BD-700 Flight Crew Operating Manual (Volume 2)

and landing the pumps will also come on automatically with engines on and at least one of the following: flaps > 0°, landing gear down and in flight or low wing fuel condition (600 lbs each wing). Each AUX pump may be inhibited by selecting off a switch on the fuel control panel. NOTE When an AUX pump is used for wing transfer mode of operation and an AC pump fails, priority is given to the engine feed system and the automatic wing transfer operation will be inhibited. The pumps are automatically controlled by the Secondary Power Distribution Assembly (SPDA). FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−3 FUEL SYSTEM SYNOPTIC PAGE (CONT'D) Aft Transfer Pumps Two aft transfer pumps and associated shut-off valves are used to transfer fuel from the aft fuel tanks to the wing tanks. Transfer is scheduled by the fuel computer or by a switch selection on the fuel control panel. Centre Transfer Pumps Two centre transfer pumps (controlled by the FMQGC) are used to transfer fuel from the centre tank to the main wing tank. FUEL CONTROL PANEL The fuel control panel is located on the overhead panel in the flight compartment. The fuel control panel defines the operational modes, component controls and component inhibits. The fuel control panel has switches, which when selected, override the automatic control of certain components within the fuel system. Switch selections from this panel are sent to the ACPC. The ACPC will then control the system from the inputs received from the panel. The switch lamps come on in combination with certain EICAS messages, which represent the panel configuration or failure within a given system. GF1210_003 selection − Provides a means of transferring fuel from one wing to the other. Controlled by the FMQGC. selection − A left to right or a right to left selection, provides a means of transferring fuel (in the direction of the arrow) from one wing tank to the other. selection − Provides a method of inhibiting wing to wing transfer. PRI PUMPS Switch light − Indicates that both left wing primary pumps have been disarmed. The right PRI PUMPS switch has similar logic. AUX PUMP switch light − Indicates that the right auxiliary pump has been disarmed. The left AUX PUMP has similar logic. XFEED SOV switch light − Will come on when the valve does not go to the commanded position. light − When the switch is selected, the crossfeed valve opens and interconnects the engine feed lines. AFT XFER Switch selection − Provides a means of transferring fuel from the aft tank to the wing tank. Controlled by the FMQGC. selection − Provides a manual method of controlling the transfer schedule. selection − Inhibits the forward/aft transfer of fuel. RECIRC switch (If installed) light − Indicates that the FRTT valve is open when com- manded by flight crew. AUTO <− or −> OFF OPEN OFF AUTO ON OFF ON AUX PUMP has similar FAIL OFF AUTO WING XFER OFF AUTO AFT XFER OFF ON WING FEED INHIBIT AUX PUMP OFF PRI PUMP OFF L RECIRC ON L WING FEED INHIBIT AUX PUMP OFF PRI PUMP OFF R RECIRC ON R XFEED SOV FAIL OPEN WING XFEED switch FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−4 FUEL TANKS All fuel is carried in three integral tanks (left wing, right wing and centre wing) and a smaller aft fuselage tank (contained in a structurally enclosed bladder). The inboard section of each wing is designated as a feed tank, from which each engine draws its fuel. Fuel flows from the outboard sections of each wing tank, into the feed tank (by gravity), through swing check valves in the baffles of each main tank. The check valves allow fuel flow in the inboard direction only. This will restrict large fuel movements and limit centre of gravity shifts in airplane changes of attitude. Fuel is also transferred into the feed tanks from the centre wing and aft fuselage tanks by the transfer system. SERVICE POINTS GF1210_004 WING FUEL TANK WATER DRAIN AFT FUEL TANK FUEL AND WATER DRAIN WING FUEL TANK GRAVITY FUEL FILL CENTRE WING GRAVITY FUEL FILL WING FUEL TANK WATER DRAIN CENTRE FUEL TANK WATER DRAINS GRAVITY FUEL FILL LEGEND LOWER SURFACE UPPER SURFACE All tanks have flush self-closing water drain valves, installed at various low points, to permit draining of any accumulated water or residual fuel. They are located at the low point of each wing. Three gravity fill caps are provided for wing and centre tank gravity refueling. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−5 VENT SYSTEM An open vent (no float valves or flame arrestors) system is used to control the pressure in the fuel tanks. It consists of vent line tubing and ram air outlets (scoops) to ensure adequate venting of all fuel tanks. The vent lines connect the two air scoops to the fuel tanks and the fuel tanks to each other. The lines are drained of fuel which is returned to the feed tanks during operation. The low point of the main vent line is continuously scavenged by a jet pump. The vent line distribution is to a high point in the fuselage, preventing fuel from reaching either of the two ram outlets and spilling overboard. If any fuel passes the high point, it is collected by the surge box and is drained back to the tank before it reaches the outlet. Each surge box vent line tubing runs vertically along the fuselage side wall and is coupled to the wing, centre and aft tanks. The vent system is fully redundant such that any single blockage does not affect the venting capability. VENT SYSTEM SCHEMATIC GF1210_005 LEFT WING TANK RIGHT WING TANK AFT TANK CENTRE WING TANK LEFT SURGE BOX RIGHT SURGE BOX AIR SCOOP AIR SCOOP Relief valves are used to protect the tanks from over pressurization, in the case of failure of the vent system and/or refuel shut off valve. They are located in the wing, centre and aft tanks. The aft tank relief valve has a similar function as the centre and wing tank relief system, but also incorporates a negative pressure relief feature which can activate in an emergency descent. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−6 TRANSFER SYSTEM Fuel contained in the centre tank and the aft fuselage tank cannot be fed directly to the engine, but must be first delivered to the feed tanks by the transfer pumps. The normal sequence of fuel usage is to transfer centre tank fuel into the wings as required to keep the wings full during climb and cruise while holding the aft fuselage tank full. After depletion of centre tank fuel quantity, fuel continues to be burned from the wing tanks until 5500 lbs of fuel remains in either wing tank, at which point, transfer of fuel from the aft tank to the feed tanks is initiated. The transfer from the aft tank is then continuous until the aft tank is empty. When the aft fuselage tank fuel is depleted, no further transfer of fuel is required, since all remaining fuel is contained in the wing tanks. Effectivity: • Airplanes 9002, 9004 thru 9082 not incorporating Service Bulletin: • SB 700−28−033, Fuel Management and Quantity Gauging System (FMQGS) − FMQGS Computer Change to Part No. GP546−1501−5. After depletion of centre tank fuel quantity, fuel continues to be burned from the wing tanks until 4000 lbs of fuel remains in either wing tank, at which point, transfer of fuel from the aft tank to the feed tanks is initiated. The transfer from the aft tank is then continuous until the aft tank is empty. When the aft fuselage tank fuel is depleted, no further transfer of fuel is required, since all remaining fuel is contained in the wing tanks. Control of fuel transfer from the centre and aft tanks is normally under control of the fuel computer. Manual override is provided to command transfer of aft tank fuel into the feed tanks via the fuel control panel. There is no manual override for the centre tank transfer system. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−7 TRANSFER SYSTEM (CONT'D) Centre Transfer Fuel transfer from the centre tank to wing tank is completely automatic through the control of the FMQGC. The FMQGC monitors the fuel level and quantities in the wing tank (using fuel probes, compensators, densitometers and temperature sensors) to control fuel transfer from the centre tank to the wing tanks. Fuel will be transferred from the centre tank and delivered to the wing feed tanks, through the use of two centre transfer pumps. The FMQGC will start the applicable centre transfer pump(s) when each individual wing tank reaches approximately 93% of its fuel tank capacity. The FMQGC will automatically stop the centre transfer pump(s) when the respective wing tank reaches greater than 97% of its fuel tank capacity. CENTRE TRANSFER PUMPS GF1210_006 FUEL P P TOTAL FUEL 37200 LBS FUEL USED 5200 LBS 13500 LBS 13500 LBS 8000 LBS 2200 LBS AUX AUX °C 23 °C 23 °C 32 °C 32 APU P P P P P P P P The FUEL synoptic page represents the centre tank transfer operation with both engines running. Wing Transfer The wing transfer system permits fuel to be pumped from either side of the airplane to the other, using the DC auxiliary pumps and motor operated shut-off valves. The wing transfer system provides a means of correcting lateral fuel imbalance. It may be used in automatic mode via FMQGC or manual mode as selected by the cockpit fuel control panel. Fuel imbalance at a predetermined value will be annunciated on the EICAS display in the form of a caution message. Auto Wing Transfer In the wing transfer automatic mode, the FMQGC will correct lateral fuel imbalances of 400 pounds on ground and in flight. The FMQGC will control and operate the DC auxiliary pumps and wing transfer SOV’s as necessary to pump fuel from the feed tank into the opposite wing. Once commanded on, the wing transfer system remains on until lateral fuel imbalance is ± 50 pounds. In the event of a centre tank transfer pump failure, fuel will be transferred from the operating centre tank transfer pump to its respective wing tank. The automatic wing transfer system will maintain lateral fuel balance, to ensure that fuel contained in the centre tank is available to both engines. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−8 TRANSFER SYSTEM (CONT'D) Manual Wing Transfer In manual mode, the wing transfer system is controlled using the fuel WING XFER switch. Once selected, the wing fuel transfer continues until the WING XFER switch is selected off on the fuel control panel. DC Auxiliary Pump In wing transfer demand, commanded on by the FMQGC. Wing Transfer Shut-Off Valve Commanded on by the FMQGC or manually by the switch on the fuel control panel. GF1210_007 FUEL P P TOTAL FUEL 13450 LBS FUEL USED 29200 LBS 5400 LBS 5850 LBS 0 LBS 2200 LBS AUX AUX °C 23 °C 23 °C 32 °C 32 APU P P P P P P P P AUTO WING XFER OFF The FUEL synoptic page represents the left to right wing transfer mode of operation with both engines running. Crossfeed The crossfeed system permits interconnection between the left and right engine feed lines, using a shut-off valve. This will enable both engines to be fed by either feed tank or alternatively enable a single engine to be supplied from both feed tanks. For normal airplane operations, the crossfeed shut-off valve is closed, isolating the feed lines and ensuring that each engine is supplied fuel only from its own side of the airplane. Opening the crossfeed shut-off valve interconnects the feed lines, enabling fuel to flow from one engine feed line to the other. No automatic means of controlling the crossfeed SOV is provided and selection has to be made using the XFEED SOV switch on the fuel control panel. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−9 TRANSFER SYSTEM (CONT'D) Crossfeed (Cont’d) In single engine operating mode with the crossfeed shut-off valve opened, fuel flows from both feed tanks via the AC primary pumps to the single engine and fuel flow rates from both sides of the airplane are considered essentially the same. Therefore the airplane can be flown indefinitely without developing any significant lateral fuel imbalance. Engine Feed Shut-Off Valve Commanded off when the fire handle is pulled. Crossfeed Shut-Off Valve Crossfeed shut-off valve is selected open by the switch on the fuel control panel. GF1210_008 FUEL P P TOTAL FUEL 13400 LBS FUEL USED 28600 LBS 5600 LBS 5600 LBS 0 LBS 2200 LBS AUX AUX °C 23 °C 23 °C 32 APU P P LO PRESS P P P P P P °C 32 XFEED SOV FAIL OPEN The FUEL synoptic page represents the fuel crossfeed mode of operation, with the crossfeed shut-off valve selected open, left engine shut down, left engine feed shut-off valve closed and the right engine running. A secondary use of the crossfeed system (as a back-up to the wing transfer system) is to provide means of correcting lateral C of G imbalances, by temporarily inhibiting the flow fuel from the light side of the airplane. Fuel will then be supplied to both engines from the “heavy” side until lateral fuel imbalance is within desired limits. CAUTION The possibility of engine flameout could occur, if the crossfeed valve is not opened prior to inhibiting the fuel pumps. In this operating mode, the crossfeed valve is selected open via the “XFEED SOV” switch on the fuel control panel. The fuel pumps on the light side of the airplane are turned off, using the applicable AUX PUMP and PRI PUMP switches. Fuel will then be supplied from the heavy side of the airplane only, thereby correcting the lateral fuel imbalance. Crossfeed continues in this mode until the crew deselects the switches after lateral balance is achieved. NOTE It is important that the crew monitor system operation in this mode, since crossfeed will continue until manually deselected. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−10 TRANSFER SYSTEM (CONT'D) Crossfeed (Cont’d) In the event that a lateral fuel imbalance occurs outside design limits, it will be annunciated on EICAS, prompting the crew to take action. Crossfeed Shut-Off Valve Crossfeed shut-off valve is selected open by the switch on the fuel control panel. L WING FEED INHIBIT GF1210_010 FUEL P P TOTAL FUEL 12400 LBS FUEL USED 29600 LBS 5600 LBS 4600 LBS 0 LBS 2200 LBS AUX AUX °C 23 °C 23 °C 32 °C 32 APU P P P P P P P P AUX PUMP OFF PRI PUMP OFF XFEED SOV FAIL OPEN The FUEL synoptic page represents the fuel crossfeed mode (back-up) of operation. The system is shown with the crossfeed shut-off valve selected open, left auxiliary pump inhibited, left forward and aft boost pumps inhibited and both engines running. Aft Transfer Fuel contained in the aft tank is retained until late in the flight, in order to maintain a favorable aft centre of gravity (C of G). The aft transfer schedule is normally controlled automatically by the FMQGC. Fuel can also be transferred or inhibited manually from aft tank to wing tank, using the AFT XFER switch on the fuel control panel, if desired. Aft transferring of fuel is achieved using the two AC boost pumps and two shut-off valves. Each of the two transfer pumps in the system has sufficient capacity to maintain the transfer schedule in the event of a failure of one of the pumps. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−11 TRANSFER SYSTEM (CONT'D) Aft Transfer (Cont’d) When the aft transfer system is commanded to operate, the aft tank refuel transfer valve and the aft transfer pump come on. Fuel is then pumped by the aft transfer pump into its respective feed tank. Aft Transfer Pump In the AUTO mode, the transfer schedule is controlled by the FMQGC. Manual mode ON or OFF transfers or inhibits fuel transfer to the wings. GF1210_011 FUEL TOTAL FUEL 9000 LBS FUEL USED 32000 LBS 4000 LBS 4000 LBS 0 LBS 1000 LBS AUX AUX °C 23 °C 23 °C 32 °C 32 APU P P P P P P P P P P AUTO AFT XFER OFF ON The FUEL synoptic page represents the fuel aft transfer mode of operation, with both engines running. The system is shown transferring fuel from the aft tanks to their respective wing tanks. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−12 ENGINE FEED SYSTEM Fuel is provided to each engine from the two AC boost pumps. In normal operation, both boost pumps are continuously on and provide all engine fuel flow once the engine is started. The AC pumps are located in the inboard section of each wing (feed tank) and each AC pump is powered by a separate bus. Engine start capability and relight is provided by using the DC Auxiliary (AUX) pumps located in both feed tanks. These DC pumps will turn off as AC electrical power becomes available and the AC boost pumps are operating. Loss of pressure at any AC boost pump causes the DC pump to come on, to provide a back up of the remaining boost pump. The DC pumps also come on automatically for take-off, based on flaps/slats position and weight on wheels logic. The engine fuel burn schedule is automatically controlled by the FMQGC to ensure correct distribution for all airplane configurations. The engine fuel burn sequence is as follows: • Fuel from the wing tanks will burn first, • When the wing tanks get below 93%, fuel transfers from the center tank to the wing tank until it is at or above 97%, • When the center tank empties, fuel from the wing tanks continue to burn, • When either wing tank reaches 5500 lb, fuel transfers from the aft tank, • Once the aft tank is empty, the wing tanks will continue to burn the remaining fuel. Effectivity: • Airplanes 9002, 9004 thru 9082 not incorporating Service Bulletin: • SB 700−28−033, Fuel Management and Quantity Gauging System (FMQGS) − FMQGS Computer Change to Part No. GP546−1501−5. The engine fuel burn sequence is as follows: • Fuel from the wing tanks will burn first, • When the wing tanks get below 93%, fuel transfers from the center tank to the wing tank until it is at or above 97%, • When the center tank empties, wing tank continue to burn, • When either wing tank reaches 4000 lb, fuel transfers from the aft tank, • Once the aft tank is empty, the wing tanks will continue to burn the remaining fuel. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−13 ENGINE FEED SYSTEM (CONT'D) Engine Feed System Indication The left FUEL synoptic display represents the engine starting mode of operation with the right DC pump running. In this scenario, the right engine is starting using the battery as the only source of electrical power, Auxiliary Power Unit (APU) and left engine are off. The right FUEL synoptic display represents the right engine on speed and electrical AC power established. GF1210_012 FUEL TOTAL FUEL 38400 LBS FUEL USED 300 LBS 14600 LBS 14600 LBS 9200 LBS AUX AUX °C 23 °C 23 °C 32 APU P P LOPRESS P P P P P P P P FUEL TOTAL FUEL 38400 LBS FUEL USED 300 LBS 14600 LBS 14600 LBS 9200 LBS 0 LBS AUX AUX °C 23 °C 23 °C 32 °C 32 APU P P LOPRESS P P P P P P P P °C 32 0 LBS The FUEL synoptic display below represents airplane configuration with the APU shut down, both engines on speed, AC pumps running and the DC pumps on standby. GF1210_013 FUEL TOTAL FUEL 38400 LBS FUEL USED 300 LBS 14600 LBS 14600 LBS 9200 LBS 0 LBS AUX AUX °C 23 °C 23 °C 32 APU P P P P P P P 32 °C P P P FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−14 APU FUEL FEED The APU start capability is normally provided by the DC AUX pump(s). The fuel supplied to the APU is taken from the right engine feed line. The APU can also be fed from the left engine feed line using the left DC AUX pump (powered by DC ESS bus) and opening the crossfeed shut-off valve. A motor operated fire shut-off valve is used in the APU feed line in order to isolate the flow of fuel to the APU in case of a fire or rotor burst. The FUEL synoptic page top view represents the APU starting with the right DC pump running and battery power only as the single source of electrical power. In the lower view, the APU is fed from the right engine feed line using the AC pumps. APU start in progress, left and right engines are off. APU FEED SHUT-OFF VALVE Green outline will be indicated when the APU is on speed. TOP VIEW GF1210_014 NOTE APU − FUEL TOTAL FUEL 38400 LBS FUEL USED 300 LBS 14600 LBS 14600 LBS 9200 LBS 0 LBS AUX AUX °C 23 °C 23 °C 32 °C 32 APU P P LOPRESS P P P P P P P P LOPRESS APU on speed, left and right engines on and AC electrics established. LOWER VIEW GF1210_015 NOTE FUEL TOTAL FUEL 38400 LBS FUEL USED 300 LBS 14600 LBS 14600 LBS 9200 LBS 0 LBS AUX AUX °C 23 °C 23 APU P P P P °C 32 P P P P P P °C 32 FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−15 FUEL QUANTITY AND INDICATION The fuel quantity gauging system is an ac-type capacitance system. Fuel quantity probes, compensators, densitometers, temperature sensors and high level detectors are inputs received by the FMQGC. The FMQGC uses this acquired data to compute the fuel quantity for each tank and total fuel quantity remaining on board the airplane. The FMQGC outputs the computed individual fuel tank, total quantity and fuel temperature for EICAS display. The fuel system computer corrects for airplane pitch attitude and presents the corrected information of individual tank quantities and total fuel quantity displayed on EICAS. Fuel FLow Readout Indicates fuel flow in pounds per hour (PPH) to the respective engine. EICAS PRIMARY DISPLAY Total Fuel Readout Indicates total fuel quantity in pounds (lbs), of all the tanks. Green − Total fuel quantity is valid and in normal range. Amber − The fuel quantity is low. Dashed − Fuel quantity is not valid. Fuel Quantity Readout (wing tank) Indicates fuel quantity in the respective wing tank, in pounds (lbs). Green − Left and right tanks are balanced. Amber − A fuel quantity imbalance exists or applicable tank is less than 600 lbs (272 KG). Dashed − Fuel quantity is not valid Fuel Quantity Readout (aft tank) Indicates fuel quantity in the aft tank, in pounds (lbs). Green − Quantity is valid. Amber − The aft tank fuel transfer is off schedule. Dashed − Fuel quantity is not valid. Fuel Quantity Readout (center fuselage tank) Indicates fuel quantity in the centre tank, in pounds (lbs). Green − Quantity is valid. Dashed − Fuel quantity is not valid. TOTAL FUEL (LBS) 41550 14600 14600 10000 2350 ND STAB NU RUDDER NL LWD RWD NR TRIMS 7.2 N2 FF (PPH) OIL TEMP OIL PRESS 93.4 5750 115 81 93.4 5750 115 81 AIL GF1210_016 The FMQGS can display fuel quantity in either LB (standard) or KG (optional). The primary EICAS page displays fuel quantity in all fuel tanks and total fuel in the airplane. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−16 FLIGHT MANAGEMENT DISPLAY When both engines are started, the Fuel Management System (FMS) fuel quantity switches from Fuel Management Quantity Gauging System (FMQGS), to computed fuel quantity, based on fuel flow data from the engines and APU. GF1210_017 Compare Fuel Quantity Displays when the gauge fuel quantity and the calculated FMS fuel quantity differs by more than 2%. BOW 48500 5/170 PASS / @ LB PERFORMANCE INIT−LB 5/5 FUEL (GAUGE) 25300 (25300) ACTIVE FLT PLAN ORIGIN KPHX 055 154 NM CLS 1/4 00 + 21 .75M/ A 10000 SJN 059 121 NM 00 + 15 .75M/FL350 TAKEOFF INIT ABQ DEPARTURE 0 0 COMPARE FUEL QUANT Fuel quantity information to the FMS is used for monitoring and sensing, to assist in determining a fuel leak. When a fuel leak is detected, a crew alert (“MSG” on the primary flight display) will be displayed and a message will appear on the scratchpad of the FMS CDU. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−17 REFUEL/DEFUEL SYSTEM Pressure refueling/defueling operations are controlled from the refuel/defuel control panel. Pressure refueling can be accomplished in “MANUAL” or “AUTO” mode of operation. GF1210_018 GRAVITY FILL CAP GROUNDING POINTS GROUNDING POINT REFUEL/DEFUEL ACCESS PANEL PROXIMITY SENSOR GROUNDING POINT REFUEL/DEFUEL PANEL LOCATION CLOSE OPEN IF INSTALLED REFUEL/DEFUEL PANEL MASTER ON INCR DECR PRESEL RIGHT AFT TOTAL LEFT CTR 30000 10000 8000 LB 30000 10000 2000 LB MANUAL LEFT CTR RIGHT AFT OPEN CLOSE REFUEL DEFUEL AUTO REFUEL START REFUEL AUTO STOP AFT ON OFF SHUT OFF TEST REFUEL/DEFUEL PANEL LEFT CENTER RIGHT AFT PRESEL TOTAL MANUAL LEFT CTR RIGHT AFT OPEN CLOSE INCR DECR PRESEL START STOP/ SOV TEST REFUEL DEFUEL AUTO OFF MANUAL REFUEL REFUEL NO AFT OFF Gravity filling via a filler point is also provided for the wing and centre wing tanks. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−18 REFUEL/DEFUEL PANEL GF1210_019 PRESELECT TOTAL QTY DISPLAY Displays the fuel quantity target for automatic refueling. Set in 100 lb (50 KG) increments. LEFT/RIGHT/CTR/AFT/TOTAL Displays the current fuel quantity in each tank and the total quantity in all tanks. Quantities are displayed in 50 lb (25 KG) increments. PRESEL INCR/DECR Increases or decreases the preselect quantity for AUTO refueling. FUEL SOVs Allows tanks to be refueled or defueled manually. MODE SELECTOR MANUAL REFUEL − Enables manual refueling using the fuel SOVs. MANUAL DEFUEL− Enables manual defueling using the fuel SOVs. AUTO MODE AUTO REFUEL − Enables automatic refueling. AUTO REFUEL − NO AFT− Enables automatic refueling and inhibits aft tank refueling. OFF POSITION OFF − Removes power form the panel. START−STOP/SOV TEST START − Initiates refueling. STOP/SOV TEST − Stops automatic refueling or enables testing of the refuel SOVs and circuitry during fueling. REFUEL/DEFUEL PANEL LEFT CENTER RIGHT AFT PRESEL TOTAL MANUAL LEFT CTR RIGHT AFT OPEN CLOSE INCR DECR PRESEL START STOP/ SOV TEST REFUEL DEFUEL AUTO OFF MANUAL REFUEL REFUEL NO AFT FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−19 REFUEL/DEFUEL PANEL (CONT'D) GF1210_020 PRESELECT TOTAL QTY DISPLAY Displays the fuel quantity target for automatic refueling. Set in 100 lb (50 KG) increments. LEFT/RIGHT/CTR/AFT/TOTAL Displays the current fuel quantity in each tank and the total quantity of all tanks. Quantities are displayed in 50 lb (25 KG) increments. INCR/DECR Increases or decreases the preselect quantity for AUTO refueling. MANUAL FUEL SOVs Allows tanks to be refueled or defueled manually. MASTER ON/OFF Supplies power to the components required for fueling/defueling. SHUT OFF TEST When selected shuts off all valves to verify their operation. It also carries out a test of the high level sensors and circuitry in each tank during refueling. AFT ON/OFF Enables or disables the automatic function of refueling the aft tank. START/STOP (for AUTO mode only) START − Starts automatic refueling. STOP − Stops automatic refueling. MODE SELECTOR REFUEL − Enables manual refueling. AUTO REFUEL − Enables automatic refueling. DEFUEL − Enables manual defueling. REFUEL/DEFUEL PANEL MASTER ON INCR DECR PRESEL RIGHT AFT TOTAL LEFT CTR 30000 10000 8000 LB 30000 10000 2000 LB MANUAL LEFT CTR RIGHT AFT OPEN CLOSE REFUEL DEFUEL AUTO REFUEL START REFUEL AUTO STOP AFT ON OFF SHUT OFF TEST OFF Normal Fuel Loading The normal fuel loading is as follows: • Wing tanks only if the required fuel load is equal to or less than the wing tank capacity. • Wing tanks full and the remainder in the aft tank if the required fuel load is greater than the wing tank capacity, but less than or equal to the combined capacity of the wing and aft tanks. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−20 REFUEL/DEFUEL PANEL (CONT'D) Normal Fuel Loading (Cont’d) • Any fuel in excess of the combined capacity of the wing and aft tanks is placed in the centre tank. NOTE The left and right wing tank quantities must be within 400 lbs (181 KG) for normal fuel loading. An additional switch position on the refuel/defuel panel allows auto refueling without adding fuel to the aft tank. REFUEL NO AFT This switch position inhibits refueling of the aft tank. IF INSTALLED GF1210_021 AFT ON OFF REFUEL DEFUEL AUTO OFF MANUAL REFUEL REFUEL NO AFT If the aft tank fueling is inhibited by the switch then the refuel sequence is as follows: • Wing tanks only if the required fuel load is equal to or less than the wing tank capacity. • Wing tanks full and the remainder in the centre tank if the required fuel load is greater than the total wing capacity. Gravity Refueling The wing tanks may be refueled through over wing gravity fill adapters located on top of both left and right wings. It is not possible to completely fill either wing tank by gravity fueling, since the fill adapters are located outboard and below the maximum fuel level. The centre tank may be refueled through a gravity fill adapter located on top of the right hand wing. Gravity fueling of the aft tank is not provided. Pressure Refueling Pressure refueling is accomplished through the single point refuel/defuel adapter, located in the right hand wing root and is controlled by the refuel/defuel control panel. An optional duplicate refuel/defuel control panel can be installed in the flight compartment. NOTE A “SHUT-OFF TEST” must be carried out prior to all refueling operations. If the test is successful a “SOV PASS” is displayed in the PRESEL window. If the test fails a “SOV FAIL” is displayed in the PRESEL window. “SOV FAIL” will be displayed in the tank window for the failed shut-off valve, alternating display of the tank quantity. Pressure refueling may be performed in either “AUTOMATIC” or “MANUAL” mode. The airplane does not have a fuel jettison system. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−21 REFUEL/DEFUEL PANEL (CONT'D) Pressure Refueling (Cont’d) A preselect fuel quantity is used during automatic refueling of the airplane. This method will allow the airplane to be filled automatically to the desired fuel state selected. NOTE The preselect quantity is the desired final total fuel quantity in the tanks and not the quantity to be added. In “AUTOMATIC” mode, fuel quantity added to each tank is automatically controlled by the FMQGC to give the correct distribution for the presented total quantity. Refueling flow is stopped when the total fuel quantity reaches the preselect quantity and the appropriate SOVs are commanded close. Manual Refueling In “MANUAL” mode, it permits the operator to select and control the fuel quantity to be added in each tank through the refuel/defuel panel. In this mode, the high level sensors automatically close the refuel/defuel SOVs if the maximum fuel level capacity is reached. Suction Defueling Suction defueling of the fuel tanks is carried out by applying suction (recommended pressure −8 psig) to the single point refuel/defuel adapter, using the refuel/defuel control panel. • Wing Tank − Suction defueling of the wing tanks is accomplished by opening a valve which connects the refuel/defuel manifold to the engine feed line. This allows fuel to be drawn out of the tank through the suction defuel check valve in the feed tank. • Centre Tank − The centre tank is defueled through the refuel/defuel shut-off valve. • Aft Tank − The aft tank may be suction defueled using the same line and shut-off valve used for pressure refueling of the tank. Pressure Defueling Pressure defueling of the fuel tanks is accomplished through the fuel shut-off valves and single point adapter. Pressure defueling is identical to suction defueling, except that primary defueling flow is provided by the AC boost pumps or DC auxiliary pump in each feed tank. NOTE AC or DC electrical power is required to operate the airplane pumps for this procedure. Direct pressure defueling of the wing tank is accomplished using the AC boost pumps or DC auxiliary pump in each feed tank. Direct pressure defueling of the centre tank is not possible. Centre tank fuel may however be transferred to the wing tanks using the centre tank transfer pumps. From there, it may then be defueled via the wing tank. Direct pressure defueling of the aft fuselage tank is not possible. Aft fuselage tank fuel may however be transferred to the wing tanks using the aft transfer pump. From the wing tank, it may then be defueled via the wing tank. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−22 REFUEL/DEFUEL PANEL (CONT'D) Fault Reporting Fault reporting is in the form of error messages which will appear in the display windows of the refuel/defuel panel. In the event of a fuel computer failure, a “FMQGC” will be displayed in the TOTAL window and “FAILURE” in the PRESEL window. An example of fault reporting is illustrated below: REPEATER This indicates that two panels are powered on. GF1210_022 LEFT CENTRE RIGHT AFT PRESEL TOTAL 10000 8000 10000 30000 2000 REPEATER If installed, the following information may be displayed in either or both quantity windows: IMBALANCE Displayed if an imbalance condition exists. The tank affected displays will alternate between IMBAL and tank quantity every two seconds. GF1210_023 PRESEL RIGHT AFT TOTAL LEFT CTR 30000 10000 8000 LB 30000 10000 2000 LB 20000 IMBAL 2000 LB Error Messages The following messages may be displayed on the refuel/defuel panel if a fault exists: INHIBIT In manual refuel or defuel mode, displayed when a tank switch is in the “OPEN” position. In pressure defuel mode, displayed when an engine is on (no fire handles pulled). In auto mode, displayed when the preselected fuel quantity is valid, airplane is in CAIMS maintenance mode or the SOV shut-off test fails. FULL Displayed when the high level shut-off has been activated. LOAD ERROR In auto refuel mode, displayed when an invalid fuel distribution is selected. Example, one tank contains more fuel than the target quantity assigned by the automatic distribution. IMBAL Displayed when a predetermined fuel quantity imbalance exists between the left and right wings. REPEATER Displayed in the PRESEL window of the external Refuel/Defuel Panel when two panels are powered “ON”. The panel located in the flight compartment is in control and the outside panel provides quantity display only. Dashes ( _ _ _ _ _ _ ) will be displayed for fuel quantity if the computed value is invalid. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−23 REFUEL/DEFUEL PANEL (CONT'D) FAILED Displayed in the PRESEL window if the Refuel/Defuel Panel is not functional. FMQGC − FAILURE FMQGC will be displayed in the TOTAL window and FAILURE in the PRESEL window if the Refuel/Defuel Panel is not communicating with the fuel computer. Refueling Distribution Refer to Refuel/Defuel Schematic for component location, recognition and operation. All fuel tanks can be refueled either automatically (by the FMQGC) or manually (by the refuel/defuel panel). The recommended pressure is 50 psig. for pressure refueling. A balance line in each tank is used during refueling to transfer fuel to the most outboard section of the wing. The filling sequence of the wing compartment during pressure refueling is as follows: • Cell 2 is filled directly by the refuel system, fuel flows inboard by gravity into: • Cell 1, which is the inboard section including the feed tank. After inboard cells 1 and 2 are completely filled: • Cell 3 is filled to capacity by overflow of cell 2 fuel through the balance tube connecting cells 2 and 3. The aft and centre tanks will be refuelled simultaneously (automatically by the FMQGC) to maintain centre-of-gravity (C of G) limits. High level sensors installed in each tank automatically close the refuel/defuel SOVs, if the maximum fuel level capacity is reached. Relief valves augment the normal vent system to prevent overpressure in case of overfilling a tank. As with the wing tanks, automatic refueling of the centre tank is controlled by the FMQGC, with automatic shut-off commanded by the high level sensor. Automatic refueling of the aft tank is controlled by the FMQGC, with automatic shut-off commanded by the high level sensor. Fuel Re-Circulation System (On airplanes with SB 700−28−034 incorporated) The Fuel Re-Circulation system is designed to prevent the bulk fuel temperature from reaching the freezing point by recirculating heated fuel to the wing fuel tank. The system is operated through the L and R RECIRC switches on the Fuel Control panel. Heat is generated by the engine oil cooling system. Cold fuel circulated through the Fuel Cooled Oil Cooler (FCOC) where the heat from the engine oil is transferred to the fuel. The Fuel Return To Tank (FRTT) valve allows the heated fuel to return to the wing fuel tank. Each FRTT valve is electrically controlled and fuel pressure operated. The aircraft main fuel pump pressure is insufficient to activate the FRTT valve, thus the engine must be running for the FRTT valve to open. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−24 REFUEL/DEFUEL PANEL (CONT'D) Fuel Re-Circulation System (On airplanes with SB 700−28−034 incorporated) (Cont’d) GF1210_024 Bulk Fuel Temperature Heated Fuel Temperature Sensor FUEL-RETURN-TO-TANK CELL3 CELL1 CELL2 CENTRE TANK CENTRE TRANSFER PUMP AUXILIARY DC PUMP WING TRANSFER SHUT-OFF VALVE P P P P TS P P P P P P TS TS TS TS AFT TRANSFER PUMP RE-CIRCULATION AFT TRANSFER LINE ENGINE FEED MAIN AC PUMPS AFT TRANSFER SHUT-OFF VALVE AFT TANK FCOC FCOC TS LEGEND VALVE LINE SHUT-OFF VALVE FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−25 REFUEL/DEFUEL PANEL (CONT'D) Fuel Re-Circulation System (On airplanes with SB 700−28−034 incorporated) (Cont’d) The FRTT valves are powered by their dedicated circuit breakers on DC BUS 1 and 2. Effectivity: • Airplanes 9002 thru 9122 not incorporating Service Bulletin: • SB 700−28−039, Distribution − Permanent Wiring Configuration for the Fuel Re-Circulation System Following Power Source Change. The FRTT valve circuit breakers are tied to the Refuel/Defuel Control Panel circuit breakers on the APU Battery Bus. When the FRTT valve is open, fuel returns to the wing tank through the re-circulation line. The re-circulation line joins the aft tank transfer line. This slightly decreases the transfer rate of the aft tank to the feed tanks. Heated fuel is then distributed to the number 1 and 2 cell of the wing fuel tank. No fuel is distributed to the number 3 cell as it will have emptied before the local fuel temperature reaches −40°C (°F). Both the re-circulation line and the aft tank transfer line are fitted with a check valve to prevent crossflow or fuel propagation due to a ruptured line. The wing fuel tanks are fitted with many fuel temperature sensors; the left wing has two and the right wing has three. During normal operation (with the Fuel Re-Circulation selected OFF), the Fuel Management and Quantity Gauging System (FMQGS) computer reads all temperature sensors but will display only the lowest temperature. When the Fuel Re-Circulation system is selected ON, the FMQGS computer reads the inboard temperature sensor as it will be the one who reads the highest temperature. This logic is also used to determine the credibility of a failed temperature sensor in order to display the FUEL TEMP SENSOR FAIL caution message. In the event that only one side has been selected ON, the temperature displayed on the OFF side will be the lowest among all submerged temperature sensors of that side. Operation of the Fuel Re−Circulation System is allowed only during cruise flight above 34,000 feet to ensure an additional safety margin in case of a main fuel pump failure. Wide Cut Fuel operations are limited to 13,000 feet until the bulk fuel temperature is below 15°C. Display of system status is provided through EICAS messages. A L (R) FUEL RECIRC FAIL caution message will be displayed on the EICAS status page when the FRTT valve is not in the commanded or allowed position. Finally, the L (R) FUEL RECIRC ON status message will be displayed when the system operates properly and within specification. The FUEL HI TEMP caution message is posted when the bulkhead fuel temperature exceeds 43°C when the Fuel Re-circulation System is inoperative. To prevent the system from operating above the freezing level, the set point has been reduced to 0°C when the system is selected on. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−26 REFUEL/DEFUEL SCHEMATIC GF1210_025 CELL 1 CELL 2 CELL 3 RV RV RV SHUT-OFF VALVES Refuel/ Defuel Panel TO FMQGC BALANCE TUBE BAFFLED RIBS RELIEF VALVE SUCTION DEFUEL CHECK VALVE DEFUEL SHUT-OFF VALVE CROSSFEED VALVE SHUT-OFF VALVE TO AFT TANK CENTRE TANK REFUEL/DEFUEL CHECK VALVE SINGLE POINT REFUEL ADAPTER H H H H HIGH LEVEL SENSOR REFUEL/DEFUEL MANIFOLD RV PRESSURE REFUEL CHECK VALVE Left main refuel Fuel distribution lines Right main refuel Centre refuel/defuel Aft refuel/defuel and main defuel LEGEND FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−27 FUEL FILTERS, QUANTITY AND TEMPERATURE READOUTS GF1210_026 Engine Inlet Fuel Temperature Green − Engine fuel temperature is > 5°C. Amber − Engine fuel temperature is < 5°C . Wing Fuel Quantity Indicates fuel quantity in the respective wing tank, in pounds (lbs) Fuel Quantity Readout (Centre Fuselage Tank) Indicates fuel quantity in the centre tank, in pounds (lbs). Fuel Quantity Readout (aft tank) Indicates fuel quantity in the aft tank, in pounds (lbs). Fuel Used Quantity Readout Indicates fuel quantity burned. Fuel Filter Green − Indicates normal fuel flow through the filter. Amber − Fuel pressure drop exists across the filter. Total Fuel Quantity Indicates fuel quantity in all fuel tanks, in pounds (lbs). Fuel Filter Flow Line Green − Indicates normal fuel flow to the engine. Amber − Fuel pressure drop exists across the filter, flow line from the filter to the engine turns amber. Bulk Fuel Temperature Readout Green − Temperature of fuel in tanks is between −35°C and +42°C. Amber − Temperature of fuel in tanks is lower than −35°C or greater than +42°C. On airplanes with SB 700−28−034 incorporated: If Fuel Re−Circulation system is On: Green − Temperature of fuel in tanks is between −35°C and 0°C. Amber − Temperature of fuel in tanks is lower than −35°C or greater than 0°C. FUEL TOTAL FUEL 42800 LBS FUEL USED 200 LBS 14900 LBS 14900 LBS 11100 LBS AUX AUX °C 23 °C 23 APU P P °C 32 P P P P P P P P 2200 LBS °C 32 FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−28 FUEL PUMP DISPLAYS GF1210_027 Centre Transfer Pumps Controlled by the FMQGC and transfers centre tank fuel to the wing tanks. L or R AC Boost Pumps ON − At all times with the engines running. OFF − When commanded by the switch on the Fuel Control Panel. L or R DC Auxiliary Pumps ON − For engine starting, take−off and landing, primary pump failure and wing transfer of fuel. NOTE: The AUX PUMP cannot be used to support the engine feed system and wing transfer at the same time. OFF − When commanded by the switch on the Fuel Control Panel or when both primary pumps are on. Aft Transfer Pumps ON − When requested by the computer or selected on the Fuel Control Panel. OFF − When commanded by the switch on the Fuel Control Panel or when commanded by the FMQGC in AUTO mode. FUEL TOTAL FUEL 37000 LBS FUEL USED 5600 LBS 13200 LBS 13600 LBS 8000 LBS AUX AUX °C 23 °C 23 APU °C 32 P P P P P 2200 LBS °C 32 P P P P P FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−29 FUEL SHUT-OFF DISPLAYS GF1210_028 Engine Feed Shut-Off Valve Activated by the engine run switches on the throttle quadrant. Applicable engine FIRE DISCH handle. APU Feed Shut-Off Valve Activated by the RUN position switch on the APU control panel. Also controlled by the APU FIRE DISCH handle. Aft Tank Transfer Valve Controlled by the FMQGC or the AFT XFER switch on the fuel control panel. Wing Transfer SOV Controlled by the FMQGC or the WING XFER switch on the fuel control panel. Fuel Crossfeed SOV Controlled by the switch on the Fuel Control Panel. It is used to interconnect the engine feed lines. FUEL TOTAL FUEL 10400 LBS FUEL USED 32000 LBS 4000 LBS 4600 LBS 0 LBS AUX AUX °C 23 °C 23 APU °C 32 P P P P 1800 LBS °C 32 P P P P P P FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−30 FUEL SYNOPTIC PAGE SYMBOLS The following represents the EICAS symbols and flow line logic for the fuel synoptic page. The symbols are shown in serviceable and failure conditions. EICAS Philosophy GF1210_029 VALVE AND FLOW LINE LOGIC OPEN VALVE NOT FAILED CLOSED TRANSIT INVALID VALVE FAILED DIRECTION OF FLOW PUMP AND FLOW LINE LOGIC ON PUMP INVALID OFF FAILED OFF PUMP FAILED ON P P P P P DIRECTION OF FLOW FUEL MANAGEMENT QUANTITY GAUGING SYSTEM (FMQGS) The FMQGS consists of a dual channel computer with BITE, utilizing capacitance type probes in each tank to continuously measure the quantity of usable fuel. The fuel computer performs all digital processing related to the system control and indication and performs computations associated with fuel gauging system requirements. The following schematic represents inputs and outputs of various components and systems operations. FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−31 FMQGC SCHEMATIC ENGINE INDICATING AND CREW ALERTING SYSTEM AND CENTRAL AIRCRAFT INFORMATION MANAGEMENT SYSTEM FMQGC CHANNEL 1 CHANNEL 2 LEFT WING TANK RIGHT WING TANK CENTRE WING TANK AFT TANK Fuel Quantities Fuel Temperature EICAS Messages Caution Advisory Status EICAS Inputs from other sources Sensor Data: Tank Probes Compensators Densitometer Temperature Hi/Lo Level Pump Pressure Switches SOVs Position Feedback Cockpit Control Panel Cockpit Fuel Fire Handles Panel APU On L Engine On R Engine On Fuel System Components Refuel Defuel Panel Displays Data: Total Fuel Quantity Individual Tank Quantities Preselect Quantity Alert Messages Boost Pumps INHIB Wing Transfer Mode Aft Transfer Mode XFEED Mode Input and output Input or output LEGEND Engine Start GF1210_030 FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−32 EICAS MESSAGES GF1210_031 WING TO CTR LEAK Indicates that the fuel level in the centre tank has increased by 600 lbs or more. L−R PRI FUEL PUMPS Indicates that the forward and aft primary AC pumps on the affected side have failed to operate when requested. FUEL COMPUTR FAIL Indicates that both channels of the fuel system computer have failed. AFT XFER OFF SCHED Indicates that fuel transfer from the aft tanks to the wings is unable to keep pace with the optimum aft transfer schedule. −> FUEL XFER FAIL Transfer from the left wing to the right wing has been requested and failed. FUEL UNIT MISMATCH The refuel/defuel panel and EICAS indications are correct but in different units of measurements. FUEL IMBALANCE Indicates that a fuel quantity imbalance exists between the left and right wing tanks of: More than 1100 lbs (499 KG) in flight. Between 600 lbs (272 KG) and 1100 lbs (499 KG) on ground or in Take-off / Approach configuration. FUEL LO QTY Indicates fuel in the left or right wing tank is less than 600 lbs (272 KG). <− FUEL XFER FAIL Transfer from right wing to left wing has been requested and failed. −> FUEL XFER ON Indicates that fuel is being transferred from the left wing tank to the right wing unrequested. <− FUEL XFER ON Indicates that fuel is being transferred from the right wing tank to the left wing unrequested. FUEL TEMP SENSOR On ground, indicates that a fuel temperature sensor is failed. With flaps deployed, will be posted only if the failure requires corrective action. L−R FUEL RECIRC FAIL Indicates that the FRTT valve is not in the commanded or allowed position. On airplanes with SB 700-28-036 incorporated: Indicates that the FRTT valve is not in the commanded position. FUEL IMBALANCE FUEL COMPUTR FAIL L−R PRI FUEL PUMPS FUEL UNIT MISMATCH WING TO CTR LEAK AFT XFER OFF SCHED FUEL TEMP SENSOR L−R FUEL RECIRC FAIL FUEL LO QTY −> FUEL XFER FAIL −> FUEL XFER ON <− FUEL XFER FAIL <− FUEL XFER ON FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−33 EICAS MESSAGES (CONT'D) AFT XFER FAIL Both left and right aft transfer components have failed to operate when requested. Aft tank fuel is no longer available. CTR FUEL XFER FAIL Indicates that both left and right centre tank pumps have failed to operate when requested. L−R WING FULL Indicates that fuel quantity in the affected wing tank has exceeded its maximum allowable value. WING FUEL HI TEMP Indicates that the left or right wing fuel bulk temperature is greater than 42°C. On airplanes with SB 700-28-034 incorporated: If Fuel Re-Circulation system is On: Indicates that the left or right wing fuel bulk temperature is greater than 0°C. If Fuel Re-Circulation system is Off: Indicates that the left or right wing fuel bulk temperature is greater than 42°C. WING FUEL LO TEMP Indicates that either the left or right wing fuel bulk temperature is at or below −35°C. L−R ENG FUEL SOV Indicates that the engine fuel shut-off valve on the affected side is not in its commanded state. APU FUEL SOV Indicates that the APU fuel shut-off valve has failed. AFT XFER FAIL APU FUEL SOV L−R ENG FUEL SOV CTR FUEL XFER FAIL WING FUEL HI TEMP WING FUEL LO TEMP L−R WING FULL GF1210_032 FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−34 EICAS MESSAGES (CONT'D) GF1210_033 FUEL COMPUTR FAULT Indicates that either channel of the computer has failed. <− FUEL XFER ON Indicates that the right to left transfer system is in the AUTO mode of operation. AFT XFER FAULT Indicates that either a left or right aft tank fuel transfer component has failed to operate when requested. AFT XFER OFF SCHED Indicates aft tank fuel transfer to the wings, in advance of the optimum transfer schedule. FUEL QTY DEGRADED Indicates that the fuel computer detects a loss of fuel gauging accuracy. <− XFER VALVE OPEN Indicates that the wing transfer valve has failed to close at the completion of wing transfer operation. L−R R/D VALVE OPEN Indicates that the left and right refuel/defuel valves have failed to close (after refuel/defuel operation) when requested. AFT R/D VALVE OPEN The aft refuel/defuel valve has failed to close (after refuel/defuel operation) when requested. XFEED VALVE FAIL Indicates that the crossfeed valve is not in its commanded position. CTR XFER FAULT Indicates a centre fuel transfer fault exists (either the left or right fuel transfer is not working). L−R PRI FUEL PUMP Indicates that a single primary fuel pump on the affected side has failed to operate when requested. On airplanes with SB 700-28-036 incorporated: FUEL RECIRC ON Indicates that the FRTT valve is not in an allowed position. −> FUEL XFER ON Indicates that the left to right transfer system is in the AUTO mode of operation. −> XFER VALVE OPEN Indicates that the wing transfer valve has failed to close at the completion of wing transfer operation. L−R AUX FUEL PUMP Indicates that the auxiliary fuel pump on the affected side has failed to operate when requested. <− XFER VALVE OPEN <− FUEL XFER ON FUEL COMPUTR FAULT AFT XFER FAULT AFT XFER OFF SCHED FUEL QTY DEGRADED L−R R/D VALVE OPEN AFT R/D VALVE OPEN L−R PRI FUEL PUMP L−R AUX FUEL PUMP CTR XFER FAULT XFEED VALVE FAIL −> FUEL XFER ON −> XFER VALVE OPEN FUEL RECIRC ON FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−35 EICAS MESSAGES (CONT'D) AFT FUEL XFER ON Indicates aft fuel transfer is in progress under manual control. −> FUEL XFER ON Indicates that the left to right transfer system is in the MANUAL mode of operation. L−R PRI PUMPS OFF Indicates that the forward and aft boost pumps on the affected side are inhibited. <− FUEL XFER ON Indicates that the right to left transfer system is in the MANUAL mode of operation. AFT FUEL XFER OFF Indicates aft fuel transfer has been inhibited. WING FUEL XFER OFF Indicates that transfer of fuel from left to right and from right to left has been selected off. XFEED VALVE OPEN Indicates that the crossfeed shut-off valve is open. L−R AUX PUMP OFF Indicates that the auxiliary pump on the affected side has been inhibited. L−R FUEL SOV CLSD Indicates that the fuel shut-off valve on the affected side is closed. APU FUEL SOV CLSD Indicates that APU fuel shutoff valve is closed. FUEL RECIRC ON Indicates that the FRTT valves are opened when commanded by flight crew. GF1210_034 L−R AUX PUMP OFF L−R PRI PUMPS OFF −> FUEL XFER ON AFT FUEL XFER ON <− FUEL XFER ON AFT FUEL XFER OFF XFEED VALVE OPEN WING FUEL XFER OFF APU FUEL SOV CLSD L−R FUEL SOV CLSD FUEL RECIRC ON FUEL REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−10−36 CB - FUEL SYSTEM GF1220_001 STAT SYS BUS PREV CNTL TEST PAGE NEXT PAGE EMER CNTL BUS CIRCUIT BREAKER − SYSTEM 1/2 SYSTEM CIRCUIT BREAKER AFCS AIR COND/PRESS APU BLEED CAIMS COMM DOORS ELEC ENGINE FIRE FLT CONTROLS FUEL BRT L ENG FUEL SOV 4/6 CB − FUEL SYSTEM DC EMER DCPC L FUEL RECIRC VLV DC 1 L FWD PRI PUMP AC 2 R AFT PRI PUMP AC 4 R AUX PUMP BATT R CTR XFER PUMP AC 4 IN IN IN IN IN IN R ENG FUEL SOV 5/6 CB − FUEL SYSTEM DC EMER DCPC R FUEL RECIRC VLV DC 2 R FWD PRI PUMP AC 3 R/D MOTOR VALVES APU BATT ASCA R/D PANEL COCKPIT APU BATT ASCA R/D PANEL EXT APU BATT ASCA IN IN IN IN IN IN XFER SOV C 1/6 CB − FUEL SYSTEM DC ESS XFER SOV O DC ESS XFER SOV C BATT XFER SOV O BATT AFT TANK L PUMP AC 2 AFT TANK L SOV C DC 1 IN IN IN IN IN IN AFT TANK L SOV O 2/6 CB − FUEL SYSTEM DC 1 AFT TANK R PUMP AC 3 AFT TANK R SOV C DC 2 AFT TANK R SOV O DC 2 APU FIRE SOV DC EMER DCPC FUEL COMPUTR CH A BATT IN IN IN IN IN IN FUEL COMPUTR CH B 3/6 CB − FUEL SYSTEM DC ESS FUEL R/D CH A APU BATT ASCA FUEL R/D CH B APU BATT ASCA L AFT PRI PUMP AC 1 L AUX PUMP DC ESS L CTR XFER PUMP AC 1 IN IN IN IN IN IN R/D SOL VALVES 6/6 CB − FUEL SYSTEM APU BATT ASCA XFEED SOV C BATT XFEED SOV O BATT IN IN IN FUEL EMS CIRCUIT PROTECTION REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−20−1 CB - FUEL SYSTEM (CONT'D) Effectivity: • Airplanes 9002 thru 9122 not incorporating Service Bulletin: • SB 700−24−045, AC and DC Power Distribution − Unit Change and Activation of Build 4 Electrical System. GF1220_002 STAT SYS BUS PREV CNTL TEST PAGE NEXT PAGE EMER CNTL BUS CIRCUIT BREAKER − SYSTEM 1/2 SYSTEM CIRCUIT BREAKER AFCS AIR COND/PRESS APU BLEED CAIMS COMM DOORS ELEC ENGINE FIRE FLT CONTROLS FUEL BRT BATT 1/8 CB − FUEL SYSTEM XFER SOV O XFER SOV C AFT TANK L PUMP AFT TANK L SOV C IN XFER SOV C IN IN IN IN DC ESS DC ESS BATT XFER SOV O AC 2 DC 1 IN AC 1 3/8 CB − FUEL SYSTEM FUEL R/D CH A FUEL R/D CH B L AUX PUMP L CTR XFER PUMP IN FUEL COMPUTR CH B IN IN IN IN DC ESS APU BATT ASCA APU BATT ASCA L AFT PRI PUMP DC ESS AC 1 IN DC 2 2/8 CB − FUEL SYSTEM AFT TANK R PUMP AFT TANK R SOV C APU FIRE SOV FUEL COMPUTR CH A IN AFT TANK L SOV O IN IN IN IN DC 1 AC 3 DC 2 AFT TANK R SOV O DC EMER DCPC BATT IN DC 1 L FWD PRI PUMP L RECIRC SOV 1 C L RECIRC SOV 2 C L RECIRC SOV 2 O IN L ENG FUEL SOV IN IN IN IN DC EMER DCPC AC 2 DC 1 L RECIRC SOV 1 O DC 1 DC 1 IN L RECIRC SOV 3 O R AFT PRI PUMP R AUX PUMP R CTR XFER PUMP R ENG FUEL SOV IN L RECIRC SOV 3 C IN IN IN IN DC 1 DC 1 AC 4 BATT AC 4 DC EMER DCPC CB − FUEL SYSTEM IN 5/8 R RECIRC SOV 1 C R RECIRC SOV 1 O R RECIRC SOV 2 C R RECIRC SOV 2 O R RECIRC SOV 3 C IN R FWD PRI PUMP IN IN IN IN AC 3 DC 2 DC 2 DC 2 DC 2 DC 2 CB − FUEL SYSTEM IN 6/8 IN R RECIRC SOV 3 O DC 2 APU BATT ASCA R/D MOTOR VALVES R/D PANEL COCKPIT R/D SOL VALVES XFEED SOV C IN IN IN IN APU BATT ASCA APU BATT ASCA R/D PANEL EXT APU BATT ASCA BATT IN IN XFEED SOV O BATT CB − FUEL SYSTEM 8/8 4/8 CB − FUEL SYSTEM CB − FUEL SYSTEM 7/8 FUEL EMS CIRCUIT PROTECTION REV 41, Jul 08, 2004 Flight Crew Operating Manual CSP 700−6 Volume 2 12−20−2