- Información
- Chat IA
Fuel System 1 de aerpespacial
Control Automatico (ingenieria mecatroni)
Universidad Tecnológica de Tecamachalco
Recomendado para ti
Comentarios
Vista previa del texto
F900EX EASY 02-28-
CODDE 1 PAGE 1 / 2
DGT
ATA 28 – FUEL SYSTEM
TABLE OF CONTENTS
ISSUE 4
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
02-28-00 F900EX EASY
PAGE 2 / 2 CODDE 1
ISSUE 4
ATA 28 – FUEL SYSTEM
TABLE OF CONTENTS
DGT
INTENTIONALLY LEFT BLANK
02-28-05 F900EX EASY
PAGE 2 / 6 CODDE 1
ISSUE 4
ATA 28 – FUEL SYSTEM
GENERAL
DGT
FIGURE 02-28-05-00 FLIGHT DECK OVERVIEW
F900EX EASY 02-28-
CODDE 1 PAGE 3 / 6
DGT
ATA 28 – FUEL SYSTEM
GENERAL
ISSUE 4
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 USG 3,999 l
FUEL TANKS LOCATION
FIGURE 02-28-05-01 TANKS LOCATION
F900EX EASY 02-28-
CODDE 1 PAGE 5 / 6
DGT
ATA 28 – FUEL SYSTEM
GENERAL
ISSUE 4
Fueling connector
Pressure fueling panel
Fuel vent
Fuel vent
Fuel vent
FIGURE 02-28-05-04 PRESSURE FUELING PANEL AND FUELING CONNECTOR LOCATION
02-28-05 F900EX EASY
PAGE 6 / 6 CODDE 1
ISSUE 4
ATA 28 – FUEL SYSTEM
GENERAL
DGT
INTENTIONALLY LEFT BLANK
02-28-10 F900EX EASY
PAGE 2 / 6 CODDE 1
ISSUE 4
ATA 28 – FUEL SYSTEM
DESCRIPTION
DGT
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
F900EX EASY 02-28-
CODDE 1 PAGE 3 / 6
DGT
ATA 28 – FUEL SYSTEM
DESCRIPTION
ISSUE 4
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
F900EX EASY 02-28-
CODDE 1 PAGE 5 / 6
DGT
ATA 28 – FUEL SYSTEM
DESCRIPTION
ISSUE 4
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.
02-28-10 F900EX EASY
PAGE 6 / 6 CODDE 1
ISSUE 4
ATA 28 – FUEL SYSTEM
DESCRIPTION
DGT
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
02-28-15 F900EX EASY
PAGE 2 / 12 CODDE 1
ISSUE 4
ATA 28 – FUEL SYSTEM
CONTROL AND INDICATION
DGT
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
F900EX EASY 02-28-
CODDE 1 PAGE 3 / 12
DGT
ATA 28 – FUEL SYSTEM
CONTROL AND INDICATION
ISSUE 4
TO ACTIVATE
CONTROL FUNCTION
TO DEACTIVATE
SYNOPTIC
Open (Auto mode)
Closed (Auto mode)
Auto mode
Closed (Manual mode)
Failure in closed position
Failure in open position
pushbutton
CLOSED
REAR
XFR
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
F900EX EASY 02-28-
CODDE 1 PAGE 5 / 12
DGT
ATA 28 – FUEL SYSTEM
CONTROL AND INDICATION
ISSUE 4
TO ACTIVATE
CONTROL FUNCTION
TO DEACTIVATE
SYNOPTIC
Open (1Í3) Push on to open the valve Open (1Î3)
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.
02-28-15 F900EX EASY
PAGE 6 / 12 CODDE 1
ISSUE 4
ATA 28 – FUEL SYSTEM
CONTROL AND INDICATION
DGT
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 seconds. Depress the corresponding softkey for less than 0 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
Fuel System 1 de aerpespacial
Materia: Control Automatico (ingenieria mecatroni)
Universidad: Universidad Tecnológica de Tecamachalco
- Descubrir más de:
