Bombardier-Challenger_01-Fuel庞巴迪挑战者燃油

航空发表于 2010-5-9 09:05:41

Bombardier-Challenger_01-Fuel
 
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航空发表于 2010-5-9 09:06:00

cnaMMBFUQGr OPERATING MANUAL PSP 601A-6 SECTION 1 FUEL TABLE OF CONTENTS GENERAL FUEL STORAGE FUEL FEED A. Ejector Pumps B. Electric Pumps C. Engine Feed D. APU Fuel Feed E. Tank Vent System REFUEL/DEFUEL SYSTEM A. Pressure Refuel/Defuel System B. Pressure Refueling C. Suction Defueling D. Gravity Refueling and Defueling FUEL QUANTITY INDICATING SYSTEM TAIL FUEL TANK SYSTEM A. General B. Refueling and Defueling C. Fuel Transfer D. Fuel Jettison System E. Tail Tank Vent System F. System Operation Page 1 2 3 3 3 4 4 4 5 5 5 6 6 7 7 7 7 7 8 8 8 LIST OF ILLUSTRATIONS Figure Title Page Number 1 Fuel Feed System - Schematic (2 Sheets) 11 2 Fuel Control Panel (2 Sheets) 13 3 Refuel/Defuel System - Schematic 15 12 - CONTENTS Page 1 Apr 10/95 OPERATING MANUAL PSP 601A-6 Figure Title Page Number 4 Refuel/Defuel Control Panel 16 5 Fuel Quantity Indicating System 17 6 Fuel Specific Weight 18 7 Tail Tank System - Schematic 19 8 Tail Tank Control Panel (2 Sheets) 20 12 - CONTENTS Page 2 Apr 10/95 GSSSmricjer OPERATING MANUAL PSP 6C1A-6 SECTION 12 FUEL 1. GENERAL (Figure 1) The fuel system has a three-tank configuration consisting of left and right main tanks, and an auxiliary tank, On aircraft 5135 and subsequent and aircraft incorporating Canadair Service Bulletin 601-0262, a tail tank is installed (refer to paragraph 6.). 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 pressure refuel/defuel adapter is provided. Gravity refueling or defueling is also possible. Fuel and water drains are located at various low points on the fuel system. 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 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. SECTION 12 Page 1 Apr 10/95 OPERATING MANUAL PSP 601A-6 2. FUEL STORAGE (Figure 1) The entire wing box structure is sealed to form three tanks: the left and right main tanks and the primary section of the auxiliary tank. Front and rear sections (double-walled tanks) of the auxiliary tank are installed in the fuselage forward and aft of the primary auxiliary tank. The capacities of the tanks, in litres (US gallons) of usable fuel, are: Pressure refueling Gravity refueling (approx.) Litres (US gallons) Litres (US gallons) Left main tank 2733 (722) 2536 (670) Right main tank 2733 (722) 2536 (670) Auxiliary tank 3823 (1010) 3569 (943) Total 9289 (2454) 8641 (2283) A balance line, equipped with an electrically operated cross-flow valve, connects the main tanks at their lowest points. Selecting the X-FLOW switch/light, opens the cross-flow valve to allow the main tank fuel quantities to equalize by gravity. On aircraft 5001, 5027 and subsequent and aircraft incorporating Canadair Service Bulletin 601-0225, an electrically operated cross-feed valve is connected at each end of the balance line. Selecting the LEFT TO RIGHT or RIGHT TO LEFT switch/lights, opens the associated cross-feed valve to allow fuel to enter the auxiliary tank. Fuel is then transferred to the main tanks by the engine ejector pumps with engines running or by the electrical boost pumps with engines shut down. A safety feature prevents opening of both cross-feed valves at the same time. Approximately 8 minutes after fuel balancing commences, the selected switch/light begins to flash as a reminder that the cross-feed valve is open. The primary section of 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 main ejector pumps and are maintained full by gravity feed lines and the scavenge ejector lines from the main tanks. The electric fuel pumps are also located inside the auxiliary tank, beside the collector tanks. When in operation, each electric pump draws fuel only from its corresponding collector tank. Flush-mounted access panels 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 engine fuel 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. The three sections (or tanks) that make up the auxiliary tank are interconnected and are treated as one tank for the purpose of refueling, defueling and fuel feed. SECTION 12 Page 2 Apr 10/95 OPERATING MANUAL PSP 601 A - 6 FUEL FEED (Figures 1 and 2) Independent fuel supplies are provided for the engines and the APU. In normal operation, the left and right engines are fed by the main ejector pumps in the left and right collector tanks respectively. The two electric pumps serve as backups to the main ejectors. The APU supply is drawn directly from the right main tank by an electric pump. NOTE: To avoid fuel spillage through the fuel tank vent system, the electric fuel pumps must not remain on for more than 5 minutes without the engines running. 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 main pumps is provided by the high-pressure section of the associated engine pump. B. Electric Pumps Two electric fuel pumps are connected to the collector tanks and serve as sources of fuel pressure during engine starting and as backups for the main fuel ejectors. The pumps are controlled by the two PUMP switch/lights on the fuel control panel in conjunction with pressure switches in the outlet lines of the main fuel ejectors. The PUMP switch/lights arm both electric fuel pumps. If a low fuel pressure condition exists at the outlet of the associated main fuel ejector, both of the electric pumps come on to ensure that an adequate flow of fuel is delivered to the engine pump. The electric pumps shut down automatically when the required output pressure is re-established at the outlet of the main ejector. On aircraft 5135 and subsequent, should the electric fuel pumps fail or if they are selected off, the FUEL LO PRESS lights will come on. SECTION 12 Page 3 Apr 10/95 ctrnvencjer OPERATING MANUAL PSP 601A-6 C. Engine Feed The main ejector pumps provide a continuous fuel flow to the engine pumps 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 engine pump. One-way check valves on the feed lines control the direction of flow so that each ejector supplies only the engine associated with i t. The collector tanks are kept f u l l by gravity feed lines from the associated main tanks supplemented by scavenge ejectors. The scavenge ejectors ensure that the collector tanks are supplied with main tank fuel during low fuel conditions and during f l i g h t with high nose-up attitudes. The sequence of fuel transfer between the auxiliary tank and the main tanks is such that all the fuel carried aboard the aircraft is transferred to the main tanks before being fed to the collector tanks. When the main tank fuel level drops below approximately 93% of f u l l, transfer of fuel from the auxiliary tank begins automatically to maintain that level in the main tanks. The transfer is effected by two transfer ejectors which are provided with motive flow by bleeds from the engine feed lines. Float valves control the transfer of fuel to approximately the 93% f u l l level. D. APU Fuel Feed The APU is supplied with fuel by an electric fuel pump located in the right main fuel tank. APU fuel is also routed via a fuel/oil heat exchanger to cool the APU generator o i l . The APU pump is controlled by a switch/light on the APU control panel (refer to Section 5). The APU fuel feed line is f i t t e d with an electrically operated fuel selector valve. To ensure uninterrupted operation of the APU during negative 6 conditions, a negative G protection fuel feed line connects with the l e f t engine fuel feed line. The line is f i t t e d with an electrically operated fuel shutoff valve and a one-way differential check valve which opens when the main APU supply pressure drops below the pressure in the engine fuel line. During normal operation, both of the shutoff and selector valves on the APU fuel system are opened and closed simultaneously by the START/STOP switch/light on the APU control panel (refer to Section 5). Operation of the APU FIRE PUSH switch/light closes both the APU fuel shutoff and selector valves. E. Tank Vent System The fuel tanks are vented to atmosphere through common vent lines which terminate at NACA scoops on the l e f t and right lower wing surfaces. The vent lines are continuously purged whenever the scavenge ejectors operate. SECTION 12 Page 4 Jan 06/98 OPERATING MANUAL PSP 601A-6 4. REFUEL/DEFUEL SYSTEM (Figures 3 and 4) Refueling and defueling is carried out using the single point pressure refuel/defuel adapter on the right wing leading edge f i l l e t , or through gravity f i l l e r caps and drain valves associated with each fuel tank. Tank venting is maintained by the fuel tank vent system or, during pressure refueling operations, by vent relief valves which act to prevent tank overpressures. The action of level control valves provides fuel expansion space and protection against over-filling by limiting the full fuel volume to 98% of the total tank volume. The location of the gravity-filler caps limits the full fuel volume to approximately 91% of the total tank volume. A. Pressure Refuel/Defuel System This system consists of a standard single point refuel/defuel adapter and a refuel/defuel control panel in the right wing f i l l e t. The pressure refuel/defuel system can accept the following maximum pressures and flow rates: Maximum refuel rate 946 litres (250 US gallons)/minute Maximum refuel pressure 55 psi Maximum defuel rate 537 litres (142 US gal Ions)/minute Maximum defuel suction 8 psi (negative pressure) After suitable pressure or suction has been established at the refuel/defuel adapter, the transfer of fuel into or out of the fuel tanks is obtained by energizing and de-energizing the tank shutoff valves on the fueling manifold. The tanks can also be defueled without electrical power using only the suction applied by the fuel tender. B. Pressure Refueling With the POWER switch ON, the MODE selector set to FUEL and the FUEL/DEF switches selected to FUEL, fuel pressure is allowed to open the tank shutoff valves. Fuel flows from the shutoff valves through pilot lines to the level control valves in the fuel tanks. When the tanks are f u l l, the floats of the level control valves close the pilot lines. Back pressure, transmitted through the pilot lines closes the shutoff valves to stop the flow of fuel to the tanks. Valve positions are monitored by the SOV OP and SOV CL lights on the refuel/defuel control panel (refer to Figure 4). Testing the operation of the tank shutoff valves and their associated level control valves is done by simulating a full-tank condition. This is accomplished by f i l l i ng bowls which surround each float with fuel. The test is carried out while refueling is in progress using the MODE selector switch. It takes 20 to 30 seconds to f i l l the bowls which, when f u l l , cause the system to respond as i f the tank was f u l l . Refueling operation is re-established by reselecting the MODE selector to the normal FUEL position. SECTION 12 Page 5 Apr 10/95 OPERATING MANUAL PSP 0O1A-6 Vent relief valves, one in each main tank and one in the primary section of the auxiliary tank, prevent fuel tank overpressure should the fuel tank vent system or the tank shutoff valves fail during pressure refueling. Each vent relief valve is connected by a pressure-sensing line to the fueling manifold and is designed to open on positive fluid pressure only, therefore remaining closed during suction defueling. The vent relief valve positions are monitored via the green VV OPEN lights on the refuel/defuel control panel* C. Suction Defueling The aircraft may be completely defueled without electrical power via the single point refuel/defuel adapter. A fuel tender suction of 8 psi will open the tank shutoff valves. When the tanks are empty, the valves close by spring pressure. The tanks may also be selectively defuel ed provided by refuel/defuel panel is electrically powered and the MODE selector is set to DEFUEL. Starting and stopping of defueling of a given tank is accomplished by selecting the associated FUEL/DEF switch to DEF and OFF respectively. D. Gravity Refueling and Defueling The fuel tanks may be filled by gravity through f i l l e r caps. The f i l l er caps of the l e f t and right main tanks are mounted flush with the upper skin of the l e f t and right wing respectively. The f i l l e r cap for the auxiliary tank is recessed below the right wing skin adjacent to the wing root f i l l e t. A plug-type electrical grounding attachment, placarded ELECTRICAL GROUND STUD, is located just forward of each f i l l e r cap on the lower surface of the wing leading edge. Gravity defueling is carried out through gravity defueling drains located at the lowest point in each tank. Each drain consists of a capped orifice into which an adapter is inserted to allow fuel to drain from the tank. In addition to the gravity defueling receptacles, water drains are provided at various locations on the lower wing surface. The valves are opened by using a screwdriver to depress and rotate the valve core to expose drain holes on the base of the valve housing. i SECTION 12 Page 6 Apr 10/95 fonssumssncfBr OPERATING MANUAL PSP 601A-6 | 5. FUEL QUANTITY INDICATING SYSTEM (Figures 5 and 6) The fuel quantity indicating system consists of capacitance-type fuel quantity sensors in the fuel tanks, a signal conditioner to power the quantity sensors and process their fuel quantity signals, and a fuel quantity panel powered by a signal data converter. The individual tank and total usable fuel contents in pounds are displayed as digital readouts on the FUEL QUANTITY panel. The fuel quantity displayed for each main tank includes the fuel contained in the associated collector tank. The fuel quantity displayed for the auxiliary tank includes the fuel contained in the primary, front and rear sections of the auxiliary tank. 6. TAIL FUEL TANK SYSTEM (Figures 7 and 8) A. General On aircraft 5135 and subsequent and aircraft incorporating Canadair Service Bulletin 601-0262, the tail cone structure forward of the kevlar fairing is sealed to form a 187.7 US gallon (827 litre) fuel tank. The complete tail tank system consists of provisions for powered or gravity fuel transfer, fuel jettison, pressure refueling and defueling and quantity sensing. Controls and indicators for the system include a T/TANK FUEL TRANS panel and a modified FUEL QUANTITY panel in the flight compartment. On aircraft 5135 and subsequent, the T/TANK FUEL TRANS panel is integrated as part of the FUEL CONTROL panel. A T TANK TEST panel on the bulkhead behind the copilot's seat is provided for maintenance purposes, B. Refueling and Defueling The tail tank is pressure refueled and defueled via the existing fueling adapter on the right wing f i l l e t . A line fitted with two shutoff valves feeds fuel from the fueling adapter and fuel manifold to the tail tank. The shutoff valves are controlled by switch selections on the modified refuel/defuel panel and signals from a level switch, designated the full level switch, in the tail tank. No provisions are made for gravity fueling of the tail tank. C. Fuel Transfer A 28 volt dc boost pump in the tail tank transfers fuel to the primary auxiliary tank via a transfer shutoff valve and transfer line. The boost pump is controlled by the tail tank AWED/OFF switch selections and signals from two level switches, one in the primary auxiliary tank designated auxiliary tank level switch No. 1 and one in the tail tank designated tail tank level switch No. 1. SECTION 12 Page 7 Apr 10/95 OPERATING MANUAL PSP 601A-6 On aircraft 5135 and subsequent and aircraft incorporating Canadair Service Bulletin 601-0355, an in-line/backup electrical boost pump is installed to improve transfer rate. The in-line pump automatically comes on if the primary transfer rate is low or if the auxiliary and/or tail tank level switch fails. The fuel transfer line is protected by a nitrogen pressurized shroud on that part of its run subject to possible damage from an engine rotorburst. Sudden loss of pressure in the shroud is detected and fuel transfer from the tail tank is automatically stopped. If powered fuel flow fails, gravity feed to the transfer line and thence to the primary auxiliary tank takes place via a gravity transfer shutoff valve. This valve is controlled open and closed by a flow switch in the transfer line and a level switch, tail tank level switch No. 2, in the tail tank. D. Fuel Jettison System Tail tank fuel can be jettisoned through an overboard line opening under the tail cone. A shutoff valve, controlled by switch/light selection on the T/TANK FUEL TRANS panel or the FUEL CONTROL panel (aircraft 5135 and subsequent), is opened to allow gravity flow of fuel into the overboard line. E. Tail Tank Vent System Tail tank venting is maintained through a vent line and check valve connected to the ram air duct and an opening under the tail cone. In the event of a failure of the refuel/defuel system components, fuel flow through the vent line opening under the tail cone is sufficient to prevent tank overpressure. F. System Operation (1) Refueling and Defueling Tail tank refueling is possible only when all other tanks are full. Until this condition is satisfied, the two shutoff valves in the tail tank fueling line are closed by signals from a level switch in the primary auxiliary tank, auxiliary tank level switch No. 2. When the fueling nozzle is connected and refueling pressure is applied, the closed position of the shutoff valves is verified by the green CL light above the TAIL switch on the refuel/defuel panel. With the panel MODE selector at FUEL, the TAIL switch set to FUEL and all other fuel tanks full, the amber OP light comes on to indicate that the tail tank fueling line shutoff valves are open. At the maximum refueling pressure of 55 psi, refueling is accomplished at a rate of 45 US gallons per minute until the tail tank full level switch signals that the full level (85% of tank volume) is reached and closes the shutoff valves. At any time during refueling operations, the shutoff valves can be closed by setting the TAIL switch to OFF or the MODE selector to OFF or DEFUEL. SECTION 12 Page 8 Apr 10/95 eSSS&icjer OPERATING MANUAL PSP 601A-6 Defueling can be carried out at any time, regardless of the fuel quantity in the other tanks, by setting the MODE selector to DEFUEL and the TAIL switch to DEF. The OP light will then come on to indicate that the shutoff valves are open and that defueling is talcing place. At the maximum defueling pressure of 8 psi negative, the tank is defueled at the rate of 15 US gallons per minute. When the tail tank is empty, the shutoff valves close and the CL light comes on. At any time during defueling, the shutoff valves can be closed by setting the TAIL switch to OFF or the MODE selector to OFF or FUEL. Before fueling operations are started, the correct functioning of the system components can be checked by setting the TAIL switch to FUEL and the MODE selector to TEST. This causes flow from a pilot line into a bowl on the tail tank full level switch to simulate the tank full condition. Correct operation of the system components is observed i f the OP light comes on, then goes out followed by the CL light's coming on. (2) Fuel Transfer With the tail tank ARMED/OFF switch set to ARMED, the transfer shutoff valve opens and the transfer boost pump comes on as signaled by the auxiliary tank level switch No. 1 when the primary auxiliary tank fuel quantity decreases below a preset level. Transfer is carried out at a rate of 15 pounds per minute until the unusable fuel level (1.3 US gallons) is sensed by tail tank level switch No. 1. At this point, the transfer shutoff valve closes and the boost pump shuts down. I f the ARMED/OFF switch set to OFf while usable fuel remains in the tail tank, the amber NOT ARMED light comes on. If, in this condition, the fuel quantity in the primary auxiliary tank is allowed to reach the level sensed by auxiliary tank level switch No. 2, the NOT ARMED light flashes. If the ARMED/OFF switch is then set to ARMED, the light goes out and transfer starts immediately. On aircraft 5135 and subsequent and aircraft incorporating Canadair Service Bulletin 601-0355, a failure of powered fuel transfer is detected by the transfer line flow sensor which signals the transfer shutoff valve closed, shuts down the boost pump, opens the gravity transfer shutoff valve and turns on the in-line/backup pump. The SEC TRANS light comes on to indicate that fuel transfer by the in-line/backup pump is taking place. Transfer continues at a minimum rate of 8 pounds per minute until tail tank level switch No. 2 senses that approximately 2.3 US gallons of fuel remain in the t a i l tank. At this level, the SEC TRANS light goes out, the gravity transfer shutoff valve closes and the in-line/backup pump shuts down. SECTION 12 Page 9 Apr 10/95 GttsuShiQtBr OPERATING MANUAL PSP 601A-6 On aircraft not incorporating Canadair Service Bulletin 601-0355, a failure of powered fuel transfer is detected by the transfer line flow sensor which signals the transfer shutoff valve closed, shuts down the boost pump and opens the gravity transfer shutoff valve. The GRAV TRANS light comes on to indicate that gravity transfer is taking place. Transfer continues at 6 to 8 pounds per minute until tail tank level switch No. 2 senses that approximately 2.3 US gallons of fuel remain in the tail tank. At this level, the GRAV TRANS light goes out and the gravity shutoff valve closes. A perforation of the nitrogen pressurized shroud surrounding part of the transfer line is detected by a pressure switch which signals all open shutoff valves to close and shuts down the boost pump. Transfer of fuel from the tail tank is not possible until the shroud is replaced and pressurized* (3) Fuel Jettison On aircraft 5135 and subsequent and aircraft incorporating Canadair Service Bulletin 601-0362, pressing the DUMP SWITCH ARMED switch light causes the switch/light to come on green and arms the jettison system. With the system armed, pressing the DUMP SELECT switch/light causes the switch to cane on green and the DUMP OPEN light to cane on white opens the jettison shutoff valve. Fuel is then discharged through the overboard line at approximately 100 pounds per minute. Fuel jettison can be stopped by pressing the DUMP SWITCH ARMED or the DUMP SELECT switch light again to close the jettison shutoff valve. On aircraft not incorporating Canadair Service Bulletin 601-0362, pressing the DUMP SWITCH ARMED switch light causes the switch/light to come on green and arms the jettison system. With the system armed, pressing the PRESS TO DUMP switch/light causes the switch to cone on green and opens the jettison shutoff valve. Fuel is then discharged through the overboard line at approximately 100 pounds per minute. Fuel jettison can be stopped by pressing the DUMP SWITCH ARMED or the PRESS TO DUMP switch/light again to close the jettison shutoff valve. i SECTION 12 Page 10 Apr 10/95 OPERATING MANUAL PSP 601A-6 (FRONT SECTION) CLOSE RIGHT ENGINE CLOSE FIRE I <%J9H J LEGEND CLOSE OPEN/ CLOSE ARU FIRE PUSH EFFECTMTY:A/C 5001,5027 AND 6UBS AND A/C POST SB 601-0225 mmniH ezza is FUEL FEED MOTIVE FLOW SCAVENGE FLOW TRANSFER FLOW APU GF*I COOLING FLOW EJECTOR ELECTRIC PUMP PRESSURE SENSOR FLOW SENSOR CHECK VAVLE f J»« n>A«Maw an. m* I >—* ;QaiEW-E3|ff« icalggslFaii^jEgB Fuel Feed System - Schematic Figure 1 (Sheet 1) SECTION 12 Page 11 Apr 10/95 OPERATING MANUAL f*SP 601A-6 (FRONT SECTION) LEFT ENGINE ^mnm^ + + u APU NEGATJVE-G PROTECTION SHUTOFF VALVE IMEMQ M K *JSM CLOSE APU SELECTOR VALVE APU RIGHT ENGINE CLOSE CLOSE OPEN/ CLOSE EFFECnVTTY:A/C 5002 TO 5026 PRE SB 601-0225 LEGEND FUEL FEED MOTIVE FLOW l U I I I t l l l l SCAVENGE FLOW H A W TRANSFER FLOW \SSSA APU GBl COOLING FLOW QC^J EJECTOR ELECTRIC PUMP PRESSURE SENSOR f S g l FLOW SENSOR ^STl CHECK VAVLE Fuel Feed System - Schematic Figure 1 {Sheet 2) SECTION 12 Page 12 Apr 10/95 OPERATING MANUAL PSP 601A-6 LTANK AND R TANK FEED SWITCH/LIGHTS (2) When pressed in, appropriate crossfeed valve opens. green LEFT TO RIGHT or RJGHTTO LEFT light comes on andlue! flows into auxiliary tank by gravity. When pressed out. eroasfeed valve doses and light goes out L TANK AND R TANK EJCTRS LIGHTS (2) Amber SCAV light comes on rf scavenge ejector failure is detected by flow sensor at ejector outlet. Amber MAIN light comes on if main ejector failure b detected by pressure switch at ejector outlet. L TANK AND R TANK PUMP SWTTCH/UGHTS O Control operation of electric fuel pumps in conjunction with pressure switches at main ejector outlets. If a PUMP switch/fight is pressed in, wd low pressure condition is detected at outlet of associated main ejector, both electric fuel pumps come on to maintain required fuel flow to affected engine. Green ON light comes on if associated engine pump b operating. Amber INOP ight comes on if a pump failure occurs. pump switch is out or if PUMP FUEL CONTROL -PUSH ON OFF- 1 SCAV J 1 MAM j 1 °^ II 1 MOP II 1 OPEN 1! ON j II WOf i j SCAV 1 1 MAIN II VALVE CLOSED LIGHTS (21 White VALVE CLOSED light < shutoff valve is closed. i on if associated firewall fuel X-FLOW SWITCH/LIGHT When pressed in, balance fine cross-flow valve opens, green OPEN ight comes on and left and right main tanks equalize by gravity flow. When pressed out. balance i n e shutoff valve doses and tight goes out. NOTE Refer to Section 17 for osteite of fuel temperature indicator, 9nd FILTER and LOW PRESS fights. EFFECnVITY: A/C5001.6027 AND SUBS AND A/C POST SB 601-0225 Fuel Control Panel SECTION 12 Figure 2 (Sheet 1) Page 13 Apr 10/95 OPERATING MANUAL PSP 601A-6 L TANK AND R TANK PUMP SWITCH/LIGHTS © Control operation of electric fuel pumps in conjunction with pressure switches at main ejector outlets. LTANK AND R TANK EJCTRS UGHTS (2) Amber SCAV light comas on if scavenge ejector failure is detected by flow sensor at ejector outlet. if e PUMP switch/light is pressed in, *n6 low pressure condition is detected at outlet of associated main ejector, both elect, ic fuel pumps come on to maintain required fuel flow to affected engine. Green ON tight comes on if associated engine pump is operating. Amber INOP Eght comes on if associated pump switch b out or rf a pump failure occurs. Amber MAIN tight comes on if main ejector failure is detected by pressure* switch at ejector outlet. VALVE CLOSED UGHTS C2J White VALVE CLOSED light ( shutoff valve is closed. . on if associated firewall fuel X-FLOW SWTTCH/U6KT i oressed in, balance fne cross-flow valve opens, green OPEN ight comes on and left and right main tanks equalize by gravity flow. When pressed out, balance few shutoff valve closes and ight goes out. NOTE ncfar to Secoon 17 for details of fuel temperature nxScmoc, and FILTH* and LOW PRESS fights. EFFECTJVITY: A/C 5002 TO 502t PRE 88 601-022$ Fuel Control Panel Figure 2 (Sheet 2) SECTION 12 Page 14 Apr 10/95 OPERATING MANUAL PSP 601A-6 LEVEL CONTROL VALVE/FLOAT SOLENOID VALVE- (OoMd during system tost) LEFT MAIN TANK REFUEL/DEFUEL ADAPTER TANK SHUTOFF VALVE TWO-WAY CHECK VALVE AUXIUARYTANK TF* RIGHT MAIN TANK | onn |jllslsdr "J| OKN |] •}}g|o»|] I MODE w w v I > UN AUX LMN *=f L SELECTED TANKS ONLY - i VENT REUEF VALVE ^ I ow ||lcL|oi|{cMo4|cajc4| ft vvV 1 ctggpTH sov MODE POWER) TAIL R.MAIN AUX L.MAJN *UfL/JXR»ft> bH-kCI IVIIY: A « 5001 TO 5134 PRE SB 801-0262 LEGEND REFUEL/DEFUEL LINES LEVEL CONTROL PILOT LINES PRESSURE-SENSING LINES EFFECnVITY: A/C 5185 AND SUBS AND A/C POST SB 601-0262 Refuel/Defuel System - Schematic Figure 3 SECTION 12 Page 15 Apr 10/95 OPERATING MANUAL PSP 601A-6 8 °* (I |1CI|OP|MJ CLJOpjfl CLJOPfrjj Ci.foqP^^^ MODE J T £ S T ^ — ^ OFF TOWER I TAIL R.MAIN AUX EFFECTMTY: A/C 5135 AND SUBS AND A/C POST SB 601-02*2 POWER ON INDICATOR Green light comes on when POWER switch is set to ON. VENT RELIEF VALVE STATUS LIGHTS SHUTOFF VALVES STATUS LIGHTS Green CL lipht comes on rf POWER switch is ON and associated tank shutoff valve is on if POWER switch is tank shutoff valve is open. POWER SWITCH Setting switch to ON arms contacts of MODE selector switch. Switch connects cvectty to ZB'VOft dc osttory direct bus. Fight cornpartrnent switch selection n not necessary during, pressure ftrfusJ/dofuet operations. FUEL/DEF SWITCHES Controls operation of tank shutoff valves in conjunction with mode selections on MODE selector switch. MODE SELECTOR SWITCH FUEL - Opens tank shutoff valves in conjunction with FUEL sanction on FUEL/DEF switches to perrrst pressure refueling. DEFUEl - Opens tank shutoff valves in conjunction with OET selection on FUEL/DEF switches to permit suction defusing. OFF - Disarms FUEL/DEF switches. TEST - Teats operation of tank shutoff verves by simulating fufi fuel condition in tanks. With fueling pressure applied at refusing nozzle. POWER switch ON and FUEL/DEF switches set at FUEL. SOV-CL lights go out and SOV-OP lights come on for 20 to 30 seconds. Correct operation of shutoff valves is vxficated when SOV-CL fights come on mwTwoiatery after SOVOP fcghts go out. Refuel/Defuel Control Panel SECTION 12 Figure 4 Page 16 Apr 10/95 OPERATING MANUAL PSP 601A-6 CAPACITANCE TYPE FUEL QUANTITY SENSORS 6 in each main tank. 3 in primary auxftsry tank. 1 in each collector tank. 11n tafl tank [7J r® SIGNAL CONDITIONER Converts return signals from quantity sensors into dc signals suitable for use by quantity indicator. U<=> SIGNAL CONDITIONER SIGNAL DATA CONVERTER SIGNAL DATA CONVERTER Provides dual power supply, tapped from the battery bus and the dc essential bus. for the noscator logic arcuita and display lamps. EFFECTTYTTY: A/C 5135 AND SUBS AND A/C POST SB 601-0262 DIGITAL READOUTS ImernaHy illuminated digital displays. Readouts provide continpus indication of "usable fuel quantity in each tank plus system total. EFFECTIVITY B A/C 5135 AND SUBS AND A/C POST SB 601-0232 CENTRE INSTRUMENT PANEL NOTE Refer to Section 17 for details of indicator test. Fuel Quantity Indicating System SECTION 12 Figure 5 Page 17 Apr 10/95 crS&Encjetr OPERATING MANUAL PSP 601A-6 7.51 1 j 1 1 1 j 7.4 7.3 73 SPECIFICATION LIMITS FUEL SP GR (60/60 F) KEROSENE 0.775 - 0.845 WIDE CUT 0.751 - 0.802 5.6 -60 -40 -20 0 20 40 60 80 100 120 140 160 TEMPERATURE °F Fuel Specific Weight SECTION 12 Figure 6 page 18 Apr 10/95 OPERATING MANUAL PSP 601A-6 FUELING ADAPTER AND MANIFOLD LEGEND ELECTRIC PUMP C 3 — PRESSURE SENSOR § FLAME ARRESTER F ^ l CHECK VALVE ^ » t FLOW SENSOR E A/C 5135 AND SUBS AND A« POST SB 601-0356 gj A/C 5001 TO 5134 PRE SB 601-0355 H AfC 5135 AND SUBS AND JVC POST SB 601-0362 B A/C 5001 TO 5134 PRE SB 501-0352 Tail Tank System - Schematic Figure 7 SECTION 12 Page 19 Apr 10/95 OPERATING MANUAL PSP 601A-6 DUMP SWITCH ARMED SWITCH/LIGHT j . green DUMP SW ARMED kgrncomo on and PRESS TO DUMP SWItCR/bght 9 JHtflBO. PRESS TO DUMP SWITCH/LIGHT i PRESS NOT ARMEO LIGHT Amber bght comes on steady <f usab<e fuel is m tail tank and ARMED/OF? switch cs in OFF position. If toei «n primary auxiliary tank cs aBowed to decrease to preset level, kght comes on flashing. GRAY TRANS LIGHT AmDer light comes on to indicate that gravity transfer is in progress. Light goes out when transfer PRESS TO DUMP m SEC DUMP SWITCH / LIGHT When armed DUMP SELECT comes on green and when pressed. white DUMP OPEN kgti comes on end jettison ehutotf VI)VB opens. T«B fenktuei i t dteeheiged at 100 pounds / minute. SECTRANS LIGHT Amber Mght comes on to indicate that the beck-up putnp is on (eutomatteaBy) IT primary transfer rate is low or the auxiary and / or tei tank leva! switch fails. ARMED/OFF SWITCH fn ARMED position transfer shutott valve opens and booAi pump transfers tuoi to pnmary auxifeary lank on s»gn*s from muubmy tank and tail tank level switches. fcwcnvnv A/C SOOt TO SIM El AJC POST SB 001-0355 B A/CP08T88081-0362 Tail Tank Control Panel Figure 8 (Sheet 1) SECTION 12 Page 20 Apr 10/95 OPERATING MANUAL PSP 601A-6 @ I L £ ' j, -PUSH C* «* — If"' C -==-^=iJ - ^ I M P X^LOV; pijklP J1 ?CAV irsrisii r irTOKT -^T^n "3 1 i .XA i I jlC* C3EC 1 ^^-V^Os^ - -^ / / !! cm. I i: Ik^J^ 1 DUMP SWITCH ARMED SWITCH/LIGHT i DUMP SW ARMED tight comes on and PRESS TO DUMP switch/light is armed. DUMP SWITCH /LIGHT Whan armed DUMP SELECT comae on graan and whan pressed, while DUMP OPEN tight comas on and jettison shutoff vaJve opens. Tail tank tuei is discharged at 100 pounds / minute. Amber ligh: comes on steady if usabte tuei is in tail tank and ARMED/OFF switch is in OFF position, if fuel in primary auxiliary tank is allowed to decrease to preset level, light comes on hashing. SEC TRANS LIGHT Amber Hght comes on to Indicate thai the back-up pump is on (automaticaBy) fl primary transfer rate is low or the auxitary and /or tail tank level ewtteh tails. ARMED/OFF SWITCH ftr> ARMED position transfer shutotf valve opens and boost pump transfers fuel to primary auxiliary tank on signals from auxiliary tank and tail tank level switches. EFFECnVTTY: A/C 5135 ft SUBS Tail Tank Control Panel Figure 8 {Sheet 2) SECTION 12 Page 21 Apr 10/95

f214216709 发表于 2010-5-18 10:36:26

Fuel庞巴迪挑战者燃油

guomai127 发表于 2010-9-11 09:24:09

:lol :lol :lol

dul 发表于 2011-2-11 13:30:45

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bocome 发表于 2011-7-31 11:17:48

飞行操纵飞行操纵

autofannuaa 发表于 2011-12-7 14:14:06

偶然经过，学习一下

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航空论坛_航空翻译_民航英语翻译_飞行翻译's Archiver

Bombardier-Challenger_01-Fuel庞巴迪挑战者燃油

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