曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費(fèi)者

fuel sloshing and sudden center-of-gravity changes that could result as fuel
moves about a partially filled tank. One-way flapper valves also control fuel
movement by opening to allow fuel movement inward while preventing
outward movement.
Each wing tank has a fuel filler cap on the upper wing surface near the
outboard end of the fuel tank.
B. Fuel Hoppers:
A 190 U.S. gallon (719 liter) fuel hopper in each wing tank extends laterally
from the centerline rib to the wing’s first structural rib. The hopper’s forward
wall and the rear wing spar form the forward and aft confines. Flapper
valves in the forward wall open to allow hopper refilling during fueling or
when the wing fuel tank fuel level is higher than hopper fuel level.
Each hopper supplies its respective engine with fuel. The left hopper also
supplies the APU. Each hopper contains the following:
• Fuel pump manifold and associated plumbing
• Fuel tank low level sensor
• Hydraulic fluid heat exchanger
• Fuel quantity probe with compensator
• Motive flow ejector pump
A crossflow shutoff valve in the left hopper allows fuel balance to be
adjusted. A fuel temperature bulb provides a signal for cockpit indications
of fuel temperature.
Simultaneous defueling of both tanks is provided through a suction
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-28-00
Page 9
October 11/01
Revision 5
defueling line and an intertank shutoff valve inside the right fuel hopper.
A motive flow ejector pump, supplied with motive fuel flow from the fuel
pump manifold, transfers fuel from respective fuel tank into the hopper
faster than the engine can consume it at maximum cruise power. Excess
fuel then overflows the hopper back into the wing tank. With a supply
pressure of 25 psig and a maximum motive flow of approximately 750
Pounds Per Hour (PPH) at the ejector pump’s inlet, the ejector pump
produces a minimum induced flow of approximately 4500 PPH. This
assists the boost pumps in maintaining the required fuel pressure at the
engine-driven pump inlets.
C. Gravity Water / Fuel Drain System:
Two types of manually operated drain valves allow fuel sampling, draining
of accumulated water and gravity draining of the wing tanks and fuel
hopper. The majority of the drain valves are located on the bottom of the
wing, adjacent to the fuselage centerline. Each fuel tank also has a drain
valve near the rear spar at the wing root and another valve in the vent
plenum near the wing tip.
The four valves closest to the fuselage centerline are protruding type
valves and are placarded as fuel / water low point drains. Pushing the valve
up with a Phillips screwdriver, then rotating the valve 90° locks the valve
open, allowing draining to occur. Rotating the valve stem 90° (or more if
necessary) in the opposite direction reseats and closes the valve.
The remaining valves are flush type valves. They are opened by pushing
the valve inward with an appropriate tool and rotating the valve stem 90°.
Rotating the valve stem 90° (or more if necessary) in the opposite direction
reseats and closes the valve.
D. Fuel Ventilation System:
The fuel ventilation system is an open vent system that slightly pressurizes
the fuel during flight and prevents tank over-pressurization during fueling
operations. Operation of the system is fully automatic.
Two vent ducts attached to the inside of the upper wing surface run from a
Y-pipe assembly near the wing center section to the vent plenum in the
wingtip. The Y-pipe assembly connects to a float-operated vent / relief
valve that allows tank venting and prevents tank over-pressurization during
refueling by venting the inboard part of the tank through the vent ducts to
the vent plenum. Float-operated vent valves, downstream of the Y-pipe
assembly, drain the fuel vent system.
A non-relieving float-operated vent valve connects each vent duct to the
vent plenum. Two smaller float valves provide additional venting for the
vent valves. A flush vent then connects the vent plenum to the atmosphere
through a flush NACA-type vent on the wing’s lower surface. In flight, the
NACA duct slightly pressurizes the wing tank.
E. Over-Wing (Gravity) Fueling System:
The over-wing (gravity) fueling system provides an alternate method of
fueling the tanks if pressure-fueling equipment is not available. An overwing
(gravity) fueling adapter assembly is installed in each wing fuel tank.
The adapter has a standpipe filler neck that limits wing tank capacity to
approximately 2,185 gallons (8,271 liters). This equates to approximately
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：灣流4操作手冊 Gulfstream IV Operating Manual 2(32)