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cooling between cycles.
After 3 attempts, a 15−minute cooling period is required.
C. Dry Motoring / Cranking Cycle
Dry motoring / cranking time limits are as given in para 2.B., Engine Start.
Dry motoring / cranking is performed with the ENGINE RUN switches OFF.
LIMITATIONS
POWER PLANT
Flight Crew Operating Manual Mar 12, 2004
CSP 700−5000−6
Volume 1
02−05−2
2. STARTER CRANKING LIMITS (GROUND AND AIR) (CONT'D)
D. Engine Air Start Envelope
See Figure 02−05−1.
0
5
30
35
25
10
15
20
50 75 100 125 150 175 200 225 250 275 300 325 350
Altitude (1,000 Feet)
340 KIAS
8,000 feet
20,000 feet
115 knots
150 knots
Indicated Airspeed (Knots)
GF0205_002
ATS ENVELOPE ENVELOPE
WINDMILL
N 2 > 8%
Engine Air Start Envelope
Figure 02−05−1
LIMITATIONS
POWER PLANT
Mar 12, 2004 Flight Crew Operating Manual
CSP 700−5000−6
Volume 1
02−05−3
3. FUEL
A. Fuel Imbalance
The maximum permissible fuel imbalance between the contents of the main left tank and the
main right tank is as follows:
WING TANK FUEL LOAD ON GROUND AND DURING
TAKE-OFF AND LANDING DURING FLIGHT
Less than
8823 kg (19,450 lb) 488 kg (1100 lb) 488 kg (1100 lb)
From 8823 kg (19,450 lb)
to 9186 kg (20,250 lb)
488 kg (1100 lb)
to 266 kg (600 lb) 488 kg (1100 lb)
Greater than
9186 kg (20,250 lb) 266 kg (600 lb) 488 kg (1100 lb)
B. Usable Fuel Load
The maximum usable fuel load for each fuel tank is given below:
PRESSURE REFUEL (+0 / -1% WING TANKS, +0 / -3% CENTER TANK)
TANK VOLUME FUEL MASS †
Left main tank 8,435 litres 2,229 USG 6,825 kg 15,050 lb
Right main tank 8,435 litres 2,229 USG 6,825 kg 15,050 lb
Centre tank 3,418 litres 903 USG 2,775 kg 6,100 lb
Total 20,288 litres 5,361 USG 16,425 kg 36,200 lb
† based on a fuel density of 0.809 kg / litre (6.75 lb / USG), rounded to the nearest 25 Kg or
50 lb. Fuel Mass is provided for reference only and should not be considered limiting.
GRAVITY REFUEL (AIRPLANE LEVEL)
TANK VOLUME FUEL MASS †
Left main tank 7,760 litres 2,050 USG 6,275 kg 13,850 lb
Right main tank 7,760 litres 2,050 USG 6,275 kg 13,850 lb
Centre tank 3,142 litres 830 USG 2,550 kg 5,600 lb
Total 18,662 litres 4,930 USG 15,100 kg 33,300 lb
† based on a fuel density of 0.809 kg / litre (6.75 lb / USG), rounded to the nearest 25 Kg or
50 lb. Fuel Mass is provided for reference only and should not be considered limiting.
Fuel remaining in a tank when the appropriate fuel quantity indicator reads zero is not usable.
C. Fuel Distribution
Fuel in the centre tank must be considered unusable unless each wing tank is full at
departure, and the planned cruise altitude is greater than 30,000 feet.
If use of the centre tank is planned, the tank fuel load is to be no less than 230 kg (500 lb) to
ensure transfer pumps reprime.
LIMITATIONS
POWER PLANT
Flight Crew Operating Manual REV 4, Jun 22, 2005
CSP 700−5000−6
Volume 1
02−05−4
3. FUEL (CONT'D)
D. Minimum Fuel Quantity for Goaround
The minimum fuel quantity for goaround
is 266 kg (600 lb) per wing (with wings level) and
assuming a maximum airplane climb attitude of 10° nose up.
E. Fuels and Fuel Additives
When using wide cut or CIS fuels, operation is limited to 13,000 feet until the bulk fuel
temperature is below 15 °C.
Mixing of fuels is permitted.
Takeoff
with bulk fuel temperature indications outside the limits stated is prohibited.
During flight, bulk fuel temperature must remain above the applicable bulk fuel freezing point.
Fuels conforming to any of the following specifications are approved for use.
(1) CANADIAN FUELS
FUEL SPEC BULK FUEL TAKE-OFF
LIMIT
BULK FUEL
FREEZING
MIN °C MAX °C POINT
Kerosene CAN 2 − 3.23 −30 °C 54 °C −40 °C
CAN 2 − 3.23 −37 °C 54 °C −47 °C
WideCut
CAN 2 − 3.22 −40 °C 43 °C −50 °C
CAN 2 − 3.22 −48 °C 43 °C −58 °C
(2) AMERICAN FUELS
FUEL SPEC BULK FUEL TAKE-OFF
LIMIT
BULK FUEL
FREEZING
MIN °C MAX °C POINT
Kerosene ASTM D1655 − JET A −30 °C 54 °C −40 °C
ASTM D1655 − JET A1 −37 °C 54 °C −47 °C
MIL−T−83133 − JP−8 −37 °C 54 °C −47 °C
　
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