US Airways 2007 Annual Report Download - page 782

1 AIRCRAFT CONFIGURATION
The Guarantees defined below are applicable to the A330-200 Aircraft powered as described in the Standard Specification Ref. ** as amended by
Specification Change Notices (SCN) for:
a) Design Weights to:
Maximum Design Take-Off Weight **
Maximum Design Landing Weight **
Maximum Design Zero Fuel Weight **
b) Fitting of Rolls-Royce Trent 772B EP engines
for deliveries from ** onwards without taking into account any further changes thereto as provided in the Agreement, herein after referred as "the
Specification".
2 MISSION GUARANTEE
2.1 The A330-200 Aircraft will be capable of carrying a fixed zero fuel weight of ** over a guaranteed still air stage distance of ** when operated under
the conditions defined below:
2.2 The departure airport conditions are such to allow the required Takeoff Weight to be used without any restriction.
The destination airport conditions are such to allow the required Landing Weight to be used without any restriction.
2.3 An allowance of ** is included for take-off and climb to ** altitude with acceleration to climb speed at a temperature of **.
2.4 Climb from ** pressure altitude up to cruise altitude using maximum climb thrust, cruise at a fixed Mach number of ** at pressure altitudes of ** and
descent to 1,500 ft pressure altitude are conducted in ISA+10°C conditions. Climb and descent speeds below ** will be ** CAS.
2.5 An allowance of ** of fuel is considered for approach and landing at the destination airport.
2.6 Stage distance is defined as the distance covered during climb, cruise and descent as defined in paragraphs 2.4 above.
2.7 At the end of approach and landing ** of usable fuel will remain in the tanks. This represents the estimated fuel required for:
LA 8D — 2 of 9
USA — Airbus A330 Purchase Agreement
EXECUTION PRIVILEGED AND CONFIDENTIAL
**Confidential Treatment Requested.