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OPERATING MANUAL
PSP 601A-6
SECTION 1
FUEL
TABLE OF CONTENTS
GENERAL
FUEL STORAGE
FUEL FEED
A. Ejector Pumps
B. Electric Pumps
C. Engine Feed
D. APU Fuel Feed
E. Tank Vent System
REFUEL/DEFUEL SYSTEM
A. Pressure Refuel/Defuel System
B. Pressure Refueling
C. Suction Defueling
D. Gravity Refueling and Defueling
FUEL QUANTITY INDICATING SYSTEM
TAIL FUEL TANK SYSTEM
A. General
B. Refueling and Defueling
C. Fuel Transfer
D. Fuel Jettison System
E. Tail Tank Vent System
F. System Operation
Page
1
2
3
3
3
4
4
4
5
5
5
6
6
7
7
7
7
7
8
8
8
LIST OF ILLUSTRATIONS
Figure Title Page
Number
1 Fuel Feed System - Schematic (2 Sheets) 11
2 Fuel Control Panel (2 Sheets) 13
3 Refuel/Defuel System - Schematic 15
12 - CONTENTS
Page 1
Apr 10/95
OPERATING MANUAL
PSP 601A-6
Figure Title Page
Number
4 Refuel/Defuel Control Panel 16
5 Fuel Quantity Indicating System 17
6 Fuel Specific Weight 18
7 Tail Tank System - Schematic 19
8 Tail Tank Control Panel (2 Sheets) 20
12 - CONTENTS
Page 2
Apr 10/95
GSSSmricjer
OPERATING MANUAL
PSP 6C1A-6
SECTION 12
FUEL
1. GENERAL (Figure 1)
The fuel system has a three-tank configuration consisting of left and right
main tanks, and an auxiliary tank,
On aircraft 5135 and subsequent and aircraft incorporating Canadair Service
Bulletin 601-0262,
a tail tank is installed (refer to paragraph 6.).
The principal components of the aircraft fuel system include fuel tanks,
independent ejector pumps for each engine, two electric pumps, and a fuel
feed system for the auxiliary power unit (APU). A single pressure
refuel/defuel adapter is provided. Gravity refueling or defueling is also
possible. Fuel and water drains are located at various low points on the
fuel system.
The relatively high elevation of the fuel lines, running from the top of the
wing box centre section up to the engine nacelle level, protects them from
damage in the event of a wheels-up landing.
Control of the fuel system components and fuel quantity indication are
provided by the FUEL CONTROL and FUEL QUANTITY panels on the centre
instrument panel. The FUEL QUANTITY panel provides an indication of
individual tank and total fuel quantity.
In addition to supplying the engines and the APU with fuel, the system
provides a flow of fuel to cool the APU generator oil.
SECTION 12
Page 1
Apr 10/95
OPERATING MANUAL
PSP 601A-6
2. FUEL STORAGE (Figure 1)
The entire wing box structure is sealed to form three tanks: the left and
right main tanks and the primary section of the auxiliary tank. Front and
rear sections (double-walled tanks) of the auxiliary tank are installed in
the fuselage forward and aft of the primary auxiliary tank. The capacities
of the tanks, in litres (US gallons) of usable fuel, are:
Pressure refueling Gravity refueling (approx.)
Litres (US gallons) Litres (US gallons)
Left main tank 2733 (722) 2536 (670)
Right main tank 2733 (722) 2536 (670)
Auxiliary tank 3823 (1010) 3569 (943)
Total 9289 (2454) 8641 (2283)
A balance line, equipped with an electrically operated cross-flow valve,
connects the main tanks at their lowest points. Selecting the X-FLOW
switch/light, opens the cross-flow valve to allow the main tank fuel
quantities to equalize by gravity.
On aircraft 5001, 5027 and subsequent and aircraft incorporating Canadair
Service Bulletin 601-0225,
an electrically operated cross-feed valve is connected at each end of the
balance line. Selecting the LEFT TO RIGHT or RIGHT TO LEFT switch/lights,
opens the associated cross-feed valve to allow fuel to enter the auxiliary
tank. Fuel is then transferred to the main tanks by the engine ejector pumps
with engines running or by the electrical boost pumps with engines shut down.
A safety feature prevents opening of both cross-feed valves at the same time.
Approximately 8 minutes after fuel balancing commences, the selected
switch/light begins to flash as a reminder that the cross-feed valve is open.
The primary section of the auxiliary tank contains the left and right
collector tanks which feed the left and right engines, respectively. The
collector tanks enclose the left and right main ejector pumps and are
maintained full by gravity feed lines and the scavenge ejector lines from the
main tanks. The electric fuel pumps are also located inside the auxiliary
tank, beside the collector tanks. When in operation, each electric pump
draws fuel only from its corresponding collector tank.
Flush-mounted access panels are installed on the lower wing surface to
provide access to the interior of the fuel tanks. Three similar panels serve
as supports for the electric fuel pumps of the engine fuel and APU fuel feed
systems. A cover on these panels can be removed to permit servicing of the
fuel pump motor elements without draining the associated fuel tanks and
lines.
The three sections (or tanks) that make up the auxiliary tank are
interconnected and are treated as one tank for the purpose of refueling,
defueling and fuel feed.
SECTION 12
Page 2
Apr 10/95
OPERATING MANUAL
PSP 601 A - 6
FUEL FEED (Figures 1 and 2)
Independent fuel supplies are provided for the engines and the APU. In
normal operation, the left and right engines are fed by the main ejector
pumps in the left and right collector tanks respectively. The two electric
pumps serve as backups to the main ejectors. The APU supply is drawn
directly from the right main tank by an electric pump.
NOTE: To avoid fuel spillage through the fuel tank vent system, the electric
fuel pumps must not remain on for more than 5 minutes without the
engines running.
A. Ejector Pumps
An ejector pump operates on the same principle as a venturi tube to
convert a small-volume/high-pressure input (motive flow) at the throat of
the unit into a large-volume/low-pressure output flow at the ejector
nozzle. Motive flow for the scavenge and main pumps is provided by the
high-pressure section of the associated engine pump.
B. Electric Pumps
Two electric fuel pumps are connected to the collector tanks and serve as
sources of fuel pressure during engine starting and as backups for the
main fuel ejectors. The pumps are controlled by the two PUMP
switch/lights on the fuel control panel in conjunction with pressure
switches in the outlet lines of the main fuel ejectors. The PUMP
switch/lights arm both electric fuel pumps. If a low fuel pressure
condition exists at the outlet of the associated main fuel ejector, both
of the electric pumps come on to ensure that an adequate flow of fuel is
delivered to the engine pump. The electric pumps shut down automatically
when the required output pressure is re-established at the outlet of the
main ejector.
On aircraft 5135 and subsequent,
should the electric fuel pumps fail or if they are selected off, the FUEL
LO PRESS lights will come on.
SECTION 12
Page 3
Apr 10/95
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OPERATING MANUAL
PSP 601A-6
C. Engine Feed
The main ejector pumps provide a continuous fuel flow to the engine pumps
at a pressure and volume sufficient for maximum engine consumption and
motive flow requirements. The fuel from each ejector flows through a
feed line across the firewall fuel shutoff valve to the inlet of the
engine pump. One-way check valves on the feed lines control the
direction of flow so that each ejector supplies only the engine
associated with i t.
The collector tanks are kept f u l l by gravity feed lines from the
associated main tanks supplemented by scavenge ejectors. The scavenge
ejectors ensure that the collector tanks are supplied with main tank fuel
during low fuel conditions and during f l i g h t with high nose-up attitudes.
The sequence of fuel transfer between the auxiliary tank and the main
tanks is such that all the fuel carried aboard the aircraft is
transferred to the main tanks before being fed to the collector tanks.
When the main tank fuel level drops below approximately 93% of f u l l,
transfer of fuel from the auxiliary tank begins automatically to maintain
that level in the main tanks. The transfer is effected by two transfer
ejectors which are provided with motive flow by bleeds from the engine
feed lines. Float valves control the transfer of fuel to approximately
the 93% f u l l level.
D. APU Fuel Feed
The APU is supplied with fuel by an electric fuel pump located in the
right main fuel tank. APU fuel is also routed via a fuel/oil heat
exchanger to cool the APU generator o i l . The APU pump is controlled by a
switch/light on the APU control panel (refer to Section 5).
The APU fuel feed line is f i t t e d with an electrically operated fuel
selector valve. To ensure uninterrupted operation of the APU during
negative 6 conditions, a negative G protection fuel feed line connects
with the l e f t engine fuel feed line. The line is f i t t e d with an
electrically operated fuel shutoff valve and a one-way differential check
valve which opens when the main APU supply pressure drops below the
pressure in the engine fuel line.
During normal operation, both of the shutoff and selector valves on the
APU fuel system are opened and closed simultaneously by the START/STOP
switch/light on the APU control panel (refer to Section 5). Operation of
the APU FIRE PUSH switch/light closes both the APU fuel shutoff and
selector valves.
E. Tank Vent System
The fuel tanks are vented to atmosphere through common vent lines which
terminate at NACA scoops on the l e f t and right lower wing surfaces. The
vent lines are continuously purged whenever the scavenge ejectors
operate.
SECTION 12
Page 4
Jan 06/98
OPERATING MANUAL
PSP 601A-6
4. REFUEL/DEFUEL SYSTEM (Figures 3 and 4)
Refueling and defueling is carried out using the single point pressure
refuel/defuel adapter on the right wing leading edge f i l l e t , or through
gravity f i l l e r caps and drain valves associated with each fuel tank. Tank
venting is maintained by the fuel tank vent system or, during pressure
refueling operations, by vent relief valves which act to prevent tank
overpressures. The action of level control valves provides fuel expansion
space and protection against over-filling by limiting the full fuel volume to
98% of the total tank volume. The location of the gravity-filler caps limits
the full fuel volume to approximately 91% of the total tank volume.
A. Pressure Refuel/Defuel System
This system consists of a standard single point refuel/defuel adapter and
a refuel/defuel control panel in the right wing f i l l e t.
The pressure refuel/defuel system can accept the following maximum
pressures and flow rates:
Maximum refuel rate 946 litres (250 US gallons)/minute
Maximum refuel pressure 55 psi
Maximum defuel rate 537 litres (142 US gal Ions)/minute
Maximum defuel suction 8 psi (negative pressure)
After suitable pressure or suction has been established at the
refuel/defuel adapter, the transfer of fuel into or out of the fuel tanks
is obtained by energizing and de-energizing the tank shutoff valves on
the fueling manifold. The tanks can also be defueled without electrical
power using only the suction applied by the fuel tender.
B. Pressure Refueling
With the POWER switch ON, the MODE selector set to FUEL and the FUEL/DEF
switches selected to FUEL, fuel pressure is allowed to open the tank
shutoff valves. Fuel flows from the shutoff valves through pilot lines
to the level control valves in the fuel tanks. When the tanks are f u l l,
the floats of the level control valves close the pilot lines. Back
pressure, transmitted through the pilot lines closes the shutoff valves
to stop the flow of fuel to the tanks. Valve positions are monitored by
the SOV OP and SOV CL lights on the refuel/defuel control panel (refer to
Figure 4).
Testing the operation of the tank shutoff valves and their associated
level control valves is done by simulating a full-tank condition. This
is accomplished by f i l l i ng bowls which surround each float with fuel.
The test is carried out while refueling is in progress using the MODE
selector switch. It takes 20 to 30 seconds to f i l l the bowls which, when
f u l l , cause the system to respond as i f the tank was f u l l . Refueling
operation is re-established by reselecting the MODE selector to the
normal FUEL position.
SECTION 12
Page 5
Apr 10/95
OPERATING MANUAL
PSP 0O1A-6
Vent relief valves, one in each main tank and one in the primary section
of the auxiliary tank, prevent fuel tank overpressure should the fuel
tank vent system or the tank shutoff valves fail during pressure
refueling. Each vent relief valve is connected by a pressure-sensing
line to the fueling manifold and is designed to open on positive fluid
pressure only, therefore remaining closed during suction defueling. The
vent relief valve positions are monitored via the green VV OPEN lights on
the refuel/defuel control panel*
C. Suction Defueling
The aircraft may be completely defueled without electrical power via the
single point refuel/defuel adapter. A fuel tender suction of 8 psi will
open the tank shutoff valves. When the tanks are empty, the valves close
by spring pressure.
The tanks may also be selectively defuel ed provided by refuel/defuel
panel is electrically powered and the MODE selector is set to DEFUEL.
Starting and stopping of defueling of a given tank is accomplished by
selecting the associated FUEL/DEF switch to DEF and OFF respectively.
D. Gravity Refueling and Defueling
The fuel tanks may be filled by gravity through f i l l e r caps. The f i l l er
caps of the l e f t and right main tanks are mounted flush with the upper
skin of the l e f t and right wing respectively. The f i l l e r cap for the
auxiliary tank is recessed below the right wing skin adjacent to the wing
root f i l l e t.
A plug-type electrical grounding attachment, placarded ELECTRICAL GROUND
STUD, is located just forward of each f i l l e r cap on the lower surface of
the wing leading edge.
Gravity defueling is carried out through gravity defueling drains located
at the lowest point in each tank. Each drain consists of a capped
orifice into which an adapter is inserted to allow fuel to drain from the
tank.
In addition to the gravity defueling receptacles, water drains are
provided at various locations on the lower wing surface. The valves are
opened by using a screwdriver to depress and rotate the valve core to
expose drain holes on the base of the valve housing.
i SECTION 12
Page 6
Apr 10/95
fonssumssncfBr
OPERATING MANUAL
PSP 601A-6
| 5. FUEL QUANTITY INDICATING SYSTEM (Figures 5 and 6)
The fuel quantity indicating system consists of capacitance-type fuel
quantity sensors in the fuel tanks, a signal conditioner to power the
quantity sensors and process their fuel quantity signals, and a fuel quantity
panel powered by a signal data converter. The individual tank and total
usable fuel contents in pounds are displayed as digital readouts on the FUEL
QUANTITY panel. The fuel quantity displayed for each main tank includes the
fuel contained in the associated collector tank. The fuel quantity displayed
for the auxiliary tank includes the fuel contained in the primary, front and
rear sections of the auxiliary tank.
6. TAIL FUEL TANK SYSTEM (Figures 7 and 8)
A. General
On aircraft 5135 and subsequent and aircraft incorporating Canadair
Service Bulletin 601-0262,
the tail cone structure forward of the kevlar fairing is sealed to form a
187.7 US gallon (827 litre) fuel tank. The complete tail tank system
consists of provisions for powered or gravity fuel transfer, fuel
jettison, pressure refueling and defueling and quantity sensing.
Controls and indicators for the system include a T/TANK FUEL TRANS panel
and a modified FUEL QUANTITY panel in the flight compartment.
On aircraft 5135 and subsequent,
the T/TANK FUEL TRANS panel is integrated as part of the FUEL CONTROL
panel.
A T TANK TEST panel on the bulkhead behind the copilot's seat is provided
for maintenance purposes,
B. Refueling and Defueling
The tail tank is pressure refueled and defueled via the existing fueling
adapter on the right wing f i l l e t . A line fitted with two shutoff valves
feeds fuel from the fueling adapter and fuel manifold to the tail tank.
The shutoff valves are controlled by switch selections on the modified
refuel/defuel panel and signals from a level switch, designated the full
level switch, in the tail tank.
No provisions are made for gravity fueling of the tail tank.
C. Fuel Transfer
A 28 volt dc boost pump in the tail tank transfers fuel to the primary
auxiliary tank via a transfer shutoff valve and transfer line.
The boost pump is controlled by the tail tank AWED/OFF switch selections
and signals from two level switches, one in the primary auxiliary tank
designated auxiliary tank level switch No. 1 and one in the tail tank
designated tail tank level switch No. 1.
SECTION 12
Page 7
Apr 10/95
OPERATING MANUAL
PSP 601A-6
On aircraft 5135 and subsequent and aircraft incorporating Canadair
Service Bulletin 601-0355,
an in-line/backup electrical boost pump is installed to improve transfer
rate. The in-line pump automatically comes on if the primary transfer
rate is low or if the auxiliary and/or tail tank level switch fails.
The fuel transfer line is protected by a nitrogen pressurized shroud on
that part of its run subject to possible damage from an engine
rotorburst. Sudden loss of pressure in the shroud is detected and fuel
transfer from the tail tank is automatically stopped.
If powered fuel flow fails, gravity feed to the transfer line and thence
to the primary auxiliary tank takes place via a gravity transfer shutoff
valve. This valve is controlled open and closed by a flow switch in the
transfer line and a level switch, tail tank level switch No. 2, in the
tail tank.
D. Fuel Jettison System
Tail tank fuel can be jettisoned through an overboard line opening under
the tail cone. A shutoff valve, controlled by switch/light selection on
the T/TANK FUEL TRANS panel or the FUEL CONTROL panel (aircraft 5135 and
subsequent), is opened to allow gravity flow of fuel into the overboard
line.
E. Tail Tank Vent System
Tail tank venting is maintained through a vent line and check valve
connected to the ram air duct and an opening under the tail cone. In the
event of a failure of the refuel/defuel system components, fuel flow
through the vent line opening under the tail cone is sufficient to
prevent tank overpressure.
F. System Operation
(1) Refueling and Defueling
Tail tank refueling is possible only when all other tanks are full.
Until this condition is satisfied, the two shutoff valves in the tail
tank fueling line are closed by signals from a level switch in the
primary auxiliary tank, auxiliary tank level switch No. 2.
When the fueling nozzle is connected and refueling pressure is
applied, the closed position of the shutoff valves is verified by the
green CL light above the TAIL switch on the refuel/defuel panel.
With the panel MODE selector at FUEL, the TAIL switch set to FUEL and
all other fuel tanks full, the amber OP light comes on to indicate
that the tail tank fueling line shutoff valves are open. At the
maximum refueling pressure of 55 psi, refueling is accomplished at a
rate of 45 US gallons per minute until the tail tank full level
switch signals that the full level (85% of tank volume) is reached
and closes the shutoff valves. At any time during refueling
operations, the shutoff valves can be closed by setting the TAIL
switch to OFF or the MODE selector to OFF or DEFUEL.
SECTION 12
Page 8
Apr 10/95
eSSS&icjer
OPERATING MANUAL
PSP 601A-6
Defueling can be carried out at any time, regardless of the fuel
quantity in the other tanks, by setting the MODE selector to DEFUEL
and the TAIL switch to DEF. The OP light will then come on to
indicate that the shutoff valves are open and that defueling is
talcing place. At the maximum defueling pressure of 8 psi negative,
the tank is defueled at the rate of 15 US gallons per minute. When
the tail tank is empty, the shutoff valves close and the CL light
comes on. At any time during defueling, the shutoff valves can be
closed by setting the TAIL switch to OFF or the MODE selector to OFF
or FUEL.
Before fueling operations are started, the correct functioning of the
system components can be checked by setting the TAIL switch to FUEL
and the MODE selector to TEST. This causes flow from a pilot line
into a bowl on the tail tank full level switch to simulate the tank
full condition. Correct operation of the system components is
observed i f the OP light comes on, then goes out followed by the CL
light's coming on.
(2) Fuel Transfer
With the tail tank ARMED/OFF switch set to ARMED, the transfer
shutoff valve opens and the transfer boost pump comes on as signaled
by the auxiliary tank level switch No. 1 when the primary auxiliary
tank fuel quantity decreases below a preset level. Transfer is
carried out at a rate of 15 pounds per minute until the unusable fuel
level (1.3 US gallons) is sensed by tail tank level switch No. 1. At
this point, the transfer shutoff valve closes and the boost pump
shuts down.
I f the ARMED/OFF switch set to OFf while usable fuel remains in the
tail tank, the amber NOT ARMED light comes on. If, in this
condition, the fuel quantity in the primary auxiliary tank is allowed
to reach the level sensed by auxiliary tank level switch No. 2, the
NOT ARMED light flashes. If the ARMED/OFF switch is then set to
ARMED, the light goes out and transfer starts immediately.
On aircraft 5135 and subsequent and aircraft incorporating Canadair
Service Bulletin 601-0355,
a failure of powered fuel transfer is detected by the transfer line
flow sensor which signals the transfer shutoff valve closed, shuts
down the boost pump, opens the gravity transfer shutoff valve and
turns on the in-line/backup pump. The SEC TRANS light comes on to
indicate that fuel transfer by the in-line/backup pump is taking
place. Transfer continues at a minimum rate of 8 pounds per minute
until tail tank level switch No. 2 senses that approximately 2.3 US
gallons of fuel remain in the t a i l tank. At this level, the SEC
TRANS light goes out, the gravity transfer shutoff valve closes and
the in-line/backup pump shuts down.
SECTION 12
Page 9
Apr 10/95
GttsuShiQtBr
OPERATING MANUAL
PSP 601A-6
On aircraft not incorporating Canadair Service Bulletin 601-0355,
a failure of powered fuel transfer is detected by the transfer line
flow sensor which signals the transfer shutoff valve closed, shuts
down the boost pump and opens the gravity transfer shutoff valve.
The GRAV TRANS light comes on to indicate that gravity transfer is
taking place. Transfer continues at 6 to 8 pounds per minute until
tail tank level switch No. 2 senses that approximately 2.3 US gallons
of fuel remain in the tail tank. At this level, the GRAV TRANS light
goes out and the gravity shutoff valve closes.
A perforation of the nitrogen pressurized shroud surrounding part of
the transfer line is detected by a pressure switch which signals all
open shutoff valves to close and shuts down the boost pump. Transfer
of fuel from the tail tank is not possible until the shroud is
replaced and pressurized*
(3) Fuel Jettison
On aircraft 5135 and subsequent and aircraft incorporating Canadair
Service Bulletin 601-0362,
pressing the DUMP SWITCH ARMED switch light causes the switch/light
to come on green and arms the jettison system. With the system
armed, pressing the DUMP SELECT switch/light causes the switch to
cane on green and the DUMP OPEN light to cane on white opens the
jettison shutoff valve. Fuel is then discharged through the
overboard line at approximately 100 pounds per minute. Fuel jettison
can be stopped by pressing the DUMP SWITCH ARMED or the DUMP SELECT
switch light again to close the jettison shutoff valve.
On aircraft not incorporating Canadair Service Bulletin 601-0362,
pressing the DUMP SWITCH ARMED switch light causes the switch/light
to come on green and arms the jettison system. With the system
armed, pressing the PRESS TO DUMP switch/light causes the switch to
cone on green and opens the jettison shutoff valve. Fuel is then
discharged through the overboard line at approximately 100 pounds per
minute. Fuel jettison can be stopped by pressing the DUMP SWITCH
ARMED or the PRESS TO DUMP switch/light again to close the jettison
shutoff valve.
i
SECTION 12
Page 10
Apr 10/95
OPERATING MANUAL
PSP 601A-6
(FRONT SECTION)
CLOSE
RIGHT
ENGINE
CLOSE FIRE I
<%J9H J
LEGEND
CLOSE
OPEN/
CLOSE
ARU
FIRE
PUSH
EFFECTMTY:A/C 5001,5027 AND 6UBS
AND A/C POST SB 601-0225
mmniH
ezza
is
FUEL FEED
MOTIVE FLOW
SCAVENGE FLOW
TRANSFER FLOW
APU GF*I COOLING FLOW
EJECTOR
ELECTRIC PUMP
PRESSURE SENSOR
FLOW SENSOR
CHECK VAVLE
f
J»« n>A«Maw an. m* I >—*
;QaiEW-E3|ff«
icalggslFaii^jEgB
Fuel Feed System - Schematic
Figure 1 (Sheet 1)
SECTION 12
Page 11
Apr 10/95
OPERATING MANUAL
f*SP 601A-6
(FRONT SECTION)
LEFT
ENGINE
^mnm^
+ + u APU NEGATJVE-G
PROTECTION
SHUTOFF VALVE
IMEMQ
M K
*JSM
CLOSE
APU SELECTOR
VALVE
APU
RIGHT
ENGINE
CLOSE
CLOSE
OPEN/
CLOSE
EFFECnVTTY:A/C 5002 TO 5026
PRE SB 601-0225
LEGEND
FUEL FEED
MOTIVE FLOW
l U I I I t l l l l SCAVENGE FLOW
H A W TRANSFER FLOW
\SSSA APU GBl COOLING FLOW
QC^J EJECTOR
ELECTRIC PUMP
PRESSURE SENSOR
f S g l FLOW SENSOR
^STl CHECK VAVLE
Fuel Feed System - Schematic
Figure 1 {Sheet 2) SECTION 12
Page 12
Apr 10/95
OPERATING MANUAL
PSP 601A-6
LTANK AND R TANK FEED SWITCH/LIGHTS (2)
When pressed in, appropriate crossfeed valve opens.
green LEFT TO RIGHT or RJGHTTO LEFT light comes on
andlue! flows into auxiliary tank by gravity. When pressed
out. eroasfeed valve doses and light goes out
L TANK AND R TANK EJCTRS LIGHTS (2)
Amber SCAV light comes on rf
scavenge ejector failure is detected
by flow sensor at ejector outlet.
Amber MAIN light comes on if
main ejector failure b detected by
pressure switch at ejector outlet.
L TANK AND R TANK PUMP SWTTCH/UGHTS O
Control operation of electric fuel pumps in conjunction with
pressure switches at main ejector outlets.
If a PUMP switch/fight is pressed in, wd low pressure condition is
detected at outlet of associated main ejector, both electric fuel
pumps come on to maintain required fuel flow to affected engine.
Green ON light comes on if associated engine pump b operating.
Amber INOP ight comes on if
a pump failure occurs.
pump switch is out or if
PUMP
FUEL CONTROL
-PUSH ON OFF-
1 SCAV J
1 MAM j
1 °^ II
1 MOP II 1 OPEN
1! ON j
II WOf i
j SCAV 1
1 MAIN II
VALVE CLOSED LIGHTS (21
White VALVE CLOSED light <
shutoff valve is closed.
i on if associated firewall fuel
X-FLOW SWITCH/LIGHT
When pressed in, balance fine cross-flow valve opens,
green OPEN ight comes on and left and right main
tanks equalize by gravity flow. When pressed out.
balance i n e shutoff valve doses and tight goes out.
NOTE
Refer to Section 17 for osteite of fuel temperature
indicator, 9nd FILTER and LOW PRESS fights.
EFFECnVITY: A/C5001.6027 AND SUBS
AND A/C POST SB 601-0225
Fuel Control Panel SECTION 12
Figure 2 (Sheet 1) Page 13
Apr 10/95
OPERATING MANUAL
PSP 601A-6
L TANK AND R TANK PUMP SWITCH/LIGHTS ©
Control operation of electric fuel pumps in conjunction with
pressure switches at main ejector outlets.
LTANK AND R TANK EJCTRS UGHTS (2)
Amber SCAV light comas on if scavenge ejector failure is detected
by flow sensor at ejector outlet.
if e PUMP switch/light is pressed in, *n6 low pressure condition is
detected at outlet of associated main ejector, both elect, ic fuel
pumps come on to maintain required fuel flow to affected engine.
Green ON tight comes on if associated engine pump is operating.
Amber INOP Eght comes on if associated pump switch b out or rf
a pump failure occurs.
Amber MAIN tight comes on if main ejector failure is detected by
pressure* switch at ejector outlet.
VALVE CLOSED UGHTS C2J
White VALVE CLOSED light (
shutoff valve is closed.
. on if associated firewall fuel
X-FLOW SWTTCH/U6KT
i oressed in, balance fne cross-flow valve opens,
green OPEN ight comes on and left and right main
tanks equalize by gravity flow. When pressed out,
balance few shutoff valve closes and ight goes out.
NOTE
ncfar to Secoon 17 for details of fuel temperature
nxScmoc, and FILTH* and LOW PRESS fights.
EFFECTJVITY: A/C 5002 TO 502t
PRE 88 601-022$
Fuel Control Panel
Figure 2 (Sheet 2)
SECTION 12
Page 14
Apr 10/95
OPERATING MANUAL
PSP 601A-6
LEVEL CONTROL
VALVE/FLOAT
SOLENOID VALVE-
(OoMd during
system tost)
LEFT MAIN TANK
REFUEL/DEFUEL
ADAPTER
TANK SHUTOFF
VALVE
TWO-WAY
CHECK VALVE
AUXIUARYTANK
TF*
RIGHT MAIN TANK
| onn |jllslsdr
"J| OKN |]
•}}g|o»|] I MODE
w w v I >
UN AUX LMN *=f
L SELECTED TANKS ONLY - i
VENT REUEF
VALVE
^
I ow ||lcL|oi|{cMo4|cajc4|
ft vvV 1
ctggpTH
sov MODE
POWER) TAIL R.MAIN AUX L.MAJN
*UfL/JXR»ft>
bH-kCI IVIIY: A « 5001 TO 5134 PRE SB 801-0262
LEGEND
REFUEL/DEFUEL LINES
LEVEL CONTROL PILOT LINES
PRESSURE-SENSING LINES
EFFECnVITY: A/C 5185 AND SUBS AND
A/C POST SB 601-0262
Refuel/Defuel System - Schematic
Figure 3
SECTION 12
Page 15
Apr 10/95
OPERATING MANUAL
PSP 601A-6
8 °* (I |1CI|OP|MJ CLJOpjfl CLJOPfrjj Ci.foqP^^^
MODE
J T £ S T ^ — ^ OFF
TOWER I TAIL R.MAIN AUX
EFFECTMTY: A/C 5135 AND SUBS AND
A/C POST SB 601-02*2
POWER ON INDICATOR
Green light comes on when POWER switch is
set to ON.
VENT RELIEF VALVE STATUS LIGHTS SHUTOFF VALVES STATUS LIGHTS
Green CL lipht comes on rf POWER switch
is ON and associated tank shutoff valve is
on if POWER switch is
tank shutoff valve is open.
POWER SWITCH
Setting switch to ON arms contacts of MODE
selector switch. Switch connects cvectty to
ZB'VOft dc osttory direct bus. Fight cornpartrnent
switch selection n not necessary during, pressure
ftrfusJ/dofuet operations.
FUEL/DEF SWITCHES
Controls operation of tank shutoff valves in
conjunction with mode selections on MODE
selector switch.
MODE SELECTOR SWITCH
FUEL - Opens tank shutoff valves in conjunction
with FUEL sanction on FUEL/DEF switches to
perrrst pressure refueling.
DEFUEl - Opens tank shutoff valves in
conjunction with OET selection on FUEL/DEF
switches to permit suction defusing.
OFF - Disarms FUEL/DEF switches.
TEST - Teats operation of tank shutoff verves by
simulating fufi fuel condition in tanks. With
fueling pressure applied at refusing nozzle.
POWER switch ON and FUEL/DEF switches set
at FUEL. SOV-CL lights go out and SOV-OP
lights come on for 20 to 30 seconds. Correct
operation of shutoff valves is vxficated when
SOV-CL fights come on mwTwoiatery after SOVOP
fcghts go out.
Refuel/Defuel Control Panel SECTION 12
Figure 4 Page 16
Apr 10/95
OPERATING MANUAL
PSP 601A-6
CAPACITANCE TYPE FUEL QUANTITY SENSORS
6 in each main tank.
3 in primary auxftsry tank.
1 in each collector tank.
11n tafl tank [7J
r®
SIGNAL CONDITIONER
Converts return signals from quantity sensors into dc signals
suitable for use by quantity indicator.
U<=>
SIGNAL
CONDITIONER
SIGNAL
DATA
CONVERTER
SIGNAL DATA CONVERTER
Provides dual power supply,
tapped from the battery bus and
the dc essential bus. for the
noscator logic arcuita and
display lamps.
EFFECTTYTTY: A/C 5135 AND SUBS AND
A/C POST SB 601-0262
DIGITAL READOUTS
ImernaHy illuminated digital displays.
Readouts provide continpus indication of
"usable fuel quantity in each tank plus
system total.
EFFECTIVITY
B A/C 5135 AND SUBS AND
A/C POST SB 601-0232 CENTRE INSTRUMENT PANEL
NOTE
Refer to Section 17 for
details of indicator test.
Fuel Quantity Indicating System SECTION 12
Figure 5 Page 17
Apr 10/95
crS&Encjetr
OPERATING MANUAL
PSP 601A-6
7.51 1 j 1 1 1 j
7.4
7.3
73
SPECIFICATION LIMITS
FUEL SP GR (60/60 F)
KEROSENE 0.775 - 0.845
WIDE CUT 0.751 - 0.802
5.6
-60 -40 -20 0 20 40 60 80 100 120 140 160
TEMPERATURE °F
Fuel Specific Weight SECTION 12
Figure 6 page 18
Apr 10/95
OPERATING MANUAL
PSP 601A-6
FUELING ADAPTER
AND MANIFOLD
LEGEND
ELECTRIC PUMP
C 3 — PRESSURE SENSOR
§ FLAME ARRESTER
F ^ l CHECK VALVE
^ » t FLOW SENSOR
E A/C 5135 AND SUBS AND
A« POST SB 601-0356
gj A/C 5001 TO 5134 PRE SB 601-0355
H AfC 5135 AND SUBS AND
JVC POST SB 601-0362
B A/C 5001 TO 5134 PRE SB 501-0352
Tail Tank System - Schematic
Figure 7
SECTION 12
Page 19
Apr 10/95
OPERATING MANUAL
PSP 601A-6
DUMP SWITCH ARMED SWITCH/LIGHT
j . green DUMP SW ARMED
kgrncomo on and PRESS TO DUMP
SWItCR/bght 9 JHtflBO.
PRESS TO DUMP SWITCH/LIGHT
i PRESS
NOT ARMEO LIGHT
Amber bght comes on steady <f usab<e
fuel is m tail tank and ARMED/OF?
switch cs in OFF position. If toei «n
primary auxiliary tank cs aBowed to
decrease to preset level, kght comes on
flashing.
GRAY TRANS LIGHT
AmDer light comes on to indicate
that gravity transfer is in progress.
Light goes out when transfer
PRESS
TO
DUMP m
SEC
DUMP SWITCH / LIGHT
When armed DUMP SELECT comes on
green and when pressed. white DUMP OPEN
kgti comes on end jettison ehutotf VI)VB
opens. T«B fenktuei i t dteeheiged at
100 pounds / minute.
SECTRANS LIGHT
Amber Mght comes on to indicate
that the beck-up putnp is on
(eutomatteaBy) IT primary transfer
rate is low or the auxiary and / or
tei tank leva! switch fails.
ARMED/OFF SWITCH
fn ARMED position transfer shutott valve
opens and booAi pump transfers tuoi to
pnmary auxifeary lank on s»gn*s from
muubmy tank and tail tank level switches.
fcwcnvnv
A/C SOOt TO SIM
El AJC POST SB 001-0355
B A/CP08T88081-0362
Tail Tank Control Panel
Figure 8 (Sheet 1)
SECTION 12
Page 20
Apr 10/95
OPERATING MANUAL
PSP 601A-6
@ I L £ ' j, -PUSH C* «* —
If"' C -==-^=iJ - ^ I M P X^LOV; pijklP J1
?CAV irsrisii r irTOKT -^T^n
"3
1
i .XA i I
jlC* C3EC
1 ^^-V^Os^
- -^ / / !! cm. I i:
Ik^J^
1
DUMP SWITCH ARMED SWITCH/LIGHT
i DUMP SW ARMED
tight comes on and PRESS TO DUMP
switch/light is armed.
DUMP SWITCH /LIGHT
Whan armed DUMP SELECT comae on
graan and whan pressed, while DUMP OPEN
tight comas on and jettison shutoff vaJve
opens. Tail tank tuei is discharged at
100 pounds / minute.
Amber ligh: comes on steady if usabte
tuei is in tail tank and ARMED/OFF
switch is in OFF position, if fuel in
primary auxiliary tank is allowed to
decrease to preset level, light comes on
hashing.
SEC TRANS LIGHT
Amber Hght comes on to Indicate
thai the back-up pump is on
(automaticaBy) fl primary transfer
rate is low or the auxitary and /or
tail tank level ewtteh tails.
ARMED/OFF SWITCH
ftr> ARMED position transfer shutotf valve
opens and boost pump transfers fuel to
primary auxiliary tank on signals from
auxiliary tank and tail tank level switches.
EFFECnVTTY: A/C 5135 ft SUBS
Tail Tank Control Panel
Figure 8 {Sheet 2)
SECTION 12
Page 21
Apr 10/95

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