Bombardier-Challenger_00-Fuel庞巴迪挑战者燃油

航空发表于 2010-5-8 08:03:23

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航空发表于 2010-5-8 08:03:39

-cinhaaplleanirg er OPERATING MANUAL PSP 606 SECTION 12 FUEL TABLE OF CONTENTS Subject SYSTEM CONFIGURATIONS GENERAL FUEL STORAGE FUEL DISTRIBUTION Ejector Pumps Engine Feed APU Fuel Feed Standby Feed Tank Vent System REFUEL/DEFUEL SYSTEM Pressure Refuel/Defuel System Pressure Refueling Pressure Defueling Gravity Refueling and Defueling FUEL QUANTITY INDICATING SYSTEM Page 1 1 2 7 10 11 12 12 18 19 21 Figure Number LIST OF ILLUSTRATIONS Title 1 Fuel Feed System - Schematic 2 Auxiliary Fuel Tanks 3 Fuel Control Panel (2 Sheets) 4 Fuel Tank Vent System (3 Sheets) 5 Refuel/Defuel System - Schematic 6 Refuel/Defuel Control Panel 7 Fuel Quantity Indicating System 8 Fuel Specific Weight Page 3/4 5/6 8 13 16 17 20 22 12 - CONTENTS Page 1 Feb 15/96
canadair chauenQer OPERATING MANUAL PSP 606 SECTION 12 FUEL SYSTEM CONFIGURATIONS The fuel system has one of two fuel tank configurations: a basic three-tank configuration consisting of left and right main tanks and an auxiliary tank; or a five-tank configuration, of larger capacity, which has two additional auxiliary tanks, designated the forward and rear auxiliary tanks, respectively. The systems and operations described in the following paragraphs apply to both of these configurations unless otherwise noted. GENERAL (Figure 1) The principal components of the aircraft fuel system include fuel tanks, independent ejector pumps for each engine, two electric pumps, and a fuel feed system for the auxiliary power unit (APU). A single point pressure refuel/ defuel adapter is provided and gravity refueling/defueling is carried out through filler caps on the upper wing surface. Fuel and water drains are located at various low points on the fuel system components to permit manual drainage of the fuel tanks. All the fuel and vent lines routed through the fuselage are surrounded by airtight fireproof shrouds which have integral vent and drainage lines. The relatively high elevation of the fuel lines, running from the top of the wing box centre section up to the engine nacelle level, protects them from damage in the event of a wheels-up landing. Control of the fuel system components and fuel quantity indication are provided by the FUEL CONTROL and FUEL QUANTITY panels on the centre instrument panel. The FUEL CONTROL panel has system caution lights as well as pump and valve switch/lights and a fuel temperature gauge. The FUEL QUANTITY panel provides an indication of individual tank and total fuel quantity. In addition to supplying the engines and the APU with fuel, the system provides a flow of fuel to cool the APU generator oil and, on aircraft that do not incorporate Canadair Service Bulletin 600-0318, the No. 3 hydraulic system fluid. Fuel in excess of the APU feed requirements is tapped from a return line from the APU and used as the cooling medium. SECTION 12 Page 1 Mar 01/85 canadair ctiaiienc/er OPERATING MANUAL PSP 606 FUEL STORAGE (Figures 1 and 2) Conforming to a wet wing design concept, the entire wing box structure is sealed to form three tanks: the left and right main tanks and the auxiliary tank. The left and right main tanks are formed by the wing box structure outboard of wing station 45-00 (left and right) and the auxiliary tank occupies the space enclosed by the wing box centre section. The capacities of the tanks, in litres (US gallons) of useable fuel, are: Pressure refueling Litres (US gallons) Gravity refueling (approx.) Litres (US gallons) Left main tank Right main tank Auxiliary tank Totals Aircraft 1072. Aircraft with aft CI] CI] 2716 2733 2716 2733 2835 3193 3823 8267 8301 8625 9255 (717.5) (722) (717.5) (722) (749) (843.5) (1010) (2184) (2193) (2278.5) (2445) fuselage tank. and forward fuselage tank. m [23 [33 2519 2536 2519 2536 2835 3569 7873 7907 8607 (665.5) (670) (665.5) (670) (749) (943) (2080) (2089) (2274) The system contains approximately 110 pounds various system components. of unusable fuel trapped in the In the main tanks, the ribs of the wing box assembly act as baffles to limit centre of gravity shifts by restricting the sudden displacement of a large volume of fuel with changes in the aircraft's attitude. Fuel in the main tanks flows inboard through lightening holes in the wing ribs. Flapper check valves, installed on the ribs at WS85.50 and HS148.00 ensure that a portion of the fuel in the main tanks remains trapped between these wing stations and the auxiliary tank at all times during flight. A balance line, equipped with an electrically-operated shutoff valve, connects the main tanks at their lowest points. The shutoff valve is controlled by the X FLOW switch/light on the FUEL CONTROL panel and is opened to allow the main tank fuel quantities to equalize by gravity. SECTION 12 Page 2 Feb 12/88 cacnhaadnaeirri Qer OPERATING MANUAL PSP 606 The auxiliary tank contains the left and right collector tanks which feed the left and right engines, respectively- The collector tanks enclose the left and right primary ejector pumps and are maintained in the full-fuel state by gravity feed lines and the scavenge ejector lines from the main tanks- The electric fuel pumps of the standby fuel feed system are also located inside the auxiliary tank, mounted beside the collector tanks- When in operation, each electric pump draws fuel only from its corresponding collector tank. Twenty-nine flush-mounted access panels, twenty-seven for the main tanks and two for the auxiliary tank, are installed on the lower wing surface to provide access to the interior of the fuel tanks. Three similar panels serve as supports for the electric fuel pumps of the standby and APU fuel feed systems. A cover on these panels can be removed to permit servicing of the fuel pump motor elements without draining the associated fuel tanks and lines. SECTION 12 Page 2A Feb 12/88
canadsur zzfoaiiencier OPERATING MANUAL PSP 606 TO FORWARD AUXILIARY TANK TO APU FUEL CONTROL SYSTEM Fuel Feed System - Schematic Figure 1 CENTRIFUGAL ELEMENT GEAR PUMP ELEMENT 1 ENGINE DRIVEN PUMP • 2 ENGINE DRIVEN PUMP • 3 MOTIVE FLOW LINE 4 FILTER 5 FLOW SWITCH - LEFT SCAVENGE EJECTOR 6 LEFT SCAVENGE EJECTOR 7 LEFT VENT LINES PURGE CONNECTION 8 LEFT TRANSFER LINE FLOAT VALVE 9 LEFT TRANSFER LINE 10 LEFT SCAVENGE EJECTOR LINE 11 FLAPPER CHECK VALVES - WING STATION 85 12 GRAVITY FEED LINE - LEFT MAIN TANK TO LEFT COLLECTOR TANK 13 COLLECTOR TANK VENT LIMES 14 LEFT AND RIGHT PRIMARY FUEL EJECTORS 15 PRESSURE SWITCHES - LEFT AND RIGHT PRIMARY FUEL EJECTORS 16 LEFT AND RIGHT ELECTRIC BOOST PUMPS 17 PRESSURE SWITCHES - LEFT AND RIGHT ELECTRIC PUMPS 18 LEFT TRANSFER EJECTOR MOTIVE FLOW LINE 19 RIGHT TRANSFER EJECTOR MOTIVE FLOW LINE 20 MAIN TANKS BALANCE LINE 21 BALANCE LINE SHUTOFF VALVE 22 LEFT AND RIGHT TRANSFER EJECTORS 23 LEFT AND RIGHT ENGINE FUEL FEED LINES 24 LEFT FIREWALL FUEL SHUTOFF VALVE 25 APU NEGATIVE-G PROTECTION LINE SHUTOFF VALVE 26 ONE-WAY CHECK VALVE 27 GRAVITY FEED LINE - RIGHT MAIN TANK TO RIGHT COLLECTOR TANK 28 FLAPPER CHECK VALVES - WING STATION 85 29 GRAVITY FILLER CAP - AUXILIARY TANK 30 RIGHT SCAVENGE EJECTOR LINE 31 RIGHT TRANSFER LINE 32 RIGHT TRANSFER LINE FLOAT VALVE 33 RIGHT VENT LINES PURGE CONNECTION 34 RIGHT SCAVENGE EJECTOR 35 APU FUEL PUMP 36 MOTIVE FLOW LINE 37 FLOW SWITCH - RIGHT SCAVENGE EJECTOR 38 FILTER 39 HEAT EXCHANGER - NO.3 HYDRAULIC SYSTEM 40 APU FUEL FEED LINE 41 CROSSOVER LINE 42 APU FUEL SHUTOFF VALVE 43 HEAT EXCHANGER - APU GENERATOR OIL COOLER 44 FILTER 45 APU NEGATIVE-G PROTECTION FUEL FEED LINE LEGEND ENGINE AND APU FUEL FEED EJECTOR MOTIVE FLOW LINES 33111111 SCAVENGE EJECTOR FLOW TRANSFER EJECTOR FLOW " " " APU FEED RETURN FLOW EFFECTIVITY Applicable only to aircraft with additional auxiliary tanks installed. Designated primary auxiliary tank on aircraft with additional auxiliary tanks installed (refer to Figure 2). Aircraft that do not incorporate Canadair Service Bulletin 600-0318. Aircraft incorporating Canadair Service Bulletin 600-0407. 0 SECTION 12 Page 3/4 Feb 12/88 OPERATING MANUAL PSP 606 AUXILIARY TANK SYSTEM VENT LINES REAR AUXILIARY TANK Auxiliary Fuel Tanks Figure 2 SECTION 12 Page 5/6 Feb 12/88 VENT SHUTOFF VALVE FORWARD AUXILIARY TANK GRAVITY TRANSFER LINE PRIMARY AUXILIARY TANK EFFECnVTTY: Applicable only to aircraft with additional auxiliary tanks installed. canadair chauenQer OPERATING MANUAL PSP 606 On aircraft with additional auxiliary tanks, the auxiliary tank described above is designated the primary auxiliary tank and is connected by gravity flow transfer lines to the forward and rear auxiliary tanks. The additional auxiliary tanks are located under the floor beams of the centre fuselage immediately in front of and behind the fuselage pressure structure over the wing. The tanks are of double-walled aluminum alloy construction and the space between the outer and inner walls is drained and vented overboard. A general arrangement view of the additional auxiliary tank installation and its associated components is shown on Figure 2. The additional auxiliary tanks increase the usable fuel capacity of the system by 1782 pounds (805 kg). FUEL DISTRIBUTION (Figures 1 and 3) Independent fuel supplies are provided for the engines and the APU. In normal operation, the left and right engines are fed by the primary ejector pumps in the left and right collector tanks respectively. Two electric pumps are mounted beside the collector tanks and serve as backups to the primary ejectors. The APU supply is drawn directly from the right main tank by an electric pump. A. Ejector Pumps An ejector pump operates on the same principle as a venturi tube to convert a small volume/high pressure input (motive flow) at the throat of the unit into a large volume/low pressure output flow at the ejector nozzle. Motive flow for the scavenge and primary pumps is provided by the high pressure stage of a two-stage engine-driven pump (EDP). The motive flow reaches pressures between 50 and 350 psi and is routed back to the fuel storage area through the engine pylon via a one-way check valve. Given a motive flow of 7.05 gal/min at 300 psi, each primary ejector produces an output flow of 25.0 gal/min at 21 psi. The output from the other ejectors is somewhat lower. Compared with conventional electric fuel pumps, the ejectors require minimal maintenance and greatly improve fuel system reliability. B. Engine Feed The primary eiector pumps provide a continuous fuel flow to the engine driven pumps (EDP) at a pressure and volume sufficient for maximum engine consumption and motive flow requirements. The fuel from each ejector flows through a feed line across the firewall fuel shutoff valve to the inlet of the EDP. One-way check valves on the feed lines control the direction of flow so that each ejector supplies only the engine associated with it. SECTION 12 Page 7 Apr 4/83 canadair chaiiencjer OPERATING MANUAL PSP 606 PUMP SWITCH/LIGHTS Switch/lights control operation of electric fuel pumps in conjunction with pressure switches at primary ejector outlets. If a PUMP switch/light is in the pressed in position, and low pressure condition is detected at outlet of associated primary ejector, both electric fuel pumps come on to maintain required fuel flow to affected engine. Pressure switches at primary ejector outlets operate at 13 psi increasing pressure and 10 psi decreasing pressure. PUMP ON/INOP LIGHTS Green ON light comes on if the associated electric pump is operating. Amber INOP light comes on if the associated pump switch is out or if a pump failure occurs. RTANK /

f214216709 发表于 2010-5-18 10:38:39

庞巴迪挑战者燃油

guomai127 发表于 2010-9-11 09:18:08

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dul 发表于 2011-2-11 13:31:40

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bocome 发表于 2011-7-31 11:16:40

庞巴迪挑战者燃油

domoto0516 发表于 2011-10-22 18:53:23

龐巴迪的挑戰永無止境

autofannuaa 发表于 2011-12-7 14:02:20

偶然经过，学习一下

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Bombardier-Challenger_00-Fuel庞巴迪挑战者燃油

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