FUEL SYSTEM 1. MAIN TANKS ¡ 18450 kgs x 2 ¡ 2 AC motor driven pumps in each Main tank (4 total) ¡ 1 DC powered by the BAT Bus in the Left tank operates automatically : - with no AC available and APU switch ON - in flight when Left N2 is below 67% ( stops at 75%)+ fuel pressure low + APU switch OFF
- Low Output pressure on any of the 4 pumps + EICAS msg.
ON
(amber) - Main Tank pump switch is OFF + EICAS msg
PRESS
¡ LEFT FORWARD pump operates auto (ground!) for APU when AC available even with switch OFF (light out)
2. CENTER TANK ¡ 36500 kgs ¡ 2 AC motor driven pumps with 2 times wing tank pumps output pressure ¡ Pump switch OFF = No LOW PRESSURE light nor EICAS ¡ Inhibited with N2 < 50% (ground + flight) to reduce electrical loads ¡ Auto Scavenge system to BOTH main tanks with wing tank half empty
P R E S S
ON
(amber)
- No fuel remaining with pump switch ON - Output pressure low with pump switch ON - Associated N2 below 50% with pump switch ON
3. CROSSFEED ¡ X-FEED OPS = 2 valves or 1 valve (depending on aircraft options)
VALVE
(amber) = Valve is not in signaled position + EICAS msg.
4. FUEL CONFIG FUEL CONFIG
(amber)
- > 500 kgs in center with both fuel pumps switches OFF + EICAS Message - LOW fuel condition (less than 1000 kgs in any MAIN tank) + EICAS Message - Fuel Unbalance (700 -1100 kg) between main tanks + EICAS Message
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BOEING 767 SYSTEMS REVIEW
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5. SURGE ¡ Surge tanks in each wingtip drained to the center tank.
6. FUEL QUANTITY ¡ Probes Ô Fuel Quantity processor (density correction) Ô Indicator + FMC ¡ Fuel Quantity Test (Accessory Panel) : Fuel quantity indicators display all (8) except first figure of total quantity displays (1) : - fuel temperature displays « -188 » - initiates caution aural + Master Caution (inhibited on ground with engines OFF) + EICAS LOW FUEL msg. and FUEL CONFIG light.
7. FUEL TEMPERATURE ¡ Fuel temperature is measured by a single probe in the Left main tank & displayed on the Fuel temperature selector.
8. GROUND TRANSFER ¡ On ground with fuel pumps source tank ON opening appropriate defueling valve
9. FUEL JETTISON ¡ Discharge nozzles inboard of each outboard aileron ¡ Only operational for the CENTER tank ¡ Switch ON : - 2 JETTISON pumps ON - 2 JET TRANSFER VALVES opened - 1200 kg/min. for 2 nozzles (with Centre fuel pumps ON) / 600 kg/min. without Centre fuel pumps - 30 min. to empty the Centre tank when full ¡ Electrical load shedding will occur during fuel jettison : - Equipment cooling fans (equipment cooling system reverts to OVRD mode) - Bulk cargo vent fan - Selecting light (landing lights, wing illumination, logo lights, galley lights) - Window heat 3L & 3R - PAX entertainment equipment - Water line heaters
FAULT
(amber) : jettison pump(s) and/or transfer valve(s) disagree with jettison switch position
ON
VALVE
- ON : opens respective jettison nozzle - (amber) : valve position disagrees with switch position
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Smartcockpit.com
BOEING 767 SYSTEMS REVIEW
ENGINE FUEL SCHEMATIC
Copyright Smartcockpit.com Ludovic ANDRE / version 00
