFT TEMP SENSOR ! <T ! >T ! C02J !
! E5 ! FLSCU1 T2 L/TEMP SEN(DUMMY)! <T ! >T ! C02J !
! F5 ! FLSCU2 LOG 1 R/IDG COOLING ! SHUT ! OPEN ! C02C !
! G5 ! FLSCU2 LOG 2 C/TK PUMP CONT! ON ! OFF ! C02H !
! H5 ! FLSCU2 SENS FAILURE MONITOR! OK ! FAIL ! C03E !
! J5 ! FLSCU2 T1 RIGHT TEMP SENSOR! <T ! >T ! C03F !
! K5 ! FLSCU2 T2 R/TEMP SEN(DUMMY)! <T ! >T ! C04F !
! L5 ! NOT USED ! ! ! !
! M5 ! NOT USED ! ! ! !
! N5 ! NOT USED ! ! ! !
! P5 ! NOT USED ! ! ! !
! Q5 ! NOT USED ! ! ! !
! R5 ! NOT USED ! ! ! !
! A6 ! NOT USED ! ! ! !
! B6 ! NOT USED ! ! ! !
! C6 ! NOT USED ! ! ! !
! D6 ! NOT USED ! ! ! !
! E6 ! NOT USED ! ! ! !
! F6 ! NOT USED ! ! ! !
! G6 ! NOT USED ! ! ! !
! H6 ! NOT USED ! ! ! !
! J6 ! NOT USED ! ! ! !
! K6 ! NOT USED ! ! ! !
! L6 ! NOT USED ! ! ! !
! M6 ! NOT USED ! ! ! !
! N6 ! NOT USED ! ! ! !
! P6 ! NOT USED ! ! ! !
! Q6 ! NOT USED ! ! ! !
! R6 ! NOT USED ! ! ! !
! A7 ! LEFT NORM SELECTED ! NOT NORM ! NORM ! C08D !
! B7 ! CENTER NORM SELECTED ! NOT NORM ! NORM ! C09B !
! C7 ! RIGHT NORM SELECTED ! NOT NORM ! NORM ! C08B !
! D7 ! ACT 1 NORM SELECTED ! NOT NORM ! NORM ! C10B !
! E7 ! ACT 2 NORM SELECTED ! NOT NORM ! NORM ! C09A !
! F7 ! GND/FLT ! FLIGHT ! GROUND ! B05F !
! G7 ! SPATTIAL CONFIG - MOD I/P ! OFF ! ON ! C07D !
! H7 ! NOT USED ! ! ! !
! J7 ! NOT USED ! ! ! !
! K7 ! NOT USED ! ! ! !
! L7 ! NOT USED ! ! ! !
! M7 ! NOT USED ! ! ! !
! N7 ! NOT USED ! ! ! !
! P7 ! NOT USED ! ! ! !
! Q7 ! NOT USED ! ! ! !
! R7 ! NOT USED ! ! ! !
-----------------------------------------------------------------------------

(23) INPUT PARAMETERS
There are four pages of input parameters that supply data.
They are:
  • (a) INPUT PARAMETERS, Page 1 - FQIS INPUT PARAMETERS VALUES MENU
  • (b) INPUT PARAMETERS, Page 2 - FQIS CAPACITANCES DEVICES IN pF
  • (c) INPUT PARAMETERS, Page 3 - FQIS PROBES CAPACITANCES IN pF
  • (d) INPUT PARAMETERS, Page 4 - FQIS DISCRETE INPUTS.

(a) INPUT PARAMETERS, Page 1 - FQIS INPUT PARAMETERS VALUES
F CFDS(FUEL) - INPUT PARAMETERS, page 1 (FQIS INPUT PARAMETERS) ** ON A/C NOT FOR ALL
This page shows:
  • The permittivity to 3 decimal places (Left, Center and Right tanks)
  • Fuel temperatures from Probe 2 temp sensor(s)
  • Fuel temperature from Probe 13 temp sensor(s)
  • The velocity from Ultracomp (center and right tanks)
  • The density calculated for each tank
  • The effective pitch
  • The effective roll.

NOTE: : Probe 2 and 13 incorporates a single channel RTD temperature sensor.

The measured values from the Ultracomp of the fuel permittivity, temperature, and velocity are shown on this page. These values are used to calculate the density shown for each tank.

The measured fuel permittivities from the Dualcomp (A) and (B) respectively, are shown on this page, as is the measured value of fuel temperature from the Probe 2 and 13 locations.

Attitude data is calculated from the longitudinal, lateral, and normal accelerations supplied by ADIRS.
The Input Parameter values will be shown as long as they are measured, (even if out of valid range). A dash is shown if the parameter is not measured (due to a detected circuit failure).
Any Input Parameter values on this page (or page 2) that are failed or not available may be replaced by crosses (X).

(b) INPUT PARAMETERS, Page 2 - FQIS DEVICE CAPACITANCES (Ref. Fig 307A)
F CFDS(FUEL) - INPUT PARAMETERS, Pages 2 and 3 (FQIS PROBE CAPACITANCES) ** ON A/C NOT FOR ALL
This page gives the values (in picofarads) for all the capacitance devices in the wing and center tanks. That is for:
  • The probes
  • The Dualcomps
  • The Ultracomps.

From the example of this page, the values can be read across to the applicable devices cross reference to obtain the tank and probe/sensor number.

The probe numbers can be related to FINs by reference to Figure 301H.

The values will be shown as long as they are measured, (even if out of valid range). A dash is shown if the parameter is not measured (due to a detected circuit failure).
If a parameter is not available (eg. due to a FQIC failure) the applicable value will be replaced by Xs.

------------------------------------------------------------------------------
! Line ! Field 1 ! Field 2 ! Field 3 ! Field 4 !
------------------------------------------------------------------------------
! 3 ! Probe 1 LW ! Probe 2 LW ! Probe 3 LW ! Probe 4 LW !
! 4 ! Probe 5 LW ! Probe 6 LW ! Probe 7 LW ! Probe 8 LW !
! 5 ! Probe 9 LW ! Probe 10 LW ! Probe 11 LW ! Probe 12 LW !
! 6 ! Probe 13 LW ! Probe 14 LW ! DUALCOMP K1 LW ! DUALCOMP K2 LW !
! 7 ! Probe 1 C ! Probe 2 C ! Probe 3 C ! Probe 4 C !
! 8 ! Probe 5 not used ! not used ! ULTRACOMP C !
! 9 ! Probe 1 RW ! Probe 2 RW ! Probe 3 RW ! Probe 4 RW !
! 10 ! Probe 5 RW ! Probe 6 RW ! Probe 7 RW ! Probe 8 RW !
! 11 ! Probe 9 RW ! Probe 10 RW ! Probe 11 RW ! Probe 12 RW !
! 12 ! Probe 13 RW ! Probe 14 RW ! not used ! ULTRACOMP RW !
-----------------------------------------------------------------------------
LW = Left Wing Tank, C = Center Tank, RW = Right Wing Tank

(c) INPUT PARAMETERS, Page 3 - FQIS PROBE CAPACITANCES
F CFDS(FUEL) - INPUT PARAMETERS, Page 4 (FQIS DISCRETE INPUTS) ** ON A/C NOT FOR ALL
This page shows the values in pF for each probe within the ACT's and the fuel quantity in Lbs or Kgs.
The values depend on the aircrafts pin programming of each tank in the order shown in the table below:

Table - FQIS Input Parameters Page 3 - Parameter order
-----------------------------------------------------------------------------
! Line ! Data !
!-----------------------------------------------------------------------------!
! 4 ! Probe 1A1 ! Probe 2A1 ! Probe 1A2 ! Probe 2A2 !
!----------!----------------------------!------------!-----------!------------!
! 8 ! not used ! not used ! Qty T ! not used ! not used !
! 9 ! not used ! Qty LI ! Qty C ! Qty RI ! not used !
! 10 ! Qty LO ! not used ! Qty A1 ! not used ! Qty RO !
! 11 ! not used ! not used ! Qty A2 ! not used ! not used !
-----------------------------------------------------------------------------
LO = Left Outer Tank for
LI = Left Inner Tank
RO = Right Outer Tank
RI = Right Inner Tank
A1= ACT 1 , A2= ACT 2. Blank if ACT not fitted.
L CELL = Left Collector Cell, R CELL = Right Collector Cell
T = Total.

NOTE: Input Parameter Values on Pages 1, 2 or 3 that have failed or not available are replaced by (X) as shown in the table below:

---------------------------------------------------------
! Parameter ! Actual Value ! XX..X !
------------- -------------------------!-----------------
! Dielectric ! Display value computed ! Value not !
! ! for each tank. If ! available !
! ! uncovered the value ! !
! ! will be close to 1 ! !
!-------------------------------------------------------!
! ULTRACOMP,V ! Display velocity of ! Value not !
! ! sound for center and ! available !
! ! right tank as ! !
! ! determined by the ! !
! ! Ultracomp ! !
!-------------------------------------------------------!
! Temperature ! Display signed fuel ! Value not !
! ! temperature. For A319 ! available !
! ! and A320 display Outer ! !
! ! and Inner Temperatures.! !
! ! For A321 display both ! !
! ! Channels for each wing ! !
!-------------------------------------------------------!
! Attitude ! Value from ADIRS + ! Blank Display !
! ! channel number of ! if ADIRS CH 1 !
! ! available data. CH 1 ! and CH 2 are !
! ! preferred ! not available !
!-------------------------------------------------------!
! Probe ! Probe available and ! Probe not !
! Capacitance ! capacitance range ! available !
! ! check not failed ! !
! ! ! !
!-------------------------------------------------------!

(d) INPUT PARAMETERS, Page 4 - FQIS DISCRETE INPUTS (Ref. Table of discrete Inputs). This page shows the states of all the discrete inputs to the FQIC. This includes in a grid of 7 rows (labelled 1 to 7) and 16 columns (labelled A to R), the FLSS, the Refuel system and ICTV inputs that are monitored by the FQIC.
The page is updated at a rate of 5.4s +/- 250mS.

Table 302A - FQIS DISCRETE INPUTS Bit Position Cross Reference
-----------------------------------------------------------------------------
! BIT ! DISCRETE SIGNAL ! STATE 0 ! STATE 1 ! FQIC PIN !
! POSITION ! NAME ! ! ! !
!----------!----------------- !-----------------!-------------!---------------
! A1 ! PPA1Si1 ! ACT1 NOT FITTED ! ACT1 FITTED ! C06D !
!----------!----------------- !-----------------!-------------!--------------!
! B1 ! PPA2Si1 ! ACT2 NOT FITTED ! ACT2 FITTED ! C06C !
!----------!----------------- !-----------------!-------------!---------------
! C1 ! PP1 ! NOT SET ! SET ! C06H !
!----------!----------------- !-----------------!-------------!--------------!
! D1 ! PP2 ! NOT SET ! SET ! C06G !
!----------!----------------- !-----------------!-------------!--------------!
! E1 ! PPA1Si2 ! ACT1 NOT FITTED ! ACT1 FITTED ! C05F !
!----------!----------------- !-----------------!-------------!---------------
! F1 ! PPA2Si2 ! ACT2 NOT FITTED ! ACT2 FITTED ! C06F !
!----------!----------------- !-----------------!-------------!---------------
! G1 ! PPLK ! KG ! LB ! C06E !
!----------!----------------- !-----------------!-------------!--------------!
! H1 ! PP3 ! NOT SET ! SET ! C05E !
!----------!----------------- !-----------------!-------------!--------------!
! J1 ! PP4 ! NOT SET ! SET ! C05H !
!----------!----------------- !-----------------!-------------!--------------!
! K1 ! PP ! NOT SET ! SET ! C05G !
!----------!----------------- !-----------------!-------------!--------------!
! L1 ! FLSCU1 BITE 2 ! INACTIVE ! ACTIVE ! B14E !
!----------!----------------- !-----------------!-------------!--------------!
! M1 ! FLSCU1 BITE 3 ! INACTIVE ! ACTIVE ! B15F !
!----------!----------------- !-----------------!-------------!--------------!
! N1 ! FLSCU1 BITE 4 ! INACTIVE ! ACTIVE ! B15E !
!----------!----------------- !-----------------!-------------!---------------
! P1 ! FLSCU2 BITE 2 ! INACTIVE ! ACTIVE ! B12E !
!----------!----------------- !-----------------!-------------!--------------!
! Q1 ! FLSCU2 BITE 3 ! INACTIVE ! ACTIVE ! B13F !
!----------!----------------- !-----------------!-------------!--------------!
! R1 ! FLSCU2 BITE 4 ! INACTIVE ! ACTIVE ! B13E !
!----------!----------------- !-----------------!-------------!--------------!
! A2 ! CkptPri ! OFF ! ON ! C07E !
!----------!----------------- !-----------------!-------------!--------------!
! B2 ! DefSel ! NOT DEFUEL ! DEFUEL ! C09F !
!----------!----------------- !-----------------!-------------!--------------!
! C2 ! HiLevT ! OFF ! ON ! C10G !
!----------!----------------- !-----------------!-------------!--------------!
! D2 ! ReBusPwr ! NO ! YES ! C09E !
!----------!----------------- !-----------------!-------------!--------------!
! E2 ! ReSel ! NOT SELECTED ! SELECTED ! C08E !
!----------!----------------- !-----------------!-------------!--------------!
! F2 ! CroVMon ! OK ! FAIL ! C08F !
!----------!----------------- !-----------------!-------------!--------------!
! G2 ! Not Used ! - ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! H2 ! RepDoOp ! NOT OPEN ! OPEN ! C08C !
!----------!----------------- !-----------------!-------------!--------------!
! J2 ! Bat / Main ! MAIN ! BATTERY ! C08H !
!----------!----------------- !-----------------!-------------!--------------!
! K2 ! CkptPlft ! OK ! FAIL ! C07C !
!----------!----------------- !-----------------!-------------!--------------!
! L2 ! RePPFlt ! OK ! FAIL ! C07H !
!----------!----------------- !-----------------!-------------!--------------!
! M2 ! RcPlFlt ! OK ! FAIL ! C07G !
!----------!----------------- !-----------------!-------------!--------------!
! N2 ! CkptInc ! NOT INC ! INC ! C05D !
!----------!----------------- !-----------------!-------------!--------------!
! P2 ! CkPtDec ! NOT DEC ! DEC ! C05C !
!----------!----------------- !-----------------!-------------!--------------!
! Q2 ! RePInc ! NOT INC ! INC ! C04K !
!----------!----------------- !-----------------!-------------!--------------!
! R2 ! RePDec ! NOT DEC ! DEC ! C04J !
!----------!----------------- !-----------------!-------------!--------------!
! A3 ! FL1LS1 ! DRY ! WET ! C04D !
!----------!----------------- !-----------------!-------------!--------------!
! B3 ! FL1LS2 ! DRY ! WET ! C04C !
!----------!----------------- !-----------------!-------------!--------------!
! C3 ! FL1LS3 ! WET ! DRY ! C04H !
!----------!----------------- !-----------------!-------------!--------------!
! D3 ! FL1LS4 ! WET ! DRY ! C04H !
!----------!----------------- !-----------------!-------------!--------------!
! E3 ! FL1LS5 ! DRY ! WET ! C03B !
!----------!----------------- !-----------------!-------------!--------------!
! F3 ! FL1LS6 ! WET ! DRY ! C03A !
!----------!----------------- !-----------------!-------------!--------------!
! G3 ! FL1LS7 ! WET ! DRY ! C01K !
!----------!----------------- !-----------------!-------------!--------------!
! H3 ! FL1LS8 ! DRY ! WET ! C03J !
!----------!----------------- !-----------------!-------------!--------------!
! J3 ! FL1LS10 ! WET ! DRY ! C03D !
!----------!----------------- !-----------------!-------------!--------------!
! K3 ! FL1LS11 ! WET ! DRY ! C03C !
!----------!----------------- !-----------------!-------------!--------------!
! L3 ! FL1LS12 ! WET ! DRY ! C03H !
!----------!----------------- !-----------------!-------------!--------------!
! M3 ! FL1LS13 ! WET ! DRY ! C03G !
!----------!----------------- !-----------------!-------------!--------------!
! N3 ! FL1LS14 ! WET ! DRY ! C02B !
!----------!----------------- !-----------------!-------------!--------------!
! P3 ! FL1LS15 ! WET ! DRY ! C02A !
!----------!----------------- !-----------------!-------------!--------------!
! Q3 ! FLSCU 1 BITE 1 ! INACTIVE ! ACTIVE ! B14F !
!----------!----------------- !-----------------!-------------!--------------!
! R3 ! FLSCU 2 BITE 1 ! INACTIVE ! ACTIVE ! B12F !
!----------!----------------- !-----------------!-------------!--------------!
! A4 ! FL2LS1 ! DRY ! WET ! C02G !
!----------!----------------- !-----------------!-------------!--------------!
! B4 ! FL2LS2 ! DRY ! WET ! C01B !
!----------!----------------- !-----------------!-------------!--------------!
! C4 ! FL2LS3 ! WET ! DRY ! C01A !
!----------!----------------- !-----------------!-------------!--------------!
! D4 ! FL2LS4 ! WET ! DRY ! C01K !
!----------!----------------- !-----------------!-------------!--------------!
! E4 ! FL2LS5 ! DRY ! WET ! C01J !
!----------!----------------- !-----------------!-------------!--------------!
! F4 ! FL2LS6 ! WET ! DRY ! C01D !
!----------!----------------- !-----------------!-------------!--------------!
! G4 ! FL2LS7 ! WET ! DRY ! C01C !
!----------!----------------- !-----------------!-------------!--------------!
! H4 ! FL2LS8 ! DRY ! WET ! C01H !
!----------!----------------- !-----------------!-------------!--------------!
! J4 ! FL2LS10 ! WET ! DRY ! C01G !
!----------!----------------- !-----------------!-------------!--------------!
! K4 ! FL2LS11 ! WET ! DRY ! C02E !
!----------!----------------- !-----------------!-------------!--------------!
! L4 ! FL2LS12 ! WET ! DRY ! C01E !
!----------!----------------- !-----------------!-------------!--------------!
! M4 ! FL2LS13 ! WET ! DRY ! C01F !
!----------!----------------- !-----------------!-------------!--------------!
! N4 ! FL2LS14 ! WET ! DRY ! C02F !
!----------!----------------- !-----------------!-------------!--------------!
! P4 ! FL2LS15 ! WET ! DRY ! C04F !
!----------!----------------- !-----------------!-------------!--------------!
! Q4 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! R4 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! A5 ! FL1Lo1 ! SHUT ! OPEN ! C04B !
!----------!----------------- !-----------------!-------------!--------------!
! B5 ! FL1Lo2 ! ON ! OFF ! C04A !
!----------!----------------- !-----------------!-------------!--------------!
! C5 ! FL1SFM ! OK ! FAIL ! CO2K !
!----------!----------------- !-----------------!-------------!--------------!
! D5 ! FL1T1 ! <T ! >T ! C02J !
!----------!----------------- !-----------------!-------------!--------------!
! E5 ! FL1T2 ! <T ! >T ! C02J !
!----------!----------------- !-----------------!-------------!--------------!
! F5 ! FL2Lo1 ! SHUT ! OPEN ! C02C !
!----------!----------------- !-----------------!-------------!--------------!
! G5 ! FL2Lo2 ! ON ! OFF ! C02H !
!----------!----------------- !-----------------!-------------!--------------!
! H5 ! FL2SFM ! OK ! FAIL ! C03E !
!----------!----------------- !-----------------!-------------!--------------!
! J5 ! FL2T1 ! <T ! >T ! C03F !
!----------!----------------- !-----------------!-------------!--------------!
! K5 ! FL2T2 ! <T ! >T ! C04F !
!----------!----------------- !-----------------!-------------!--------------!
! L5 ! FL3LS1 ! DRY ! WET ! C10D !
!----------!----------------- !-----------------!-------------!--------------!
! M5 ! FL3LS2 ! DRY ! WET ! C10C !
!----------!----------------- !-----------------!-------------!--------------!
! N5 ! FL3LS3 ! WET ! DRY ! C10H !
!----------!----------------- !-----------------!-------------!--------------!
! P5 ! FL3LS5 ! DRY ! WET ! C09G !
!----------!----------------- !-----------------!-------------!--------------!
! Q5 ! FL3LS7 ! WET ! DRY ! C09H !
!----------!----------------- !-----------------!-------------!--------------!
! R5 ! FL3LS8 ! DRY ! WET ! C08D !
!----------!----------------- !-----------------!-------------!--------------!
! R6 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! A6 ! FQI CH1 !Left Refuel Valve!Left Refuel ! - !
! ! ! Command OFF !Valve Command! !
! ! ! ! ON ! !
!----------!----------------- !-----------------!-------------!--------------!
! B6 ! FQI CH1 ! Centre Refuel !Centre Refuel! - !
! ! ! Valve Command ! Valve ! !
! ! ! OFF ! Command ON ! !
!----------!----------------- !-----------------!-------------!--------------!
! C6 ! FQI CH1 ! Right Refuel !Right Refuel ! - !
! ! ! Valve Command !Valve Command! !
! ! ! OFF ! ON ! !
!----------!----------------- !-----------------!-------------!--------------!
! D6 ! FQI CH2 !ACT1 Refuel Valve!ACT1 Refuel ! - !
! ! ! Command OFF !Valve Command! !
! ! ! ! ON ! !
!----------!----------------- !-----------------!-------------!--------------!
! E6 ! FQI CH2 !ACT2 Refuel Valve!Left Refuel ! - !
! ! ! Command OFF !Valve Command! !
! ! ! ! ON ! !
!----------!----------------- !-----------------!-------------!--------------!
! F6 ! Not Used ! - ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! G6 ! LFTV OPFB !Left Forward ICTV!Left Forward ! B07C !
! ! ! Not Open !ICTV Open ! !
!----------!----------------- !-----------------!-------------!--------------!
! H6 ! LFTV SHFB !Left Forward ICTV!Left Forward ! B06C !
! ! ! Not Shut ! ICTV Shut ! !
!----------!----------------- !-----------------!-------------!--------------!
! J6 ! RFTV OPFB !Right Forward !Right Forward! B09C !
! ! !ICTV Not Used !ICTV Open ! !
!----------!----------------- !-----------------!-------------!--------------!
! K6 ! RFTV SHFB !Right Forward !Right Forward! B08C !
! ! !ICTV Not Shut !ICTV Shut ! !
!----------!----------------- !-----------------!-------------!--------------!
! L6 ! LAFTV OPFB !Left Aft ICTV Not!Left Aft ICTV! B07B !
! ! ! Used ! Open ! !
!----------!----------------- !-----------------!-------------!--------------!
! M6 ! LATV SHFB !Left AFt ICTV Not!Left AFt ICTV! B06B !
! ! ! Shut ! Shut ! !
!----------!----------------- !-----------------!-------------!--------------!
! N6 ! RATV OPFB ! Right Aft ICTV !Right Aft ! B09B !
! ! ! Not Open ! ICTV Open ! !
!----------!----------------- !-----------------!-------------!--------------!
! Q6 ! FICTVR ! FWD Delatch !FWD Delatch ! B11C !
! ! ! Inactive ! Active ! !
!----------!----------------- !-----------------!-------------!--------------!
! R6 ! AICTVR ! AFT Delatch !FWD Delatch ! B11B !
! ! ! Inactive ! Active ! !
!----------!----------------- !-----------------!-------------!--------------!
! A7 ! LNORM ! NOT NORMAL ! NORMAL ! C08D !
!----------!----------------- !-----------------!-------------!--------------!
! B7 ! ctrNORM ! NOT NORMAL ! NORMAL ! C09B !
!----------!----------------- !-----------------!-------------!--------------!
! C7 ! RNORM ! NOT NORMAL ! NORMAL ! C08B !
!----------!----------------- !-----------------!-------------!--------------!
! D7 ! A1NORM ! NOT NORMAL ! NORMAL ! C10B !
!----------!----------------- !-----------------!-------------!--------------!
! E7 ! A2NORM ! NOT NORMAL ! NORMAL ! C09A !
!----------!----------------- !-----------------!-------------!--------------!
! F7 ! GND/FLT ! FLIGHT ! GROUND ! B05F !
!----------!----------------- !-----------------!-------------!--------------!
! G7 ! - ! CH1 Fault ! No Fault ! - !
!----------!----------------- !-----------------!-------------!--------------!
! H7 ! - ! CH2 Fault ! No Fault ! - !
!----------!----------------- !-----------------!-------------!--------------!
! J7 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! K7 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! L7 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! M7 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! N7 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! P7 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! Q7 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!
! R7 ! - ! Not Used ! - ! - !
!----------!----------------- !-----------------!-------------!--------------!

(24) COMMAND FLSS BITE
The FLSS BITE COMMAND from the MCDU (CFDS) tests sensors in all the satisfied groups at the same time. This is done in a shorter (5 second) sequence. The Intercell Transfer Valves (ICTVs) are not tested by this test. They are tested once only after the power-up FLSS BITE.
The FLSS STATUS page is shown 5 seconds after the COMMAND FLSS BITE option request is made. The FLSS STATUS page will show the new results overwriting any previous results from either an Automatic power-up FLSS BITE test or the CFDS commaned FLSS BITE test.
During the 5 second delay the page will show IN PROGRESS if the COMMAND FLSS BITE has started.
If some of the conditions listed above are not correct the page will show FLSS TEST NOT AVAILABLE with some indication of the cause, for example REFUEL IN PROGRESS.
The selection of the COMMAND FLSS BITE on the Slave Channel will cause the message FLSS TEST NOT AVAILABLE ON THIS CHANNEL to be shown. The option to change to the master channel directly is also given.
The use of the COMMAND FLSS BITE option requests the FQIC to start the COMMAND FLSS BITE. The COMMAND FLSS BITE will start if:
  • the master channel is selected on the CFDS
  • a request for this BITE is received by the FQIC from the CFDS
  • the main power is on
  • the main power has been on for at least 22 seconds
  • the landing gear is down
  • the Flight Phase is 1 (aircraft on the ground)
  • a manual high level test is not in progress
  • the FQIC Grade is 1, 2 or 3
  • the automatic power-on FLSS BITE test is not in progress
  • a refuel is not in progress.
NOTE: The center tank sensors 21QJ and 22QJ are only BITE tested if the center tank fuel quantity is greater than 650kg (1430lb).
NOTE: If a center tank is not installed the BITE test is done with Dummy sensors 35QJ and 36QJ.
NOTE: If a center tank is not installed the sensors:
  • 23QJ1(2)
  • 24QJ1(2)
  • 25QJ1(2)
  • 26QJ1(2)
  • 27QJ1(2) and Logic 2 are not FLSS BITE tested.
(25) COMMAND FLSS BITE
The use of the COMMAND FLSS BITE option causes the initiation of the FLSS BITE tests as decribed in the FLSS STATUS menu option, (see Para 2.A.(7) ).

While the tests are in progress the display/page will show:
  • FLSS BITE - RESULTS AVAILABLE WITHIN 150S

The FLSS BITE tests will continue and not be aborted if the RETURN option (to the main menu page is selected).
When the tests finsh the results are stored and are available by access to the FLSS STATUS page.

When the tests finsh normally the results will be reported directly on the FLSS STATUS page.
(26) COMMAND FLSS BITE
The FLSS BITE COMMAND from the MCDU (CFDS) tests sensors in all BITE groups in sequence. The minimum time for the test is 180 seconds. The Intercell Transfer Valves (ICTVs) are not tested by this test. They are tested once only after the power-up FLSS BITE.
The FLSS STATUS page is shown 5 seconds after the COMMAND FLSS BITE option request is made. The FLSS STATUS page will show the new results overwriting any previous results from either an Automatic power-up FLSS BITE test or the CFDS commanded FLSS BITE test.
During the 5 second delay the page will show IN PROGRESS if the COMMAND FLSS BITE has started.
The FLSS STATUS page will show FLSS TEST NOT AVAILABLE if not available with some indication of the cause, for example REFUEL IN PROGRESS.
The use of the COMMAND FLSS BITE option requests the FQIC to start the COMMAND FLSS BITE. The COMMAND FLSS BITE will start if:
  • A request for this BITE is received by the FQIC from the CFDS
  • The main power is on
  • The main power has been on for at least 22 seconds
  • The landing gear is down
  • The Flight Phase is 1 (aircraft on the ground)
  • A manual high level test is not in progress
  • The FQIC Grade is 1, 2 or 3
  • The automatic power-on FLSS BITE test is not in progress.
B. Trouble-shooting Data
(1) The above data can now be found in the Aircraft Maintenance Manual (Ref. AMM 28420074000900).
NOTE: The data has effectively moved for the reasons that follow:

  • errors can occur when the same data is to be given in two different manuals (the AMM and the TSM)

  • the AMM tasks numbering system enables the page block 201 TSM text to be hyperlinked (jump or link) to a specfic AMM task (AirNav)

  • in the TSM it is only possible to hyperlink to the start of the page block 301 using the 'Supporting data' button (AirNav) or the 'Page 301' bookmark button (PDF).
(2) The above data can now be found in the Aircraft Maintenance Manual (Ref. AMM 28420074000700).
NOTE: The data has effectively moved for the reasons that follow:

  • errors can occur when the same data is to be given in two different manuals (the AMM and the TSM)

  • the AMM tasks numbering system enables the page block 201 TSM text to be hyperlinked (jump or link) to a specfic AMM task (AirN#agrave#v)

  • in the TSM it is only possible to hyperlink to the start of the page block 301 using the 'Supporting data' button (AirN#agrave#v) or the 'Page 301' bookmark button (PDF).
(3) The above data can now be found in the Aircraft Maintenance Manual (Ref. AMM 28420074000900).
NOTE: The data has effectively moved for the reasons that follow:

  • Errors can occur when the same data is to be given in two different manuals (the AMM and the TSM)

  • The AMM tasks numbering system enables the page block 201 TSM text to be hyperlinked (jump or link) to a specfic AMM task (AirN#agrave#v)

  • In the TSM it is only possible to hyperlink to the start of the page block 301 using the 'Supporting data' button (AirN#agrave#v) or the 'Page 301' bookmark button (PDF).
** ON A/C NOT FOR ALL
2. Tank Units DC Capacitance Values
(Smiths FQIS)

The DC capacitance values in Table 304 below have been included to enable the
NOTE: If the probe was submerged in fuel immediately before the value is checked it will be 0.36% larger than the MEAN THEORETICAL VALUE (MTV) shown. After one hour the value will decrease to 0.15% larger than the MTV. This later value will stay constant for approximately sixty hours in a sealed empty tank.
This NOTE is not applicable to the cadensicons.
NOTE: The values shown for fuel probes with a full cell/tank are given as an aid only. These values will change with:
  • the permittivity of the fuel in the cell/tank
  • the proportion of the probe in fuel after the refuel valve has closed.
NOTE: The values for a cadensicon with a full cell/tank should be within the values shown. The values take into account the expected variations in the fuel permittivity.
NOTE: The probes identified with an asterisk (*) are not used on two tank aircraft.

NOTE: A tolerance of + or - 0.03pF plus the tolerance of the DC Capacitance Tester is recommened. This is over and above the values shown in the table below. This gives an allowance for non-laboratory conditions, different operators, and the accuracy of the Test Set used.
NOTE: When measuring the probes 24QT1(2) and 39QT (the probes with a CIC), the CIC Signal Line or the Probe Signal Line, whichever is NOT being measured, must be linked to the Return Line of the respective group.
Table 304 - Tank Units DC Capacitance Values
-------------------------------------------------------------------------
! ! ! MEAN ! TOLERANCE ! FULL TANK !
! FIN ! PROBE ! THEORETICAL ! AT DRY pF ! pF !
! ! FUNCTIONAL DESIGNATION ! pF DRY ! + OR - ! !
!----------!------------------------!-------------!-----------!-----------!
! 21QT1(2) ! PROBE-FUEL QTY, L/R ! 70.29 ! 0.70 ! 146.84 !
! ! INNER CELL No. 1 ! ! ! !
! ! ! ! ! !
! 22QT1(2) ! PROBE-FUEL QTY, L/R ! 68,86 ! 0.70 ! 143.85 !
! ! INNER CELL No. 2 ! ! ! !
! ! ! ! ! !
! 23QT1(2) ! PROBE-FUEL QTY, L/R ! 57.93 ! 0.58 ! 121.00 !
! ! INNER CELL No. 3 ! ! ! !
! ! ! ! ! !
! 24QT1(2) ! PROBE-FUEL QTY, and ! 31.36 ! 0.32 ! 65.39 !
! ! PROBE-COMPENSATOR L/R ! 13.68 ! 0.15 ! 28.33 !
! ! INNER CELL No. 4 ! ! ! !
! ! ! ! ! !
! 25QT1(2) ! PROBE-FUEL QTY, L/R ! 61.25 ! 0.60 ! 127.97 !
! ! INNER CELL No. 5 ! ! ! !
! ! ! ! ! !
! 26QT1(2) ! PROBE-FUEL QTY, L/R ! 56.08 ! 0.56 ! 117.11 !
! ! INNER CELL No. 6 ! ! ! !
! ! ! ! ! !
! 27QT1(2) ! PROBE-FUEL QTY, L/R ! 44.23 ! 0.44 ! 92.33 !
! ! INNER CELL No. 7 ! ! ! !
! ! ! ! ! !
! 28QT1(2) ! PROBE-FUEL QTY, L/R ! 39.81 ! 0.40 ! 83.05 !
! ! INNER CELL No. 8 ! ! ! !
! ! ! ! ! !
! 29QT1(2) ! PROBE-FUEL QTY, L/R ! 35.21 ! 0.35 ! 73.40 !
! ! INNER CELL No. 9 ! ! ! !
! ! ! ! ! !
! 30QT1(2) ! PROBE-FUEL QTY, L/R ! 35.21 ! 0.35 ! 73.40 !
! ! INNER CELL No. 10 ! ! ! !
! ! ! ! ! !
! 31QT1(2) ! PROBE-FUEL QTY, L/R ! 27.60 ! 0.27 ! 57.40 !
! ! INNER CELL No. 11 ! ! ! !
! ! ! ! ! !
! 32QT1(2) ! PROBE-FUEL QTY, L/R ! 33.90 ! 0.34 ! 70.63 !
! ! INNER CELL No. 12 ! ! ! !
! ! ! ! ! !
! 33QT1(2) ! PROBE-FUEL QTY, L/R ! 25.91 ! 0.26 ! 53.94 !
! ! OUTER CELL No. 13 ! ! ! !
! ! ! ! ! !
! 34QT1(2) ! PROBE-FUEL QTY, L/R ! 20.52 ! 0.21 ! 42.62 !
! ! OUTER CELL No. 14 ! ! ! !
! ! ! ! ! !
! 35QT * ! PROBE-FUEL QTY, CTR ! 81.86 ! 0.82 ! 170.98 !
! ! TANK No. 1 ! ! ! !
! ! ! ! ! !
! 36QT * ! PROBE-FUEL QTY, CTR ! 81.86 ! 0.82 ! 170.98 !
! ! TANK No. 2 ! ! ! !
! ! ! ! ! !
! 37QT * ! PROBE-FUEL QTY, CTR ! 81.86 ! 0.82 ! 170.98 !
! ! TANK No. 3 ! ! ! !
! ! ! ! ! !
! 38QT * ! PROBE-FUEL QTY, CTR ! 81.86 ! 0.82 ! 170.98 !
! ! TANK No. 4 ! ! ! !
! ! ! ! ! !
! 39QT * ! PROBE-FUEL QTY, and ! 59.49 ! 0.60 ! 124.28 !
! ! PROBE-COMPENSATOR, CTR ! 13.68 ! 0.15 ! 28.33 !
! ! TANK No. 5 ! ! ! !
-------------------------------------------------------------------------




----------------------------------------------------------------------------
! ! ! MEAN ! ! !
! ! ! THEORETICAL ! ! !
! FIN ! PROBE ! pF ! TOLERANCE ! FULL TANK !
! ! FUNCTIONAL DESIGNATION !--------------! AT DRY pF ! pF !
! ! ! DRY ! EMPTY ! + OR - ! !
! ! ! ! WET ! ! !
!----------!------------------------!------!-------!-----------!-------------!
! 19QT1(2) ! SENSOR-CADENSICON L/R ! 94.9 ! 95.5 ! 1.0 ! 188.5-214.0 !
! ! INNER CELL ! ! ! ! !
! ! ! ! ! ! !
! 20QT * ! SENSOR-CADENSICON CTR ! 94.9 ! 95.5 ! 1.0 ! 188.5-214.0 !
! ! TANK ! ! ! ! !
----------------------------------------------------------------------------

For the additional values referred to in NOTE 1 above see
F Additional DC Capacitance Values When Empty Tank Probes are Wet ** ON A/C NOT FOR ALL
(Simmonds FQIS)

The DC capacitance values in Table 304A below have been included to enable the technician to appreciate the range of values possible on the CFDS(FUEL), Input Parameters, page 2.
NOTE: If the probe was submerged in fuel immediately before the value is checked it will be 0.36% larger than the MEAN THEORETICAL VALUE (MTV) shown. After one hour the value will decrease to 0.15% larger than the MTV. This later value will stay constant for approximately sixty hours in a sealed empty tank.
NOTE: The values shown for fuel probes with a full tank are given as an aid only. These values will change with:
  • the permittivity of the fuel in the cell/tank
  • the proportion of the probe in fuel after the refuel valve has closed.
NOTE: The values for an ultracomp and a dualcomp with a full tank are given as an aid only. The values given are nominal and variations can be expected with fuel of different permittivities.

NOTE: A tolerance of + or - 0.03pF plus the tolerance of the DC Capacitance Tester is recommended. This is over and above the values shown in the table below. This gives an allowance for non-laboratory conditions, different operators, and the accuracy of the Test Set used.
Table 304A - Tank Units DC Capacitance Values
-----------------------------------------------------------------------------
! ! ! MEAN ! TOLERANCE ! FULL TANK !
! FIN ! PROBE ! THEORETICAL ! AT DRY pF ! pF !
! ! FUNCTIONAL DESIGNATION ! pF DRY ! + OR - ! !
!----------!----------------------------!-------------!-----------!-----------!
! 21QT1(2) ! PROBE-FUEL QTY, L/R No. 1 ! 64.516 ! 0.62 ! 135.45 !
! ! ! ! ! !
! 54QT1(2) ! PROBE-FUEL QTY, L/R No. 2 ! 63.122 ! 0.60 ! 132.62 !
! ! ! ! ! !
! 23QT1(2) ! PROBE-FUEL QTY, L/R No. 3 ! 52.723 ! 0.55 ! 110.59 !
! ! ! ! ! !
! 56QT1(2) ! PROBE-FUEL QTY, L/R No. 4 ! 40.983 ! 0.49 ! 86.16 !
! ! ! ! ! !
! 25QT1(2) ! PROBE-FUEL QTY, L/R No. 5 ! 56.145 ! 0.57 ! 117.82 !
! ! ! ! ! !
! 26QT1(2) ! PROBE-FUEL QTY, L/R No. 6 ! 51.012 ! 0.54 ! 107.08 !
! ! ! ! ! !
! 27QT1(2) ! PROBE-FUEL QTY, L/R No. 7 ! 40.180 ! 0.49 ! 84.35 !
! ! ! ! ! !
! 28QT1(2) ! PROBE-FUEL QTY, L/R No. 8 ! 36.252 ! 0.47 ! 76.26 !
! ! ! ! ! !
! 29QT1(2) ! PROBE-FUEL QTY, L/R No. 9 ! 31.149 ! 0.44 ! 65.38 !
! ! ! ! ! !
! 30QT1(2) ! PROBE-FUEL QTY, L/R No. 10 ! 31.149 ! 0.44 ! 65.38 !
! ! ! ! ! !
! 59QT1(2) ! PROBE-FUEL QTY, L/R No. 11 ! 29.908 ! 0.43 ! 62.57 !
! ! ! ! ! !
! 60QT1(2) ! PROBE-FUEL QTY, L/R No. 12 ! 22.700 ! 0.40 ! 47.72 !
! ! ! ! ! !
! 61QT1(2) ! PROBE-FUEL QTY, L/R No. 13 ! 17.947 ! 0.37 ! 34.67 !
! ! ! ! ! !
! 34QT1(2) ! PROBE-FUEL QTY, L/R No. 14 ! 17.947 ! 0.37 ! 34.67 !
! ! ! ! ! !
! 35QT ! PROBE-FUEL QTY, CTR No. 1 ! 75.968 ! 0.72 ! 158.27 !
! ! ! ! ! !
! 36QT ! PROBE-FUEL QTY, CTR No. 2 ! 75.968 ! 0.72 ! 158.27 !
! ! ! ! ! !
! 37QT ! PROBE-FUEL QTY, CTR No. 3 ! 75.968 ! 0.72 ! 158.27 !
! ! ! ! ! !
! 38QT ! PROBE-FUEL QTY, CTR No. 4 ! 75.968 ! 0.72 ! 158.27 !
! ! ! ! ! !
! 39QT ! PROBE-FUEL QTY, CTR No. 5 ! 67.663 ! 0.65 ! 141.88 !
-----------------------------------------------------------------------------



----------------------------------------------------------------------------
! ! ! MEAN ! TOLERANCE ! !
! FIN ! PROBE ! THEORETICAL ! AT DRY pF ! FULL TANK !
! ! FUNCTIONAL DESIGNATION ! pF DRY ! + OR - ! pF !
!----------!------------------------!--------------!-----------!-------------!
! 50QT ! ULTRACOMP CTR TANK ! 57.000 ! 0.83 ! 118.43 !
! ! ! ! ! !
! 52QT ! ULTRACOMP R WING TK ! 57.000 ! 0.83 ! 118.43 !
! ! ! ! ! !
! 53QT ! DUALCOMP L WING TK !(A) 57.000 ! 0.83 ! 118.43 !
! !(Contains 2 compensators!(B) 57.000 ! 0.83 ! 118.43 !
! ! A and B) ! ! ! !
----------------------------------------------------------------------------

For the additional values referred to in NOTE 1 above see
F Additional DC Capacitance Values When Empty Tank Probes are Wet ** ON A/C NOT FOR ALL
(Simmonds FQIS)

The DC capacitance values in Table 304 below have been included to enable the technician to appreciate the range of values possible on the CFDS(FUEL), Input Parameters, page 2.
NOTE: If the probe was submerged in fuel immediately before the value is checked it will be 0.36% larger than the MEAN THEORETICAL VALUE (MTV) shown. After one hour the value will decrease to 0.15% larger than the MTV. This later value will stay constant for approximately sixty hours in a sealed empty tank.

NOTE: The values shown for fuel probes with a full cell/tank are given as an aid only. These values will change with:
  • The permittivity of the fuel in the cell/tank
  • The proportion of the probe in fuel after the refuel valve has closed.
NOTE: The values for an ultracomp and a dualcomp with full tank are given as an aid only. The values given are nominal and variations can be expected with fuel of different permittivities.

NOTE: A tolerance of + or - 0.03pF plus the tolerance of the DC Capacitance Tester is recommended. This is over and above the values shown in the table below. This gives an allowance for non-laboratory conditions, different operators, and the accuracy of the Test Set used.
Table 304 - Tank Units DC Capacitance Values
-------------------------------------------------------------------------
! ! ! MEAN ! TOLERANCE ! FULL TANK !
! FIN ! PROBE ! THEORETICAL ! AT DRY pF ! pF !
! ! FUNCTIONAL DESIGNATION ! pF DRY ! + OR - ! !
!----------!------------------------!-------------!-----------!-----------!
! 21QT1(2) ! PROBE-FUEL QTY, L/R ! 64.5 ! 0.60 ! 134.22 !
! ! INNER CELL No. 1 ! ! ! !
! ! ! ! ! !
! 92QT1(2) ! PROBE-FUEL QTY, L/R ! 63.1 ! 0.60 ! 131.39 !
! ! INNER CELL No. 2 ! ! ! !
! ! ! ! ! !
! 23QT1(2) ! PROBE-FUEL QTY, L/R ! 52.7 ! 0.55 ! 109.63 !
! ! INNER CELL No. 3 ! ! ! !
! ! ! ! ! !
! 56QT1(2) ! PROBE-FUEL QTY, and ! 41.0 ! 0.50 ! 85.16 !
! ! PROBE-COMPENSATOR L/R ! ! ! !
! ! INNER CELL No. 4 ! ! ! !
! ! ! ! ! !
! 25QT1(2) ! PROBE-FUEL QTY, L/R ! 56.1 ! 0.55 ! 116.82 !
! ! INNER CELL No. 5 ! ! ! !
! ! ! ! ! !
! 26QT1(2) ! PROBE-FUEL QTY, L/R ! 51.0 ! 0.50 ! 106.04 !
! ! INNER CELL No. 6 ! ! ! !
! ! ! ! ! !
! 27QT1(2) ! PROBE-FUEL QTY, L/R ! 40.2 ! 0.50 ! 83.47 !
! ! INNER CELL No. 7 ! ! ! !
! ! ! ! ! !
! 28QT1(2) ! PROBE-FUEL QTY, L/R ! 36.3 ! 0.50 ! 75.23 !
! ! INNER CELL No. 8 ! ! ! !
! ! ! ! ! !
! 29QT1(2) ! PROBE-FUEL QTY, L/R ! 31.1 ! 0.45 ! 64.52 !
! ! INNER CELL No. 9 ! ! ! !
! ! ! ! ! !
! 30QT1(2) ! PROBE-FUEL QTY, L/R ! 31.1 ! 0.45 ! 64.52 !
! ! INNER CELL No. 10 ! ! ! !
! ! ! ! ! !
! 31QT1(2) ! PROBE-FUEL QTY, L/R ! 24.8 ! 0.40 ! 51.33 !
! ! INNER CELL No. 11 ! ! ! !
! ! ! ! ! !
! 32QT1(2) ! PROBE-FUEL QTY, L/R ! 29.9 ! 0.45 ! 61.93 !
! ! INNER CELL No. 12 ! ! ! !
! ! ! ! ! !
! 93QT1(2) ! PROBE-FUEL QTY, L/R ! 22.7 ! 0.40 ! 46.96 !
! ! OUTER CELL No. 13 ! ! ! !
! ! ! ! ! !
! 34QT1(2) ! PROBE-FUEL QTY, L/R ! 17.9 ! 0.35 ! 36.98 !
! ! OUTER CELL No. 14 ! ! ! !
! ! ! ! ! !
! 35QT * ! PROBE-FUEL QTY, CTR ! 76.0 ! 0.70 ! 158.24 !
! ! TANK No. 1 ! ! ! !
! ! ! ! ! !
! 36QT * ! PROBE-FUEL QTY, CTR ! 76.0 ! 0.70 ! 158.24 !
! ! TANK No. 2 ! ! ! !
! ! ! ! ! !
! 37QT * ! PROBE-FUEL QTY, CTR ! 76.0 ! 0.70 ! 158.24 !
! ! TANK No. 3 ! ! ! !
! ! ! ! ! !
! 38QT * ! PROBE-FUEL QTY, CTR ! 75.9 ! 0.70 ! 158.24 !
! ! TANK No. 4 ! ! ! !
! ! ! ! ! !
! 51QT * ! PROBE-FUEL QTY, CTR ! 67.7 ! 0.70 ! 140.82 !
! ! TANK No. 5 ! ! ! !
-------------------------------------------------------------------------




----------------------------------------------------------------------------
! ! ! MEAN ! ! !
! ! ! THEORETICAL ! ! !
! FIN ! PROBE ! pF ! TOLERANCE ! FULL TANK !
! ! FUNCTIONAL DESIGNATION !--------------! AT DRY pF ! pF !
! ! ! DRY ! EMPTY ! + OR - ! !
! ! ! ! WET ! ! !
!----------!------------------------!------!-------!-----------!-------------!
! 53QT ! DUALCOMP L WING TK ! 56.6 ! 56.7 ! 0.8 ! 117.58 !
! (52QT) ! (ULTRACOMP R WING TK) ! ! ! ! !
! ! ! ! ! ! !
! 50QT * ! ULTRACOMP CTR TANK ! 56.6 ! 56.7 ! 0.8 ! 117.58 !
----------------------------------------------------------------------------

For additional values referred to in NOTE 1 above see
F Additional DC Capacitance Values When Empty Tank Probes are Wet ** ON A/C NOT FOR ALL
ACT Tank Units DC Capacitance Values (Simmonds FQIS)

Each ACT fuel probe have one FQIS capacitive sensor, and two FLSS thermistor (Resistance Temperature Detector - RTD) sensors together in one LRU.

For the ACT Fuel Level Sensors Operating (Changeover) Values see Chap. 28-46-00, P. Block 301.

-------------------------------------------------------------------------
! ! ! MEAN ! TOLERANCE ! FULL TANK !
! FIN ! PROBE ! THEORETICAL ! AT DRY pF ! pF !
! ! FUNCTIONAL DESIGNATION ! pF DRY ! + OR - ! !
!----------!------------------------!-------------!-----------!-----------!
! 65QT1 ! PROBE-FUEL QTY, ! 83.6 ! 0.8 ! 171.55 !
! ! No. 1 ACT 1 ! ! ! !
! ! ! ! ! !
! 66QT1 ! PROBE-FUEL QTY, ! 83.6 ! 0.8 ! 171.55 !
! ! No. 2 ACT 1 ! ! ! !
-------------------------------------------------------------------------

NOTE: The capacitance pF value for a full tank is given for:
  • an ACT filled to high level sensor fuel shutoff
  • a fuel with a standard permittivity of 2.1
The value on the vertical scale is the additional value of capacitance in pF to be added to the MEAN THEORETICAL (MTV) when the fuel tanks are wet.

EXAMPLE (Smiths FQIS)

The MTV for Probe 21QT1 is 70.29pF.

Immediately after draining an additional 0.25pF is to be added to this value, (from slope 1).
70.29 + 0.25 = 70.54pF

After one hour this additional value will have reduced to 0.105pF, (from slope 2).
70.29 + 0.105 = 70.395pF

This later value will remain constant for sixty hours in a sealed tank.
The value on the vertical scale is the additional value of capacitance in pF to be added to the MEAN THEORETICAL (MTV) when the fuel tanks are wet.

EXAMPLE (Simmonds FQIS)

The MTV for Probe 21QT1 is 64.516pF.

Immediately after draining an additional 0.25pF is to be added to this value, (from slope 1).
64.516 + 0.2 = 64.716pF

After one hour this additional value will have reduced to 0.105pF, (from slope 2).
64.516 + 0.105 = 64.616pF

This later value will remain constant for sixty hours in a sealed tank.
** ON A/C NOT FOR ALL
3. Maintenance Notices
The maintenance notices that follow are to give you an introduction or understanding of possible reported problems associated with the FQIS.

The maintenance notices provide useful data for the maintenance staff.
-----------------------------------------------------------------------------
! MAINTENANCE NOTICE !
! MALFUNCTION (Deviation from the desired system operation) !
! CFDS - AVIONIC STATUS - FUEL (CLASS 3) faults !
!-----------------------------------------------------------------------------!
! !
! General Description The message FUEL (CLASS 3) is not shown on !
! the AVONIC STATUS option, and therefore the !
! class 3 faults are not declared, when they !
! exist in the fuel system. !
! !
! Action Will be corrected at a future FQIC software !
! standard. !
! !
! The FUEL system menu option, CLASS 3 FAULTS !
! must be selected to see if there are any !
! class 3 faults. !
-----------------------------------------------------------------------------

-----------------------------------------------------------------------------
! MAINTENANCE NOTICE !
! MALFUNCTION (Deviation from the desired system operation) !
! CFDS - FUEL, PROBLEMS WITH FLSS STATUS PAGE !
!-----------------------------------------------------------------------------!
! !
! General Description All FLSS STATUS BITE results originally !
! showing a F (failed) are replaced with !
! a P (passed) after the transition into !
! flight and then back to ground. !
! !
! NOTE: The above applies if the Level sensor !
! failures were identified during the !
! FQIC power up or the COMMAND FLSS !
! BITE. !
! !
! Action Mod TBA (SB28-TBA ) !
! Will be corrected at FQIC software !
! standard TBA !
! !
! Maintenance steps are necessary, starting !
! with a fresh FLSS BITE test. !
! !
! !
-----------------------------------------------------------------------------

-----------------------------------------------------------------------------
! MAINTENANCE NOTICE !
! MALFUNCTION (Deviation from the desired system operation) !
! CFDS - FUEL, PROBLEMS WITH REPORTING CLASS 3 FAILURES !
!-----------------------------------------------------------------------------!
! !
! General Description 1 Class 3 failures will not be reported via !
! the CFDS FQIS STATUS page if there are any !
! of the following class 1 failures present: !
! - Center Tank Ultracomp Vos/Temp 50QT !
! - Right Wing Tank Ultracomp Vos/Temp 52QT !
! - Collector Cell Temp sensors (A&B) 54QT1/2 !
! !
! General Description 2 Class 3 failures will also not be reported !
! via the CFDS CLASS 3 FAULTS page if there !
! are any of the above class 1 failures !
! present during the related Flight Leg. !
! !
! Action Mod TBA (SB28-TBA ) !
! Will be corrected at FQIC software !
! standard TBA !
! !
! Maintenance steps are necessary. !
! !
! !
-----------------------------------------------------------------------------

-----------------------------------------------------------------------------
! MAINTENANCE NOTICE !
! MALFUNCTION (Deviation from the desired system operation) !
! CFDS - FUEL, PROBLEMS WITH THE INPUT PARAMETERS PAGES !
!-----------------------------------------------------------------------------!
! !
! General Description The following deviations occur: !
! !
! 1. There is no +/- sign displayed with the !
! Ultracomp & Collector Cell temp values. !
! !
! 2. Dashes are shown for values that are !
! out of range for the items that follow: !
! - UCMP V !
! - temperature !
! - UCMP K !
! - DCMP KA !
! - DCMP KB !
! - probe values (PROBE CAPACITANCE page). !
! !
! Action Mod TBA (SB28-TBA ) !
! Will be corrected at FQIC software !
! standard TBA !
! !
! Maintenance steps are not necessary. !
-----------------------------------------------------------------------------

-----------------------------------------------------------------------------
! MAINTENANCE NOTICE !
! MALFUNCTION (Deviation from the desired system operation) !
! CFDS - FQIS FAILURES NOT REPORTED WHEN ONE CHANNEL IS NOT POWERED !
!-----------------------------------------------------------------------------!
! !
! General Description When one channel is not powered, the !
! failure of any further FQIS components is !
! not reported by the CFDS. !
! !
! This therefore applies to components !
! associated with the remaining powered !
! channel. !
! !
! Action Mod TBA (SB28-TBA ) !
! Will be corrected at FQIC software !
! standard TBA !
! !
! Maintenance steps are necessary as shown by !
! first channel failure. !
! !
! !
-----------------------------------------------------------------------------

[Rev.8 from Aug 2018] 2026.04.04 04:29:13 UTC
"WTRUIB" 2025