United Airlines 2012 Annual Report Download - page 401

Attachment A1
No. 6-1162-RCN-1937
GEnx-1B*** Engines
Page 22
5.3 In the event a change is made to any law, governmental regulation or requirement, or in the interpretation of any such law, governmental regulation or
requirement that affects the certification basis for the Aircraft as described in Paragraphs 3.1 or 5.2, and as a result thereof, a change is made to the
configuration and/or the performance of the Aircraft in order to obtain certification, the guarantees set forth in this Attachment shall be appropriately
modified to reflect any such change.
5.4 The takeoff portion of the mission guarantees are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway,
*** mph tires, with anti-skid operative. The takeoff performance is based on an alternate forward center of gravity limit of *** percent of the mean
aerodynamic chord. The takeoff performance is based on engine power extraction for normal operation of the air conditioning with thermal anti-icing
turned off and ***. Unbalanced field length calculations and the improved climb performance procedure will be used for takeoff as required.
5.5 The enroute one-engine-inoperative altitude guarantee is based on engine power extraction for air conditioning with one pack operating. No engine
power extraction for thermal anti-icing is provided unless otherwise specified. ***
5.6 The all-engine altitude capability guarantees, and the climb, cruise and descent portions of the mission guarantees include allowances for normal
power extraction and engine power extraction for normal operation of the air conditioning system. Normal operation of the air conditioning system
shall be defined as pack switches in the “Auto” position, the temperature control switches in the “Auto” position that results in a nominal cabin
temperature of ***°F, and all air conditioning systems operating normally. No engine power extraction for thermal anti-icing is provided unless
otherwise specified. ***
5.7 The all-engine altitude capability guarantees, and the climb, cruise and descent portions of the mission guarantees are based on an Aircraft center of
gravity location, as determined by Boeing, not to be aft of *** percent of the mean aerodynamic chord.
5.8 Performance, where applicable, is based on a fuel Lower Heating Value (LHV) of ***BTU per pound and a fuel density of *** pounds per U.S.
gallon.
P.A. No. 2484
AERO-B-BBA4-M12-0853 SS12-0424