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is permitted only if the resulting CG remains ahead of 34% MAC.
OR
Alternative AUX/TAIL Fuel Distribution for Aft CG Limit at ZFW:
• If the aircraft CG at ZFW is within the envelope aft lower zone (CG between 32,000 lb/35%,
30,000 lb/34%, 28,000 lb/34%, 26,000 lb/32.5% and 26,000 lb/35%) an alternative manual
fuel distribution may be applied. Auxiliary tank quantity must be full, or at least 2.95 times
the tail tank quantity (as shown in Figure 02−05−2, Detail C, Alternative Fuel Distribution
for Take-Off).
LIMITATIONS
Power Plant
Vol. 1 02−05−5
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
8. FUEL (CONT'D)
DFM0205_005
Auxiliary Tank Quantity/Tail Tank Quantity − Relation Verses Centre of Gravity (Page 1 of 2)
Figure 02−05−2
LIMITATIONS
Power Plant
02−05−6
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
8. FUEL (CONT'D)
DFM0205_006
Auxiliary Tank Quantity/Tail Tank Quantity − Relation Verses Centre of Gravity (Page 2 of 2)
Figure 02−05−2
LIMITATIONS
Power Plant
02−05−7
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
8. FUEL (CONT'D)
Take-off with up to 230 kg (500 lb) of fuel in the auxiliary tank is permitted, provided that there is
at least 690 kg (1500 lb) of fuel in each wing tank and no fuel in the tail tank.
Take-off with more than 230 kg (500 lb) of fuel in the auxiliary tank is permitted, provided that the
minimum quantity of fuel in each wing tank is as per Figure 02−05−3.
• For example, if there is at least 1,724 kg (3,800 lb) of fuel in each wing tank, then according
to Figure 02−05−3, the take-off weight cannot exceed 21,319 kg (47,000 lb).
• Conversely, if the take-off weight is for example 20,366 kg (44,900 lb), then according to
Figure 02−05−3, there must be at least 1,247 kg (2,750 lb) of fuel in each wing tank.
On airplanes 5301, 5303 to 5639 NOT incorporating Service Bulletin 604–11–001:
Take-off with more than 230 kg (500 lb) of fuel in the auxiliary tank is permitted, provided that
the minimum quantity of fuel in each wing tank is as per Figure 02−05−4.
• For example, if there is at least 1,724 kg (3,800 lb) of fuel in each wing tank, then according
to Figure 02−05−4, the take-off weight cannot exceed 21,046 kg (46,400 lb).
• Conversely, if the take-off weight is for example 20,094 kg (44,300 lb), then according to
Figure 02−05−4, there must be at least 1,247 kg (2,750 lb) of fuel in each wing tank.
The minimum fuel quantity for go-around is 230 kg (500 lb) per wing (with the airplane level) and
assuming a maximum airplane climb attitude of 10° nose up.
LIMITATIONS
Power Plant
Vol. 1 02−05−8
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
8. FUEL (CONT'D)
DFM0205_007
LIMITATIONS
Power Plant
Vol. 1 02−05−9
REV 71, Oct 31/07
Minimum Wing Tank Fuel Quantity for Take-Off
Figure 02−05−3
CL−604 Operating Manual
PSP 604−6
8. FUEL (CONT'D)
On airplanes 5301, 5303 to 5639 NOT incorporating Service Bulletin 604–11–001:
DFM0205_008
Minimum Wing Tank Fuel Quantity for Take-Off
(Airplanes 5301, 5303 to 5639 NOT incorporating Service Bulletin 604–11–001)
Figure 02−05−4
LIMITATIONS
Power Plant
Vol. 1 02−05−10
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
8. FUEL (CONT'D)
A. Fuel Temperature
Take-off with engine fuel temperature indications below 5°C (41°F) is prohibited.
Take-off with bulk fuel temperature indications below the limits stated is prohibited.
During flight, bulk fuel temperature must remain above the applicable bulk fuel freezing point.
FUEL BULK FUEL TAKE-OFF
LIMIT
BULK FUEL FREEZING
POINT
ASTM D1655 JET A –30°C –40°C
ASTM D1655 JET A1 –37°C –47°C
ASTM D6615 JET B –40°C –50°C
MIL–DTL–5624 JP 4 –48°C –58°C
MIL–DTL–5624 JP 5 –36°C –46°C
MIL–DTL–83133 JP 8 –37°C –47°C
GB 6537 No. 3 JET –37°C –47°C
Russian TS-1 –43°C [†]
Russian RT –40°C [†]
Ukrainian TS-1 –42°C –52°C
Ukrainian RT –42°C –52°C
[†] Russian TS-1 and RT fuels with a freeze point of not higher than –50°C are
　
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