TANKS - DESCRIPTION AND OPERATION

** ON A/C NOT FOR ALL

1. General

A. Description
There is one fuel tank in each wing and one in the center wing box. The total usable fuel capacity is 23700 l (6261 USgal). The usable fuel capacity of each tank is shown in Table 001. The total unusable fuel capacity is 89.7 l (23.7 USgal). The unusable fuel quantities are shown in Table 002.

There is one fuel tank in each wing (divided into an inner and outer cell) and one in the center wing box. The total usable fuel capacity is 24209 l (6395 USgal). The usable fuel capacity of each tank is shown in Table 001. The total unusable fuel capacity is 82.1 l (21.7 USgal). The unusable fuel quantities are shown in Table 002.

There is one fuel tank in each wing (divided into an inner and outer cell) and one in the center wing box. The total usable fuel capacity is 23860 l (6303 USgal). The usable fuel capacity of each tank is shown in Table 001. The total unusable fuel capacity is 82.1 l (21.7 USgal). The unusable fuel quantities are shown in Table 002.

There is one fuel tank in each wing (divided into an inner and outer cell) and one in the center wing box. The total usable fuel capacity is 24167 l (6384 USgal). The usable fuel capacity of each tank is shown in Table 001. The total unusable fuel capacity is 82.1 l (21.7 USgal). The unusable fuel quantities are shown in Table 002.

There is one fuel tank in each wing and one in the center wing box. The total usable fuel capacity is 24050 l (6353 USgal). The usable fuel capacity of each tank is shown in Table 001. The total unusable fuel capacity is 89.7 l (23.7 USgal). The unusable fuel quantities are shown in Table 002.

B. Description

There is one fuel tank in each wing and one in the center wing box. There are also two vent surge tanks, one in each wing, outboard of the wing tank. Each tank is a part of the aircraft structure. The materials used to seal the tanks are fully resistant to the fuels and the fuel additives.

The aircraft also has provision for three Additional Center Tanks (ACTs). One ACT can be installed in the forward cargo compartment and two in the aft cargo compartment. The aircraft can operate with zero, one, two or three ACTs.

The total usable fuel capacity is:

with no ACTs installed - 23580 liters (6229 USgal)

with one ACT installed - 26701 liters (7054 USgal)

with two ACTs installed - 29822 liters (7878 USgal)

with three ACTs installed - 32943 liters (8703 USgal)

The usable fuel capacity of each tank is shown in Table 001 and Table 002.

The total unusable fuel capacity is:

with no ACTs installed - 89.7 liters (23.7 USgal)

with one ACT installed - 106.7 liters (28.2 USgal)

with two ACTs installed - 123.7 liters (32.7 USgal)

with three ACTs installed - 140.7 liters (37.2 USgal)

The unusable fuel quantity of each tank is shown in Table 003 and Table 004.

There is one fuel tank in each wing and one in the center wing box. There are also two vent surge tanks, one in each wing, outboard of the wing tank. Each tank is a part of the aircraft structure. The materials used to seal the tanks are fully resistant to the fuels and the fuel additives.

The aircraft also has provision for two Additional Center Tanks (ACTs). These ACTs can be installed in the aft cargo compartment. The aircraft can operate with zero, one or two ACTs.

The total usable fuel capacity is:

with no ACTs installed - 23580 liters (6229 USgal)

with one ACT installed - 26701 liters (7054 USgal)

with two ACTs installed - 29822 liters (7878 USgal)

The usable fuel capacity of each tank is shown in Table 001 and Table 002.

The total unusable fuel capacity is:

with no ACTs installed - 89.7 liters (23.7 USgal)

with one ACT installed - 106.7 liters (28.2 USgal)

with two ACTs installed - 123.7 liters (32.7 USgal)

The unusable fuel quantity of each tank is shown in Table 003 and Table 004.
The aircraft has the fuel tanks that follow:

a LH wing tank
a RH wing tank
a center tank.

There is also a vent surge tank at the end of each wing.

The fuel tanks and the vent surge tanks are each integral-tanks and are part of the aircraft structure. The materials which seal the tanks are fully resistant to the fuels and fuel additives that they hold.

The aircraft also has provision for two Additional Center Tanks (ACTs) which can be installed in the aft cargo compartment. The aircraft can operate with zero, one or two ACTs installed.

The total usable fuel capacity is:

with no ACTs installed - 23700 liters (6260 USgal)

with one ACT installed - 26692 liters (7050 USgal)

with two ACTs installed - 29684 liters (7840 USgal)

The total unusable fuel capacity is:

with no ACTs installed - 89.7 liters (23.8 USgal)

with one ACT installed - 106.7 liters (28.3 USgal

with two ACTs installed - 123.7 liters (32.8 USgal)

The usable and unusable fuel quantities are shown in Table 001 thru Table 006.

The aircraft has the fuel tanks that follow:

a LH wing tank
a RH wing tank
a center tank.

with no ACTs installed - 24050 liters (6353 USgal)

with one ACT installed - 27042 liters (7144 USgal)

with two ACTs installed - 30034 liters (7934 USgal)

The total unusable fuel capacity is:

with no ACTs installed - 89.7 liters (23.8 USgal)

with one ACT installed - 106.7 liters (28.3 USgal

with two ACTs installed - 123.7 liters (32.8 USgal)

The usable and unusable fuel quantities are shown in Table 001 thru Table 006.

There are also two vent surge tanks. The vent surge tanks are located in each wing outboard of the wing tank.

Each tank is a part of the aircraft structure. All the materials used to seal the tanks are fully resistant to all the fuels and the fuel additives.

-----------------------------------------------------------

! FUEL ! LH ! CTR ! RH ! Total !

! TANK ! Wing ! (Transfer) ! Wing ! !

!----------------!---------!------------!---------!---------!

! VOLUME (liter) ! 7750 ! 8200 ! 7750 ! 23700 !

! (USgal) ! 2047 ! 2166 ! 2047 ! 6260 !

! WEIGHT (kg) ! 6084 ! 6437 ! 6084 ! 18605 !

! (lb) ! 13413 ! 14191 ! 13413 ! 41017 !

------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities

Table 001

NOTE: These fuel quantities are the minimum. It is possible they could be higher.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.4 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.4 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.5 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.3 !

! BOTH WING TANKS ! 38.4 ! 10.2 ! 30.1 ! 66.4 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 89.7 ! 23.8 ! 70.3 ! 155.1 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities

Table 002

-----------------------------------------------------------------------------

! FUEL ! LH Wing ! Center ! RH Wing ! Total !

! TANK ! inner outer ! ! inner outer ! !

!----------------!------------------!------------!------------------!---------!

! VOLUME (liter) ! 7100 ! 880 ! 8250 ! 7099 ! 880 ! 24209 !

! (USgal) ! 1876 ! 232 ! 2180 ! 1876 ! 232 ! 6396 !

! WEIGHT (kg) ! 5573 ! 691 ! 6476 ! 5572 ! 691 ! 19003 !

! (lb) ! 12286 ! 1523 ! 14278 ! 12285 ! 1523 ! 41895 !

-----------------------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities

Table 001

NOTE: These fuel quantities are the minimum. It is possible they could be higher.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 25.6 ! 6.8 ! 20.1 ! 44.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.4 !

! BOTH SURGE TANKS ! 0.5 ! 0.1 ! 0.4 ! 0.9 !

! BOTH WING TANK INNER CELLS ! 28.0 ! 7.4 ! 22.0 ! 48.4 !

! BOTH WING TANK OUTER CELLS ! 4.0 ! 1.1 ! 3.1 ! 6.9 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 82.1 ! 21.7 ! 64.4 ! 142.0 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities

Table 002

-----------------------------------------------------------------------------

! FUEL ! LH Wing ! Center ! RH Wing ! Total !

! TANK ! inner outer ! ! inner outer ! !

!----------------!------------------!------------!------------------!---------!

! VOLUME (liter) ! 6925 ! 880 ! 8250 ! 6925 ! 880 ! 23860 !

! (USgal) ! 1830 ! 232 ! 2180 ! 1830 ! 232 ! 6304 !

! WEIGHT (kg) ! 5436 ! 691 ! 6476 ! 5436 ! 691 ! 18730 !

! (lb) ! 11984 ! 1523 ! 14278 ! 11984 ! 1523 ! 41292 !

-----------------------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities

Table 001

NOTE: These fuel quantities are the minimum. It is possible they could be higher.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 25.6 ! 6.8 ! 20.1 ! 44.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.4 !

! BOTH SURGE TANKS ! 0.5 ! 0.1 ! 0.4 ! 0.9 !

! BOTH WING TANK INNER CELLS ! 28.0 ! 7.4 ! 22.0 ! 48.4 !

! BOTH WING TANK OUTER CELLS ! 4.0 ! 1.1 ! 3.1 ! 6.9 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 82.1 ! 21.7 ! 64.4 ! 142.0 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities

Table 002

-----------------------------------------------------------------------------

! FUEL ! LH Wing ! Center ! RH Wing ! Total !

! TANK ! inner outer ! ! inner outer ! !

!----------------!------------------!------------!------------------!---------!

! VOLUME (liter) ! 7093 ! 867 ! 8248 ! 7092 ! 867 ! 24167 !

! (USgal) ! 1874 ! 229 ! 2179 ! 1873 ! 229 ! 6384 !

! WEIGHT (kg) ! 5568 ! 681 ! 6475 ! 5567 ! 681 ! 18971 !

! (lb) ! 12275 ! 1501 ! 14275 ! 12273 ! 1501 ! 41824 !

-----------------------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities

Table 001

NOTE: These fuel quantities are the minimum. It is possible they could be higher.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 25.6 ! 6.8 ! 20.1 ! 44.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.4 !

! BOTH SURGE TANKS ! 0.5 ! 0.1 ! 0.4 ! 0.9 !

! BOTH WING TANK INNER CELLS ! 28.0 ! 7.4 ! 22.0 ! 48.4 !

! BOTH WING TANK OUTER CELLS ! 4.0 ! 1.1 ! 3.1 ! 6.9 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 82.1 ! 21.7 ! 64.4 ! 142.0 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities

Table 002

-----------------------------------------------------------

! FUEL ! LH ! CTR ! RH ! Total !

! TANK ! Wing ! (Transfer) ! Wing ! !

!----------------!---------!------------!---------!---------!

! VOLUME (liter) ! 7925 ! 8200 ! 7925 ! 24050 !

! (USgal) ! 2094 ! 2166 ! 2094 ! 6354 !

! WEIGHT (kg) ! 6221 ! 6437 ! 6221 ! 18879 !

! (lb) ! 13715 ! 14191 ! 13715 ! 41621 !

------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities

Table 001

NOTE: These fuel quantities are the minimum. It is possible they could be higher.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.4 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.4 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.5 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.3 !

! BOTH WING TANKS ! 38.4 ! 10.2 ! 30.1 ! 66.4 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 89.7 ! 23.8 ! 70.3 ! 155.1 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities

Table 002

-----------------------------------------------------------------------------

! FUEL ! LH Wing ! Center ! RH Wing ! Total !

! TANK ! inner outer ! ! inner outer ! !

!----------------!------------------!------------!------------------!---------!

! VOLUME (liter) ! 6874 ! 864 ! 8248 ! 6874 ! 864 ! 23724 !

! (USgal) ! 1816 ! 228 ! 2179 ! 1816 ! 228 ! 6267 !

! WEIGHT (kg) ! 5396 ! 678 ! 6475 ! 5396 ! 678 ! 18623 !

! (lb) ! 11896 ! 1495 ! 14275 ! 11896 ! 1495 ! 41057 !

-----------------------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities

Table 001

NOTE: These fuel quantities are the minimum. It is possible that they can be higher than the minimum.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 25.6 ! 6.8 ! 20.1 ! 44.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.4 !

! BOTH SURGE TANKS ! 0.5 ! 0.1 ! 0.4 ! 0.9 !

! BOTH WING TANK INNER CELLS ! 28.0 ! 7.4 ! 22.0 ! 48.4 !

! BOTH WING TANK OUTER CELLS ! 4.0 ! 1.1 ! 3.1 ! 6.9 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 82.1 ! 21.7 ! 64.4 ! 142.0 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities

Table 002

-----------------------------------------------------------

! FUEL ! LH ! CTR ! RH ! Total !

! TANK ! Wing ! (Transfer) ! Wing ! !

!----------------!---------!------------!---------!---------!

! VOLUME (liter) ! 7925 ! 8200 ! 7925 ! 24050 !

! (USgal) ! 2094 ! 2166 ! 2094 ! 6354 !

! WEIGHT (kg) ! 6221 ! 6437 ! 6221 ! 18879 !

! (lb) ! 13715 ! 14191 ! 13715 ! 41621 !

------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities (with no ACTs installed)

Table 001

NOTE: These fuel quantities are the minimum. It is possible they could be higher.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.3 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.4 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.3 !

! BOTH WING TANKS ! 38.4 ! 10.2 ! 30.1 ! 66.6 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 89.7 ! 23.8 ! 70.3 ! 155.0 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities (with no ACTs installed)

Table 002

-----------------------------------------------------------------------

! FUEL ! LH ! CTR ! ACT1 ! RH ! Total !

! TANK ! Wing ! (Transfer) ! ! Wing ! !

!----------------!---------!------------!---------!--------!------------!

! VOLUME (liter) ! 7925 ! 8200 ! 2992 ! 7925 ! 27042 !

! (USgal) ! 2094 ! 2166 ! 790 ! 2094 ! 7144 !

! WEIGHT (kg) ! 6221 ! 6437 ! 2349 ! 6221 ! 21228 !

! (lb) ! 13715 ! 14191 ! 5179 ! 13715 ! 46800 !

-----------------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities (with ACT1 installed)

Table 003

NOTE: These fuel quantities are the minimum. It is possible they could be higher.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.3 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.4 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.4 !

! BOTH WING TANKS ! 38.4 ! 10.2 ! 30.2 ! 66.6 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

! ACT1 ! 17.0 ! 4.5 ! 13.3 ! 29.3 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 106.7 ! 28.3 ! 83.7 ! 184.4 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities (with ACT1 installed)

Table 004

----------------------------------------------------------------------------

! FUEL ! LH ! CTR ! ACT1 ! ACT2 ! RH ! Total !

! TANK ! Wing ! (Transfer) ! ! ! Wing ! !

!----------------!---------!------------!-------!-------!---- --!-----------!

! VOLUME (liter) ! 7925 ! 8200 ! 2992 ! 2992 ! 7925 ! 30034 !

! (USgal) ! 2094 ! 2166 ! 790 ! 790 ! 2094 ! 7934 !

! WEIGHT (kg) ! 6221 ! 6437 ! 2349 ! 2349 ! 6221 ! 23577 !

! (lb) ! 13715 ! 14191 ! 5179 ! 5179 ! 13715 ! 51979 !

----------------------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities (with ACT1 and ACT2 installed)

Table 005

NOTE: These fuel quantities are the minimum. It is possible they could be higher.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.3 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.4 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.4 !

! BOTH WING TANKS ! 38.4 ! 10.2 ! 30.2 ! 66.6 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

! ACT1 ! 17.0 ! 4.5 ! 13.3 ! 29.3 !

! ACT2 ! 17.0 ! 4.5 ! 13.3 ! 29.3 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 123.7 ! 32.8 ! 97.0 ! 213.7 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities (with ACT1 and ACT2 installed)

Table 006

-----------------------------------------------------------

! FUEL ! LH ! CTR ! RH ! Total !

! TANK ! Wing ! (Transfer) ! Wing ! !

!----------------!---------!------------!---------!---------!

! VOLUME (liter) ! 7690 ! 8200 ! 7690 ! 23580 !

! (USgal) ! 2031 ! 2166 ! 2031 ! 6228 !

! WEIGHT (kg) ! 6037 ! 6437 ! 6037 ! 18511 !

! (lb) ! 13309 ! 14191 ! 13309 ! 40809 !

------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities (with no ACT installed)

Table 001

NOTE: These fuel quantities are the minimum. It is possible that they can be higher than the minimum.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.3 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.4 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.3 !

! BOTH WING TANKS ! 38.4 ! 10.2 ! 30.1 ! 66.6 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 89.7 ! 23.8 ! 70.3 ! 155.0 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities (with no ACT installed)

Table 002

---------------------------------------------------------------------------

! FUEL ! LH ! CTR ! ACT ! RH ! Total !

! TANK ! Wing ! (Transfer) ! ! Wing ! !

!----------------!---------!------------!-------------!--------!------------!

! VOLUME (liter) ! 7690 ! 8200 ! 2992 ! 7690 ! 26572 !

! (USgal) ! 2031 ! 2166 ! 790 ! 2031 ! 7018 !

! WEIGHT (kg) ! 6037 ! 6437 ! 2349 ! 6037 ! 20860 !

! (lb) ! 13309 ! 14191 ! 5178 ! 13309 ! 45987 !

---------------------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities (with ACT installed)

Table 001-A

NOTE: These fuel quantities are the minimum. It is possible that they can be higher than the minimum.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.4 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.4 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.5 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.4 !

! BOTH WING TANKS ! 38.4 ! 10.2 ! 30.2 ! 66.4 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

! ACT (AUXILIARY CENTER TANK) ! 17.0 ! 4.5 ! 13.3 ! 29.4 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 106.7 ! 28.3 ! 83.7 ! 184.6 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities (with ACT installed)

Table 002-A

-----------------------------------------------------------

! FUEL ! LH ! CTR ! RH ! Total !

! TANK ! Wing ! (Transfer) ! Wing ! !

!----------------!---------!------------!---------!---------!

! VOLUME (liter) ! 7690 ! 8200 ! 7690 ! 23580 !

! (USgal) ! 2031 ! 2166 ! 2031 ! 6228 !

! WEIGHT (kg) ! 6037 ! 6437 ! 6037 ! 18511 !

! (lb) ! 13309 ! 14191 ! 13309 ! 40809 !

------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities (with no ACTs installed)

Table 001

NOTE: These fuel quantities are the minimum. It is possible that they can be higher than the minimum.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.3 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.4 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.3 !

! BOTH WING TANKS ! 38.4 ! 10.2 ! 30.1 ! 66.6 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 89.7 ! 23.8 ! 70.3 ! 155.0 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities (with no ACTs installed)

Table 002

-----------------------------------------------------------------------

! FUEL ! LH ! CTR ! ACT1 ! RH ! Total !

! TANK ! Wing ! (Transfer) ! ! Wing ! !

!----------------!---------!------------!---------!--------!------------!

! VOLUME (liter) ! 7690 ! 8200 ! 2992 ! 7690 ! 26572 !

! (USgal) ! 2031 ! 2166 ! 790 ! 2031 ! 7018 !

! WEIGHT (kg) ! 6037 ! 6437 ! 2349 ! 6037 ! 20860 !

! (lb) ! 13309 ! 14191 ! 5179 ! 13309 ! 45988 !

-----------------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities (with ACT1 installed)

Table 003

NOTE: These fuel quantities are the minimum. It is possible that they can be higher than the minimum.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.3 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.4 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.4 !

! BOTH WING TANKS ! 38.4 ! 10.2 ! 30.2 ! 66.6 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

! ACT1 ! 17.0 ! 4.5 ! 13.3 ! 29.3 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 106.7 ! 28.3 ! 83.7 ! 184.4 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities (with ACT1 installed)

Table 004

----------------------------------------------------------------------------

! FUEL ! LH ! CTR ! ACT1 ! ACT2 ! RH ! Total !

! TANK ! Wing ! (Transfer) ! ! ! Wing ! !

!----------------!---------!------------!-------!-------!---- --!-----------!

! VOLUME (liter) ! 7690 ! 8200 ! 2992 ! 2992 ! 7690 ! 29564 !

! (USgal) ! 2031 ! 2166 ! 790 ! 790 ! 2031 ! 7808 !

! WEIGHT (kg) ! 6037 ! 6437 ! 2349 ! 2349 ! 6037 ! 23209 !

! (lb) ! 13309 ! 14191 ! 5179 ! 5179 ! 13309 ! 51167 !

----------------------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities (with ACT1 and ACT2 installed)

Table 005

NOTE: These fuel quantities are the minimum. It is possible that they can be higher than the minimum.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.3 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.4 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.4 !

! BOTH WING TANKS ! 38.4 ! 10.2 ! 30.2 ! 66.6 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

! ACT1 ! 17.0 ! 4.5 ! 13.3 ! 29.3 !

! ACT2 ! 17.0 ! 4.5 ! 13.3 ! 29.3 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 123.7 ! 32.8 ! 97.0 ! 213.7 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities (with ACT1 and ACT2 installed)

Table 006

-----------------------------------------------------------

! FUEL ! LH ! CTR ! RH ! Total !

! TANK ! Wing ! (Transfer) ! Wing ! !

!----------------!---------!------------!---------!---------!

! VOLUME (liter) ! 7690 ! 8200 ! 7690 ! 23580 !

! (USgal) ! 2031 ! 2166 ! 2031 ! 6228 !

! WEIGHT (kg) ! 6037 ! 6437 ! 6037 ! 18511 !

! (lb) ! 13309 ! 14191 ! 13309 ! 40809 !

------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities

Table 001

NOTE: These fuel quantities are the minimum value. It is possible that they could be higher.

---------------------------------------------------

! FUEL ! ACT1 ! ACT2 ! ACT4.1 !

! TANK ! ! ! !

!-----------------------!--------!--------!---------!

! VOLUME (liter) ! 3121 ! 3121 ! 3121 !

! (USgal) ! 825 ! 825 ! 825 !

! WEIGHT (kg) ! 2497 ! 2497 ! 2497 !

! (lb) ! 5504 ! 5504 ! 5504 !

---------------------------------------------------

SG = 0.8

Usable Fuel Tank Capacities - ACTs (if installed)

Table 002

NOTE: These fuel quantities are the minimum value. It is possible that they could be higher.

-----------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.4 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.5 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.3 !

! BOTH WING TANKS ! 38.4 ! 10.1 ! 30.1 ! 66.4 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 89.7 ! 23.7 ! 70.3 ! 155.0 !

-----------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities

Table 003

-----------------------------------------------------------------------------

! FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ACT1 ! 17.0 ! 4.5 ! 13.6 ! 30.0 !

! ACT2 ! 17.0 ! 4.5 ! 13.6 ! 30.0 !

! ACT4.1 ! 17.0 ! 4.5 ! 13.6 ! 30.0 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL (three ACTs installed) ! 51.00 ! 13.5 ! 40.8 ! 90.0 !

-----------------------------------------------------------------------------

SG = 0.8

Unusable Fuel Capacities - ACTs (if installed)

Table 004

------------------------------------------------------------

! FUEL ! LH ! CTR ! RH ! Total !

! TANK ! Wing ! (Transfer) ! Wing ! !

!----------------!---------!------------!---------!---------!

! VOLUME (liter) ! 7690 ! 8200 ! 7690 ! 23580 !

! (USgal) ! 2031 ! 2166 ! 2031 ! 6228 !

! WEIGHT (kg) ! 6037 ! 6437 ! 6037 ! 18511 !

! (lb) ! 13309 ! 14191 ! 13309 ! 40809 !

------------------------------------------------------------

SG = 0.785

Usable Fuel Tank Capacities

Table 001

NOTE: These fuel quantities are the minimum value. It is possible that they could be higher.

---------------------------------------------------

! FUEL ! ACT AFT1 ! ACT AFT2 !

! TANK ! ! !

!-----------------------!------------!------------!

! VOLUME (liter) ! 3121 ! 3121 !

! (USgal) ! 825 ! 825 !

! WEIGHT (kg) ! 2497 ! 2497 !

! (lb) ! 5504 ! 5504 !

---------------------------------------------------

SG = 0.8

Usable Fuel Tank Capacities - ACTs (if installed)

Table 002

NOTE: These fuel quantities are the minimum value. It is possible that they could be higher.

------------------------------------------------------------------------------

! SYSTEM/FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!-----------------------------------!--------------------!--------------------!

! ENGINE FEED SYSTEM ! 24.5 ! 6.5 ! 19.2 ! 42.3 !

! VENT SYSTEM ! 0.0 ! 0.0 ! 0.0 ! 0.0 !

! REFUEL SYSTEM ! 0.8 ! 0.2 ! 0.6 ! 1.4 !

! CENTER TANK TRANSFER SYSTEM ! 2.6 ! 0.7 ! 2.0 ! 4.5 !

! BOTH SURGE TANKS ! 0.2 ! 0.1 ! 0.2 ! 0.3 !

! BOTH WING TANKS ! 38.4 ! 10.1 ! 30.1 ! 66.4 !

! CENTER TANK ! 23.2 ! 6.1 ! 18.2 ! 40.1 !

!-----------------------------------!----------!---------!----------!---------!

! TOTAL ! 89.7 ! 23.7 ! 70.3 ! 155.0 !

------------------------------------------------------------------------------

SG = 0.785

Unusable Fuel Tank Capacities

Table 003

----------------------------------------------------------------------------------

! FUEL TANK ! CAPACITY ! WEIGHT !

! ! (liter) (USgal) ! (kg) (lb) !

!---------------------------------------!--------------------!--------------------!

! ACT AFT1 ! 17.0 ! 4.5 ! 13.6 ! 30.0 !

! ACT AFT2 ! 17.0 ! 4.5 ! 13.6 ! 30.0 !

!---------------------------------------!----------!---------!----------!---------!

! TOTAL (two ACTs installed) ! 34.00 ! 9.0 ! 27.2 ! 60.0 !

----------------------------------------------------------------------------------

SG = 0.8

Unusable Fuel Capacities - ACTs (if installed)

Table 004

** ON A/C NOT FOR ALL

2. Component Location

Tanks - Component Location ** ON A/C NOT FOR ALL

Water Drain Valves - Component Location ** ON A/C NOT FOR ALL

Tanks - Component Location (ACT(s) installed) ** ON A/C NOT FOR ALL

Water Drain Valves - Component Location (ACT(s) installed) ** ON A/C NOT FOR ALL

Tanks - Component Location (ACT provision) ** ON A/C NOT FOR ALL

Water Drain Valves - Component Location (ACT provision) ** ON A/C NOT FOR ALL

Tanks - Component Location ** ON A/C NOT FOR ALL

Water Drain Valves - Component Location ** ON A/C NOT FOR ALL

Leak Monitor ** ON A/C NOT FOR ALL

Tanks - Component Location (ACT(s) installed) ** ON A/C NOT FOR ALL

Water Drain Valves - Component Location (ACT(s) installed) ** ON A/C NOT FOR ALL

Tanks - Component Location (ACT provision) ** ON A/C NOT FOR ALL

Water Drain Valves - Component Location (ACT provision) ** ON A/C NOT FOR ALL

FIN	FUNCTIONAL DESIGNATION	PANEL	ZONE	ATA REF
** ON A/C ALL
21QM	VALVE-WATER DRAIN, L VENT SURGE TK		550	28-11-41
22QM	VALVE-WATER DRAIN, R VENT SURGE TK		650	28-11-41
** ON A/C NOT FOR ALL
23QM	VALVE-WATER DRAIN, L WING TK OUTR		540	28-11-41
24QM	VALVE-WATER DRAIN, R WING TK OUTR		640	28-11-41
** ON A/C ALL
25QM	VALVE-WATER DRAIN, L WING TK INR	540AB	540	28-11-41
26QM	VALVE-WATER DRAIN, R WING TK INR	640AB	640	28-11-41
94QM	VALVE-WATER DRAIN, L CTR TK	147AZ	141	28-11-41
95QM	VALVE-WATER DRAIN, R CTR TK	148AZ	142	28-11-41
** ON A/C NOT FOR ALL
174QM1	VALVE-WATER DRAIN NO 1, ACT1	826AR	150	28-10-00
175QM1	VALVE-WATER DRAIN NO 2, ACT1	826AR	150	28-10-00
185QM	LEAK MONITOR-ACT	826AR	152	28-10-00
190QM1	BAG ACT 1		150	28-10-00
** ON A/C NOT FOR ALL
190QM2	BAG ACT 2		150	28-10-00
** ON A/C NOT FOR ALL
214QM	CLACK VALVE	540RB	540	28-11-42
215QM	CLACK VALVE	640RB	640	28-11-42
216QM	CLACK VALVE	540RB	540	28-11-42
217QM	CLACK VALVE	640RB	640	28-11-42
** ON A/C NOT FOR ALL
226QM1	VALVE-WATER DRAIN, ACT1		152	28-21-52
226QM2	VALVE-WATER DRAIN, ACT2		152	28-21-52
254QM	LEAK MONITOR-ACT, AFT		152	28-10-00
255QM	LEAK MONITOR-PIPES, AFT ACT		152	28-10-00
259QM1	BAG ACT 1 A319CJ		150	28-10-00
259QM2	BAG ACT 2 A319CJ		150	28-10-00

** ON A/C NOT FOR ALL

3. System Description

A. LH and RH Wing Tanks

Tanks - Component Location ** ON A/C NOT FOR ALL

The fuel tanks and the vent surge tanks are between:

The front and the rear spars of the wing box
The wing top and bottom skins.

Ribs connect the front spar to the rear spar and divide the wing into compartments. Some of these ribs are sealed, thus divide the wing box into the different tanks. The tanks are located as follows:

The LH (RH) wing tank is between RIB1 and RIB22
The LH (RH) vent surge tank is between RIB22 and RIB26.

Access to the wing and vent surge tanks is possible through the access panels in the wing bottom skin (Ref. AMM D/O 57-27-00-00).

Tanks - Component Location ** ON A/C NOT FOR ALL

The fuel tanks and the vent surge tanks are between the front and the rear spars of the wing box, and the wing top and bottom skins. Ribs connect the front spar to the rear spar and divide the wing into compartments. Some of these ribs are sealed, and thus divide the wing box into the different tanks. The tanks are located as follows:

The LH(RH) wing tank (inner cell) is between RIB1 and RIB15
The LH(RH) wing tank (outer cell) is between RIB15 and RIB22
The LH(RH) vent surge tank is between RIB22 and RIB26.

Access to the wing and vent surge tanks is through the access panels in the wing bottom skin (Ref. AMM D/O 57-27-00-00).

Tanks - Component Location (ACT(s) installed) ** ON A/C NOT FOR ALL

Tanks - Component Location (ACT provision) ** ON A/C NOT FOR ALL

The fuel tanks and the vent surge tanks are between:

The front and the rear spars of the wing box
The wing top and bottom skins.

Ribs connect the front spar to the rear spar and divide the wing into compartments. Some of these ribs are sealed, thus divide the wing box into the different tanks. The tanks are located as follows:

The LH (RH) wing tank is between RIB1 and RIB22
The LH (RH) vent surge tank is between RIB22 and RIB26.

Access to the wing and vent surge tanks is possible through the access panels in the wing bottom skin (Ref. AMM D/O 57-27-00-00).

Tanks - Component Location (ACT(s) installed) ** ON A/C NOT FOR ALL

Tanks - Component Location (ACT provision) ** ON A/C NOT FOR ALL

The fuel tanks and the vent surge tanks are between:

The front and the rear spars of the wing box
The wing top and bottom skins.

Ribs connect the front spar to the rear spar and divide the wing into compartments. Some of these ribs are sealed, thus divide the wing box into the different tanks. The tanks are located as follows:

The LH (RH) wing tank is between RIB1 and RIB22
The LH (RH) vent surge tank is between RIB22 and RIB26.

Access to the wing and vent surge tanks is possible through the access panels in the wing bottom skin (Ref. AMM D/O 57-27-00-00).

B. Center Tank

The center tank is installed between:

The RIB1 (LH) and the RIB1 (RH)
The front spar FR36 and the rear spar FR42
The center wing top and bottom skin.

Access to the center tank is possible through the access panels in the rear spar (Ref. AMM D/O 57-10-00-00).

C. Additional Center Tanks

One ACT can be installed in the forward cargo compartment and two in the aft cargo compartment. The aircraft can operate with zero, one, two or three ACTs, as necessary. They are installed in their number sequence in the positions that follow:

ACT1 in the aft cargo compartment, between FR47.2 and FR47.5
ACT2 in the aft cargo compartment, between FR47.5 and FR50
ACT4.1 in the forward cargo compartment, between FR35.1 and FR35.4.

The ACT(s) is (are) connected to the center tank and to each other by refuel/transfer pipes and vent pipes. Blanks are installed on the pipe connections when the ACT(s) is (are) not installed. All the pipes have shrouds. The space between the pipes and the shrouds is drained and vented to the drain mast.

Each ACT is a rigid container which holds a flexible bladder tank (bag tank). The bottom of the rigid container is a pallet which has a cavity drain line and a connection for a water drain valve.

The bladder tank is attached by cord to the inner sides of the rigid container. The space (cavity) between the rigid container and the bladder tank, drains and vents to the drain mast through the cavity drain line. The bladder tank has a water drain valve and contains fuel system components for the:

Venting system (Ref. AMM D/O 28-12-00-00)
ACT fuel transfer system (Ref. AMM D/O 28-28-00-00)
Quantity indicating system (Ref. AMM D/O 28-42-00-00)
Level sensing system (Ref. AMM D/O 28-46-00-00).

The drain line from the ACT(s) has three leak monitors 253QM, 254QM and 255QM (Ref. AMM D/O 28-28-00-00). They are connected as follows:

253QM, to the cavity drain and pipe shroud drain-line from the forward ACT
254QM, to the cavity drain line from the aft ACT(s)
255QM, to the pipe shroud drain-line from the aft ACT(s).

The leak monitors keep a small quantity of drainage for a leak test of the fuel system.

Two ACTs can be installed in the aft cargo compartment. The aircraft can operate with zero, one or two ACTs, as necessary. They are installed in their number sequence in the positions that follow:

ACT AFT1, between FR47.2 and FR47.5
ACT AFT2, between FR47.5 and FR50.

Venting system (Ref. AMM D/O 28-12-00-00)
ACT fuel transfer system (Ref. AMM D/O 28-28-00-00)
Quantity indicating system (Ref. AMM D/O 28-42-00-00)
Level sensing system (Ref. AMM D/O 28-46-00-00).

The drain line from the ACT(s) has two leak monitors 254QM and 255QM (Ref. AMM D/O 28-28-00-00). They are connected as follows:

254QM, to the cavity drain line from the aft ACT(s)
255QM, to the pipe shroud drain-line from the aft ACT(s).

The leak monitors keep a small quantity of drainage for a leak test of the fuel system.

D. Additional Center Tanks

Two ACTs can be installed in the aircraft which can operate with zero, one or two ACTs as necessary. When the ACTs are not installed, the applicable pipe connections in the fuselage are sealed with caps.

When the ACTs are installed they are put in the aft cargo compartment in the positions that follow:

ACT1, between FR47.2 and FR47.5
ACT2, between FR47.5 and FR50.

ACT1 is connected to the center tank, and to ACT2 by refuel/transfer pipes and by vent pipes. Blanks are installed on the pipe connections when the ACT2 is not installed. All the pipes have shrouds to make sure that fuel does not go into the fuselage if leakage from the pipes occurs. The space between the pipes and the shrouds is drained and vented to the drain mast.

Each ACT is a rigid container which holds a flexible bladder tank (bag tank). The bladder tank holds the fuel and is attached by cord to the inner sides of the rigid container. The space (cavity) between the rigid container and the bladder tank, drains and vents to the drain mast through the cavity drain line. The bottom of the rigid container is a pallet which has cavity drain connections and water drain valve connections. There are two water drain valves in the tank which also contains fuel system components for the:

venting system (Ref. AMM D/O 28-12-00-00)
ACT fuel transfer system (Ref. AMM D/O 28-28-00-00)
quantity indicating system (Ref. AMM D/O 28-42-00-00)
level sensing system (Ref. AMM D/O 28-46-00-00).

The drain line from the ACT/s has two leak monitors 184QM and 185QM. They are connected as follows:

184QM, to the shroud drain pipe (Ref. AMM D/O 28-28-00-00)
185QM, to the ACT cavity drain pipe.

The leak monitors keep a small quantity of drainage for fuel leak analysis.

E. Water Drain Valves

Water Drain Valves - Component Location ** ON A/C NOT FOR ALL

Each tank has one or more water drain valves. They are used to:

Drain the water from the fuel in the fuel tanks
Drain all the remaining fuel from the tank (for maintenance).

Water Drain Valves - Component Location (ACT(s) installed) ** ON A/C NOT FOR ALL

Water Drain Valves - Component Location (ACT provision) ** ON A/C NOT FOR ALL

Each tank has one or more water drain valves. They are used to:

Drain the water from the fuel in the fuel tanks
Drain all the remaining fuel from the tank (for maintenance).

Water Drain Valves - Component Location (ACT(s) installed) ** ON A/C NOT FOR ALL

Water Drain Valves - Component Location (ACT provision) ** ON A/C NOT FOR ALL

Each tank has one or more water drain valves. They are used to:

Drain the water from the fuel in the fuel tanks
Drain all the remaining fuel from the tank (for maintenance).

The water drain valves are installed at the lowest part of each tank as follows:

outboard of RIB22 (vent surge tank drain)
outboard of RIB1 (wing tank drain)
inboard of RIB1 LH and RH (center tank drain).

The water drain valves are installed at the lowest part of each tank as follows:

outboard of RIB22 (vent surge tank drain)
outboard of RIB15 (wing-tank outer-cell drain)
outboard of RIB1 (wing-tank inner-cell drain)
inboard of RIB1 LH and RH (center tank drain).

The water drain valves are installed at the lowest part of each tank as follows:

Outboard of RIB22 (vent surge tank drain)
Outboard of RIB1 (wing tank drain)
Inboard of RIB1 LH and RH (center tank drain).

When the ACT(s) is (are) installed, the water drain valves are installed at the lowest part of each ACT as follows:

Between FR35.1 and FR35.2 (ACT4.1 drain)
Between FR47.2 and FR47.3 (ACT1 drain)
Between FR47.5 and FR48 (ACT2 drain).

One water drain valve is installed in a drain hole at the bottom of each bladder tank. ACT1, ACT2 and ACT4.1 each have two drain holes, one forward and one aft, connected by a double-walled channel. The water drain valve is installed in the forward drain hole and when operated, controls the flow from both drain holes.

The water drain valves are installed at the lowest part of each tank as follows:

Outboard of RIB22 (vent surge tank drain)
Outboard of RIB1 (wing tank drain)
Inboard of RIB1 LH and RH (center tank drain).

When the ACT(s) is (are) installed, the water drain valves are installed at the lowest part of each ACT as follows:

Between FR47.2 and FR47.3 (ACT AFT1 drain)
Between FR47.5 and FR48 (ACT AFT2 drain).

One water drain valve is installed in a drain hole at the bottom of each bladder tank. ACT AFT1 and ACT AFT2 each have two drain holes, one at the forward and one at the aft of the ACT connected by a double-walled channel. The water drain valve is installed in the forward drain hole and when operated, it controls the flow from both drain holes.
The water drain valves are installed at the lowest part of each tank as follows:

outboard of RIB22 (vent surge tank drain)
outboard of RIB1 (wing tank drain)
inboard of RIB1 LH and RH (center tank drain).

When the ACT/s is/are installed there also water drain valves:

aft of FR47.2 and forward of FR47.5, one on each side of the aircraft center line (ACT1 drain)
aft of FR47.5 and forward of FR50, one on each side of the aircraft center line (ACT2 drain).

F. Clack Valves

Tanks - Component Location ** ON A/C NOT FOR ALL

Clack valves are at the bottom of the RIB2 and the RIB22.

Tanks - Component Location ** ON A/C NOT FOR ALL

Clack valves are at the bottom of the RIB2.
The clack valves in the RIB2 let the fuel enter the area between RIB1 and RIB2 but do not let fuel outboard of the RIB2. This makes sure that the main fuel pumps are always in fuel (Ref. AMM D/O 28-21-00-00).
The clack valves in the RIB22 let the fuel that has entered the vent surge tanks return to the related wing tank. The clack valves do not let fuel enter the vent surge tanks from the wing tanks (Ref. AMM D/O 28-12-00-00).

** ON A/C NOT FOR ALL

4. Power Supply
Not applicable

** ON A/C NOT FOR ALL

5. Interfaces
Not applicable

** ON A/C NOT FOR ALL

6. Component Description

A. Water Drain Valve FIN: 21-QM FIN: 22-QM FIN: 23-QM FIN: 24-QM FIN: 25-QM FIN: 26-QM FIN: 94-QM FIN: 95-QM
21QM(22QM), 25QM(26QM), 94QM, 95QM

Water Drain Valves - Component Location ** ON A/C NOT FOR ALL

The primary components are:

the body, which has a mounting flange
a remote inlet (wing-tank water drain only)
an outer valve and spring
an inner valve and spring
a support guide.

21QM(22QM), 23QM(24QM), 25QM(26QM), 94QM, 95QM

Water Drain Valves - Component Location ** ON A/C NOT FOR ALL

The primary components are:

the body, which has a mounting flange
a remote inlet (wing-tank water drain only)
an outer valve and spring
an inner valve and spring
a support guide.

B. Water Drain Valve (aircraft with ACT provision)
21QM(22QM), 23QM(24QM), 25QM(26QM), 94QM, 95QM

Water Drain Valves - Component Location (ACT provision) ** ON A/C NOT FOR ALL

The primary components of a water drain valve are:

A body with a mounting flange
An inlet (wing-tank water drain only)
An outer valve and a spring
An inner valve and a spring
A support guide.

21QM(22QM), 25QM(26QM), 94QM, 95QM

Water Drain Valves - Component Location (ACT provision) ** ON A/C NOT FOR ALL

The primary components of a water drain valve are:

A body with a mounting flange
An inlet (wing-tank water drain only)
An outer valve and a spring
An inner valve and a spring
A support guide.

C. Water Drain Valve (aircraft with ACT(s) installed)
21QM(22QM), 23QM(24QM), 25QM(26QM), 94QM, 95QM, 226QM1, 226QM2, 226QM3, 226QM4, 226QM5, 226QM6

Water Drain Valves - Component Location (ACT(s) installed) ** ON A/C NOT FOR ALL

The primary components of a water drain valve are:

A body with a mounting flange
An inlet (wing-tank water drain only)
An outer valve and a spring
An inner valve and a spring
A support guide.

21QM(22QM), 25QM(26QM), 94QM, 95QM, 226QM1, 226QM2

Water Drain Valves - Component Location (ACT(s) installed) ** ON A/C NOT FOR ALL

The primary components of a water drain valve are:

A body with a mounting flange
An inlet (wing-tank water drain only)
An outer valve and a spring
An inner valve and a spring
A support guide.

D. Water Drain Valve

Water Drain Valves - Component Location ** ON A/C NOT FOR ALL

21QM(22QM) in the vent surge tank
25QM(26QM) in the wing tank
94QM(95QM) in the center tank
174QM1(175QM1) in the ACT1 (when installed)
174QM2(175QM2) in the ACT2 (when installed).

The primary components of a water drain valve are:

the body, which has a mounting flange
a remote inlet (wing-tank water drain only)
an outer valve and spring
an inner valve and spring
a support guide.

The mounting flange connects the valve to the aircraft skin. The body contains the inner and outer valves and springs. The outer valve is installed in the inner valve and the springs keep the two valves in the closed position. The support guide keeps the two valves aligned when they operate. The remote inlet has a short pipe connected to it, which goes to the lowest part of the fuel tank.

The mounting flange connects the water drain valve to:

The aircraft skin (wing and center tanks)
The ACT(s) (if installed).

The body contains the inner and outer valves and the springs. The springs keep the two valves in the closed position. The support guide keeps the two valves aligned when they operate. The inlet has a short pipe connected to it which goes to the lowest part of the fuel tank.

The water drain valves in the center tank and the vent surge tanks do not have a remote inlet. Thus they only drain their adjacent area.

The water drain valves in the center tank, the vent surge tanks and the ACT(s) (when installed) do not have inlets. Thus they only drain their adjacent area.

The water drain valves in the center tank, the vent surge tanks and the ACT/s (when installed) do not have a remote inlet. Thus they only drain their adjacent area.

E. ACT Bag
259QM1, 259QM2, 259QM3, 259QM4, 259QM5, 259QM6
For each installed ACT, the flexible bladder tank is a synthetic rubber bag installed in a rigid container. Cord attachments attach the bag to the rigid container until the bag does not fall below its weight.
An inward pressure relief-valve (Ref. AMM D/O 28-12-00-00) is installed in the top wall of the tank bag. The valve prevents high pressure differentials across the tank bag during descent.
259QM1, 259QM2
For each installed ACT, the flexible bladder tank is a synthetic rubber bag installed in a rigid container. Cord attachments attach the bag to the rigid container until the bag does not fall below its weight.
An inward pressure relief-valve (Ref. AMM D/O 28-12-00-00) is installed in the top wall of the tank bag. The valve prevents high pressure differentials across the tank bag during descent.

F. ACT Bag
190QM1 and 190QM2 (when the ACT/s is/are installed)
For each ACT, the flexible bladder tank is a synthetic rubber bag installed in a rigid container. Cord attachments attach the bag to the rigid container so that the bag does not fall under its own weight.
An inward pressure relief valve (Ref. AMM D/O 28-12-00-00) is installed in the top wall of the tank bag. The valve prevents high pressure differentials across the tank bag during descent.

G. ACT Leak Monitor (185QM)

Leak Monitor ** ON A/C NOT FOR ALL

The leak monitor connects to the drain line from the ACT/s.
A spur pipe connects the leak monitor to the drain line. A manually operated check valve is installed on the end of the spur pipe. The check valve lets a sample be removed to show if there is any fuel leakage from the ACT bag/s. To operate the valve the valve piston must be pushed in. This lifts the check valve and lets the fluid flow through the outer valve assembly.

When the ACT/s is/are not installed the applicable pipe connections in the fuselage are sealed caps.

** ON A/C NOT FOR ALL

7. Operation/Control and Indicating
The operation of the tanks is fully automatic. There is no control of the vent system and it gives no indications.

** ON A/C NOT FOR ALL

8. BITE Test
Not applicable

[Rev.10 from 2021] 2026.04.02 07:01:07 UTC