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CL−604 Airplane Flight Manual
PSP 604−1
7. PERFORMANCE (CONT'D)
(d) Take-Off Speeds
When dispatching with one hydraulic AC motor pump inoperative, and operating at or
below 4,000 feet pressure altitude, apply VR and V2 corrections as shown on
Figure 07−08−7 and Figure 07−08−8 respectively.
For V1, when dispatching with hydraulic AC motor pump 2B inoperative, use the
highest V1MCG or multiply the VR from Figure 07−08−7 by a factor of 0.86 (–16%).
DFM0708_008
VR Adjustment
Figure 07−08−7
DFM0708_007
V2 Adjustment
Figure 07−08−8
SUPPLEMENT 8
Operation With Airplane Systems Inoperative
07−08−01−12
REV 71, Oct 31/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
7. PERFORMANCE (CONT'D)
(3) OBSTACLE CLEARANCE
When dispatching with one hydraulic AC motor pump inoperative, the normal net take-off
flight path must be used (i.e. take-off thrust is to be used for acceleration segment).
When operating below 4,000 feet pressure altitude, apply the obstacle clearance
reference climb gradient corrections as shown on Figure 07−08−9.
NOTE
Corrections are applicable to all bleed configurations.
DFM0708_009
Obstacle Clearance Reference Climb Gradient Corrections
Figure 07−08−9
SUPPLEMENT 8
Operation With Airplane Systems Inoperative
07−08−01−13
REV 71, Oct 31/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
7. PERFORMANCE (CONT'D)
The reduced maximum level-off height for a given obstacle clearance gradient is
determined from Figure 07−08−10.
DFM0708_010
Net Take-Off Flight Path
Figure 07−08−10
SUPPLEMENT 8
Operation With Airplane Systems Inoperative
07−08−01−14
REV 71, Oct 31/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
7. PERFORMANCE (CONT'D)
Example: DETERMINATION OF THE MAXIMUM ALLOWABLE TAKE-OFF WEIGHT
FOR A GIVEN OBSTACLE
Associated Conditions:
Airport altitude = Sea level (0 ft)
Ambient temperature = 30°C (ISA + 15°C)
Reported wind = 20 knots (headwind)
Take-off flaps = 20°
APR = Off
Anti-ice = Off
10th stage bleeds = Closed
Obstacle height = 3,125 feet above the airport
Obstacle distance = 12,000 meters (39,372 feet) from
reference zero (end of the take-off
distance)
The example in Figure 07−08−10 shows that the required obstacle clearance reference
gradient is 8% and the minimum level-off height is 3,475 feet, which is below the
maximum level-off height of 3,950 feet for this reference gradient at the end of the second
segment. The gross level-off height selected for take-off must therefore not be less than
3,475 feet and not greater than 3,950 feet. A gross level-off height of 3,475 feet will be
used for the present example.
Entering the bottom end of Figure 06−04−3 from the basic Airplane Flight Manual with a
reference gradient of 8%, correcting for a 20 knot headwind, adding the gradient
correction of 1.9% from Figure 07−08−9 and correcting for APR selected OFF, gives a
gradient value of 11.4%. Combining this value with the given ambient temperature of
30°C at sea level shows that the maximum weight to achieve a reference climb gradient
of 8% is 15,100 kg (33,290 lb). Therefore, the maximum take-off weight limited by
obstacle clearance requirements is 15,100 kg (33,290 lb).
SUPPLEMENT 8
Operation With Airplane Systems Inoperative
07−08−01−15
REV 71, Oct 31/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
7. PERFORMANCE (CONT'D)
(4) APPROACH AND LANDING CLIMB
When dispatching with one hydraulic AC motor pump inoperative, and operating at or
below 4,000 feet pressure altitude, apply approach and landing climb gradient corrections
as shown on Figure 07−08−11 and Figure 07−08−12 respectively.
NOTE
Corrections are applicable to all bleed configurations.
DFM0708_011
Approach Climb Gradient Corrections
Figure 07−08−11
SUPPLEMENT 8
Operation With Airplane Systems Inoperative
07−08−01−16
REV 71, Oct 31/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
7. PERFORMANCE (CONT'D)
DFM0708_012
SUPPLEMENT 8
Operation With Airplane Systems Inoperative
07−08−01−17
REV 71, Oct 31/07
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