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310/350 237 239 238 211 237 239 237 210 235 237 232 202
330/370 216 218 217 192 215 217 215 191 214 216 213 185
350/390 196 197 196 174 195 197 195 173 194 196 193 167
370/410 178 178 179 160 177 178 177 158 176 177 174 151
BLEED CORRECTIONS
ENGINE ANTI ICE ON TOTAL ANTI ICE ON PACK FLOWHI AND/OR
CARGO COOL ON
≤􀀃ISA􀀃+4􀀃-􀀃100􀀃ft􀀃-􀀃200􀀃ft􀀃-􀀃250􀀃ft􀀃
ISA +20 -2 500 ft -3 000 ft - 500 ft
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
A330/A340 FLEET PER-CRZ-AEO-ALT-10 P 3/8
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
A330/A340 FLEET PER-CRZ-AEO-ALT-10 P 4/8
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
A330/A340 FLEET PER-CRZ-AEO-ALT-10 P 5/8
FCOM 19 AUG 10
CRUISE LEVEL CHARTS
Applicable to: ,
These charts have been established for a center of gravity at 37 % MAC.
Maximum and optimum altitudes are given for different temperatures at long range speed, M 0.82,
M 0.83 and M 0.84
Note: 1. Optimum and maximum altitudes curves do not cover for M 0.82, M 0.83 and M 0.84
the whole weight range because above a given weight these Mach numbers cannot be
maintained, whatever the altitude.
2. The n =1.3 g (n = 1.4 g) curve indicates the buffet margin.
OPTIMUM WEIGHT FOR 4 000 FT STEP CLIMB
WEIGHT (1 000 kg)
≤ ISA +10 ISA +15 ISA +20
STEP
CLIMB
FROM/TO LRM .80 M.82 M.84 LR M .80 M.82 M .84 LRM .80 M.82 M.84
310/350 235 237 240 217 235 237 234 215 235 230 226 207
330/370 214 216 218 198 214 216 212 195 214 209 204 189
350/390 194 195 198 180 194 195 193 177 194 189 186 171
370/410 176 177 180 163 176 177 175 160 176 171 168 155
BLEED CORRECTIONS
ENGINE ANTI ICE ON TOTAL ANTI ICE ON PACK FLOWHI AND/OR
CARGO COOL ON
≤􀀃ISA􀀃+7􀀃-􀀃300􀀃ft􀀃-􀀃500􀀃ft􀀃-􀀃300􀀃ft􀀃
ISA +15 - 400 ft - 900 ft - 300 ft
ISA +20 -1 000 ft -2 000 ft - 500 ft
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
A330/A340 FLEET PER-CRZ-AEO-ALT-10 P 6/8
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
A330/A340 FLEET PER-CRZ-AEO-ALT-10 P 7/8
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
Intentionally left blank
A330/A340 FLEET PER-CRZ-AEO-ALT-10 P 8/8
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
A330/A340 FLEET PER-CRZ-AEO-ALT-20 P 1/8
FCOM 19 AUG 10
WIND ALTITUDE TRADE FOR CONSTANT SPECIFIC RANGE
WIND ALTITUDE TRADE FOR CONSTANT SPECIFIC RANGE
Applicable to:
GIVEN : Weight : 220 000 kg (485 000 lb)
Wind at FL 350 : 10 kt head
FIND : Minimum wind difference to descend to FL 310 : (21 - 1) = 20 kt
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
A330/A340 FLEET PER-CRZ-AEO-ALT-20 P 2/8
FCOM 19 AUG 10
RESULTS : Descent to FL 310 may be considered provided the tail wind at this altitude is more
than (20 - 10) = 10 kt.
GIVEN : Weight : 220 000 kg (485 000 lb)
Wind at FL 350 : 10 kt head
FIND : Minimum wind difference to descend to FL 310 : (22 - 1) = 21 kt
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
A330/A340 FLEET PER-CRZ-AEO-ALT-20 P 3/8
FCOM 19 AUG 10
RESULTS : Descent to FL 310 may be considered provided the tail wind at this altitude is more
than (21 - 10) = 11 kt.
GIVEN : Weight : 200 000 kg (441 000 lb)
Wind at FL 350 : 10 kt head
FIND : Minimum wind difference to descend to FL 310 : (25 - 3) = 22 kt
RESULTS : Descent to FL 310 may be considered provided the tail wind at this altitude is more
than (22 - 10) = 12 kt.
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
A330/A340 FLEET PER-CRZ-AEO-ALT-20 P 4/8
FCOM 19 AUG 10
WIND ALTITUDE TRADE FOR CONSTANT SPECIFIC RANGE
Applicable to: ,
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
CRUISE
ALL ENGINES OPERATIVE - ALTITUDE
　
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