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DFM0708_008
VR Adjustment
Figure 06−24−8
DFM0708_007
V2 Adjustment
Figure 06−24−9
SUPPLEMENTARY PROCEDURES
Operation with Systems Inoperative
Vol. 1 06−24−15
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
8. 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 06−24−10.
NOTE
Corrections are applicable to all bleed configurations.
DFM0708_009
Obstacle Clearance Reference Climb Gradient Corrections
Figure 06−24−10
SUPPLEMENTARY PROCEDURES
Operation with Systems Inoperative
Vol. 1 06−24−16
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
8. PERFORMANCE (CONT'D)
The reduced maximum level-off height for a given obstacle clearance gradient is
determined from Figure 06−24−11.
DFM0708_010
Net Take-Off Flight Path
Figure 06−24−11
SUPPLEMENTARY PROCEDURES
Operation with Systems Inoperative
Vol. 1 06−24−17
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
8. 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 06−24−11 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 06−24−10 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).
SUPPLEMENTARY PROCEDURES
Operation with Systems Inoperative
Vol. 1 06−24−18
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
8. 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 06−24−12 and Figure 06−24−13 respectively.
NOTE
Corrections are applicable to all bleed configurations.
DFM0708_011
Approach Climb Gradient Corrections
Figure 06−24−12
SUPPLEMENTARY PROCEDURES
Operation with Systems Inoperative
Vol. 1 06−24−19
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
8. PERFORMANCE (CONT'D)
DFM0708_012
SUPPLEMENTARY PROCEDURES
Operation with Systems Inoperative
Vol. 1 06−24−20
REV 71, Oct 31/07
Landing Climb Gradient Corrections
Figure 06−24−13
CL−604 Operating Manual
PSP 604−6
8. PERFORMANCE (CONT'D)
(5) LANDING PERFORMANCE
The maximum landing weight limited by climb requirements when dispatching with one
hydraulic AC motor pump inoperative is determined from Figure 06−24−14.
Example: ANTI-ICE ON
Associated Conditions:
Temperature = –8°C
Airport pressure altitude = 6,000 ft
Wing and cowl anti-ice = On
10th stage bleeds = Closed
As shown in the example (Figure 06−24−14, Anti-ice On), the maximum landing weight
　
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