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Start N/A N/A 700 (on ground)
850 (in flight)
Idle 58.0 (minimum) N/A 860
TakeOff
* 99.6 102.0 900 *
Max Continuous 98.9 102.0 860
− 99.8 (20 seconds) 102.5 (20 seconds) 905 (20 seconds)
Reverse Thrust − 70.0 (30 seconds) −
* Takeoff
thrust for 5 minutes with all engines operating.
Takeoff
thrust for 10 minutes in the event of an engine failure.
NOTE
Static ground operation in the range of 66% to 80% N1 is
prohibited. Acceleration/deceleration thru this range is permitted.
This limitation does not apply to reverse thrust.
C. Cold Weather Operations
Airplane operations in cold weather conditions must be conducted in accordance with
Chapter 7; SUPPLEMENTARY PROCEDURES − Cold Weather Operations.
D. Thrust Management Data
Thrust management information is advisory only. Thrust setting data presented on EICAS /
FMS must be checked for accuracy prior to use. Refer to Airplane Flight Manual, Chapter 6;
PERFORMANCE − THRUST SETTINGS.
E. Maximum Wind Speed and Direction
Engine starts are not permitted when the tailwind component exceeds 20 knots. Anytime
there is an external or EICAS indication of N1 rotation due to tailwinds, the engine must be
cranked for 30 seconds and must be followed immediately by an AUTO start.
When winds exceed 20 knots, do not exceed the minimum thrust required for taxi. When the
takeoff
crosswind component exceeds 20 knots, do not exceed 66% N1 below 30 KIAS.
There are no limits for a headwind within 10 degrees of the airplane centreline.
Refer to Chapter 4; NORMAL PROCEDURES − TAXIING AND TAKEOFF
− HIGH
CROSSWIND TAKEOFF.
LIMITATIONS
POWER PLANT
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 1
02−05−1
2. STARTER CRANKING LIMITS (GROUND AND AIR)
A. General
The starter must not be used if indicated RPM exceeds 42% N2.
B. Engine Start
Normal engine start − 3 consecutive engine start cycles of 3 minutes each with 15 seconds
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 REV 41, Jul 08, 2004
CSP 700−6
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
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
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%)
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 6,265 litres 1,655 USG 5,075 kg 11,150 lb
Aft tank 1,275 litres 337 USG 1,025 kg 2,300 lb
Total 24,410 litres 6,450 USG 19,750 kg 43,550 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 6,245 litres 1,650 USG 5,050 kg 11,150 lb
Aft tank not available not available not available not available
Total 21,765 litres 5,750 USG 17,600 kg 38,850 lb
† based on a fuel density of 0.809 kg / litre (6.75 lb / USG), rounded to the nearest 25 Kg or
　
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