F900EX EASY 02-28-00 ATA 28 – FUEL SYSTEM CODDE 1 PAGE 1 … · 2012-06-27 · F900EX EASY 02-28-05 CODDE 1 PAGE 1 / 6 DGT91832 ATA 28 – FUEL SYSTEM GENERAL ISSUE 4 DASSAULT AVIATION

F900EX EASY 02-28-00

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ATA 28 – FUEL SYSTEM TABLE OF CONTENTS

ISSUE 4

DASSAULT AVIATION Proprietary Data

02-28 ATA 28 – FUEL SYSTEM

02-28-00 TABLE OF CONTENTS

02-28-05 GENERAL

Introduction Sources Fuel tanks location

02-28-10 DESCRIPTION

Sub-systems Distribution

02-28-15 CONTROL AND INDICATION

Control Indication

02-28-20 SYSTEM PROTECTION

Introduction Circuit breakers Fire control panel

02-28-25 NORMAL OPERATION

Introduction On ground operation In-flight operation

02-28-30 ABNORMAL OPERATION

Introduction BP 1 failure X-BP valves usage XFR valve failure and possible AFT CG exceedance CAS messages

02-28-35 FUELING OPERATION

Introduction Refueling operation Gravity refueling De-fueling

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ATA 28 – FUEL SYSTEM TABLE OF CONTENTS

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INTENTIONALLY LEFT BLANK

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ATA 28 – FUEL SYSTEM GENERAL

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INTRODUCTION

Fuel system provides engines and APU with pressurized fuel.

It is composed of three independent groups of fuel tanks (left, center and right) that feed their respective engine and the APU.

Total usable fuel quantity is 21,000 lb / 9,525.5 kg / 3,133.5 USG / 11,862.5 l).

Weights are calculated for a fuel density of 6.7 lb per USG (0,803 kg/l).

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FIGURE 02-28-05-00 FLIGHT DECK OVERVIEW

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SOURCES

LH WING TANK + HALF CENTER WING BOX +

LH FRONT TANK

FRONT TANK + CENTER TANK + REAR COMPARTMENT TANK

RH WING TANK + HALF CENTER WING BOX +

RH FRONT TANK

7,036 lb

3,191 kg

1,050 USG

3,974 l

6,885 lb

3,123 kg

1,027 USG

3,889 l

7,079 lb

3,211 kg

1,056.5 USG

3,999 l

FUEL TANKS LOCATION

FIGURE 02-28-05-01 TANKS LOCATION

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FIGURE 02-28-05-02 NEGATIVE PRESSURE RELIEF VALVES AND GRAVITY FILLER PORTS LOCATION

FIGURE 02-28-05-03 SUMP DRAIN VALVES LOCATION

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Fueling connector

Pressure fueling panel

Fuel vent

Fuel vent

Fuel vent

FIGURE 02-28-05-04 PRESSURE FUELING PANEL AND FUELING CONNECTOR LOCATION

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ATA 28 – FUEL SYSTEM DESCRIPTION

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SUB-SYSTEMS

TANKS

Fuel storage consists of three tank groups. Each group normally supplies fuel to its respective engine. All tanks are a structural part of the airplane, except central rear tank. Crossfeed valves allow fuel transfer between tanks and engine fuel feed from any tank in the event of fuel imbalance or boost pump failure. The tanks are pressurized by LP bleed air from No 1 and No 2 engines. The pressure is regulated at 2.9 psi and is automatically controlled by the pneumatic system. Pressurization enables fuel supply to the engine pumps in case of booster pump failure at low altitude, and to the LP booster pump at high altitude, preventing cavitation. The airplane may be pressure or gravity refueled or de-fueled under the pilot responsability.

WING AND CENTER WING TANKS

Each wing tank is divided into two sections, outboard and inboard, separated by a rib with interconnection holes at the upper part and flapper valves at the lower part. The Booster Pump (BP) compartment is located in each center wing section. It is also separated from the wing tank by a rib with interconnection holes and flapper valves. LH wing tank supplies the No 1 engine. RH wing tank supplies the No 3 engine.

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FUSELAGE TANKS

The fuselage tank group is divided into three sections: - the front tank, located immediately forward to the wing center section, - the center tank, aft to the main landing gear wheel wells, - the rear compartment tank, located in the mechanic servicing compartment.

The rear compartment tank is also connected with the center tank. The feeder tank is located in the center tank. Fuselage tank group supplies the No 2 engine and the APU.

NOTE

It is not possible to transfer fuel from fuselage tank group to wings tanks and vice-versa.

FIGURE 02-28-10-00 FUEL PRINCIPLE DIAGRAM

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BOOSTER PUMPS

Four identical, three-phased, AC powered, immersed, centrifugal fuel Booster Pumps (BP) are installed in the fuel system. Each pump has a built-in inverter that converts 28 VDC to 115 VAC 400 Hz. Each center wing tank has a booster pump compartment in the aft part, which contains one booster pump. The center tank incorporates one normal and one stand-by pump in its booster pump compartment.

JET PUMPS

The jet pumps ensure that the booster pumps remain always immersed in their compartments. They are installed in the BP compartment, all identical and operate according to the venturi principle by using motive fuel flow delivered from the booster pumps. In each wing tank group, five jet pumps transfer fuel from the outboard, inboard and center wing sections into the booster pump compartment. In the fuselage tank group, four jet pumps are installed in the booster pump compartment. Two jet pumps are used to transfer fuel from the rear tank into the center tank when the REAR XFR valve is open. The front tank is emptied by the third jet pump and the last jet pump transfer fuel from the aft part of the center tank into the booster pump compartment.

FIGURE 02-28-10-01 FUEL TANK CIRCULATION SCHEMATIC

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FUEL SYSTEM COMPUTER

The Fuel Quantity Management Computer (FQMC) includes 2 independent channels performing the following functions:

- fuel, oil, tanks gauging, - fuel flow measurement, fuel used computation, - fuel temperature measurement, - refueling valves control, - center of gravity monitoring, - fuel system integrity monitoring.

In addition, channel 1 performs APU oil low level detection. The FQMC is located in a pressurized area (aft toilet compartment), away from hot air ducts, hydraulic piping and fuel piping.

NEGATIVE PRESSURE RELIEF VALVES

The outboard end of each wing has a negative pressure relief valve to ensure that internal tank pressure does not fall under atmospheric pressure (for location refer to figure 02-28-05-02).

GRAVITY FILLER PORTS

Each wing has one gravity filler port (for location refer to Figure 02-28-05-02)

SUMP DRAINS

Fifteen sump drains are located underneath the airplane (for location refer to Figure 02-28-05-03).

FIGURE 02-28-10-02 FUEL DRAIN FILLER CUP

NOTE

The fuel drain filler cup is stored in the mechanic servicing compartment.

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DISTRIBUTION

GENERAL

The three independent groups of fuel tanks (LH wing, fuselage and RH wing) feed their respective engine. Fuselage tanks also feed the APU during ground operation. The interconnection (X-BP) system permits any booster pump to supply pressurized fuel to any engine in the event of a booster pump failure. The crosstank (X-TK) system permits to connect LH and RH wing tanks to compensate for asymmetric fuel consumption.

FIGURE 02-28-10-03 FUEL DISTRIBUTION DIAGRAM

NOTE

It is not possible to transfer fuel from LH or RH tank to central tank and conversely.

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FUSELAGE TANKS EMPTYING SEQUENCE

The fuel use sequence is automatically managed by the FQMC, opening or closing the REAR XFR control valve as necessary. In case of a FQMC malfunction, the pilot has the capability of sending a CLOSE order to the valve from the overhead panel. If this valve is jammed closed, a manual valve, control of which is located in the aft toilet compartment, allows to open it only. The FQMC balances the fuel consumption between front, center and rear compartment tanks in order to maintain the CG location within the limits. Center tanks fuel consumption is as follows :

- front tank until fuel level reaches 1,900 lb (+200 / -400 lb), - rear compartment tank in its totality, - front tank, - center tank.

During refueling, the FQMC allows the refueling of the rear compartment tank only if the front tank refuels to the 2,775 lb level.

FIGURE 02-28-10-04 CENTER TANKS DIAGRAM

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ATA 28 – FUEL SYSTEM CONTROL AND INDICATION

ISSUE 4


CONTROL

FIGURE 02-28-15-00 FUEL SYSTEM OVERHEAD PANEL

SYNTHETIC TABLE

TO ACTIVATE CONTROL FUNCTION

TO DEACTIVATE SYNOPTIC

On

BP On

Off

Failure

pushbutton

status light

pushbutton

status light

- Manually controls to On or Off BP 1 / BP 3 position

- BP 1 / BP 3 ON position activates BP 1 / BP 3 and pressurizes fuel in engine1/ 3 line

NOTE

In Auto Start mode, BP 1 / 3 are automatically

switched On at corresponding engine start

Push OFF

(BP Off)

Invalid data

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TO ACTIVATE

CONTROL FUNCTION TO DEACTIVATE

SYNOPTIC

BP On On

Failure

ST-BY BP On

ST-BY On

Off

status light

pushbutton

status light

- Manually controls to On or Off either the NORMAL BP 2 or ST-BY BP

- BP 2 and ST-BY BP operations pressurize fuel in engine 2 and APU lines

NOTE 1 In Auto Start mode, ST-BY

BP and BP 2 are automatically switched On respectively at APU and

engine No 2 start.

NOTE 2

In case of BP 2 failure, the pilot needs to push the BOOST 2 pushbutton in order to activate the ST-

BY BP. Push OFF

(BP Off) Invalid data

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TO ACTIVATE


SYNOPTIC

Open

(Auto mode)

Closed

(Auto mode)

Auto mode

Closed

(Manual mode)

Failure in

closed position

Failure in open position

pushbutton

CLOSED

REARXFR

light

- In Auto mode, the transfer valve is controlled by the FQMC to balance fuel between front / center and rear compartment tanks

- Forces the valve to CLOSED position (FQMC by-pass in case of failure of the automatic sequence)

Push off to close the

valve

Invalid data

Open

Push on to open

the valve

Closed

(1-3)

pushbutton

(1-3) Manually controls the valve to open position in order to feed :

- -No 1 engine with pressurized fuel from the RH wing tank,

- -or No 3 engine with pressurized fuel from the LH wing tank

Valve closed

Invalid data

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TO ACTIVATE


SYNOPTIC

Push on to open

the valve

Open

(1-2)

(2-3)

pushbutton

(1-2) or (2-3) : Manually controls the valves to open position in order to feed :

No 2 engine or APU with pressurized fuel from LH (2-1 open) or RH (2-3 open) wing tank

Or No 1 engine (1-2 open) or No 3 engine (2-3 open) with pressurized fuel from center tank

NOTE When X-BP (1-2) or (2-3) valves are open to feed No 1 or No 3 engines with center tank pressurized fuel, the ST-BY BP is automatically turned on to support BP 2. Fuel pressure in the feeding lines is then higher than t he nominal value. Whatever the BP 1 or BP 3 status, the respective wing tank will no more feed its respective engine.

With X-BP (1-2) or (2-3) valve open, the synoptic doesn’t display the STBY label even if ST-BY BP is running.

Valve closed

Closed

Invalid data

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TO ACTIVATE


SYNOPTIC

Open

(1 3) Push on to open

the valve

Open

(1 3)

Closed

pushbutton

- Manually controls the fuel transfer between LH and RH wing tanks

Valve closed

Invalid data

INDICATION

Fuel indications are displayed on:

- the MDU:

o FUEL synoptic,

o STAT synoptic,

- the PDU:

o HSI window,

o ENG-TRM-BRK window.

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MDU FUEL PAGE

FIGURE 02-28-15-01 FUEL PAGE EMPTY TANKS INDICATIONS

TEMP Fuel TEMPerature probe stands in the LH feeder tank and provides temperature indication on the FUEL page. FU Fuel Used is computed by the FQMC. Computation starts as soon as one engine is running and stops when the three engines are shut off. It does not compute fuel burned by the APU. It can be reset with the RESET FU soft key on the FUEL page. The fuel used reset command will not operative if the corresponding softkey is depressed for more than 0.5 seconds. Depress the corresponding softkey for less than 0.5 seconds. FQ Fuel Quantity is supplied by the Data Acquisition Unit (DAU) and FQMC. FQ1 , FQ2 and FQ3 buttons give access to a separate dialog box that displays individual fuel quantity for each tank of the group. Clicking on FQ1, 2 or 3 opens their respective window. To close the windows, place the cursor in the upper part, on the X box and click with enter button of the CCD. FR Fuel Remaining is supplied by FMS. It is the result of Fuel Quantity inserted in the Preflight POF page at system initialization minus Fuel Used

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FIGURE 02-28-15-02 FUEL FIELD FQ 1, 2 AND 3 - FULL CAPACITY

FQ1 or FQ3

OUT Wing outer tank fuel quantity

IN Wing inner tank fuel quantity

CTR Wing center tank fuel quantity

FWD Forward tank fuel quantity

FEED BP 1 or 3 compartment tank fuel quantity

FQ1 or 3 Total fuel quantity

When any of the above fuel quantity data is invalid, the corresponding indication is replaced by four amber dashes.

NOTE

With less than 500 lb in the wing outboard tanks, the fuel quantity indication for the wing outboard tanks may vary between 100 to 600 lb compared to the actual quantity

FQ2 window

Upper line BP 2 compartment tank fuel quantity

Lower line Center tank fuel quantity

FQ2 Total fuel quantity left in fuselage tank and pipes

When any of the above fuel quantity data is invalid, the corresponding indication is replaced by four amber dashes.

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Low level management

Fuel levels are monitored for each group of tank through two types of detection: - one is on when fuel quantity in a group is less than 1,000lb. The detection is based

on fuel level detection thermistors located in center wing lateral tanks, - one is on when fuel quantity in a feeder tank is less than 250 lb for group 1 and 3

and less than 200 lb for group 2. The detection is based on tests on the fuel gauged quantities.

When the 1,000 lb level is reached, amber LEVEL is displayed next to the Fuel Quantity (FQ) readout of the MDU FUEL tab and the FUEL LEVEL .. CAS message appears in CAS window.

When the 250 lb (C 1 or C 3) or 200 lb (C 2) level is reached, all the fuel quantities of the corresponding group are displayed in amber in the MDU Fuel synoptic and the LOW FUEL CAS message appears in CAS window.

NOTE

With no booster pump energized on No 2 fuel system and level below 1,100 lb, the same warning as for 200 lb appears.

Degraded gauging situations can occur during a loss of AHS (Attitude Heading reference System) or a loss of a fuel gauge. In these cases DEGRADED GAUGING CAS message appears in CAS window.

FQ (1/2/3) indication on the MDU FUEL tab is framed in amber when gauging of any tank of the corresponding group is lost and FQ is then as well framed in amber.

For example:

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FUEL LINE COLOR SYMBOLOGY

X-BP 1-3 and 3-1 valves X-TK 1-3 and 3-1 valves Fuel cross tank wing lineCrossfeed 1-3 line

Fuel supplyline 3

Crossfeed 3-2 line

X-BP 3-2 valve

Crossfeed 1-2 line

X-BP 1-2 valve

Fuel supplyline 1

Fuel suply line 2Rear X-FR valve

Fuel centertank line

FIGURE 02-28-15-03 FUEL LINE DENOMINATION

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FUEL LINE GREEN AMBER SOLID GRAY HOLLOW GRAY

Supply line 1 and 3 Normal pressure Low pressure

Low pressure, ENG 1 / 3 not running and BP 1 / 3 off.

Invalid data

Supply line 2 Normal pressure Low pressure

Low pressure, ENG 2 and APU not running, BP 2 and STBY pump off.

Invalid data

Cross-feed 1-3 line

X-BP 1-3 or 3-1 open and BP 1 or BP 3 on

X-BP 1-3 or 3-1 open and low pressure

X-BP 1-3 and 3-1 closed Invalid data

Cross-feed 1-2 line

X-BP 1-2 open and either BP 1, BP 2 or STBY pump on or X-BP 1-2 open, X-BP 3-2 open and BP 3 on

X-BP 1-2 open, BP 1, BP 2 and STBY pump off, and either X-BP3-2 closed or X-BP3-2 open and BP 3 off

X-BP1-2 closed Invalid data

Cross-feed 3-2 line

X-BP3-2 open and either BP 3, BP 2 or STBY pump on or X-BP1-2 open and BP 1 on

X-BP3-2 open, BP 3, BP 2 and STBY pump off, and either X-BP1-2 closed or X-BP1-2 open and BP 1 off

X-BP3-2 closed Invalid data

Cross tank wing line

X-TK1-3 or 3-1 valve open - X-TK1-3 or 3-1 valve

closed -

Center tank line X-FR valve open X-FR valve failed X-FR valve closed Invalid data

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MDU STAT SYNOPTIC

FIGURE 02-28-15-04 STAT SYNOPTIC INDICATION

PDU

The total Fuel Quantity (FQ = sum of the different tanks quantities) and the Fuel Remaining (FR) are permanently displayed on the PDU.

FIGURE 02-28-15-05 FUEL QTY INDICATION ON THE HSI

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FF, FU and FQ are permanently displayed on ENG-TRM-BRK window of the PDU, however this window is not available in case of TCAS RA auto pop-up.

FIGURE 02-28-15-06 PDU ENGINE WINDOW INDICATIONS

FUEL PRESSURIZATION INDICATION

A fuel pressurization indication is available in the airplane rear compartment on the right side when facing the plane nose (pressure gauge).

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ATA 28 – FUEL SYSTEM SYSTEM PROTECTION

ISSUE 4


INTRODUCTION

Electrical circuit protection is provided by conventional trip-free circuit breakers located above the overhead panel.

The fuel shut-off valve controls are on the fire protection panel located on the overhead panel.

CIRCUIT BREAKERS

FIGURE 02-28-20-00 FUEL CIRCUIT BREAKERS

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ATA 28 – FUEL SYSTEM SYSTEM PROTECTION

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FIRE CONTROL PANEL

The three FIRE pushbuttons activate the fuel shut-off valves corresponding to each engine fuel supply system.

The APU fuel supply is cut off by engine No 2 shut-off valve.

FIGURE 02-28-20-01 FIRE CONTROL PANEL

CIRCUIT PROTECTION DIAGRAM

FIGURE 02-28-20-02 CIRCUIT PROTECTION DIAGRAM

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ATA 28 – FUEL SYSTEM NORMAL OPERATION

ISSUE 4


INTRODUCTION

In the following, typical on ground and in-flight situations have been selected to help the crew to understand the symbols provided in the various panels and displays.

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ON GROUND OPERATION

AIRPLANE WITH FULL TANKS AND AUXILIARY POWER UNIT (APU) OPERATING ONLY

FIGURE 02-28-25-00 OVERHEAD PANEL DURING APU OPERATION

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FIGURE 02-28-25-01 FUEL SYNOPTIC PAGE DURING APU OPERATION

CONTEXT RESULT

APU running

APU synoptic in green ST-BY pump on + amber ST-BY Rear X-FR valve closed BP 1 and BP 3 off (engines off) Fuel Remaining does not decrease despite

APU consumption FU 2 and FU does not increase

Fuel is coming from fuselage tanks to feed the APU

ST-BY pump and fuel line synoptic in green BP 1, BP 3 and their respective fuel lines

synoptic in gray, ENG 1, ENG 2 and ENG 3 synoptic in gray All transfer valves closed

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IN-FLIGHT OPERATION

AIRPLANE FLYING IN NORMAL OPERATION (3 ENGINES RUNNING WITHOUT ANY FUEL SYSTEM FAILURE)

FIGURE 02-28-25-02 OVERHEAD PANEL DURING NORMAL IN-FLIGHT OPERATION

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FIGURE 02-28-25-03 FUEL SYNOPTIC DURING NORMAL IN-FLIGHT OPERATION

NORMAL STATUS RESULT

ENG 1, 2 and 3 running

Each tank is feeding its respective engine

- Overhead panel BP pushbuttons unlighted

- BP 1, BP 2, BP 3 and their respective fuel lines synoptic in green

- ENG 1, ENG 2 and ENG 3 synoptic in green

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ATA 28 – FUEL SYSTEM ABNORMAL OPERATION

ISSUE 4


INTRODUCTION

In the following, abnormal situations have been selected to help the crew to understand the symbols provided in the various panels and displays.

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BP 1 FAILURE

ABNORMAL STATUS

FIGURE 02-28-30-00 OVERHEAD PANEL DURING BP 1 FAILURE

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FIGURE 02-28-30-01 FUEL SYNOPTIC DURING BP 1 FAILURE

CONTEXT RESULT

BP 1 failure

FUEL PRESS 1 CAS message

Overhead panel BP pushbuttons unlighted

BP 1 and its respective fuel line synoptic in amber

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AFTER PROCEDURE COMPLETE

FIGURE 02-28-30-02 OVERHEAD PANEL AFTER BP 1 FAILURE

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FIGURE 02-28-30-03 FUEL SYNOPTIC AFTER BP 1 FAILURE

ACTION RESULT

BP 1 overhead panel pushbutton off BP 1 overhead panel OFF indication in amber

BP 1 synoptic in gray with OFF in amber

X-BP 1-3 overhead panel pushbutton pushed

X-BP overhead panel indication in amber

RH wing tank fuel is feeding ENG 1

X-BP (1-3) valve and associated fuel line synoptic in green

LH wing tank fuel is not used any more at this point and fuel quantity balance between the wing tanks needs to be managed by opening and closing the transfer valve

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FUEL BALANCE PROCEDURE AFTER BP1 FAILURE

FIGURE 02-28-30-04 OVERHEAD PANEL DURING FUEL BALANCE PROCEDURE

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FIGURE 02-28-30-05 FUEL SYNOPTIC DURING FUEL BALANCE PROCEDURE

ACTION RESULT

X-TK

overhead panel pushbutton pushed

Fuel is transferred from LH wing tank to RH wing tank

X-TK overhead panel indication in amber

X-TK valve and associated fuel line synoptic in green

X-TK indication above the valve synoptic in amber

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X-BP VALVES USAGE

If X-BP (1-2) or (2-3) valves are open, automatically the both booster pumps of the engine 2 (normal and ST-BY) are running. Whatever the state of BP 1 and/or BP 3, the fuel transfer is only operative from the center tank. In this case, no indication is displayed on the FUEL synoptic and on the overhead panel.

FIGURE 02-28-30-06 X-BP VALVES (1-2) OR (2-3) OPEN

XFR VALVE FAILURE AND POSSIBLE AFT CG EXCEEDANCE

ABNORMAL STATUS

FIGURE 02-28-30-07 OVERHEAD PANEL DURING REAR XFR VALVE FAILURE

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FIGURE 02-28-30-08 FUEL SYNOPTIC DURING REAR XFR VALVE FAILURE

CONTEXT RESULT

XFR valve failure

- CENTRAL TANK FUEL XFER and FAULT CODE CAS messages

- Overhead panel pushbuttons unlighted

- XFR valve and corresponding fuel line synoptic in amber

- Fuel quantity in amber for rear compartment tank

- CG indication in amber

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AFTER PROCEDURE COMPLETE

FIGURE 02-28-30-09 OVERHEAD PANEL AFTER REAR XFR VALVE FAILURE

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FIGURE 02-28-30-10 FUEL SYNOPTIC AFTER PROCEDURE COMPLETED

ACTION RESULT

Pull the REAR XFR handle in the aft lavatory

to open the manual valve

Rear XFR valve synoptic in amber

Corresponding fuel line synoptic in green

When rear tank is empty :

- Rear XFR valve stays open with synoptic in amber

- Corresponding fuel line synoptic in amber

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CAS MESSAGES

CAS MESSAGE DEFINITION

CENTRAL TANK FUEL XFER Abnormal operation of central tank transfer valve and/or possible aft or forward CG exceedance

FAULT CODE Refer to CODDE1 / Chapter 02 / ATA 45 - 05.

FUEL CMPTR CONFIG On ground, FQMC computer configuration mismatch

FUEL PRESS .. Low fuel pressure on engine (1/2/3)

FUELING Fueling problem (vent valves, coupling lever, door, fueling valve ...)

LOW FUEL .. Less than 250 lb of fuel remaining for LH/RH tanks or 200 lb for center tank

DEGRADED GAUGING

Degraded fuel gauging because of: - loss of IRS data (no airplane attitude correction)

- loss of one gauge

- loss of one tank gauging

FAULT CODE Refer to CODDE1 / Chapter 02 / ATA 45 - 05

FUEL LEVEL … Fuel Quantity less than 1,000 lb on fuel tank group (1/2/3)

FUEL PRESS .. FAIL On ground, indication of failure of fuel pressure sensor (1/2/3)

FUEL TEMP LOW Fuel temperature lower than – 40°C

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ATA 28 – FUEL SYSTEM FUELING OPERATION

ISSUE 4


INTRODUCTION

The airplane is normally pressure-refueled.

All tanks can be automatically refilled fully or partially through the single point fueling connector (refer to figure 02-28-05-04).

When pressurized fuel is not available, gravity refueling may be performed through two wing gravity filler ports (refer to figure 02-28-05-02).

The airplane may be de-fueled through the normal pressure-refueling system.

NOTE

For further information, refer to the Ground Servicing Manual (DGT616).

REFUELING OPERATION

The pressure-refueling system needs electrical power and a regular refueler.

The pressure refueling system is powered by the battery bus. This allows refueling without the Ground Power Unit (GPU).

The refueling pressure must be between 30 psi and 50 psi maximum. For a partial refueling, refueling stops automatically when the selected fuel quantity is attained (accuracy is of 50 lb).

Pressure refueling controls are located on the pressure fueling panel, behind an access door on the right hand lower fuselage of the airplane, aft to the wing.

NOTE

As long as fuel tanks are pressurized, the fueling panel is not electrically powered (depressurization lever needs to be pulled).


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FIGURE 02-28-35-00 FUEL HOSE

LEFTFULLlight

LEFTON/OFFswitch

STOPFUELING light

CENTERON / OFF

switch

CENTERFULL light

TOTAL QTYDigitaldisplay

FAULTlight

RIGHTFULL light

RIGHTON / OFF

switch

FULLPARTIAL

switch

INCreaseDECrease

toggle switch

TOTAL QTYSELECT

digital display

LAMPTEST

pushbutton

HIGH LEVELTEST

pushbutton

FIGURE 02-28-35-01 PRESSURE FUELING PANEL

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ISSUE 4


GRAVITY REFUELING

The airplane may be refueled through gravity filler ports located on each upper wing surface.

Electrical power on the airplane is required for gravity refueling to be able to transfer fuel from wing to center tanks.

FIGURE 02-28-35-02 GRAVITY REFUELING PORTS

The center tank refueling requires pressurized fuel.

A GRAVITY FUELING guarded switch located on the cockpit maintenance panel (right side of the copilot seat, under a cover) controls the opening of the defueling/refueling valve which allows fuel to be transferred from wings to center tanks.

FIGURE 02-28-35-03 GRAVITY FUELING GUARDED SWITCH

As there is no automatic stop, refueling progress must be monitored on the quantity indicators.

NOTE


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DE-FUELING

Apart from its center system gravity refueling function, the defueling/refueling valve can also be used for de-fueling through the pressure-refueling connector.

For this function, the valve is controlled by the DEFUELING guarded switch on the fueling panel.

FIGURE 02-28-35-04 PRESSURE FUELING PANEL

When open, the de-fueling/refueling valve interconnects the center feeder tanks with the refueling system.

NOTE


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F900EX EASY 02-28-00 ATA 28 – FUEL SYSTEM CODDE 1 PAGE 1 … · 2012-06-27 · F900EX EASY 02-28-05 CODDE 1 PAGE 1 / 6 DGT91832 ATA 28 – FUEL SYSTEM GENERAL ISSUE 4 DASSAULT AVIATION