US Airways 2007 Annual Report Download - page 815

1 AIRCRAFT CONFIGURATION
1.1 The Guarantees defined below are applicable to the A340-300 Aircraft as described in the Standard Specification Ref. ** as amended by the
Specification Change Notices (SCN's) for:
(i) Change in Design Weights to:
Maximum Design Take-Off Weight **
Maximum Design Landing Weight **
Maximum Design Zero Fuel Weight **
(ii) fitting of CFM International CFM56-5C4/P Bump Engines
herein after referred as "the Specification" without taking into account any further changes thereto as provided in the Agreement.
2 GUARANTEED PERFORMANCE
2.1 Take-off Field Length
FAR take-off field length ("TOFL") at an Aircraft gross weight of ** at the start of Take-Off Distance Available (TODA) at Sea Level pressure altitude
in ISA+15°C conditions shall be not more than a guaranteed value of **.
2.2 Second Segment Climb
The Aircraft shall meet FAR 25 regulations for one engine inoperative climb after take-off, undercarriage retracted, at a weight corresponding to the
stated weight at the start of ground run, at the altitude and temperature, and in the configuration of flap angle and safety speed required to comply with
the performance guaranteed in paragraph 2.1 and 2.3.
2.3 Take-off Weight
2.3.1 When operated under the following conditions **
Pressure altitude : **
Ambient temperature : **
Take-off run available : **
Take-off distance available : **
Accelerate-stop distance available : **
Slope : **
Wind : **
Line-up allowance TODA/TORA : **
Line-up allowance ASDA : **
Obstacles (Height/Distance above/from start of TODA): **
LA 8F — 2 of 24
USA — Airbus A330 Purchase Agreement
EXECUTION
**Confidential Treatment Requested.
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