CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
REPLENISHING, FUEL TANK - SERVICING
1.
TASK 12−11−28−620−801
Use of Fuel Additives When Pressure Refueling
A.
Reference Information
REFERENCE
B.
DESIGNATION
TASK 10−10−01−867−801
Grounding of the Aircraft
TASK 12−00−07−861−801
Connect and Energize External AC Power
TASK 12−00−07−861−802
Remove External AC Power
TASK 28−00−00−910−801
Fuel System Safety Precautions
TASK 28−10−00−620−802
Biocide Treatment of the Fuel Tanks
Tools and Equipment
REFERENCE
Commercially Available
Pneumatic Injector
Commercially Available
Shop Air, Pressure Regulating, 90 ± 10 psi
Commercially Available
Test Panel, Pressure Regulating, 0−100 psi
NOTE:
C.
Refer to the Illustrated Tool and Equipment Manual to make sure that you use
the correct equipment configuration.
Consumable Materials
REFERENCE
D.
DESIGNATION
DESIGNATION
MANUFACTURERS’ REFERENCE
AND/OR SPECIFICATION
05−091
Inhibitor, Icing, Fuel System
MIL−I−27686
11−001
Fuel Additive, Biocide
MIL−S−53021A
Job Set−Up
(1) Obey all the fuel system safety precautions when you refuel or defuel the aircraft
(TASK 28−00−00−910−801).
(2) Make sure that the aircraft is on level ground.
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
WARNING:
MAKE SURE THAT THE AIRCRAFT AND THE FUEL TENDER ARE
GROUNDED AND THAT THE FUEL NOZZLE IS ELECTRICALLY
BONDED TO THE AIRCRAFT BEFORE YOU REFUEL/DEFUEL THE
AIRCRAFT. A STATIC ELECTRIC SPARK DURING THE
REFUELING/DEFUELING CAN CAUSE AN EXPLOSION OR FIRE.
(3) Make sure that the aircraft is grounded (TASK 10−10−01−867−801).
(4) Make sure that the fuel tender is grounded.
(5) Make sure that the fuel nozzle is electrically bonded to the aircraft.
(6) Make sure that there is sufficient distance between the chocks and the nose or
main landing gear to allow for tire deflection before you refuel the aircraft.
WARNING:
BEFORE YOU REFUEL THE AIRCRAFT, MAKE SURE THAT THERE
ARE NO PERSONS, MATERIALS OR EQUIPMENT BELOW THE
AIRCRAFT. THE WEIGHT OF THE FUEL WILL COMPRESS THE
LANDING GEAR AND LOWER THE AIRCRAFT. THIS CAN CAUSE
INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(7) Remove all persons, materials and equipment from below the aircraft before you
refuel the aircraft.
(8) If it is necessary to refuel the aircraft to an accurate level, connect the external ac
power (TASK 12−00−07−861−801).
NOTE:
The EICAS is necessary to get an accurate level indication of the fuel
quantity in each tank. If you use the EICAS during the refuel procedure, it
is necessary to have two persons for this procedure. One person must be
at the refuel/defuel panel and one person must be in the flight
compartment. Intercom communications must be available before you
start the refuel procedure.
(9) Open the access doors that follow:
NOTE:
To get access to the refuel/defuel panel, release the latch and move the
panel forward.
ACCESS
DESIGNATION
162BR
Door, Pressure Refuel/Defuel Adapter
162DR
Door, Refuel/Defuel Control Panel
(10) Make sure that the switches on the refuel/defuel control panel are in the correct
configuration as follows:
(a) POWER switch is set to OFF.
(b) SOV L MAIN switch is set to CLOSED.
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
(c)
SOV TAIL switch is set to CLOSED.
(d) SOV AUX switch is set to CLOSED.
(e) SOV R MAIN switch is set to CLOSED.
E.
Procedure
Refer to Figure 301 and Figure 302.
WARNING:
OBEY THE PRECAUTIONS THAT FOLLOW WHEN YOU USE A FUEL
ADDITIVE. FUEL ADDITIVES ARE DANGEROUS BECAUSE THEY CAN
BE FLAMMABLE, POISONOUS AND CAN CAUSE INJURY.
-
USE SAFETY GOGGLES.
-
PUT ON PROTECTIVE CLOTHING.
-
DO NOT LET BIOCIDE FUEL ADDITIVE TOUCH YOUR SKIN,
EYES, AND MOUTH.
-
DO THE WORK IN AN AREA THAT HAS A GOOD FLOW OF CLEAN
AIR.
-
DO THE WORK IN AN AREA THAT HAS NO SPARKS, FLAME, OR
HOT SURFACES.
-
OBEY THE MANUFACTURER'S INSTRUCTIONS.
-
GET MEDICAL AID IF YOU GET THE FUEL ADDITIVE IN YOUR
EYES OR MOUTH, OR IF IRRITATION OCCURS.
CAUTION:
DO NOT PUT A CONCENTRATION OF BIOCIDE IN THE FUEL TANKS.
USE THE METERED INJECTION METHOD TO MIX THE BIOCIDE
DIRECTLY WITH A CONTINUOUS FLOW OF FUEL. IF YOU PUT THE
BIOCIDE DIRECTLY IN THE FUEL TANK, SALT DEPOSITS CAN
OCCUR AND CAUSE DAMAGE.
CAUTION:
DO NOT PERMIT THE FUEL ADDITIVE TO TOUCH THE INTERNAL
SURFACES OF THE FUEL TANK OR EXTERNAL PAINTED
SURFACES. HIGH CONCENTRATIONS OF THE FUEL ADDITIVE CAN
CAUSE DAMAGE.
(1) To add biocide during the pressure refuel operation, do the steps that follow:
NOTE:
If it is necessary to sterilize the fuel system, use the shock treatment
procedure (TASK 28−10−00−620−802).
(a) Remove the cap from the refuel/defuel adapter.
(b) Connect the fuel nozzle and the pneumatic injector to the refuel/defuel
adapter.
(c)
Connect the test panel and shop air to the pneumatic injector.
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
(d) If necessary, add the fungicide additive to the fuel in the concentration that
follows during the pressure refueling procedure:
NOTE:
Add the fungicide additive at a mixture concentration of 135 parts per
million (ppm) for Biobor JF or 50 ppm for Kathon FP1.5 by weight.
FUEL [1]
Pounds Gallons Gallons
(U.S.)
(Imp.)
BIOBOR JF ADDITIVE (135 ppm)
Liters
Pounds Gallons Ounces Ounces Milliliters
(U.S)
(U.S.) (Imp.)
(mL)
670
100
83.27
378.54
0.09
0.01
1.28
1.33
37.85
1 340
200
166.
53
757.08
0.18
0.03
3.84
4.00
113.
56
2 010
300
249.
80
1 135.
62
0.27
0.04
5.12
5.33
151.
42
2 680
400
333.
07
1 514.
17
0.36
0.05
6.40
6.66
189.
27
3 350
500
416.
34
1 892.
71
0.45
0.07
8.96
9.33
264.
98
6 700
1 000
832.
67
3 785.
41
0.90
0.14
17.92
18.65
529.
96
1 665.
35
7 570.
82
1.81
0.27
34.56
35.97
1 022.
06
13 400 2 000
NOTE:
[1] Do not add to JP4 grade fuel if prepared to MIL−T−5624H.
This fuel contains a 0.1 to 0.15% (by volume) concentration of
the biocide.
FUEL [1]
Pounds Gallons Gallons
(U.S.)
(Imp.)
KATHON FP1.5 ADDITIVE (50 ppm)
Liters
Pounds Gallons Ounces Ounces Milliliters
(U.S.) (U.S.) (Imp.)
(mL)
670
100
83.27
378.54
0.03
0.005
0.64
0.67
18.93
1 340
200
166.
53
757.08
0.07
0.01
1.28
1.33
37.85
2 010
300
249.
80
1 135.
62
0.10
0.015
1.92
2.00
56.78
2 680
400
333.
07
1 514.
17
0.13
0.02
2.56
2.66
75.71
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
FUEL [1]
KATHON FP1.5 ADDITIVE (50 ppm)
Pounds Gallons Gallons
(U.S.)
(Imp.)
Liters
Pounds Gallons Ounces Ounces Milliliters
(U.S.) (U.S.) (Imp.)
(mL)
3 350
500
416.
34
1 892.
71
0.17
0.025
3.20
3.33
94.64
6 700
1 000
832.
67
3 785.
41
0.34
0.05
6.40
6.66
189.
27
1 665.
35
7 570.
82
0.67
0.10
12.80
13.32
378.
54
13 400 2 000
NOTE:
[1] Do not add to JP4 grade fuel if prepared to MIL−T−5624H.
This fuel contains a 0.1 to 0.15% (by volume) concentration of
the biocide.
(e) If necessary, add the anti−icing additive to the fuel in the concentration that
follows during pressure refueling:
NOTE:
Add the anti−icing additive at a mixture concentration of 50 to 150
parts per million (ppm) by weight.
FUEL [1]
ANTI−ICING ADDITIVE [2]
Pounds
Gallons
(U.S.)
Gallons
(Imp.)
670
100
83.27
378.54
1 340
200
166.53
757.08
2 010
300
249.80
1 135.62
2 680
400
333.07
1 514.17
3 350
500
416.34
1 892.71
6 700
1 000
832.67
3 785.41
13 400
2 000
1 665.
35
7 570.82
NOTE:
Liters
Pounds Gallons Gallons
(U.S.)
(Imp.)
Liters
9.0
1.0
0.83
3.78
18.0
2.0
1.67
7.56
[1] Do not add to JP4, JP5, and JP8 grade fuels. These fuels
contain the additive.
[2] The Gate−Pack Model 2000−B Injector automatically mixes
the additive at a ratio of 1 gallon (3.78 L) per 1 000 gallons
(3 785.40 L) of fuel.
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
(f)
On the refuel/defuel control panel, do the steps that follow:
1
Set the POWER switch to FUEL.
2
Make sure that the indicator lamp comes on.
(g) Set the fuel pressure on the fuel tender to no more than 50 psi (344.75 kPa).
WARNING:
DO NOT HAVE MORE THAN 2 500 POUNDS (1 134 KG) OF
IMBALANCE BETWEEN THE MAIN TANKS DURING THE REFUEL
PROCEDURES (PRESSURE OR GRAVITY). THE AIRCRAFT CAN
MOVE AND CAUSE INJURIES TO PERSONS AND DAMAGE TO
THE EQUIPMENT.
CAUTION:
IF A FUEL IMBALANCE CAUTION INDICATION IS SHOWN ON
EICAS, STOP THE REFUEL/DEFUEL OPERATION IMMEDIATELY.
THE FUEL IMBALANCE INDICATION IS SHOWN WHEN THE
FUEL QUANTITY IS MORE THAN 800 LB (362.88 KG). IF YOU DO
NOT DO THIS YOU CAN CAUSE DAMAGE TO THE AIRCRAFT.
(h) Completely fill the main, auxiliary and tail tanks, as follows:
NOTE:
1
2
It will take approximately 24 minutes to fill an empty aircraft to full
fuel capacity.
On the refuel/defuel control panel, set the SOV switches in the correct
sequence as follows:
a
SOV L MAIN switch is set to OPEN.
b
SOV R MAIN switch is set to OPEN.
c
SOV AUX switch is set to OPEN.
d
SOV TAIL switch is set to OPEN.
Make sure of the conditions that follow:
a
OPEN indicator lights for all the SOVs come on.
b
CLOSED indicator lights for all the SOVs go off.
CAUTION:
3
STOP THE REFUEL OPERATION IMMEDIATELY IF THE
TEST CONDITIONS THAT FOLLOW DO NOT OCCUR. YOU
CAN CAUSE DAMAGE TO THE EQUIPMENT.
Press and hold the SHUT OFF TEST switch until the conditions that
follow occur:
a
HIGH LEVEL SENSORS indicator lights for all the SOVs come on.
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
b
CLOSED indicator lights for all the SOVs come on.
c
OPEN indicator lights for all the SOVs go off.
CAUTION:
4
5
Release the SHUT OFF TEST switch and make sure that the conditions
that follow occur:
a
HIGH LEVEL SENSORS indicator lights for all the SOVs go off.
b
CLOSED indicator lights for all the SOVs go off.
c
OPEN indicator lights for all the SOVs come on.
Refuel all the tanks to capacity.
NOTE:
6
(i)
STOP THE REFUEL OPERATION IMMEDIATELY IF THE
TEST CONDITIONS THAT FOLLOW DO NOT OCCUR. YOU
CAN CAUSE DAMAGE TO THE EQUIPMENT.
When the tanks are full, the applicable SOV closes
automatically, and the CLOSED indicator light comes on.
If you monitor the fuel quantity with the refuel/defuel panel, the tanks are
filled when the conditions that follow occur:
a
HIGH LEVEL SENSORS indicator lights for all the SOVs come on.
b
CLOSED indicator lights for all the SOVs come on.
c
OPEN indicator lights for all the SOVs go off.
7
If you monitor the fuel quantity with EICAS, get the primary page.
Examine the fuel quantity indications for the applicable tank (left wing,
right wing, auxiliary or tail tank). Monitor the applicable digital readout for
the applicable tank during the pressure refuel operation.
8
When each of the tanks are filled to the necessary level, set the
applicable SOV switch to CLOSED. Make sure of the conditions that
follow as each of the fuel tanks are filled to capacity:
a
HIGH LEVEL SENSORS indicator light for that SOV stays on.
b
CLOSED indicator light for that SOV comes on.
c
OPEN indicator light for that SOV goes off.
When the necessary quantity of fuel is added, do the steps that follow:
1
On the refuel/defuel control panel, set the POWER switch to OFF.
2
Make sure that the indicator lamp goes off.
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
(j)
Disconnect the fuel nozzle and the pneumatic injector from the adapter.
(k)
Install the cap on the refuel/defuel adapter.
(l)
Disconnect the fuel nozzle bonding wire.
(m) Disconnect the fuel tender ground.
(2) If necessary, disconnect the external ac power (TASK 12−00−07−861−802).
F.
Close Out
(1) Remove all tools, equipment, and unwanted materials from the work area.
(2) Latch the refuel/defuel control panel in the closed position.
(3) Close the access doors that follow:
NOTE:
To close the refuel/defuel panel, move the panel rearward and engage
the latch mechanism.
ACCESS
DESIGNATION
162BR
Door, Pressure Refuel/Defuel Adapter
162DR
Door, Refuel/Defuel Control Panel
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
2.
TASK 12−11−28−620−802
Use of Fuel Additives When Gravity Refueling
A.
Reference Information
REFERENCE
B.
DESIGNATION
TASK 10−10−01−867−801
Grounding of the Aircraft
TASK 12−00−07−861−801
Connect and Energize External AC Power
TASK 12−00−07−861−802
Remove External AC Power
TASK 28−00−00−910−801
Fuel System Safety Precautions
TASK 28−10−00−620−802
Biocide Treatment of the Fuel Tanks
Tools and Equipment
REFERENCE
Commercially Available
Pneumatic Injector
Commercially Available
Shop Air, Pressure Regulating, 90 ± 10 psi
Commercially Available
Test Panel, Pressure Regulating, 0−100 psi
NOTE:
C.
Refer to the Illustrated Tool and Equipment Manual to make sure that you use
the correct equipment configuration.
Consumable Materials
REFERENCE
D.
DESIGNATION
DESIGNATION
MANUFACTURERS’ REFERENCE
AND/OR SPECIFICATION
05−091
Inhibitor, Icing, Fuel System
MIL−I−27686
11−001
Fuel Additive, Biocide
MIL−S−53021A
Job Set−Up
(1) Obey all the fuel system safety precautions when you refuel or defuel the aircraft
(TASK 28−00−00−910−801).
(2) Make sure that the aircraft is on level ground.
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
(3) Make sure that the aircraft is in the configuration that follows:
WARNING:
MAKE SURE THAT THE AIRCRAFT AND THE FUEL TENDER ARE
GROUNDED AND THAT THE FUEL NOZZLE IS ELECTRICALLY
BONDED TO THE AIRCRAFT BEFORE YOU REFUEL/DEFUEL
THE AIRCRAFT. A STATIC ELECTRIC SPARK DURING THE
REFUELING/DEFUELING CAN CAUSE AN EXPLOSION OR FIRE.
(a) Make sure that the aircraft is grounded (TASK 10−10−01−867−801).
(b) Make sure that the fuel tender is grounded.
(c)
Make sure that the fuel nozzle is electrically bonded to the aircraft.
(d) Make sure that there is sufficient distance between the chocks and the nose or
main landing gear to allow for tire deflection before you refuel the aircraft.
WARNING:
BEFORE YOU REFUEL THE AIRCRAFT, MAKE SURE THAT
THERE ARE NO PERSONS, MATERIALS OR EQUIPMENT
BELOW THE AIRCRAFT. THE WEIGHT OF THE FUEL WILL
COMPRESS THE LANDING GEAR AND LOWER THE AIRCRAFT.
THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO
EQUIPMENT.
(e) Remove all persons, materials and equipment from below the aircraft before
you refuel the aircraft.
EFFECTIVITY: ALL
12−11−28
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
E.
Procedure
Refer to Figure 303.
WARNING:
OBEY THE PRECAUTIONS THAT FOLLOW WHEN YOU USE A FUEL
ADDITIVE. FUEL ADDITIVES ARE DANGEROUS BECAUSE THEY CAN
BE FLAMMABLE, POISONOUS AND CAN CAUSE INJURY.
-
USE SAFETY GOGGLES.
-
PUT ON PROTECTIVE CLOTHING.
-
DO NOT LET BIOCIDE FUEL ADDITIVE TOUCH YOUR SKIN,
EYES, AND MOUTH.
-
DO THE WORK IN AN AREA THAT HAS A GOOD FLOW OF CLEAN
AIR.
-
DO THE WORK IN AN AREA THAT HAS NO SPARKS, FLAME, OR
HOT SURFACES.
-
OBEY THE MANUFACTURER'S INSTRUCTIONS.
-
GET MEDICAL AID IF YOU GET THE FUEL ADDITIVE IN YOUR
EYES OR MOUTH, OR IF IRRITATION OCCURS.
CAUTION:
DO NOT PUT A CONCENTRATION OF BIOCIDE IN THE FUEL TANKS.
USE THE METERED INJECTION METHOD TO MIX THE BIOCIDE
DIRECTLY WITH A CONTINUOUS FLOW OF FUEL. IF YOU PUT THE
BIOCIDE DIRECTLY IN THE FUEL TANK, SALT DEPOSITS CAN
OCCUR AND CAUSE DAMAGE.
CAUTION:
DO NOT PERMIT THE FUEL ADDITIVE TO TOUCH THE INTERNAL
SURFACES OF THE FUEL TANK OR EXTERNAL PAINTED
SURFACES. HIGH CONCENTRATIONS OF THE FUEL ADDITIVE CAN
CAUSE DAMAGE.
(1) To add biocide during the gravity refuel operation, do the steps that follow:
NOTE:
If it is necessary to sterilize the fuel system, use the shock treatment
procedure (TASK 28−10−00−620−802).
(a) If necessary, connect the external ac power (TASK 12−00−07−861−801).
NOTE:
Because of the location of the access caps, the main tanks cannot
be filled to capacity during the gravity refuel operation. If it is
necessary to monitor the fuel quantity, the EICAS must be used.
If you use the EICAS during the refuel procedure, it is necessary to
have two persons for this procedure. One person must be at the
refuel/defuel panel and one person must be in the flight
compartment. Intercom communications must be available before
you start the refuel procedure.
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
(b) On the EICAS primary page, examine the fuel quantity indications for the
applicable tank. Monitor the digital readout for the applicable tank during the
gravity refuel operation.
NOTE:
(c)
If necessary, do the steps that follow until all the fuel tanks are filled
to capacity.
For the left wing fuel tank, open the access cap that follows:
ACCESS
550AT
DESIGNATION
Access Cap, Gravity Fuel Fill
(d) For the right wing fuel tank, open the access cap that follows:
ACCESS
650AT
DESIGNATION
Access Cap, Gravity Fuel Fill
(e) For the center fuel tank, open the access cover and the access cap that follow:
ACCESS
640AT
Access Cover
642AT
Access Cap, Gravity Fuel Fill
CAUTION:
(f)
DESIGNATION
MAKE SURE THAT THE FUEL NOZZLE DOES NOT TOUCH THE
BOTTOM OF THE FUEL TANK DURING THE GRAVITY REFUEL
PROCEDURE. THE FUEL NOZZLE CAN BREAK THE
PROTECTIVE COATING AND THIS WILL CAUSE CORROSION IN
THE FUEL TANK.
Connect the fuel nozzle bonding wire to the grounding plug in the leading edge
below the applicable access cap.
(g) Connect the fueling hose and the pneumatic injector to the filler opening of the
applicable access cap.
(h) Connect the test panel and shop air to the pneumatic injector.
(i)
Carefully put the fuel nozzle into the applicable fuel tank through the filler
opening.
(j)
If necessary, install the pneumatic injector and add the fungicide additive to the
fuel in the concentration that follows during gravity refueling:
NOTE:
Add the fungicide additive at a mixture concentration of 135 parts per
million (ppm) for Biobor JF or 50 ppm for Kathon FP1.5 by weight.
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
FUEL [1]
Pounds Gallons Gallons
(U.S)
(Imp.)
BIOBOR JF ADDITIVE (135 ppm)
Liters
Pounds Gallons Ounces Ounces Milliliters
(U.S)
(U.S.) (Imp.)
(mL)
670
100
83.27
378.54
0.09
0.01
1.28
1.33
37.85
1 340
200
166.
53
757.08
0.18
0.03
3.84
4.00
1113.
56
2 010
300
249.
80
1 135.
62
0.27
0.04
5.12
5.33
151.
42
2 680
400
333.
07
1 514.
17
0.36
0.05
6.40
6.66
189.
27
3 350
500
416.
34
1 892.
71
0.45
0.07
8.96
9.33
264.
98
6 700
1 000
832.
67
3 785.
41
0.9
0.14
17.92
18.65
529.
96
1 665.
35
7 570.
82
1.81
0.27
34.56
35.97
1 022.
06
13 400 2 000
NOTE:
[1] Do not add to JP4 grade fuel if prepared to MIL−T−5624H.
This fuel contains a 0.1 to 0.15% (by volume) concentration of
the biocide.
FUEL [1]
Pounds Gallons Gallons
(U.S.)
(Imp.)
KATHON FP1.5 ADDITIVE (50 ppm)
Liters
Pounds Gallons Ounces Ounces Milliliters
(U.S.) (U.S.) (Imp.)
(mL)
670
100
83.27
378.54
0.03
0.005
0.64
0.67
18.93
1 340
200
166.
53
757.08
0.07
0.01
1.28
1.33
37.85
2 010
300
249.
80
1 135.
62
0.1
0.015
1.92
2.00
56.78
2 680
400
333.
07
1 514.
17
0.13
0.02
2.56
2.66
75.71
3 350
500
416.
34
1 892.
71
0.17
0.025
3.20
3.33
94.64
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
FUEL [1]
KATHON FP1.5 ADDITIVE (50 ppm)
Pounds Gallons Gallons
(U.S.)
(Imp.)
6 700
1 000
13 400 2 000
NOTE:
(k)
Liters
Pounds Gallons Ounces Ounces Milliliters
(U.S.) (U.S.) (Imp.)
(mL)
832.
67
3 785.
41
0.34
0.05
6.40
6.66
189.
27
1 665.
35
7 570.
82
0.67
0.1
12.80
13.32
378.
54
[1] Do not add to JP4 grade fuel if prepared to MIL−T−5624H.
This fuel contains a 0.1 to 0.15% (by volume) concentration of
the biocide.
If necessary, install the pneumatic injector and add the anti−icing additive to
the fuel in the concentration that follows during gravity refueling:
NOTE:
Add the anti−icing additive at a mixture concentration of 50 to 150
parts per million (ppm) by weight.
FUEL [1]
ANTI−ICING ADDITIVE [2]
Pounds
Gallons
(U.S.)
Gallons
(Imp.)
670
100
83.26
378.5
1 340
200
166.52
757
2 010
300
249.78
1 135.5
2 680
400
333.03
1 514
3 350
500
416.29
1 892.5
6 700
1 000
832.58
3 785
13 400
2 000
1 665.
17
7 570
NOTE:
Liters
Pounds Gallons Gallons
(U.S.)
(Imp.)
Liters
9.0
1.0
0.83
3.78
18.0
2.0
1.67
7.56
[1] Do not add to JP4, JP5, and JP8 grade fuels. These fuels
contain the additive.
[2] The Gate−Pack Model 2000−B Injector automatically mixes
the additive at a ratio of 1 gallon (3.78 L) per 1 000 gallons
(3 785.40 L) of fuel.
(l)
Monitor the refuel operation through the filler opening, or use the EICAS to
give a more accurate quantity indication.
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WARNING:
DO NOT HAVE MORE THAN 2 500 POUNDS (1 134 KG) OF
IMBALANCE BETWEEN THE MAIN TANKS DURING THE REFUEL
PROCEDURES (PRESSURE OR GRAVITY). THE AIRCRAFT CAN
MOVE AND CAUSE INJURIES TO PERSONS AND DAMAGE TO
THE EQUIPMENT.
(m) Fill the applicable fuel tank to full capacity.
(n) When the applicable fuel tank is filled to capacity, carefully remove the fuel
nozzle and the pneumatic injector from that fuel tank.
(o) For the left wing fuel tank, close the access cap that follows:
ACCESS
550AT
DESIGNATION
Access Cap, Gravity Fuel Fill
(p) For the right wing fuel tank, close the access cap that follows:
ACCESS
650AT
DESIGNATION
Access Cap, Gravity Fuel Fill
(q) For the center fuel tank, close the access cover and the access cap that follow:
ACCESS
(r)
DESIGNATION
640AT
Access Cover
642AT
Access Cap, Gravity Fuel Fill
Disconnect the fuel nozzle bonding wire from the grounding plug on the wing
leading edge.
(2) Remove the external ac power (TASK 12−00−07−861−802).
F.
Close Out
(1) Remove all tools, equipment, and unwanted materials from the work area.
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3.
TASK 12−11−28−650−801
Pressure Refueling
A.
Reference Information
REFERENCE
B.
DESIGNATION
TASK 10−10−01−867−801
Grounding of the Aircraft
TASK 12−00−07−861−801
Connect and Energize External AC Power
TASK 12−00−07−861−802
Remove External AC Power
TASK 28−00−00−910−801
Fuel System Safety Precautions
TASK 28−10−00−210−801
General Visual Inspection of the Fuel Tank Exterior
TASK 49−10−00−866−801
Starting the Auxiliary Power Unit (APU)
TASK 49−10−00−866−802
Auxiliary Power Unit (APU) Shutdown (Normal)
Job Set−Up
(1) Obey all the fuel system safety precautions when you refuel or defuel the aircraft
(TASK 28−00−00−910−801).
(2) Make sure that the aircraft is on level ground.
WARNING:
MAKE SURE THAT THE AIRCRAFT AND THE FUEL TENDER ARE
GROUNDED AND THAT THE FUEL NOZZLE IS ELECTRICALLY
BONDED TO THE AIRCRAFT BEFORE YOU REFUEL/DEFUEL THE
AIRCRAFT. A STATIC ELECTRIC SPARK DURING THE
REFUELING/DEFUELING CAN CAUSE AN EXPLOSION OR FIRE.
(3) Make sure that the aircraft is grounded (TASK 10−10−01−867−801).
(4) Make sure that the fuel tender is grounded.
(5) Make sure that the fuel nozzle is electrically bonded to the aircraft.
(6) Make sure that there is sufficient distance between the chocks and the nose or
main landing gear to allow for tire deflection before you refuel the aircraft.
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WARNING:
REMOVE ALL PERSONS, MATERIALS AND EQUIPMENT FROM
BELOW THE AIRCRAFT BEFORE YOU DO THE REFUELLING
PROCEDURE. THE WEIGHT OF THE FUEL ADDED WILL COMPRESS
THE LANDING GEAR AND LOWER THE AIRCRAFT. THIS CAN CAUSE
INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT.
(7) Remove all persons, materials and equipment from below the aircraft before you
refuel the aircraft.
(8) If it is necessary to refuel the aircraft to an accurate level, connect and energize the
external ac power (TASK 12−00−07−861−801).
or
Proceed as follows:
(a) Start the APU (TASK 49−10−00−866−801).
(b) On the ELECTRICAL POWER control panel, set the APU GEN toggle switch
to the ON position.
NOTE:
The MFD EICAS display is necessary to get an accurate level indication
of the fuel quantity in each tank.
If you use the MFD EICAS display during the refuel procedure, it is
necessary to have two persons for this procedure. One person must be at
the refuel/defuel panel and one person must be in the flight compartment.
Intercom communications must be available before you start the refuel
procedure.
(9) Open the access doors that follow:
NOTE:
To get access to the refuel/defuel panel, release the latch and move the
panel forward.
ACCESS
DESIGNATION
162BR
Door, Pressure Refuel/Defuel Adapter
162DR
Door, Refuel/Defuel Control Panel
(10) Make sure that the switches on the refuel/defuel control panel are in the correct
configuration as follows:
(a) POWER switch is set to OFF.
(b) SOV L MAIN switch is set to CLOSED.
(c)
SOV TAIL switch is set to CLOSED.
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(d) SOV AUX switch is set to CLOSED.
(e) SOV R MAIN switch is set to CLOSED.
(11) Before you fill the fuel tanks, pull and release the T−handles on the relief valve for
the main and auxiliary fuel tanks. Make sure the relief valve opens and closes
freely.
(12) Remove the cap from the refuel/defuel adapter.
(13) Connect the fuel nozzle to the adapter.
(14) On the refuel/defuel control panel, set the POWER switch to FUEL.
(15) Make sure that the indicator lamp comes on.
(16) Set the fuel pressure on the fuel tender to no more than 50±5 psi.
(344.75±34.45 kPa).
NOTE:
C.
The maximum refueling rate for simultaneous refueling of the three tanks,
is 250 US gal/min (946 L/min) at 55 psi (379.31 kPa) and 150 US gal/min
(568 L/min) at 55 psi (379.31 kPa) for independent refueling of the main
tanks.
Procedure
Refer to Figure 301 and Figure 302.
(1) To completely fill the main, auxiliary and tail tanks, do the steps that follow:
NOTE:
It will take approximately 24 minutes to fill an empty aircraft to full fuel
capacity.
(a) On the refuel/defuel control panel, set the SOV switches in the correct
sequence as follows:
NOTE:
Make sure that the pressure is applied at the fuel nozzle before you
select a SOV toggle switch to the OPEN position.
1
SOV L MAIN switch is set to OPEN.
2
SOV R MAIN switch is set to OPEN.
3
SOV AUX switch is set to OPEN.
4
SOV TAIL switch is set to OPEN.
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(b) Make sure of the conditions that follow:
1
OPEN indicator lights for all the SOVs come on.
2
CLOSED indicator lights for all the SOVs go off.
CAUTION:
(c)
STOP THE REFUEL OPERATION IMMEDIATELY IF THE TEST
CONDITIONS THAT FOLLOW DO NOT OCCUR. YOU CAN
CAUSE DAMAGE TO THE EQUIPMENT.
Press and hold the SHUT OFF TEST switch until the conditions that follow
occur:
1
HIGH LEVEL SENSORS indicator lights for all the SOVs come on.
2
CLOSED indicator lights for all the SOVs come on.
3
OPEN indicator lights for all the SOVs go off.
CAUTION:
STOP THE REFUEL OPERATION IMMEDIATELY IF THE TEST
CONDITIONS THAT FOLLOW DO NOT OCCUR. YOU CAN
CAUSE DAMAGE TO THE EQUIPMENT.
(d) Release the SHUT OFF TEST switch and make sure that the conditions that
follow occur:
1
HIGH LEVEL SENSORS indicator lights for all the SOVs go off.
2
CLOSED indicator lights for all the SOVs go off.
3
OPEN indicator lights for all the SOVs come on.
CAUTION:
STOP THE REFUEL OPERATION IMMEDIATELY IF THE TAIL
TANK PRESSURE-RELIEF VALVE POPPET EXTENDS FROM
THE SKIN. IF YOU DO NOT STOP THE REFUEL OPERATION
IMMEDIATELY WHEN THE POPPET EXTENDS, YOU CAN CAUSE
DAMAGE TO THE EQUIPMENT.
CAUTION:
MAKE SURE A SECOND PERSON MONITORS THE TAIL TANK
PRESSURE-RELIEF VALVE POPPET LOCATED ON THE LEFT
SIDE OF THE VERTICAL STABILIZER.
CAUTION:
MAKE SURE THAT THE AIR IS COMING OUT OF THE TAIL TANK
VENT LOCATED ON THE LEFT HAND SIDE OF THE AFT
FUSELAGE. THIS WILL CONFIRM THAT THERE IS NO
BLOCKAGE IN THE TAIL TANK VENT SYSTEM.
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CAUTION:
IF A FUEL IMBALANCE CAUTION INDICATION IS SHOWN ON
THE MFD EICAS DISPLAY, STOP THE REFUEL OPERATION
IMMEDIATELY. IF YOU DO NOT DO THIS, YOU CAN CAUSE
DAMAGE TO THE AIRCRAFT.
(e) Refuel all the tanks to capacity.
NOTE:
(f)
When the tanks are full, the applicable SOV closes automatically,
and the CLOSED indicator light comes on.
Make sure that air and/or a smell of fuel comes out of the NACA scoops
located on the left and right wing between the inboard and outboard flaps, at
the trailing edge lower surface.
NOTE:
Make sure that the pressure releases through the NACA scoops.
(g) If you use only the refuel/defuel panel to monitor the fuel quantity, the tanks
are filled when the conditions that follow occur:
1
HIGH LEVEL SENSORS indicator lights for all the SOVs come on.
2
CLOSED indicator lights for all the SOVs come on.
3
OPEN indicator lights for all the SOVs go off.
(h) If you monitor the fuel quantity on the MFD EICAS display, examine the fuel
quantity indications for the applicable tank (left wing, right wing, auxiliary or tail
tank). Monitor the applicable digital readout for the applicable tank during the
pressure refuel operation.
(i)
(j)
When each of the tanks are filled, set the applicable SOV switch to CLOSED.
Make sure of the conditions that follow as each of the fuel tanks are filled to
capacity:
1
HIGH LEVEL SENSORS indicator light for that SOV stays on.
2
CLOSED indicator light for that SOV comes on.
3
OPEN indicator light for that SOV goes off.
When the fuel operation is complete, do the steps that follow:
1
On the refuel/defuel control panel, set the POWER switch to OFF.
2
Make sure that the indicator lamp goes off.
3
Disconnect the fuel nozzle from the adapter.
4
Install the cap on the refuel/defuel adapter.
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5
Disconnect the fuel nozzle bonding wire.
6
Disconnect the fuel tender ground.
WARNING:
DO NOT HAVE MORE THAN 2 500 POUNDS (1 134 KG) OF
IMBALANCE BETWEEN THE MAIN TANKS DURING THE REFUEL
PROCEDURES (PRESSURE OR GRAVITY). THE AIRCRAFT CAN
MOVE AND CAUSE INJURIES TO PERSONS AND DAMAGE TO THE
EQUIPMENT.
(2) To partially fill one (or more) of the fuel tanks, do the steps that follow:
(a) To add fuel to the left and right main (wing) tanks, do the steps that follow:
NOTE:
1
Always fill the two main (wing) tanks at the same time. This is
necessary to prevent a possible out−of−balance condition.
On the refuel/defuel control panel, set the L MAIN and R MAIN SOV
switches to OPEN, and make sure of the conditions that follow:
a
OPEN indicator lights for the L MAIN and R MAIN SOVs come on.
b
CLOSED indicator lights for the L MAIN and R MAIN SOVs go off.
CAUTION:
2
Press and hold the SHUT OFF TEST switch until the conditions that
follow occur:
a
HIGH LEVEL SENSORS indicator lights for the L MAIN and R MAIN
SOVs come on.
b
CLOSED indicator lights for the L MAIN and R MAIN SOVs come on.
c
OPEN indicator lights for the L MAIN and R MAIN SOVs go off.
CAUTION:
3
STOP THE REFUEL OPERATION IMMEDIATELY IF THE
TEST CONDITIONS THAT FOLLOW DO NOT OCCUR. YOU
CAN CAUSE DAMAGE TO THE EQUIPMENT.
STOP THE REFUEL OPERATION IMMEDIATELY IF THE
TEST CONDITIONS THAT FOLLOW DO NOT OCCUR. YOU
CAN CAUSE DAMAGE TO THE EQUIPMENT.
Release the SHUT OFF TEST switch and make sure that the conditions
that follow occur:
a
HIGH LEVEL SENSORS indicator lights for the L MAIN and R MAIN
SOVs go off.
b
CLOSED indicator lights for the L MAIN and R MAIN SOVs go off.
c
OPEN indicator lights for the L MAIN and R MAIN SOVs come on.
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CAUTION:
4
Refuel the main tanks to the necessary level.
NOTE:
5
When the tanks are full, the applicable SOV closes
automatically, and the CLOSED indicator light comes on.
Make sure that air and/or a smell of fuel comes out of the NACA scoops
located on the left and right wing between the inboard and outboard flaps,
at the trailing edge lower surface.
NOTE:
6
IF A FUEL IMBALANCE CAUTION INDICATION IS SHOWN
ON THE MFD EICAS DISPLAY, STOP THE REFUEL
OPERATION IMMEDIATELY. IF YOU DO NOT DO THIS, YOU
CAN CAUSE DAMAGE TO THE AIRCRAFT.
Make sure that the pressure releases through the NACA
scoops.
If you used only the refuel/defuel panel to monitor the fuel quantity, the
tanks are filled when the conditions that follow occur:
a
HIGH LEVEL SENSORS indicator lights for the L MAIN and R MAIN
SOVs come on.
b
CLOSED indicator lights for the L MAIN and R MAIN SOVs come on.
c
OPEN indicator lights for the L MAIN and R MAIN SOVs go off.
7
If you monitor the fuel quantity on the MFD EICAS display, examine the
fuel quantity indications for the left (main) wing and right (main) wing
tanks. Monitor the digital readout for the applicable tank during the
pressure refuel operation.
8
When the main tanks are filled to the necessary level, set the L MAIN and
R MAIN SOV switches to CLOSED. Make sure of the conditions that
follow:
a
If the tank is at full capacity, make sure that the HIGH LEVEL
SENSORS indicator lights for the L MAIN and R MAIN SOVs stay
on.
b
CLOSED indicator lights for the L MAIN and R MAIN SOVs come on.
c
OPEN indicator lights for the L MAIN and R MAIN SOVs go off.
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
WARNING:
FILL THE MAIN TANKS BEFORE YOU FUEL THE AUXILIARY
TANK AND THE TAIL TANK. FAILURE TO DO SO CAN CAUSE
THE AIRCRAFT TO MOVE. THIS CAN CAUSE INJURY TO
PERSONS AND DAMAGE TO EQUIPMENT.
(b) To add fuel to the tail and auxiliary tanks, do the steps that follow:
NOTE:
Fuel is added to the auxiliary tank only after the two main (wing)
tanks are filled to capacity.
The tail and auxiliary tanks are refuelled at the same time and in
equal proportion to each other. Selection of only one of the two tanks
is prevented until the other tank is also selected, unless the
OVERRIDE switch is selected.
(c)
1
If it is necessary to fill only the auxiliary tank, press and hold the
OVERRIDE switch on the refuel/defuel control panel. Make sure to keep
the switch in this position until the end of the refuel operation.
2
Set the TAIL and AUX SOV switches to OPEN, and make sure of the
conditions that follow:
a
OPEN indicator lights for the TAIL and AUX SOVs come on.
b
CLOSED indicator lights for the TAIL and AUX SOVs go off.
Press and hold the SHUT OFF TEST switch until the conditions that follow
occur:
1
HIGH LEVEL SENSORS indicator lights for the TAIL and AUX SOVs
come on.
2
CLOSED indicator lights for the TAIL and AUX SOVs come on.
3
OPEN indicator lights for the TAIL and AUX SOVs go off.
(d) Release the SHUT OFF TEST switch and make sure that the conditions that
follow occur:
1
HIGH LEVEL SENSORS indicator lights for the TAIL and AUX SOVs go
off.
2
CLOSED indicator lights for the TAIL and AUX SOVs go off.
3
OPEN indicator lights for the TAIL and AUX SOVs come on.
CAUTION:
STOP THE REFUEL OPERATION IMMEDIATELY IF THE TAIL
TANK PRESSURE-RELIEF VALVE POPPET EXTENDS FROM
THE SKIN. IF YOU DO NOT STOP THE REFUEL OPERATION
IMMEDIATELY WHEN THE POPPET EXTENDS, YOU CAN CAUSE
DAMAGE TO THE EQUIPMENT.
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CAUTION:
MAKE SURE A SECOND PERSON MONITORS THE TAIL TANK
PRESSURE-RELIEF VALVE POPPET LOCATED ON THE LEFT
SIDE OF THE VERTICAL STABILIZER.
CAUTION:
MAKE SURE THAT THE AIR IS COMING OUT OF THE TAIL TANK
VENT LOCATED ON THE LEFT HAND SIDE OF THE AFT
FUSELAGE. THIS WILL CONFIRM THAT THERE IS NO
BLOCKAGE IN THE TAIL TANK VENT SYSTEM.
(e) Refuel the tail and auxiliary tanks to the necessary level.
NOTE:
(f)
When the tanks are full, the applicable SOV closes automatically,
and the CLOSED indicator light comes on.
Make sure that air and/or a smell of fuel comes out of the NACA scoops
located on the left and right wing between the inboard and outboard flaps, at
the trailing edge lower surface.
NOTE:
Make sure that the pressure releases through the NACA scoops.
(g) If you used only the refuel/defuel panel to monitor the fuel quantity, the tanks
are filled when the conditions that follow occur:
1
HIGH LEVEL SENSORS indicator lights for the TAIL and AUX SOVs
come on.
2
CLOSED indicator lights for the TAIL and AUX SOVs come on.
3
OPEN indicator lights for the TAIL and AUX SOVs go off.
(h) If you monitor the fuel quantity on the MFD EICAS display, examine the fuel
quantity indications for the auxiliary and tail tanks. Monitor the digital readout
for the applicable tank during the pressure refuel operation.
(i)
(j)
When the tail and auxiliary tanks are filled to the necessary level, set the TAIL
and AUX SOV switches to CLOSED. Make sure of the conditions that follow:
1
If the tank is at full capacity, make sure that the HIGH LEVEL SENSORS
indicator lights for the TAIL and AUX SOVs stay on.
2
CLOSED indicator lights for the TAIL and AUX SOVs come on.
3
OPEN indicator lights for the TAIL and AUX SOVs go off.
Release the OVERRIDE switch (as applicable).
(3) When the necessary quantity of fuel is added, do the steps that follow:
(a) On the refuel/defuel control panel, set the POWER switch to OFF.
(b) Make sure that the indicator lamp goes off.
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(4) Disconnect the fuel nozzle from the adapter.
(5) Install the cap on the refuel/defuel adapter.
(6) Disconnect the fuel nozzle bonding wire.
(7) Disconnect the fuel tender ground.
(8) If necessary, disconnect the external ac power (TASK 12−00−07−861−802).
or
Shutdown the APU (TASK 49−10−00−866−802).
(9) Do a general visual inspection of the fuel tank exterior for leaks
(TASK 28−10−00−210−801).
D.
Close Out
(1) Remove all tools, equipment, and unwanted materials from the work area.
(2) Close the access doors that follow:
NOTE:
To close the refuel/defuel panel, move the panel rearward and engage
the latch mechanism.
ACCESS
DESIGNATION
162BR
Door, Pressure Refuel/Defuel Adapter
162DR
Door, Refuel/Defuel Control Panel
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HIGH LEVEL SENSOR
OVERRIDE
POWER
FUEL
OPEN
OFF
SOV
DEFUEL
SHUT
OFF
TEST
CLOSED
TAIL
AUX
R MAIN
LMM1211283_006
L MAIN
Refuel/Defuel Control Panel
Figure 301
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
B
A
GRAVITY FILLER CAP
CENTER TANK
RIGHT SIDE ONLY
PRESSURE FILLER CAP
(REFUEL/DEFUEL ADAPTER)
A
B
LMM1211283_001
ADAPTER PANEL
Pressure Refuel/Defuel Components − Servicing
Figure 302
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
4.
TASK 12−11−28−650−802
Gravity Refueling
A.
Reference Information
REFERENCE
B.
DESIGNATION
TASK 10−10−01−867−801
Grounding of the Aircraft
TASK 12−00−07−861−801
Connect and Energize External AC Power
TASK 12−00−07−861−802
Remove External AC Power
TASK 28−00−00−910−801
Fuel System Safety Precautions
TASK 28−10−00−210−801
General Visual Inspection of the Fuel Tank Exterior
Tools and Equipment
REFERENCE
Commercially Available
NOTE:
C.
DESIGNATION
Screen Funnel
Refer to the Illustrated Tool and Equipment Manual to make sure that you use
the correct equipment configuration.
Job Set−Up
(1) Obey all the fuel system safety precautions when you refuel or defuel the aircraft
(TASK 28−00−00−910−801).
(2) Make sure that the aircraft is on level ground.
(3) Make sure that the aircraft is in the configuration that follows:
WARNING:
MAKE SURE THAT THE AIRCRAFT AND THE FUEL TENDER ARE
GROUNDED AND THAT THE FUEL NOZZLE IS ELECTRICALLY
BONDED TO THE AIRCRAFT BEFORE YOU REFUEL/DEFUEL
THE AIRCRAFT. A STATIC ELECTRIC SPARK DURING THE
REFUELING/DEFUELING CAN CAUSE AN EXPLOSION OR FIRE.
(a) Make sure that the aircraft is grounded (TASK 10−10−01−867−801).
(b) Make sure that the fuel tender is grounded.
(c)
Make sure that the fuel nozzle is electrically bonded to the aircraft.
(d) Make sure that there is sufficient distance between the chocks and the nose or
main landing gear to allow for tire deflection before you refuel the aircraft.
EFFECTIVITY: ALL
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WARNING:
REMOVE ALL PERSONS, MATERIALS AND EQUIPMENT FROM
BELOW THE AIRCRAFT BEFORE YOU DO THE REFUELLING
PROCEDURE. THE WEIGHT OF THE FUEL ADDED WILL
COMPRESS THE LANDING GEAR AND LOWER THE AIRCRAFT.
THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO
THE EQUIPMENT.
(e) Remove all persons, materials and equipment from below the aircraft before
you refuel the aircraft.
D.
Procedure
Refer to Figure 303.
WARNING:
DO NOT HAVE MORE THAN 2 500 POUNDS (1 134 KG) OF
IMBALANCE BETWEEN THE MAIN TANKS DURING THE REFUEL
PROCEDURES (PRESSURE OR GRAVITY). THE AIRCRAFT CAN
MOVE AND CAUSE INJURIES TO PERSONS AND DAMAGE TO THE
EQUIPMENT.
CAUTION:
IF A FUEL IMBALANCE CAUTION INDICATION IS SHOWN ON EICAS,
STOP THE REFUEL/DEFUEL OPERATION IMMEDIATELY. THE FUEL
IMBALANCE INDICATION IS SHOWN WHEN THE FUEL QUANTITY IS
MORE THAN 800 LB (362.88 KG). IF YOU DO NOT DO THIS YOU CAN
CAUSE DAMAGE TO THE AIRCRAFT.
(1) If it is necessary to gravity fill the fuel tanks, or to fill only part of one or more tanks,
do the steps that follow:
NOTE:
Because of the location of the access caps, the main tanks cannot be
filled to capacity. If it is necessary to monitor the fuel quantity, the EICAS
must be used.
If you use the EICAS during the refuel procedure, it is necessary to have
two persons for this procedure. One person must be at the applicable fuel
access and one person must be in the flight compartment. Intercom
communications must be available before you start the refuel procedure.
(2) If necessary, connect the external ac power (TASK 12−00−07−861−801).
(3) On the EICAS primary page, examine the fuel quantity indications for the applicable
tank. Monitor the digital readout for the applicable tank during the gravity refuel
operation.
(4) For the left wing fuel tank, open the access cap that follows:
ACCESS
550AT
DESIGNATION
Access Cap, Gravity Fuel Fill
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(5) For the right wing fuel tank, open the access cap that follows:
ACCESS
650AT
DESIGNATION
Access Cap, Gravity Fuel Fill
(6) For the center wing fuel tank, open the access cover and access cap that follow:
ACCESS
DESIGNATION
640AT
Access Cover
642AT
Access Cap, Gravity Fuel Fill
CAUTION:
MAKE SURE THAT THE FUEL NOZZLE DOES NOT TOUCH THE
BOTTOM OF THE FUEL TANK DURING THE GRAVITY REFUEL
PROCEDURE. THE FUEL NOZZLE CAN BREAK THE PROTECTIVE
COATING AND THIS WILL CAUSE CORROSION IN THE FUEL TANK.
(7) Connect the fuel nozzle bonding wire to the grounding plug in the leading edge
below the applicable access cap.
(8) Carefully put the fuel nozzle into the applicable fuel tank through the filler opening.
(9) Monitor the refuel operation through the filler opening, or use the EICAS to give a
more accurate quantity indication.
NOTE:
If necessary, do the steps that follow until the applicable fuel tanks are
filled to the necessary capacity.
(10) Fill the applicable fuel tank with the necessary quantity of fuel.
(11) When the necessary quantity of fuel is added to the applicable fuel tank, carefully
remove the fuel nozzle.
(12) For the left wing fuel tank, close the access cap that follows:
ACCESS
550AT
DESIGNATION
Access Cap, Gravity Fuel Fill
(13) For the right wing fuel tank, close the access cap that follows:
ACCESS
650AT
DESIGNATION
Access Cap, Gravity Fuel Fill
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(14) For the center wing fuel tank, close the access cover and access cap that follow:
ACCESS
DESIGNATION
640AT
Access Cover
642AT
Access Cap, Gravity Fuel Fill
(15) Disconnect the fuel nozzle bonding wire from the grounding plug on the wing
leading edge.
(16) If necessary, remove the external ac power (TASK 12−00−07−861−802).
(17) Do a general visual inspection of the fuel tank exterior for leaks
(TASK 28−10−00−210−801).
E.
Close Out
(1) Remove all tools, equipment, and unwanted materials from the work area.
EFFECTIVITY: ALL
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WS188
WS58 GRAVITY FILLER CAP
CENTER TANK
RIGHT SIDE ONLY
WS188
NOTE
LMM1211283_002
Right side is shown.
Left side is opposite.
GRAVITY FILLER CAP
Gravity Refuel Components − Servicing
Figure 303
EFFECTIVITY: ALL
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5.
TASK 12−11−28−650−803
Suction Defueling
A.
Reference Information
REFERENCE
B.
DESIGNATION
TASK 10−10−01−867−801
Grounding of the Aircraft
TASK 12−00−07−861−801
Connect and Energize External AC Power
TASK 12−00−07−861−802
Remove External AC Power
TASK 28−00−00−910−801
Fuel System Safety Precautions
Job Set−Up
(1) Obey all the fuel system safety precautions when you refuel or defuel the aircraft
(TASK 28−00−00−910−801).
(2) Make sure that the aircraft is on level ground.
(3) Make sure that the aircraft is in the configuration that follows:
WARNING:
MAKE SURE THAT THE AIRCRAFT AND THE FUEL CONTAINER
ARE GROUNDED AND THAT THE FUEL NOZZLE IS
ELECTRICALLY BONDED TO THE AIRCRAFT BEFORE YOU
REFUEL/DEFUEL THE AIRCRAFT. A STATIC ELECTRIC SPARK
DURING THE REFUELING/DEFUELING CAN CAUSE AN
EXPLOSION OR FIRE.
(a) Make sure that the aircraft is grounded (TASK 10−10−01−867−801).
(b) Make sure that the fuel container is grounded.
(c)
Make sure that the fuel nozzle is electrically bonded to the aircraft.
(4) Connect the external ac power (TASK 12−00−07−861−801).
(5) Open the access doors that follow:
NOTE:
To get access to the refuel/defuel panel, release the latch and move the
panel forward.
ACCESS
DESIGNATION
162BR
Door, Pressure Refuel/Defuel Adapter
162DR
Door, Refuel/Defuel Control Panel
EFFECTIVITY: ALL
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(6) Make sure that the switches on the refuel/defuel control panel are in the correct
configuration as follows:
(a) POWER switch is set to OFF.
(b) SOV L MAIN switch is set to CLOSED.
(c)
SOV TAIL switch is set to CLOSED.
(d) SOV AUX switch is set to CLOSED.
(e) SOV R MAIN switch is set to CLOSED.
C.
Procedure
Refer to Figure 301 and Figure 302.
WARNING:
DO NOT HAVE MORE THAN 2 500 POUNDS (1 134 KG) OF IMBALANCE
BETWEEN THE MAIN TANKS DURING THE REFUEL PROCEDURES
(PRESSURE OR GRAVITY). THE AIRCRAFT CAN MOVE AND CAUSE
INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT.
CAUTION:
IF A FUEL IMBALANCE CAUTION INDICATION IS SHOWN ON EICAS,
STOP THE REFUEL/DEFUEL OPERATION IMMEDIATELY. THE FUEL
IMBALANCE INDICATION IS SHOWN WHEN THE FUEL QUANTITY IS
MORE THAN 800 LB (362.88 KG). IF YOU DO NOT DO THIS YOU CAN
CAUSE DAMAGE TO THE AIRCRAFT.
CAUTION:
DO NOT USE MORE THAN -8 PSI (-55 KPA) DURING THE SUCTION
DEFUEL OPERATION. THE FUEL HOSE WILL CAUSE DAMAGE TO THE
FUEL MANIFOLD.
(1) Remove the cap from the refuel/defuel adapter.
(2) Connect the fuel nozzle to the adapter.
(3) On the refuel/defuel control panel, do the steps that follow:
(a) Set the POWER switch to DEFUEL.
(b) Make sure that the indicator lamp comes on.
(4) Set the defuel pressure on the fuel tender to −8 psi (−55 kPa).
(5) To drain the main tanks, set the SOV switches on the refuel/defuel control panel as
follows:
(a) SOV L MAIN switch is set to OPEN.
(b) SOV R MAIN switch is set to OPEN.
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(6) To drain the auxiliary tanks, set the SOV switch on the refuel/defuel control panel
as follows:
(a) SOV AUX switch is set to OPEN.
(7) To drain the tail tanks, set the SOV switch on the refuel/defuel control panel as
follows:
(a) SOV TAIL switch is set to OPEN.
(8) Make sure of the conditions that follow:
(a) OPEN indicator lights for all the SOVs come on.
(b) CLOSED indicator lights for all the SOVs go off.
(9) Drain the necessary quantity of fuel from the applicable tank.
(10) To monitor the fuel quantity with EICAS, get the primary page. Examine the fuel
quantity indications for the applicable tank (left wing, right wing, auxiliary or tail
tank). Monitor the digital readout for the applicable tank during the defuel operation.
(11) When each of the tanks are drained, set the applicable SOV switch to CLOSED.
Make sure of the conditions that follow as each of the fuel tanks are drained to the
necessary level:
(a) CLOSED indicator light for that SOV comes on.
(b) OPEN indicator light for that SOV goes off.
(12) When the necessary quantity of fuel is drained from the applicable fuel tank(s), do
the steps that follow:
(a) On the refuel/defuel control panel, set the POWER switch to OFF.
(b) Make sure that the indicator lamp goes off.
(13) Disconnect the fuel nozzle from the adapter.
(14) Install the cap on the refuel/defuel adapter.
(15) Disconnect the fuel nozzle bonding wire.
(16) Disconnect the container ground.
(17) If necessary, disconnect the external ac power (TASK 12−00−07−861−802).
D.
Close Out
(1) Remove all tools, equipment, and unwanted materials from the work area.
EFFECTIVITY: ALL
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(2) Close the access doors that follow:
NOTE:
To close the refuel/defuel panel, move the panel rearward and engage
the latch mechanism.
ACCESS
DESIGNATION
162BR
Door, Pressure Refuel/Defuel Adapter
162DR
Door, Refuel/Defuel Control Panel
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
6.
TASK 12−11−28−650−804
Gravity Defueling
A.
Reference Information
REFERENCE
B.
DESIGNATION
TASK 10−10−01−867−801
Grounding of the Aircraft
TASK 28−00−00−910−801
Fuel System Safety Precautions
Tools and Equipment
REFERENCE
GSE 28−30−02
Adaptor Assy, Gravity Defueling
Commercially Available
Containers, Fuel
NOTE:
C.
DESIGNATION
Refer to the Illustrated Tool and Equipment Manual to make sure that you use
the correct equipment configuration.
Job Set−Up
WARNING:
DEFUEL THE AIRCRAFT BY GRAVITY IN AN OPEN AREA. FUEL AND
FUEL FUMES ARE POISONOUS AND HIGHLY EXPLOSIVE.
(1) Obey all the fuel system safety precautions when you refuel or defuel the aircraft
(TASK 28−00−00−910−801).
(2) Make sure that the aircraft is on level ground.
(3) Make sure the aircraft and the equipment are correctly grounded as follows:
WARNING:
MAKE SURE THAT THE AIRCRAFT AND THE FUEL CONTAINER
ARE GROUNDED AND THAT THE DEFUEL ADAPTER IS
ELECTRICALLY BONDED TO THE AIRCRAFT BEFORE YOU
REFUEL/DEFUEL THE AIRCRAFT. A STATIC ELECTRIC SPARK
DURING THE REFUELING/DEFUELING CAN CAUSE AN
EXPLOSION OR FIRE.
(a) Make sure that the aircraft is grounded (TASK 10−10−01−867−801).
(b) Make sure that the fuel container is grounded.
(c)
Make sure that the defuel adapter is electrically bonded to the aircraft.
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
D.
Procedure
Refer to Figure 304.
WARNING:
DO NOT HAVE MORE THAN 2500 POUNDS (1134 KG) OF IMBALANCE
BETWEEN THE MAIN TANKS DURING THE REFUEL/DEFUEL
PROCEDURES (PRESSURE OR GRAVITY). THE AIRCRAFT CAN MOVE
AND CAUSE INJURIES TO PERSONS AND DAMAGE TO THE
EQUIPMENT.
CAUTION:
IF A FUEL IMBALANCE CAUTION INDICATION IS SHOWN ON EICAS,
STOP THE REFUEL/DEFUEL OPERATION IMMEDIATELY. THE FUEL
IMBALANCE INDICATION IS SHOWN WHEN THE FUEL QUANTITY IS
MORE THAN 800 LB (362.88 KG). IF YOU DO NOT DO THIS YOU CAN
CAUSE DAMAGE TO THE AIRCRAFT.
NOTE:
Do the steps that follow until all the fuel tanks are completely drained.
(1) Put the fuel container below the applicable fuel drain valve.
(2) Remove the fuel drain plug.
(3) Put the defuel adapter in the valve receptacle.
(4) Put the drain nozzle into the container.
(5) Open the defuel adapter valve to let the fuel drain into the container.
(6) When the necessary quantity of fuel is drained from the applicable fuel tank, do the
steps that follow:
(a) Close the defuel adapter valve for that tank.
(b) Remove the defuel adapter from the valve receptacle.
(c)
Install the fuel drain plug.
(d) Seal the fuel container with a cap and remove it from the area.
(7) Disconnect the bonding wire from the defuel adapter.
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WARNING:
DO NOT HAVE MORE THAN 2500 POUNDS (1134 KG) OF
IMBALANCE BETWEEN THE MAIN TANKS DURING THE
REFUEL/DEFUEL PROCEDURES (PRESSURE OR GRAVITY). THE
AIRCRAFT CAN MOVE AND CAUSE INJURIES TO PERSONS AND
DAMAGE TO THE EQUIPMENT.
CAUTION:
IF A FUEL IMBALANCE CAUTION INDICATION IS SHOWN ON EICAS,
STOP THE REFUEL/DEFUEL OPERATION IMMEDIATELY. THE FUEL
IMBALANCE INDICATION IS SHOWN WHEN THE FUEL QUANTITY IS
MORE THAN 800 LB (362.88 KG). IF YOU DO NOT DO THIS YOU CAN
CAUSE DAMAGE TO THE AIRCRAFT.
(8) Put the fuel container below the applicable water drain valve.
(9) Put a screwdriver in the closed water drain valve.
(10) Push the screwdriver and turn it clockwise to open the drain valve.
(11) Be prepared to collect the applicable quantity of remaining fuel in the tank.
(12) When the necessary quantity of fuel is drained from the applicable collector tank, do
the steps that follow:
(a) Put the screwdriver in the open water drain valve.
(b) Push the screwdriver in and turn it counterclockwise to close the drain valve.
(c)
Seal the fuel container with a cap and remove it from the area.
(13) Continue to drain the collector tanks until all the collector tanks are completely
drained.
(14) Disconnect the ground from the fuel container.
E.
Close Out
(1) Remove all tools, equipment, and unwanted materials from the work area.
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
MAIN TANK DRAIN
CENTER TANK DRAIN
OPEN
PUSH TO
UNLOCK
LATCH
LMM1211283_003
RETAINER
Gravity Defuel Components − Servicing
Figure 304
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
7.
TASK 12−11−28−650−805
Defueling With the Standby Fuel Pumps
A.
Reference Information
REFERENCE
B.
DESIGNATION
TASK 07−10−01−581−801
Lifting of the Complete Aircraft With Jacks
TASK 07−10−01−586−801
Lowering of the Complete Aircraft
TASK 08−20−01−589−801
Leveling of the Aircraft on Jacks
TASK 10−10−01−867−801
Grounding of the Aircraft
TASK 12−00−07−861−801
Connect and Energize External AC Power
TASK 12−00−07−861−802
Remove External AC Power
TASK 12−11−28−650−804
Gravity Defueling
TASK 28−00−00−910−801
Fuel System Safety Precautions
TASK 54−60−01−000−801
Removal of the Pylon Access Panels
TASK 54−60−01−400−801
Installation of the Pylon Access Panels
Tools and Equipment
REFERENCE
GSE 24−00−24
Tag, Circuit Breaker
GSE 28−30−03
Kit, Pressurized Fuel Handling
Commercially Available
Containers, Fuel
Commercially Available
Torque Wrench, 30 to 40 lbf ft (40.67 to 54.23 Nm)
Commercially Available
Torque Wrench, 125 to 150 lbf ft (169.47 to 203.37
Nm)
NOTE:
C.
DESIGNATION
Refer to the Illustrated Tool and Equipment Manual to make sure that you use
the correct equipment configuration.
Job Set−Up
(1) Obey all the fuel system safety precautions when you refuel or defuel the aircraft
(TASK 28−00−00−910−801).
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(2) Make sure that the aircraft is level (TASK 08−20−01−589−801).
(3) Make sure that the aircraft is in the configuration that follows:
WARNING:
MAKE SURE THAT THE AIRCRAFT AND THE FUEL CONTAINER
ARE GROUNDED AND THAT THE FUEL NOZZLE IS
ELECTRICALLY BONDED TO THE AIRCRAFT BEFORE YOU
REFUEL/DEFUEL THE AIRCRAFT. A STATIC ELECTRIC SPARK
DURING THE REFUELING/DEFUELING CAN CAUSE AN
EXPLOSION OR FIRE.
(a) Make sure that the aircraft is grounded (TASK 10−10−01−867−801).
(b) Make sure that the fuel container is grounded.
(c)
Make sure that the fuel nozzle is electrically bonded to the fuel container.
(4) Remove the applicable access panels that follow:
(a) For the left main (wing) fuel tank, remove the pylon access panel 412BT
(TASK 54−60−01−000−801).
(b) For the right main (wing) fuel tank, remove the pylon access panel 422BT
(TASK 54−60−01−000−801).
(5) Open and tag the circuit breakers that follow:
(a) For the left main (wing) fuel tank:
LOCATION
CB NUMBER
CB NAME
ZONE
CBP−1
M9
FUEL L PUMP CONT
221
CBP−1
M10
FUEL L PUMP
221
(b) For the right main (wing) fuel tank:
LOCATION
CB NUMBER
CB NAME
ZONE
CBP−2
G7
R FUEL PUMP CONT
222
CBP−2
G8
R FUEL PUMP
222
EFFECTIVITY: ALL
12−11−28
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D.
Procedure
Refer to Figure 305.
WARNING:
DO NOT HAVE MORE THAN 2500 POUNDS (1134 KG) OF
IMBALANCE BETWEEN THE MAIN TANKS DURING THE
REFUEL/DEFUEL PROCEDURES (PRESSURE OR GRAVITY). THE
AIRCRAFT CAN MOVE AND CAUSE INJURIES TO PERSONS AND
DAMAGE TO THE EQUIPMENT.
CAUTION:
IF A FUEL IMBALANCE CAUTION INDICATION IS SHOWN ON EICAS,
STOP THE REFUEL/DEFUEL OPERATION IMMEDIATELY. THE FUEL
IMBALANCE INDICATION IS SHOWN WHEN THE FUEL QUANTITY IS
MORE THAN 800 LB (362.88 KG). IF YOU DO NOT DO THIS YOU CAN
CAUSE DAMAGE TO THE AIRCRAFT.
(1) If it is necessary to defuel the complete aircraft, do the steps that follow:
NOTE:
In the procedure that follows only one main tank is defueled at a
time. To protect against a weight imbalance, you must put a jack
below the main (wing) tank that is not yet defueled. The complete
aircraft is lifted for safety and because the specified tank for
defueling is not known.
(a) Use jacks to lift the aircraft (TASK 07−10−01−581−801).
(b) To defuel the left main (wing) tank, do the steps that follow:
1
Disconnect the fuel feed line (1) at the pylon firewall fitting (2) for the left
engine.
2
Install a protective cover on the fuel feed line.
NOTE:
Do the steps that follow until the necessary quantity of fuel is
drained or the quantity of fuel in the fuel tank is at 50 lb
(22.68 kg).
3
Put the fuel container below the applicable fuel feed line.
4
Connect the pressurized fuel handling kit to the pylon firewall fitting (2).
5
Torque the fitting (2) to 30 to 40 lbf ft (40.67 to 54.23 Nm).
6
Put the fuel nozzle into the container.
7
Open the drain valve on the fuel handling kit at the pylon firewall fitting.
8
Close the drain valve at the fuel nozzle.
9
Connect the external ac power (TASK 12−00−07−861−801).
EFFECTIVITY: ALL
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10
Remove the tags and close the circuit breakers that follow:
LOCATION
11
CB NUMBER
CB NAME
ZONE
CBP−1
M9
FUEL L PUMP
CONT
221
CBP−1
M10
FUEL L PUMP
221
Operate the standby fuel pump for the left engine as follows:
a
On the overhead panel, push the FUEL BOOST PUMP L
switch/light.
b
Make sure that the INOP light on the switch/light goes out.
c
Make sure that the ON light on the switch/light comes on.
12
Open the drain valve at the fuel nozzle to permit the fuel to drain into the
fuel container.
13
Monitor the fuel quantity remaining in the applicable fuel tank with the
EICAS or in the applicable fuel tank.
14
On the EICAS primary page, examine the fuel quantity indications for the
applicable tank. Monitor the digital readout for the applicable tank during
the defuel operation.
CAUTION:
15
16
STOP THE DEFUELING PROCEDURE WHEN THE FUEL
QUANTITY IN THE MAIN FUEL TANKS IS NEAR 50 LB
(22.68 KG). A FUEL QUANTITY OF LESS THAN 50 LB
(22.68 KG) CAN RESULT IN A DECREASE OF FLUID TO THE
PUMP MECHANISM. THIS CAN CAUSE DAMAGE TO THE
PUMP AND CAUSE IT TO BECOME TOO HOT.
Stop the defuel procedure when one of the events that follows occurs:
a
The quantity of fuel in the container is near the full mark; or
b
The necessary quantity of fuel is drained from the applicable fuel
tank (more than 50 lb (22.68 kg)); or
c
The quantity of fuel in the applicable fuel tank is at 50 lb (22.68 kg).
If the quantity of the fuel in the fuel container is near the full mark, do the
steps that follow:
a
Close the drain valve at the fuel nozzle.
b
On the overhead panel, press the FUEL BOOST PUMP L
switch/light.
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
17
18
c
Make sure that the ON light on the switch/light goes out.
d
Make sure that the INOP light on the switch/light comes on.
e
Remove the fuel nozzle and the bonding wire from the container.
f
Seal the fuel container with a cap and remove it from the area.
g
If the applicable fuel tank is not drained sufficiently, put one more
fuel container below the fuel feed line.
When the necessary quantity of fuel is drained from the applicable fuel
tank, do the steps that follow:
a
Close the drain valve at the fuel nozzle.
b
On the overhead panel, push the FUEL BOOST PUMP L
switch/light.
c
Make sure that the ON light on the switch/light goes out.
d
Make sure that the INOP light on the switch/light comes on.
e
Remove the fuel nozzle and the bonding wire from the container.
f
Seal the fuel container with a cap and remove it from the area.
Open and tag the circuit breakers that follow:
LOCATION
CB NUMBER
CB NAME
ZONE
CBP−1
M9
FUEL L PUMP
CONT
221
CBP−1
M10
FUEL L PUMP
221
19
Disconnect the pressurized fuel handling kit from the pylon firewall fitting
(2).
20
Remove the protective cover and connect the fuel feed line (1) to the
pylon firewall fitting (2).
21
Torque the pylon firewall fitting (2) to 125 to 150 lbf ft (169.47 to 203.37
Nm).
22
If it is necessary to remove all the fuel from the applicable fuel tank, use
the gravity defuel procedure (TASK 12−11−28−650−804).
23
Remove the external ac power (TASK 12−00−07−861−802).
EFFECTIVITY: ALL
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(c)
If it is necessary to defuel the right main (wing) tank, do the steps that follow:
1
Disconnect the fuel feed line (1) at the pylon firewall fitting (2) for the right
engine.
2
Install a protective cover on the fuel feed line.
NOTE:
Do the steps that follow until the necessary quantity of fuel is
drained or the quantity of fuel in the fuel tank is at 50 lb
(22.68 kg).
3
Put the fuel container below the applicable fuel feed line.
4
Connect the pressurized fuel handling kit to the pylon firewall fitting (2).
5
Torque the fitting (2) to 30 to 40 lbf ft (40.67 to 54.23 Nm).
6
Put the fuel nozzle into the container.
7
Open the drain valve on the fuel handling kit at the pylon firewall fitting.
8
Close the drain valve at the fuel nozzle.
9
Connect the external ac power (TASK 12−00−07−861−801).
10
Remove the tags and close the circuit breakers that follow:
LOCATION
11
CB NUMBER
CB NAME
ZONE
CBP−2
G7
R FUEL PUMP
CONT
222
CBP−2
G8
R FUEL PUMP
222
Operate the standby fuel pump for the right engine as follows:
a
On the overhead panel, push the FUEL BOOST PUMP R
switch/light.
b
Make sure that the INOP light on the switch/light goes out.
c
Make sure that the ON light on the switch/light comes on.
12
Open the drain valve at the fuel nozzle to permit the fuel to drain into the
fuel container.
13
Monitor the fuel quantity remaining in the applicable fuel tank with the
EICAS or in the applicable fuel tank.
EFFECTIVITY: ALL
12−11−28
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
14
On the EICAS primary page, examine the fuel quantity indications for the
applicable tank. Monitor the digital readout for the applicable tank during
the defuel operation.
CAUTION:
15
16
17
STOP THE DEFUELING PROCEDURE WHEN THE FUEL
QUANTITY IN THE MAIN FUEL TANKS IS NEAR 50 LB
(22.68 KG). A FUEL QUANTITY OF LESS THAN 50 LB
(22.68 KG) CAN RESULT IN A DECREASE OF FLUID TO THE
PUMP MECHANISM. THIS CAN CAUSE DAMAGE TO THE
PUMP AND CAUSE IT TO BECOME TOO HOT.
Stop the defuel procedure when one of the events that follows occurs:
a
The quantity of fuel in the container is near the full mark; or
b
The necessary quantity of fuel is drained from the applicable fuel
tank (more than 50 lb (22.68 kg)); or
c
The quantity of fuel in the applicable fuel tank is at 50 lb (22.68 kg).
If the quantity of the fuel in the fuel container is near the full mark, do the
steps that follow:
a
Close the drain valve at the fuel nozzle.
b
On the overhead panel, press the FUEL BOOST PUMP R
switch/light.
c
Make sure that the ON light on the switch/light goes out.
d
Make sure that the INOP light on the switch/light comes on.
e
Remove the fuel nozzle and the bonding wire from the container.
f
Seal the fuel container with a cap and remove it from the area.
g
If the applicable fuel tank is not drained sufficiently, put one more
fuel container below the fuel feed line.
When the necessary quantity of fuel is drained from the applicable fuel
tank, do the steps that follow:
a
Close the drain valve at the fuel nozzle.
b
On the overhead panel, push the FUEL BOOST PUMP R
switch/light.
c
Make sure that the ON light on the switch/light goes out.
d
Make sure that the INOP light on the switch/light comes on.
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
18
e
Remove the fuel nozzle and the bonding wire from the container.
f
Seal the fuel container with a cap and remove it from the area.
Open and tag the circuit breakers that follow:
LOCATION
CB NUMBER
CB NAME
ZONE
CBP−2
G7
R FUEL PUMP
CONT
222
CBP−2
G8
R FUEL PUMP
222
19
Disconnect the pressurized fuel handling kit from the pylon firewall fitting
(2).
20
Remove the protective cover and connect the fuel feed line (1) to the
pylon firewall fitting (2).
21
Torque the pylon firewall fitting (2) to 125 to 150 lbf ft (169.47 to 203.37
Nm).
22
If it is necessary to remove all the fuel from the applicable fuel tank, use
the gravity defuel procedure (TASK 12−11−28−650−804).
23
Remove the external ac power (TASK 12−00−07−861−802).
(2) If necessary, lower the aircraft and remove the jacks (TASK 07−10−01−586−801).
(3) Remove the tags and close the circuit breakers that follow:
(a) For the left main (wing) fuel tank:
LOCATION
CB NUMBER
CB NAME
ZONE
CBP−1
M9
FUEL L PUMP CONT
221
CBP−1
M10
FUEL L PUMP
221
(b) For the right main (wing) fuel tank:
LOCATION
CB NUMBER
CB NAME
ZONE
CBP−2
G7
R FUEL PUMP CONT
222
CBP−2
G8
R FUEL PUMP
222
EFFECTIVITY: ALL
12−11−28
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
E.
Close Out
(1) Remove all tools, equipment, and unwanted materials from the work area.
(2) Install the applicable access panels that follow:
(a) For the left main (wing) fuel tank, install the pylon access panel 412BT
(TASK 54−60−01−400−801).
(b) For the right main (wing) fuel tank, install the pylon access panel 422BT
(TASK 54−60−01−400−801).
EFFECTIVITY: ALL
12−11−28
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
1
LMM1211283_004
2
Defueling With the Standby Fuel Pumps − Servicing
Figure 305
EFFECTIVITY: ALL
12−11−28
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
8.
TASK 12−11−28−680−801
Drain Water from the Fuel Tanks
A.
Reference Information
REFERENCE
B.
DESIGNATION
TASK 10−10−01−867−801
Grounding of the Aircraft
TASK 12−11−28−750−801
Water Contamination Check
TASK 12−11−28−650−802
Gravity Refueling
TASK 28−00−00−910−801
Fuel System Safety Precautions
Tools and Equipment
REFERENCE
GSE 12C−10−04
Sampler, Fuel
Commercially Available
Bucket, Five Gallons (18.93 liters)
NOTE:
C.
DESIGNATION
Refer to the Illustrated Tool and Equipment Manual to make sure that you use
the correct equipment configuration.
Job Set−Up
NOTE:
It is recommended to wait at least one hour after refueling to perform this task.
(1) Obey all the fuel system safety precautions when you refuel or defuel the aircraft
(TASK 28−00−00−910−801).
WARNING:
MAKE SURE THAT THE AIRCRAFT AND THE FUEL CONTAINER ARE
GROUNDED AND THAT THE DEFUEL ADAPTER IS ELECTRICALLY
BONDED TO THE AIRCRAFT BEFORE YOU GRAVITY DEFUEL THE
AIRCRAFT. A STATIC ELECTRIC SPARK CAN CAUSE AN
EXPLOSION OR FIRE.
(2) Make sure that the aircraft is grounded (TASK 10−10−01−867−801).
(3) Make sure that the fuel container is grounded.
(4) Make sure the defuel adapter is electrically bonded to the aircraft.
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
D.
Procedure
Refer to Figure 306.
(1) Open each individual water drain valve.
(2) Let fuel flow from the applicable water drain valve into the bucket.
(3) Immediately close the water drain valve.
(4) Repeat steps above until no more water is contained in the fuel sample. If water is
continuing to drain then proceed to perform the water contamination check
(TASK 12−11−28−750−801).
(5) Disconnect the ground from the fuel container.
E.
Close Out
(1) Remove all tools, equipment, and unwanted materials from the work area.
EFFECTIVITY: ALL
12−11−28
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
WS244.00
WS151.01
WS88.50
WS68.75
WS48.00
WS5.00
WS12.50
A
B
A
V
I
91
1D
−I
N
LOWER WING SKIN
VALVE PORT
HOUSING
O−RING
B
LMM1211283_005
A
Water Drain Valves − Servicing
Figure 306
EFFECTIVITY: ALL
12−11−28
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
9.
TASK 12−11−28−750−801
Water Contamination Check
A.
Reference Information
REFERENCE
B.
DESIGNATION
TASK 10−10−01−867−801
Grounding of the Aircraft
TASK 12−11−28−650−802
Gravity Refueling
TASK 12−11−28−650−803
Suction Defueling
TASK 12−11−28−650−804
Gravity Defueling
TASK 12−11−28−680−801
Drain Water from the Fuel Tanks
TASK 28−00−00−910−801
Fuel System Safety Precautions
Tools and Equipment
REFERENCE
GSE 12C−10−04
NOTE:
C.
DESIGNATION
Sampler, Fuel
Refer to the Illustrated Tool and Equipment Manual to make sure that you use
the correct equipment configuration.
Job Set−Up
NOTE:
Do not move the aircraft for at least four hours before you do a water
contamination check.
(1) Obey all the fuel system safety precautions when you refuel or defuel the aircraft
(TASK 28−00−00−910−801).
(2) Make sure that the aircraft is in the configuration that follows:
WARNING:
MAKE SURE THAT THE AIRCRAFT AND THE FUEL CONTAINER
ARE GROUNDED AND THAT THE DEFUEL ADAPTER IS
ELECTRICALLY BONDED TO THE AIRCRAFT BEFORE YOU
GRAVITY DEFUEL THE AIRCRAFT. A STATIC ELECTRIC SPARK
CAN CAUSE AN EXPLOSION OR FIRE.
(a) Make sure that the aircraft is grounded (TASK 10−10−01−867−801).
(b) Make sure that the fuel container is grounded.
EFFECTIVITY: ALL
12−11−28
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
D.
Procedure
Refer to Figure 306.
(1) Open a water drain valve with the fuel sampler.
(2) Let a sufficient quantity of fuel flow from the applicable water drain valve into the
fuel sampler.
(3) Immediately close the water drain valve.
(4) Do a general visual inspection of the fuel sampler for water contamination in the
fuel.
NOTE:
A separation line is shown between the water and the fuel in the sampler.
(5) If water is found in the fuel, drain the water from the fuel tanks
(TASK 12−11−28−680−801).
(6) Do the steps above again until there is no water in the fuel.
(7) If the tail tank contains fuel, drain the tail tank contents using one of the following
tasks:
(a) Suction Defueling (TASK 12−11−28−650−803)
(b) Gravity Defueling (TASK 12−11−28−650−804).
(8) Disconnect the ground from the fuel container.
E.
Close Out
(1) If necessary, refuel the tanks to the necessary capacity
(TASK 12−11−28−650−802).
(2) Remove all tools, equipment, and unwanted materials from the work area.
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
TASK 12−11−28−910−801
10. Fuel Tank Quantity Specifications for Refueling
A.
Reference Information
REFERENCE
TASK 28−00−00−910−801
B.
DESIGNATION
Fuel System Safety Precautions
Job Set−Up
(1) Obey all the fuel system safety precautions when you refuel or defuel the aircraft
(TASK 28−00−00−910−801).
C.
Procedure
(1) Use the specified fuel quantity limits that follow when you refuel the aircraft:
(a) Fuel Tank Capacities for Pressure Refuel Operations (Available Fuel)
NOTE:
Based on a fuel density of 6.75 lb (3.06 kg).
AVAILABLE FUEL
Location
Pounds
Kilos
Gallons
(U.S.)
Gallons
(Imperial)
Liters
Left main tank
4 860
2 204.49
720
599.52
2 725.48
Right main tank
4 860
2 204.49
720
599.52
2 725.48
Center aux tank
5 062
2 296.12
750
624.50
2 839.05
Fwd aux tank
1 465
664.52
217
180.69
821.43
Aft aux tank
641
290.75
95
79.10
359.61
Left saddle tank
891
404.15
132
109.91
499.67
Right saddle tank
891
404.15
132
109.91
499.67
Tail tank
1 330
603.28
197
164.04
745.72
Total Capacity
20 000
9 072
2 963
2 467.21
11 216.14
(b) Fuel Tank Capacities for Pressure Refuel Operations (Fuel Not Available )
NOTE:
Fuel not available is the quantity of the trapped plus the residual fuel.
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
FUEL NOT AVAILABLE
(c)
Location
Pounds
Kilos
Gallons
(U.S.)
Gallons
(Imperial)
Liters
Total Capacity
129
58.51
19.10
15.90
72.30
Fuel Tank Capacities for Gravity Refuel Operations (Available Fuel)
NOTE:
Based on a fuel density of 6.75 lb (3.06 kg)/US gallon and aircraft
parked with 0.5 ° nose down and wings level.
AVAILABLE FUEL
Location
Pounds
Kilos
Gallons
(U.S.)
Gallons
(Imperial)
Liters
Left main tank
4523
2051
670
558
2536
Right main tank
4523
2051
670
558
2536
Center aux tank
6676
3028
989
823
3743
Total Capacity
15722
7130
2329
1939
8815
(d) Fuel Tank Capacities for Gravity Refuel Operations (Fuel Not Available )
NOTE:
Fuel not available is the quantity of the trapped plus the residual fuel.
FUEL NOT AVAILABLE
Location
Pounds
Kilos
Gallons
(U.S.)
Gallons
(Imperial)
Liters
Total Capacity
129
59
19
16
72
(e) Fuel Specifications
FUEL − KEROSENE TYPE
FUEL TYPE
CANADIAN
AMERICAN
BRITISH
JET A
CAN2−3.23−M81
ASTM D1655
D. ENG. RD. 2495
JET A1
CAN2−3.23−M81
ASTM D1655
D. ENG. RD. 2495
EFFECTIVITY: ALL
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CL−604 AIRCRAFT MAINTENANCE MANUAL − PART II
FUEL − WIDE CUT TYPE
FUEL TYPE
CANADIAN
AMERICAN
BRITISH
JET B
CAN2−3.23−M80
ASTM D1655
D. ENG. RD. 2486
JP4
CAN2−3.23−M80
MIL−T−5624
D. ENG. RD. 2486
EFFECTIVITY: ALL
12−11−28
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