FUEL FEED LOW PRESSURE INDICATING SYSTEM ............................................ 28-42-0 Description and Operation
Fuel Low Pressure Switches
Trouble Shooting
Adjustment/Test
Fuel Feed Low Pressure Indicating Switch.............................................................. 28-42-11 Removal/Installation
FUEL TEMPERATURE INDICATING SYSTEM......................................................... 28-43-0
Description and Operation
Fuel Temperature Bulb
Fuel Temperature Indicator
Trouble Shooting
Adjustment/Test
Fuel Temperature Bulb ............................................................................................ 28-43-11 Removal/Installation
*[1] Airplanes with center tank fuel scavenge system *[2] ALL EXCEPT airplanes with precalibrated fuel quantity indicators *[3] Airplanes with precalibrated fuel quantity indicators
5C8
Contents 28 Page 6 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 01/96
FUEL -DESCRIPTION AND OPERATION
1. General
A. The fuel system stores fuel and delivers fuel to the engines and APU. Additional components and controls in the system provide rapid fueling and defueling capabilities. The tanks, lines, fittings, and operating components in the system are compatible with all fuels meeting the engine and APU manufacturer's specifications.
B. All fuel is stored within vented areas of the wings and wing center section. The fuel storage area is divided into three integral fuel tanks: a three-cavity center tank and two wing tanks (tanks No. 1 and 2). All three tanks utilize a sealed-wing structure to retain the fuel. The center tank has a secondary fuel barrier coating on the outer surfaces of the upper panel and front spar for additional protection against fuel leaks into pressurized areas of the airplane. For information on the fuel tanks, refer to 28-10-0 and 28-11-0.
C. Fuel is loaded on airplane from a ground source through a fueling receptacle in the pressure fueling station. The tanks can be filled simultaneously or separately. Fuel can also be loaded into tanks No. 1 and 2 through overwing fueling ports. For information on the pressure fueling system, (Ref. 28-21-0).
D. Electric motor-driven boost pumps and fuel lines deliver fuel from any tank to one or both engines. Electrically operated valves control fuel crossfeed and engine fuel shutoff. Pump and valve controls, along with instruments and indicating lights for monitoring the system, are arranged on a system control panel located on the forward overhead panel. For information on the engine fuel feed system, (Ref. 28-21-0).
E. Fuel from boost pumps can also be delivered through a defueling valve into fueling manifold for removal from the airplane. For information on defueling (Ref. 28-23-0).
F. Fuel scavenge pumps, if installed, energize after the center tank is emptied by boost pumps during defueling or engine fuel feed. The scavenge pumps reduce the quantity of unusable fuel in the center tank. For information on the fuel scavenge system (Ref. 28-15-0).
5C8
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