Fuel Description

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : 055-055 Rev. Date : Nov 01, 2017 28-00-00 PB 001 CONF 00 - FUEL - GENERAL - DESCRIPTION AND OPERATION

** ON A/C ALL 28-00-00 PB 001 CONF 00 - FUEL - GENERAL - DESCRIPTION AND OPERATION

1. General Critical Design Configuration Control Limitations (CDCCL) Some procedures identify a fuel system item that is in a category known as a Critical Design Configuration Control Limitation (CDCCL). This category is applicable to items that are identified as the possible source of ignition of fuel in a fuel tank. You must keep CDCCL items in a serviceable condition. It is possible that damage, wear or changes to a CDCCL item can cause a fuel tank explosion. CDCCL items are identified by a WARNING in the procedures where they occur. When a procedure identifies a CDCCL item, it is a mandatory condition that you do the instruction correctly and accurately as the procedure tells you. A. De Desc scri ript ptio ion n The fuel system: · keeps the fuel fuel in the main fuel tanks tanks and the center tank, tank, which are open open to atmosphere atmosphere through the vent vent surge tanks · controls controls and supplies supplies the fuel in the correct correct quantities quantities to the fuel tanks tanks during during refuel operations operations · supplies supplies the fuel to to the engines engines for thrust thrust and to cool cool · supplies supplies the fuel to to the Auxilia Auxiliary ry Power Power Unit Unit (APU) (APU) · supplies supplies the fuel to cool, cool, the excess fuel fuel decreases decreases the temperature temperature of the engines engines and the Integrated Integrated Drive Generators oil · gives indicat indications ions in the cockpit cockpit of the the usual system operation operation · gives indicatio indications ns in the cockpit cockpit of the failures failures that could cause cause an unusual conditio condition. n. 2. Co Comp mpone onent nt Loca Locati tion on ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 (Ref. Fig. Fuel System - Wing and Center Tank)

Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. DOCUMENT.

Page 1 of 32


LEGEND M

VALVE ACTUATOR (SINGLE MOTOR)

S

SOLENOID OPERATED VALVE DIRECTION OF FLOW)

CLACK VALVE ( M M

VALVE ACTUATOR (TWIN MOTOR) OVERPRESSURE PROTECTOR FLOAT VALVE

MAGNETIC FUEL LEVEL INDICATOR (MLI) VENT SYSTEM FUEL DRAIN VALVE PRESSURE RELIEF VALVE

WATER DRAIN VALVE CHEC CHECK K VAL VALVE VE (

DIRE DIRECT CTIO ION N OF FLOW FLOW))

FUEL QUANTITY INDICATOR PROBE JET PUMP T

TEMPERATURE SENSOR DIFFUSER HIGH LEVEL SENSOR REFUEL/DEFUEL COUPLING R/H STANDARD L/H OPTIONAL

LOW LEVEL SENSOR CADENSICON

SENSOR

REFUEL VALVE

AIR INLET VALVE

OVERWING REFUEL ADAPTOR

RIB 11

RIB 14

RIB 16 WING TANK

FUEL VENT PROTECTOR

RIB 13

RIB 15

RIB 17 RIB 19 RIB 21

RIB 22

RIB 27

RIB 25

RIB 23

REFUEL SPILL PIPE

PRESSURE HOLDING VALVE

N_MM_280000_0_NZM0_01_00

Figure 28-00-00-15000-00-E / SHEET 1/4 - Fuel System - Wing and Center Tank ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. DOCUMENT.

Page 2 of 32


LEGEND M

VALVE ACTUATOR (SINGLE MOTOR)

S

SOLENOID OPERATED VALVE DIRECTION OF FLOW)

CLACK VALVE ( M M

VALVE ACTUATOR (TWIN MOTOR) OVERPRESSURE PROTECTOR FLOAT VALVE

MAGNETIC FUEL LEVEL INDICATOR (MLI) VENT SYSTEM FUEL DRAIN VALVE PRESSURE RELIEF VALVE

WATER DRAIN VALVE CHEC CHECK K VAL VALVE VE (

DIRE DIRECT CTIO ION N OF FLOW FLOW))

FUEL QUANTITY INDICATOR PROBE JET PUMP T

TEMPERATURE SENSOR DIFFUSER HIGH LEVEL SENSOR REFUEL/DEFUEL COUPLING R/H STANDARD L/H OPTIONAL

LOW LEVEL SENSOR CADENSICON

SENSOR

REFUEL VALVE

AIR INLET VALVE

OVERWING REFUEL ADAPTOR

RIB 11

RIB 14

RIB 16 WING TANK

FUEL VENT PROTECTOR

RIB 13

RIB 15

RIB 17 RIB 19 RIB 21

RIB 22

RIB 27

RIB 25

RIB 23

REFUEL SPILL PIPE

PRESSURE HOLDING VALVE

N_MM_280000_0_NZM0_01_00


Page 2 of 32


SEQUENCE VALVES STRAINER MAIN FUEL PUMPS

RIB 2

CENTER TANK VENT PIPE

ENGINE C/L

FUEL SUPPLY PIPE

AIR RELEASE VALVE

SUCTION VALVE

LP VALVE

T

M M RIB 1

RIB 4 RIB 6 RIB 8

FUEL DRAIN VALVE

STRAINER

MAIN FUEL PUMP PRESSURE SWITCH

REFUEL GALLERY RIB 11

RIB 9

N_MM_280000_0_NZM0_02_00


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RIB 14

RIB 15

RIB 16

M

RIB 17

M

FROM TH E

MAIN FUEL PUMPS

M

WING TANK VENT DUCT

FROM TH E SURGE TANK

N_MM_280000_0_NZM0_03_00

Figure 28-00-00-15000-00-E / SHEET 3/4 - Fuel System - Wing and Center Tank ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 32


C/L

CENTER TANK FUEL PUMP

CENTER TANK FUEL PUMP

STRAINER

STRAINER

CENTER TANK

M

APU

AP U

LP

FUEL

VALVE

CENTER TANK FUEL PUMP PRESSURE SWITCH

M

MM

APU FUEL PUMP PRESSURE SWITCH

M

M

S

DEFUEL TRANSFER VALVE

PUMP CROSSFEED VALVE

REFUEL VALVE

CENTER TANK FUEL PUMP PRESSURE SWITCH

N_MM_280000_0_NZM0_04_00

Figure 28-00-00-15000-00-E / SHEET 4/4 - Fuel System - Wing and Center Tank ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 32


** ON A/C ALL

** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 (Ref. Fig. Fuel System Control Switches SHEET 1)

Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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A

A

FUEL CONTROL PANEL

40VU

X FEED ENG 1

F U E

L

ENG 2

AP U

F U E

OPEN ON L

TK

CTR TK

P UM P S

CTR TK

1

2

FAULT

FAULT

FAULT

FAULT

O FF

O FF

O FF

M AN

PUMP 1

A U T O

R

TK

P UM P S

1

2

FAU LT

FAULT

FAULT

O FF

O FF

OF F

PUMP 2

MODE SEL

L

N_MM_280000_0_PPM0_01_00

Figure 28-00-00-15700-00-C / SHEET 1/1 - Fuel System Control Switches ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 32


** ON A/C ALL

(Ref. Fig. Engine and APU Fire Buttons and Engine Start Switches SHEET 1)


Page 8 of 32


A

B

A

B

N_MM_280000_0_SGM0_01_00

Figure 28-00-00-16000-00-A / SHEET 1/1 - Engine and APU Fire Buttons and Engine Start Switches ** ON A/C ALL Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 32


** ON A/C 016-022, 024-150, 206-206, 208-209, 215-216, 221-250, 350-350 (Ref. Fig. ECAM Displays and Control Panel SHEET 1)


Page 10 of 32


A ENGINE/WARNING DISPLAY - EXAMPLE

A A FLOOR

C

B

B

o

B

IDLE

o

TOGA

72 0

EGT °C

SYSTEM DISPLAY UNIT

FOB: 14360

F.USED 1+2 6200

3100

KG

EWD2

A LOCK S

F LOCKED F

2

10

TO

1

102.5

100.8

102.5

FUEL

72 0

EGT °C

N2 % +

C

108.6%

60.0

1.282

FF KG/H 2250

10

5

E PR

N1 MODE

IGNITION ON SIGNS ON SPLRS ON FLAPS T.D AUTO BRK MAX

2 3100

KG APU

LO 750

-11

5030

°C

F.FLOW 1+2

FOB

: :

LO 2800

10

FUEL SYSTEM PAGE EXAMPLE

5030

10

°C

75 0

-11

650 KG/MN

FUEL SYSTEM PAGE PUSHBUTTON SWITCH

14360 KG

B ECAM

N_MM_280000_0_FKM0_01_00

Figure 28-00-00-16100-00-J / SHEET 1/1 - ECAM Displays and Control Panel ** ON A/C 016-022, 024-150, 206-206, 208-209, 215-216, 221-250, 350-350 Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 32


** ON A/C ALL

** ON A/C 016-022, 024-150, 201-201, 203-203, 205-250, 350-350

EMB SB 31-1211 for A/C 219-220 (Ref. Fig. Refuel/Defuel Control Panel 800VU SHEET 1)


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A

REFUEL COUPLING

REFUEL/DEFUEL CONTROL PANEL

A

FUEL QTY

kg x 1000 INDICATOR C TR

LEFT

RIGHT

6Q T

LVL.

HI.

C TR

LEFT

RIGHT

REFUEL VALVES

MODE

OPEN

OPEN

OPEN

NORM

NORM

NORM

SHUT

SHUT

SHUT

SELECT

TEST

HI. LVL

REFUEL

BATT POWER ON

REFUEL DEFUEL CONTROL PANEL

800VU

O FF

DEFUEL XFR PRESELECTED

OPEN

LTS

R E F U E L

NORM

ACTUAL

kg x 1000

DEC

INC C K P T

E ND

PRESELECTOR

5Q T

N_MM_280000_0_SLM0_01_00

Figure 28-00-00-16700-00-A / SHEET 1/1 - Refuel/Defuel Control Panel 800VU ** ON A/C 016-022, 024-150, 201-201, 203-203, 205-250, 350-350 | EMB SB 31-1211 for A/C 219-220 Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 32


** ON A/C ALL


Page 14 of 32


3. System Description A. Storage (Ref. 28-10-00) The storage system: · contains the fuel for the engines and the APU · helps to protect the fuel system against fire · gets the warm fuel from the IDGs and returns it to the wing tanks · keeps the air pressure in the fuel system near to the external air pressure. (1) Tanks (Ref. AMM D/O 28-11-00-00) The fuel is kept in the fuel tanks that follow: · the LH wing tank · the RH wing tank · the center tank (if installed) · the Additional Center Tank(s) (ACT(s)) (if installed). Each wing contains a vent surge tank. The vent surge tanks are installed outboard of each wing tank. The vent surge tanks temporarily hold the fuel so that leakage does not occur during: · aircraft movement on the ground · aircraft rotation at take-off. All the fuel tanks and the surge tanks have water drain valves at their lowest point. After a refuel operation to the maximum tank capacity, the fuel can expand 2% (20 deg.C (36 deg.F) temperature increase) without leakage at the refuel attitude and during: · subsequent towing · aircraft movement on the ground · take-off. (2) Tank Venting System (Ref. AMM D/O 28-12-00-00) The tank venting system makes sure that the air pressure in the fuel tanks (and the vent surge tanks) keeps near to the external air pressure. The system prevents a large difference between these pressures, which can cause damage to the fuel tank/aircraft structure. This is most important: · during the refuel or defuel operations · when the aircraft climbs or descends. The vent surge tanks keep their related fuel tank open to the external air pressure. That is: · the LH vent surge tank for the LH wing tank and the center tank (if installed) · the RH vent surge tank for the RH wing tank. If a blockage occurs to the flow of air through the vent surge tank, a burst disk keeps the pressure to a specified limit. The flame arrestors in the vent system intakes give protection against ground fires. The fuel system is protected from the effects of lightning through: · the position of the vent intakes (which are outside lightning-strike zones 1 and 2 in the wing) · the thickness of the wing skins. (3) Center Tank External Ventilating System (Ref. AMM D/O 28-13-00-00) The center-tank external ventilating-system makes sure that fuel and/or fuel gas (that comes out of the center tank) does not go into the air conditioning system (Ref. AMM D/O 21-00-00-00) . (4) intercell Transfer System (Ref. AMM D/O 28-15-00-00) The intercell transfer system controls the movement of fuel from the wing-tank outer cell to the wingtank inner cell. Each wing tank has two intercell transfer valves in the bottom of the RIB15. Each intercell transfer valve has a related actuator that controls the position of the valve. The Fuel Level Sensing Control Units (FLSCUs) (Ref. AMM D/O 28-46-00-00) , give an open or shut signal to the actuators of


Page 15 of 32


the intercell transfer valve. The FLSCUs will signal the actuators to open their related valves when the low level sensors of the related wing tank inner cell become dry. (5) Fuel Recirculation for Cooling (Recirculation System) (Ref. AMM D/O 28-16-00-00) Part of the fuel supply to each engine is used for the IDG cooling-system (Ref. AMM D/O 24-21-00-00) . During the oil cooling process this fuel becomes warm. The recirculation system returns the warm fuel from the IDG cooling system to the wing tank. The Full Authority Digital Engine Control (FADEC) system (Ref. AMM D/O 73-20-00-00) stops the recirculation system if: · the fuel temperature increases to a high level · the fuel flow rate to the engine is at a high level · the engines have a gravity fuel feed only · the fuel level in the wing tanks is low · the fuel goes into a vent surge tank. B. Distribution (Ref. 28-20-00) The distribution system makes sure that the fuel: · is supplied to the two engines during all flight conditions · is supplied to the APU · can be isolated from an engine or the APU when necessary · is in the correct (and safe) configuration for flight · can be supplied to, and removed from, the aircraft. C. Distribution (Ref. 28-20-00) ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 (1) Main Fuel Pump System (Ref. AMM D/O 28-21-00-00)

There are two fuel pumps in each wing tank and two in the center tank. The fuel pumps operate together to supply fuel to their related engine. Fuel is supplied to the engines in the sequence: · center tank fuel · wing tank fuel. If one or two of the fuel pumps has a failure, or is set to OFF, the other(s) continue(s) to supply fuel to its related engine. If the crossfeed system (Ref. AMM D/O 28-23-00-00) is used, the fuel pumps can also supply fuel to the other engine. The wing tank fuel pumps also take fuel from the related wing tank and pass it through two jet pumps in the related wing tank outer cell. This flow of fuel causes the jet pumps to remove the fuel from the surge tank and the bottom of the wing tank outer cell. This fuel is then moved to one of the related intercell transfer valves. ** ON A/C ALL (2) APU Fuel-Pump System (Ref. AMM D/O 28-22-00-00) The APU fuel pump is on the rear spar of the center wing section. The APU fuel pump supplies the fuel to the APU (Ref. AMM D/O 49-30-00-00) . The APU fuel pump uses the fuel supplied from the LH wing tank. (3) Crossfeed System (Ref. AMM D/O 28-23-00-00) The valve of the crossfeed system is usually closed, and in this configuration it divides the main fuel pump system (Ref. AMM D/O 28-21-00-00) into two parts (one part for each engine). When the crossfeed valve is open, the two fuel supplies are connected together. Thus the two engines can be supplied with fuel from one of the wings or from the two wings. (4) Engine LP Fuel Shut Off (Ref. AMM D/O 28-24-00-00) The fuel flow to each engine goes through a related Low Pressure (LP) fuel valve. When necessary the LP valve isolates its engine from the fuel. The operation of the LP valve is controlled by: · the related ENG MASTER switch (Ref. AMM D/O 76-12-00-00) · the related engine FIRE PUSH switch (Ref. AMM D/O 26-12-00-00) . (5) Refuel/Defuel System (Ref. AMM D/O 28-25-00-00) The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. It is controlled by the:


Page 16 of 32


· · · · ·

control panel 800VU control panel 801VU (if installed) fuel quantity preselector 5QT fuel quantity indicator 6QT (if installed) cockpit fuel quantity preselector 10QT (if installed)

The control panels 800VU and 801VU include indicators and selector switches. The applicable indicators and switches on control panel 801VU do not operate if there is no ACT installed. A single refuel/defuel is the interface between the fuel tanks and the external fuel supply. To fill the fuel tanks to their maximum capacity, the aircraft must be level. It is possible to refuel the aircraft when it is at 2 degrees, or less, from level (but it is not possible to get the maximum capacity). The fuel supply to each fuel tank during an automatic refuel is controlled by the Fuel Quantity Indicating Computer (FQIC) (Ref. AMM D/O 28-42-00-00) . The fuel supply to each fuel tank during a manual refuel is controlled by: · the refuel/defuel control panel 800VU, for the wing tanks (and center tanks if installed) · the refuel/defuel control panel 801VU, for the ACT(s) (if installed). Defuel The main fuel pump system (Ref. AMM D/O 28-21-00-00) is used to defuel the aircraft. The pumps remove the fuel from the related wing tank and supply it to the refuel/defuel coupling. The defuel/transfer valve and the crossfeed valve (Ref. AMM D/O 28-23-00-00) must be open to defuel the aircraft. Defuel of the Center (Transfer) Tank (if installed) To defuel the center (transfer) tank the main transfer system (Ref. AMM D/O 28-26-00-00) must be used to move the fuel to the related wing tank. Defuel of the ACT(s) (if installed) Fuel in the ACT(s) must be moved to the center tank. The fuel is moved by operation of the transfer pump in the ACT transfer system (Ref. AMM D/O 28-28-00-00) . (7) APU LP Fuel Shut Off (Ref. AMM D/O 28-29-00-00) The APU LP fuel shut off valve controls the fuel supply from the fuel tank to the APU. When necessary the valve isolates the APU from its fuel supply. The operation of the APU LP valve is controlled by: · the APU MASTER SW (Ref. AMM D/O 49-42-00-00) · the APU SHUT OFF switch (Ref. AMM D/O 49-62-00-00) · the APU FIRE switch (Ref. AMM D/O 26-13-00-00) . D. Indicating (Ref. 28-40-00) The indicating system has: · the Fuel Quantity Indicating (FQI) system, which gives separate and total fuel quantity indications · the Magnetic Level Indicators (MLI), a secondary system used to estimate the fuel quantity when the aircraft is on the ground · the tank level sensing, which gives indications and warnings when the fuel is at specified levels · the fuel temperature measurement, which gives continuous temperature indications and warnings when the fuel temperature is at specified levels. (1) Quantity Indicating (Ref. AMM D/O 28-42-00-00) The FQI system measures the total quantity of fuel in the range unusable to overflow. It gives indications for these fuel tanks: · the LH and RH wing tanks · the center tank (if installed)


Page 17 of 32


· the ACT(s) (if installed). The system has FQI probes that the FQIC monitors. The FQIC uses signal conditioning to calculate the quantity of fuel in each fuel tank. The FQIC gives fuel quantity data to: · the Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) FUEL Page, which together make up the ECAM · the multi-tank fuel quantity indicator (6QT) (if installed) · the fuel quantity preselector (5QT) · the cockpit preselector (10QT) (if installed). The FQIC uses the fuel quantity data to control an automatic refuel operation to below high level (Ref. AMM D/O 28-46-00-00) . The FQIC monitors a diode within the probes 22QT1(22QT2) and 33QT1(33QT2) in the wing tanks. The FQIC uses signal conditioning to calculate the temperature of the fuel adjacent to these diodes. The fuel temperature is displayed on the System Display (SD) FUEL Page. (2) Magnetic Level Indicators (Ref. AMM D/O 28-43-00-00) The MLIs are a secondary direct-reading system used to calculate the fuel quantity in the LH wing, RH wing and center tanks (when the A/C is on the ground). It is not necessary to have electrical power to use the indicators. The combined MLI indications, aircraft attitude and fuel relative density, are converted with tables (Ref. 12-11-28) to give the amount of fuel in each tank. ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 (3) Tank Level Sensing (Ref. AMM D/O 28-46-00-00) The tank level sensing system monitors the level of fuel in: · the LH(RH) surge tank · the LH(RH) wing tank · the center tank · the ACT(s) (if installed). The tank level sensing system also monitors the temperature of the fuel in the LH(RH) wing tank.

The system has level sensors that the FLSCUs continuously monitor. The FLSCUs uses signal conditioning to find if the sensor is wet or dry. The FLSCUs use the fuel level data to: · control the operation of the intercell transfer system (Ref. AMM D/O 28-15-00-00) · control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00) · control the operation of the main fuel pump system (Ref. AMM D/O 28-21-00-00) · transmit fuel level data to the ACT transfer-control circuit (Ref. AMM D/O 28-28-00-00) (if installed) · transmit fuel level warnings to the Engine/Warning Display (EWD) (Ref. 31-66-00) · control high level shut-off for automatic and manual refuel (Ref. AMM D/O 28-25-00-00) . The tank level sensing system has temperature sensors in the wing tanks. The FLSCU uses signal conditioning to calculate the temperature of the fuel adjacent to the sensor. The FLSCU uses the temperature data from the wing tanks to control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00) . ** ON A/C ALL 4. Power Supply (Ref. Fig. Fuel System - Electrical Symbols)


Page 18 of 32


SYMBOL

SIGNIFICATION

SYMBOL

SIGNIFICATION

POSITIVE POLARITY

BUSBAR - SINGLE PHASE

NEGATIVE POLARITY AIRCRAFT STRUCTURE GROUND CONNECTION

BUSBAR - THREE PHASE CHASSIS OR FRAME CONNECTION INSIDE EQUIPMENT ONLY

A B C

CROSS REFERENCE ON SAME DIAGRAM

INDUCTOR - GENERAL

2

NOTE - WITH SPECIFIED REFERENCE ON SAME DRAWING

SWITCH - SINGLE POLE TWO WAY

2.

NOTE - WITH GENERAL REFERENCE

1

GENERAL WIRING (ANALOG)

CONDUCTORS THAT DO NOT CONNECT

SWITCH - DOUBLE POLE TWO WAY SWITCH - PUSH ON, SPRING RETURN SWITCH - PUSH ON, SPRING RETURN, TWO CIRCUITS

CONNECTION OF CONDUCTORS

CONTACTOR (CONTACTS ONLY)

DIRECTION OF SIGNAL FLOW

MECHANICAL CONNECTION

12

SWITCH - FOUR POLE, THREE WAY (SHOWN IN MECHANICAL CENTER POSITION)

DATA BUS (ONE WAY, TWELVE CONDUCTORS) DATA BUS (TWO WAY)

SWITCH - MECHANICALLY OPERATED CIRCUIT BREAKER

COMPONENT CONTOUR (COMPONENT IN HOME DRAWING)

COMPONENT CONTOUR (COMPONENT NOT IN HOME DRAWING)

CIRCUIT BREAKER WITH AUXILIARY CONTACTS

THREE-PHASE CIRCUIT BREAKER WITH AUXILIARY CONTACTS

RELAY

N_MM_280000_0_GCM0_01_00

Figure 28-00-00-26000-00-A / SHEET 1/2 - Fuel System - Electrical Symbols ** ON A/C ALL Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 19 of 32


SIGNIFICATION

SYMBOL

TRANSFORMER - TWO PRIMARY WINDINGS

SYMBOL

SIGNIFICATION

TIME DELAY RELAY (DELAY ON CLOSING)

FILAMENT

PRESSURE SWITCH

DIODE DC MOTOR

AMPLIFIER

EXTERNAL POWER RECEPTACLE

GEN

1

GENERATOR

3 PHASE MOTOR

300S

TIME DELAY RELAY (DELAY ON OPENING)

TIME DELAY RELAY (DELAY ON OPENING) 120S TDO

N_MM_280000_0_GCM0_02_00

Figure 28-00-00-26000-00-A / SHEET 2/2 - Fuel System - Electrical Symbols ** ON A/C ALL Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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(Ref. Fig. Fuel System - Electrical Power Supplies)


Page 21 of 32


A 2XP

AC BUS 2

GEN 2 9XU2

GLC2 4000XU

202XP

11XU2 1XN2

BTC-2

204XP

2XC APU GEN

8QA FUEL R IGHT WING TK /PUMP 2 SPLY

2XN2

B

7QA FUEL LEFT WING TANK PUMP 2 SUPPLY

30QA FUEL CENTER TANK

3XS GLC-APU

C

PUMP 2 SUPPLY

2PU2

14PU

8XS

3XC 3XC2

3XG

3XC1

EPC 20XG RCPT-

1PU2 TR-2

1XX

EXT PWR

14XX 101XP

1XC

103XP

11XU1 3XN1

BTC-1

2QA FUEL RIGHT WING TANK PUMP 1 SUPPLY

1XN1

1QA FUEL LEFT WING TANK PUMP 1 SUPPLY

29QA FUEL CENTER TANK PUMP 1 SUPPLY

GEN 1

AC BUS 1

D

1XP

9XU1

E

GLC1 4000XU

2PU1 12QA R WING TK/PUMP 1 STANDBY

1PU1 TR-1

F

11QA L WING TK/PUMP 1 STANDBY G 15XE 15XE1 15XE2

H

EMERG GEN

2XE GLC EMERG

8XE

4PE

4PC

3PE 1PE TR-ESS

J

8PH

1PC1 DC ESS

4PP

DC SHED ESS

8PP

801PP

401PP

K

2QG FUEL/LP VALVE/MOTOR 1/ENG 2

1QP FUEL/R WING/No 1XFR VLV SPLY

1QG FUEL/LP VALVE/MOTOR 1/ENG 2

2QP FUEL/R WING/No 1XFR VLV SPLY

55QA FUEL/SMOKE/CONFIG/PUMP CTL

2QE FUEL/X FEED/VALVE/MOTOR 1 1QT FUEL/FQI/CHANNEL/1

L

N_MM_280000_0_QJM0_01_00

Figure 28-00-00-24500-00-E / SHEET 1/3 - Fuel System - Electrical Power Supplies ** ON A/C ALL Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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A

M

N

5PU2

3XB

DC BUS 2

28 115 B

2PP

5XB

STAT INV

6PH

1PN2

1QC APU FUEL BLOW OFF CTL

11PB

2XB

12XB 901XP

202PP

10QA FUEL/PUMPS/2/R CTL AND L IND

301PP

2QF APU FUEL LP VALVE SPLY

206PP

1QE FUEL/X FEED/VALVE/MOTOR 2

C BATT BUS

3PP 1PC2 6PN

3QG FUEL/LP VALVE/MOTOR 2/ENG 1 4QG FUEL/LP VALVE/MOTOR 2/ENG 2 3QP FUEL/L WING No 2 XFR VLV SPLY

6PB2

4QP FUEL/R WING No 2 XFR VLV SPLY P 2QT FUEL/FQI/CHAN/2

BAT 2 2PB2

801XP 6PB1 2QC APU FUEL BLOW OFF PUMP

BAT 1 2PB1

204PP 3PN2

32QA FUEL/CENTER TK/PUMP 2 CTL/ CENTER TK/PUMP 1 IND

AC SHED ESS BUS 8XP 8XH

9QA FUEL/PUMPS/2/L CTL AND R IND

47QA FUEL/CENTER TK/AUTO CTL

12PB1 Q

D

AC ESS BUS 4XP

701PP 5PB1

E

DC BUS 1

3QC APU FUEL LP VALVE CTL

1PP

5PU1

F G

101PP

4QA FUEL/PUMPS/1/R CTL AND L IND

1PN1 H

103PP

J

3PN1 3QC APU FUEL PUMP CTL 3QA FUEL/PUMPS/1/L CTL AND R IND 31QA FUEL/CENTER TK/PUMP 1 CTL/ CENTER TK/PUMP 2 IND

R

K

S

L

T N_MM_280000_0_QJM0_02_00


Page 23 of 32


M N

3PX

DC SERVICE BUS

6PP 12PR-RELAY 24-67-00

601PP

8PN

2PR

11PR-RELAY 24-67-00

1QU FUEL/RFL/DFL/ XFR/DEFUEL/VALVE

P

501PP

FUELLING BUS 1

5PR RELAYREFLNG NORM/BAT

3QU-SW MODE SELECT/REFUEL /OFF/DEFUEL / XFR 28-25-00

1QJ FUEL/HI/ LVL/SPLY 2QU FUEL/RFL/ DFL/SPLY

8QT FUEL/FQI/CHANNEL /1 AND 2 FUELLING BUS 2 502PP

8PR RELAYREFLNG BUS 501PP CTL 1P R

Q 4PR

NORM BATT

OPEN SHUT

10PR SWBATTERY POWER/ ON/NORM 24-67-00

6GA LEVERL/G NORM CTL

32-31-00

R

20QU MSWREFUEL/DEFUEL CTL PNL DOOR POSITION 28-25-00

TO FQIC 28-42-00

S

T

9QT RELAYFQI PWR SPLY C/O 28-42-00

N_MM_280000_0_QJM0_03_00


Page 24 of 32


5. Interfaces ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 (Ref. Fig. Fuel System - Interfaces SHEET 1)


Page 25 of 32


ENGINE/ WARNING DISPLAY

MASTER CAUTION

31-66-00

SYSTEM DISPLAY

31-67-00 ECAM

LANDING GEAR

32-00-00

ELECTRONIC INSTRUMENT

CENTRAL WARNING

SYSTEM

SYSTEM

31-60-00

31-50-00

AIR/DATA/ INERTIAL REFERENCE

ENGINE MASTER CONTROL

SYSTEM

34-12-00

76-12

FLIGHT MANAGEMENT AND GUIDANCE

ELECTRICAL POWER

SYSTEM

22-80-00

24-00-00

FUEL

SYSTEM

APU GENERAL

28-00-00

AIR

CONDITIONING

49-00-00 21-00

CENTRALIZED FAULT DISPLAY

SYSTEM SLATS ELECTRICAL CONTROL & MONITORING

27-81

ANNUNCIATOR LIGHT TEST

ENGINE FUEL

AND DIMMING

AND CONTROL

33-14-00

73-00-00

AND DATA RECORDING

FIRE PROTECTION

SYSTEM

31-30-00

26-00-00

N_MM_280000_0_GGM0_01_01

Figure 28-00-00-27300-00-A / SHEET 1/1 - Fuel System - Interfaces ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 (Ref. Fig. Fuel System - Block Diagram SHEET 1) Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 26 of 32


FUEL RECIRCULATION FO R COOLING

QUANTITY

FUEL

FUEL LEVEL

INDICATING

SENSING

28-42-00

28-16-00

28-46-00

INTERCELL

ENGINE

TRANSFER SYSTEM

LP FUEL SHUT-OFF

28-15-00

28-24-00

MAIN FUEL PUMP SYSTEM 28-21-00

APU LP SHUT-OFF

AP U FUEL-PUMP SYSTEM

CROSSFEED SYSTEM

28-29-00

28-22-00

28-23-00

REFUEL/ DEFUEL SYSTEM 28-25-00

FUEL STORAGE/ TANKS MANUAL MAGNETIC INDICATORS

28-11-00

28-43-00

TANK VENTING SYSTEM 28-12-00 28-13-00

N_MM_280000_0_GJP0_01_00

Figure 28-00-00-27400-00-A / SHEET 1/1 - Fuel System - Block Diagram ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 27 of 32


** ON A/C ALL

6. Operation/Control and Indicating A. Operation Limits (Ref. Fig. Standard Envelope - Fuel SHEET 1)


Page 28 of 32


Pressure altitude x 1000 ft

45 Ground

T.O.

start

land

1

Yes

Yes

Yes

2

No

No

Ye s

39800ft(12130m)

40

30

Flt

2

20

9200 ft(2804m)

10

Ground

+55°at

1

zero altitude

0

-1000ft(-300m) -5

-80

-70

-60

-50

-40

-30

-20

-10

0

+10

+20

+30

+40

+50

+60

+70

OAT Degrees C

N_MM_280000_0_GLM0_01_00

Figure 28-00-00-29500-00-A / SHEET 1/1 - Standard Envelope - Fuel ** ON A/C ALL Print Date: January 19, 2018 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 29 of 32


The fuel system is designed to operate in these limits: · maximum certificated altitude 12130 m (39797 ft.) · ambient conditions. B. The fuel types that follow can be used in the fuel system: · · · · · · · ·

JET A1 JET B or JP4 JET A JP5 JP8 RT TS-1 No.3 JET. This list is for general reference only. All kerosene and wide-cut fuels that are made to these specifications and are approved in your Flight Manual, can be used in the fuel system. All the additives permitted in these specifications, plus other AIRBUS approved additives (which includes biocide and antistatic additives) can be used in the fuel system.

For usual operation, the fuel temperature range is: · a minimum of -54 deg.C (-65.2 deg.F) or the fuel freeze point · a maximum of 50 deg.C (122 deg.F) or to a temperature at which the fuel starts to boil. Different grades of fuel and the altitude of the aircraft cause differences to occur in these figures. C. Control and Indicating ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-204, 206-209, 211-250, 350-350 (Ref. Fig. Fuel System Control Switches SHEET 1) ** ON A/C 016-022, 024-150, 201-201, 203-204, 206-209, 211-250, 301-342, 350-350 (Ref. Fig. Engine and APU Fire Buttons and Engine Start Switches SHEET 1) ** ON A/C 016-022, 024-150, 206-206, 208-209, 215-216, 221-250, 350-350 (Ref. Fig. ECAM Displays and Control Panel SHEET 1) ** ON A/C 016-022, 024-150, 201-201, 203-203, 206-209, 211-250, 350-350

EMB SB 31-1211 for A/C 219-220 (Ref. Fig. Refuel/Defuel Control Panel 800VU SHEET 1) ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-204, 206-209, 211-250, 350-350 (1) Control The control of the fuel system is automatic, but the crew can manually control the system when necessary. The cockpit overhead panel 40VU has control switches for: · the main fuel pumps (Ref. AMM D/O 28-21-00-00) · the crossfeed valve (Ref. AMM D/O 28-23-00-00) . The cockpit overhead panel 25VU has the control switch APU MASTER SW. When set to ON the APU LP valve (Ref. AMM D/O 28-29-00-00) is opened and the APU fuel pump (Ref. AMM D/O 28-22-0000) operates. The cockpit overhead panel 20VU has control switches for: · ENG 1 FIRE · ENG 2 FIRE · APU FIRE.


Page 30 of 32


When operated these switches put the related engine LP valve (Ref. AMM D/O 28-2400-00) and/or the APU LP valve (Ref. AMM D/O 28-29-00-00) to the closed position. The cockpit center-pedestal panel 115VU has control switches for: · ENG 1 MASTER 1 · ENG 2 MASTER 2. These switches control the position of the related engine LP valve (Ref. AMM D/O 2824-00-00) . In a fire the ENG FIRE switches close the related LP valve. The refuel/defuel control panel(s) 800VU and 801VU (if installed) and the preselector 5QT have the switches to control the refuel of the aircraft. The defuel and fuel transfer are controlled by the switches on the panels 800VU, 801VU (if installed) and 40VU. The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur: · a warning is given on the E/WD · the FUEL page shows on the SD. The crew can use the ECAM control panel to look at the FUEL page. ** ON A/C ALL 7. BITE Test A. Hi-Level BITE (Ref. 28-46-00)

When the TEST switch (2QJ) (on the Refuel/Defuel control panel 800VU) is set to the HI. LVL position, a functional test of the hi-level circuits is done. If the circuits are serviceable, the HI. LVL. indicators (blue) (on the Refuel/Defuel Control Panel 800VU) change condition. That is, the HI. LVL. indicators that were off, come on and the HI. LVL. indicators that were on, go off. When the TEST switch is returned to its central position, the HI. LVL. indicators return to their initial condition. B. Fuel Quantity Indicating System (Ref. 28-42-00) The Fuel Quantity Indicating Computer (FQIC) does the BITE test of the Fuel Quantity Indicating System (FQIS) and of the Fuel Level Sensing System (FLSS) (Ref. AMM D/O 28-46-00-00) . The FQIS BITE test is done at aircraft power-up and is then done continuously whilst the FQIC is energized. The FLSS BITE test is done at aircraft power-up for the sensors that are fully in fuel and fully out of fuel. For the sensors that cannot be tested, the FQIC does a test of these sensors when the fuel is next at the correct level. The FLSS BITE test is only done when the aircraft is on the ground. The BITE test results can be accessed through the Multipurpose Control and Display Unit (MCDU) (Ref. AMM D/O 22-82-00-00) , in the cockpit. The FQIC results are on the FQIC STATUS page and the FLSS results are on the FLSS STATUS page. The test results can only be accessed when the aircraft is on the ground. If necessary, when the aircraft is on the ground, you can do a COMMAND FLSS BITE on the MCDU. The FQIC will do a FLSS BITE test and the results will be available on the FLSS STATUS page of the MCDU. ** ON A/C 016-022, 024-094, 101-150, 201-201, 203-250, 350-350 Figure 28-00-00-15000-00-E / SHEET 1/4 - Fuel System - Wing and Center Figure 28-00-00-15000-00-E / SHEET 2/4 - Fuel System - Wing and Center Figure 28-00-00-15000-00-E / SHEET 3/4 - Fuel System - Wing and Center Figure 28-00-00-15000-00-E / SHEET 4/4 - Fuel System - Wing and Center Figure 28-00-00-15700-00-C / SHEET 1/1 - Fuel System Control Switches

Tank Tank Tank Tank

** ON A/C ALL Figure 28-00-00-16000-00-A / SHEET 1/1 - Engine and APU Fire Buttons and Engine Start Switches ** ON A/C 016-022, 024-150, 206-206, 208-209, 215-216, 221-250, 350-350 Figure 28-00-00-16100-00-J / SHEET 1/1 - ECAM Displays and Control Panel ** ON A/C 016-022, 024-150, 201-201, 203-203, 205-250, 350-350


Page 31 of 32

Fuel Description

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