28-CONTENTS
BEJ Page 12 Mar 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
CHAPTER 28 - FUEL
TABLE OF CONTENTS_________________
Subject_______ Chapter SectionSubject_______ Page____ Effectivity___________
INDICATOR - FUEL TEMPERATURE Removal/Installation 28-43-21 401 ALL
28-CONTENTS
BEJ Page 13 Mar 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
FUEL - DESCRIPTION AND OPERATION
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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 28-10-00 and 28-11-00.
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, refer to 28-21-00.
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, refer to 28-22-00.
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, refer to 28-23-00.
F. Fuel scavenge pumps 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, refer to 28-15-00.
G. Fuel quantity indicators, in the flight compartment, and fueling quantity indicators, at the pressure fueling station, indicate the quantity of fuel on the airplane. Measuring sticks, installed on the underside of each integral tank, can also be used to determine fuel quantity. For information on the fuel quantity indicating system, refer to 28-41.
H. Fuel feed low pressure indicating lights, on the forward overhead panel, indicate low engine boost pump outlet pressure. For information on the low pressure indicating system, refer to 28-42-00.
I. A fuel temperature indicator, on the forward overhead panel, indicates fuel temperature in tank No. 1. For information on the fuel temperature indicating system, refer to 28-43-00.
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28-00-00
ALL ú ú 01 Page 1 ú Jul 15/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
J. Fuel is delivered to the APU from tank No. 1 either through an independent fuel inlet or through a connection to the engine fuel feed system. The engine ac boost pumps can be used to pressurize the APU fuel feed system. A check valve in each inlet line prevents reverse flow through the inactive inlet line. An electrically-operated shutoff valve, downstream from the inlet tee, prevents pressurization of the APU fuel line during APU shutdown. For information on the APU fuel feed system, refer to 28-22-00. For information on the APU, refer to Chapter 49, Airborne Auxiliary Power.
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