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-cinhaaplleanirg er
OPERATING MANUAL
PSP 606
SECTION 12
FUEL
TABLE OF CONTENTS
Subject
SYSTEM CONFIGURATIONS
GENERAL
FUEL STORAGE
FUEL DISTRIBUTION
Ejector Pumps
Engine Feed
APU Fuel Feed
Standby Feed
Tank Vent System
REFUEL/DEFUEL SYSTEM
Pressure Refuel/Defuel System
Pressure Refueling
Pressure Defueling
Gravity Refueling and Defueling
FUEL QUANTITY INDICATING SYSTEM
Page
1
1
2
7
10
11
12
12
18
19
21
Figure
Number
LIST OF ILLUSTRATIONS
Title
1 Fuel Feed System - Schematic
2 Auxiliary Fuel Tanks
3 Fuel Control Panel (2 Sheets)
4 Fuel Tank Vent System (3 Sheets)
5 Refuel/Defuel System - Schematic
6 Refuel/Defuel Control Panel
7 Fuel Quantity Indicating System
8 Fuel Specific Weight
Page
3/4
5/6
8
13
16
17
20
22
12 - CONTENTS
Page 1
Feb 15/96
canadair
chauenQer
OPERATING MANUAL
PSP 606
SECTION 12
FUEL
SYSTEM CONFIGURATIONS
The fuel system has one of two fuel tank configurations: a basic three-tank
configuration consisting of left and right main tanks and an auxiliary tank; or
a five-tank configuration, of larger capacity, which has two additional
auxiliary tanks, designated the forward and rear auxiliary tanks,
respectively. The systems and operations described in the following paragraphs
apply to both of these configurations unless otherwise noted.
GENERAL (Figure 1)
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 point pressure refuel/
defuel adapter is provided and gravity refueling/defueling is carried out
through filler caps on the upper wing surface. Fuel and water drains are
located at various low points on the fuel system components to permit manual
drainage of the fuel tanks.
All the fuel and vent lines routed through the fuselage are surrounded by
airtight fireproof shrouds which have integral vent and drainage lines. 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 CONTROL panel has system caution lights as well as pump and valve
switch/lights and a fuel temperature gauge. 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 and, on aircraft that do not
incorporate Canadair Service Bulletin 600-0318, the No. 3 hydraulic system
fluid. Fuel in excess of the APU feed requirements is tapped from a return
line from the APU and used as the cooling medium.
SECTION 12
Page 1
Mar 01/85
canadair
ctiaiienc/er
OPERATING MANUAL
PSP 606
FUEL STORAGE (Figures 1 and 2)
Conforming to a wet wing design concept, the entire wing box structure is sealed
to form three tanks: the left and right main tanks and the auxiliary tank.
The left and right main tanks are formed by the wing box structure outboard of
wing station 45-00 (left and right) and the auxiliary tank occupies the space
enclosed by the wing box centre section. The capacities of the tanks, in
litres (US gallons) of useable fuel, are:
Pressure refueling
Litres (US gallons)
Gravity refueling (approx.)
Litres (US gallons)
Left main tank
Right main tank
Auxiliary tank
Totals
[1] Aircraft 1072.
[2] Aircraft with aft
[33 Aircraft with aft
[1]
CI]
[2]
[3]
CI]
[2]
[3]
2716
2733
2716
2733
2835
3193
3823
8267
8301
8625
9255
(717.5)
(722)
(717.5)
(722)
(749)
(843.5)
(1010)
(2184)
(2193)
(2278.5)
(2445)
fuselage tank.
and forward fuselage tank.
[1]
[1]
[2]
[3]
m
[23
[33
2519
2536
2519
2536
2835
3569
7873
7907
8607
(665.5)
(670)
(665.5)
(670)
(749)
(943)
(2080)
(2089)
(2274)
The system contains approximately 110 pounds
various system components.
of unusable fuel trapped in the
In the main tanks, the ribs of the wing box assembly act as baffles to limit
centre of gravity shifts by restricting the sudden displacement of a large
volume of fuel with changes in the aircraft's attitude.
Fuel in the main tanks flows inboard through lightening holes in the wing
ribs. Flapper check valves, installed on the ribs at WS85.50 and HS148.00
ensure that a portion of the fuel in the main tanks remains trapped between
these wing stations and the auxiliary tank at all times during flight.
A balance line, equipped with an electrically-operated shutoff valve, connects
the main tanks at their lowest points. The shutoff valve is controlled by the
X FLOW switch/light on the FUEL CONTROL panel and is opened to allow the main
tank fuel quantities to equalize by gravity.
SECTION 12
Page 2
Feb 12/88
cacnhaadnaeirri Qer
OPERATING MANUAL
PSP 606
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 primary ejector pumps and are maintained in the full-fuel state by
gravity feed lines and the scavenge ejector lines from the main tanks- The
electric fuel pumps of the standby fuel feed system are also located inside the
auxiliary tank, mounted beside the collector tanks- When in operation, each
electric pump draws fuel only from its corresponding collector tank.
Twenty-nine flush-mounted access panels, twenty-seven for the main tanks and
two for the auxiliary tank, 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 standby 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.
SECTION 12
Page 2A
Feb 12/88
canadsur
zzfoaiiencier
OPERATING MANUAL
PSP 606 TO FORWARD
AUXILIARY
TANK
TO APU FUEL
CONTROL SYSTEM
Fuel Feed System - Schematic
Figure 1
CENTRIFUGAL ELEMENT
GEAR PUMP ELEMENT
1 ENGINE DRIVEN PUMP •
2 ENGINE DRIVEN PUMP •
3 MOTIVE FLOW LINE
4 FILTER
5 FLOW SWITCH - LEFT SCAVENGE EJECTOR
6 LEFT SCAVENGE EJECTOR
7 LEFT VENT LINES PURGE CONNECTION
8 LEFT TRANSFER LINE FLOAT VALVE
9 LEFT TRANSFER LINE
10 LEFT SCAVENGE EJECTOR LINE
11 FLAPPER CHECK VALVES - WING STATION 85
12 GRAVITY FEED LINE - LEFT MAIN TANK TO LEFT COLLECTOR TANK
13 COLLECTOR TANK VENT LIMES
14 LEFT AND RIGHT PRIMARY FUEL EJECTORS
15 PRESSURE SWITCHES - LEFT AND RIGHT PRIMARY FUEL EJECTORS
16 LEFT AND RIGHT ELECTRIC BOOST PUMPS
17 PRESSURE SWITCHES - LEFT AND RIGHT ELECTRIC PUMPS
18 LEFT TRANSFER EJECTOR MOTIVE FLOW LINE
19 RIGHT TRANSFER EJECTOR MOTIVE FLOW LINE
20 MAIN TANKS BALANCE LINE
21 BALANCE LINE SHUTOFF VALVE
22 LEFT AND RIGHT TRANSFER EJECTORS
23 LEFT AND RIGHT ENGINE FUEL FEED LINES
24 LEFT FIREWALL FUEL SHUTOFF VALVE
25 APU NEGATIVE-G PROTECTION LINE SHUTOFF VALVE
26 ONE-WAY CHECK VALVE
27 GRAVITY FEED LINE - RIGHT MAIN TANK TO RIGHT COLLECTOR TANK
28 FLAPPER CHECK VALVES - WING STATION 85
29 GRAVITY FILLER CAP - AUXILIARY TANK
30 RIGHT SCAVENGE EJECTOR LINE
31 RIGHT TRANSFER LINE
32 RIGHT TRANSFER LINE FLOAT VALVE
33 RIGHT VENT LINES PURGE CONNECTION
34 RIGHT SCAVENGE EJECTOR
35 APU FUEL PUMP
36 MOTIVE FLOW LINE
37 FLOW SWITCH - RIGHT SCAVENGE EJECTOR
38 FILTER
39 HEAT EXCHANGER - NO.3 HYDRAULIC SYSTEM
40 APU FUEL FEED LINE
41 CROSSOVER LINE
42 APU FUEL SHUTOFF VALVE
43 HEAT EXCHANGER - APU GENERATOR OIL COOLER
44 FILTER
45 APU NEGATIVE-G PROTECTION FUEL FEED LINE
LEGEND
ENGINE AND APU FUEL FEED
EJECTOR MOTIVE FLOW LINES
33111111 SCAVENGE EJECTOR FLOW
TRANSFER EJECTOR FLOW
" " " APU FEED RETURN FLOW
EFFECTIVITY
Applicable only to aircraft with
additional auxiliary tanks installed.
Designated primary auxiliary tank
on aircraft with additional auxiliary
tanks installed (refer to Figure 2).
Aircraft that do not incorporate
Canadair Service Bulletin 600-0318.
Aircraft incorporating Canadair
Service Bulletin 600-0407.
0
SECTION 12
Page 3/4
Feb 12/88
OPERATING MANUAL
PSP 606
AUXILIARY TANK
SYSTEM VENT LINES
REAR AUXILIARY
TANK
Auxiliary Fuel Tanks
Figure 2
SECTION 12
Page 5/6
Feb 12/88
VENT
SHUTOFF
VALVE
FORWARD AUXILIARY
TANK
GRAVITY
TRANSFER
LINE
PRIMARY
AUXILIARY
TANK
EFFECnVTTY: Applicable only to aircraft with additional auxiliary tanks installed.
canadair
chauenQer
OPERATING MANUAL
PSP 606
On aircraft with additional auxiliary tanks, the auxiliary tank described above
is designated the primary auxiliary tank and is connected by gravity flow
transfer lines to the forward and rear auxiliary tanks. The additional
auxiliary tanks are located under the floor beams of the centre fuselage
immediately in front of and behind the fuselage pressure structure over the
wing. The tanks are of double-walled aluminum alloy construction and the space
between the outer and inner walls is drained and vented overboard. A general
arrangement view of the additional auxiliary tank installation and its
associated components is shown on Figure 2. The additional auxiliary tanks
increase the usable fuel capacity of the system by 1782 pounds (805 kg).
FUEL DISTRIBUTION (Figures 1 and 3)
Independent fuel supplies are provided for the engines and the APU. In normal
operation, the left and right engines are fed by the primary ejector pumps in
the left and right collector tanks respectively. Two electric pumps are
mounted beside the collector tanks and serve as backups to the primary
ejectors. The APU supply is drawn directly from the right main tank by an
electric pump.
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 primary pumps is provided by the high pressure
stage of a two-stage engine-driven pump (EDP). The motive flow reaches
pressures between 50 and 350 psi and is routed back to the fuel storage
area through the engine pylon via a one-way check valve. Given a motive
flow of 7.05 gal/min at 300 psi, each primary ejector produces an output
flow of 25.0 gal/min at 21 psi. The output from the other ejectors is
somewhat lower.
Compared with conventional electric fuel pumps, the ejectors require
minimal maintenance and greatly improve fuel system reliability.
B. Engine Feed
The primary eiector pumps provide a continuous fuel flow to the engine
driven pumps (EDP) 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 EDP. One-way check valves on the feed lines control the direction of
flow so that each ejector supplies only the engine associated with it.
SECTION 12
Page 7
Apr 4/83
canadair
chaiiencjer
OPERATING MANUAL
PSP 606
PUMP SWITCH/LIGHTS
Switch/lights control operation of electric fuel pumps in
conjunction with pressure switches at primary ejector outlets.
If a PUMP switch/light is in the pressed in position, and low
pressure condition is detected at outlet of associated primary
ejector, both electric fuel pumps come on to maintain required
fuel flow to affected engine.
Pressure switches at primary ejector outlets operate at 13 psi
increasing pressure and 10 psi decreasing pressure.
PUMP ON/INOP LIGHTS
Green ON light comes on if the associated electric pump is
operating.
Amber INOP light comes on if the associated pump switch is out
or if a pump failure occurs.
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