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Example:
Indicated airspeed (IAS) = 300 KIAS
Indicated altitude (HI) = 25,000 feet
Position correction (ΔV) = –1.5 knots
Calibrated airspeed (CAS) = IAS + ΔV
= 300 + (–1.5)
= 298.5 KCAS
PERFORMANCE
General
06−01−10
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
3. CALIBRATION (CONT'D)
DFM0601_005 CHP1−09−03JUL95
PERFORMANCE
General
06−01−11
REV 66, Feb 01/07
Airspeed Position Error Correction − Standby Airspeed Indicator (Flaps Up)
Figure 06−01−5
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
3. CALIBRATION (CONT'D)
D. Altitude Position Error Correction – Standby Altimeter (Flaps Up)
Figure 06−01−6 provides the altitude position error correction for varying conditions of
indicated airspeed and indicated pressure altitude, for the standby altimeter.
Example:
Indicated airspeed (IAS) = 300 KIAS
Indicated altitude (HI) = 25,000 feet
Position correction (ΔH) = –95 feet
True pressure altitude (Hp) =HI + ΔH
= 25,000 + (–95)
= 24,905 feet
PERFORMANCE
General
06−01−12
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
3. CALIBRATION (CONT'D)
DFM0601_006 CHP1−10−03JUL95
PERFORMANCE
General
06−01−13
REV 66, Feb 01/07
Altitude Position Error Correction − Standby Altimeter (Flaps Up)
Figure 06−01−6
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
3. CALIBRATION (CONT'D)
E. Airspeed Position Error Correction – Standby Airspeed Indicator (Flaps 20°, 30°, 45°)
Figure 06−01−7 provides the airspeed position error corrections for varying conditions of flap
setting and varying indicated airspeed, for the standby airspeed indicator.
Example:
Indicated airspeed (IAS) = 180 KIAS
Flaps setting = 20°
Airspeed position correction (ΔV) = 0.7 knots
Calibrated airspeed (CAS) = IAS + ΔV
= 180 + (0.7)
= 180.7 KCAS
PERFORMANCE
General
06−01−14
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
3. CALIBRATION (CONT'D)
DFM0601_007 CHP1−11−22JUN95
PERFORMANCE
General
06−01−15
REV 66, Feb 01/07
Airspeed Position Error Correction − Standby Airspeed Indicator (Flaps 20°, 30°, 45°)
Figure 06−01−7
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
3. CALIBRATION (CONT'D)
F. Altitude Position Error Correction – Standby Altimeter (Flaps 20°, 30°, 45°)
Figure 06−01−8 provides the altitude position error corrections for varying conditions of flap
setting and varying indicated airspeed, for the standby altimeter.
Example:
Indicated altitude (HI) = 5,000 feet
Indicated airspeed (IAS) = 180 KIAS
Flaps setting = 20°
Position correction (ΔH) = 17 feet
True pressure altitude (Hp) =HI + ΔH
= 5,000 + (17)
= 5,017 feet
PERFORMANCE
General
06−01−16
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
3. CALIBRATION (CONT'D)
DFM0601_008 CHP1−12−04JUL95
PERFORMANCE
General
06−01−17
REV 66, Feb 01/07
Altitude Position Error Correction − Standby Altimeter (Flaps 20°, 30°, 45°)
Figure 06−01−8
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
4. FLIGHT CAPABILITIES
A. Reference Stall Speed – Flaps 0°/Landing Gear Up
The reference stall speeds for a flaps 0° and landing gear up configuration at varying gross
weights and pressure altitude, are provided in Figure 06−01−9. This chart is based upon the
most forward centre of gravity limit at flaps 0°. The speeds shown are valid only for pressure
altitudes at and below 15,000 feet. The reference stall speed, VSR, is equal to VS1g multiplied
by a factor of 1.02.
Example:
Gross weight = 19,500 kg (42,990 lb)
Flaps setting = 0°
Landing gear = Up
Pressure altitude = 6,000 feet
Reference stall speed = 139.4 KCAS
PERFORMANCE
General
06−01−18
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
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庞巴迪挑战者604飞机飞行手册CL604 Airplane Flight Manual 2(35)
