Climb cruise and descent performance associated with the Guarantees will include allowances for normal electrical load and for normal engine air bleed and power extraction associated with maximum cabin differential pressure as defined in Section 21-30.31 of the Specification. Cabin air conditioning management during performance demonstration as described in Subparagraph 5.3 below may be such as to optimize the Aircraft performance while meeting the minimum air conditioning requirements defined above. Unless otherwise stated no air will be bled from the engines for anti-icing.
Climb. 2. Erect scaffolds for welding and be able to tie the necessary knots
Climb. The Aircraft climbs from 1,500 feet above the departure airport altitude to 10,000 feet altitude at 250 KCAS. The Aircraft then accelerates at a rate of climb of 500 feet per minute to the recommended climb speed for minimum block fuel. The climb continues at the recommended climb speed for minimum block fuel until 0.78 Mach number is reached.
Climb. The Aircraft climbs from *** feet above the departure airport altitude to *** feet altitude at *** KCAS. The Aircraft then accelerates at a rate of climb of *** feet per minute to the recommended climb speed for minimum block fuel. The climb continues at the recommended climb speed for minimum block fuel until *** Mach number is reached. The climb continues at *** Mach number to the initial cruise altitude. The temperature is standard day during climb. Maximum climb thrust is used during climb. Cruise: The Aircraft cruises at *** Mach number. The initial cruise altitude is *** feet. A step climb or multiple step climbs of *** feet altitude may be used when beneficial to minimize fuel burn. The temperature is standard day during cruise. The cruise thrust is not to exceed maximum cruise thrust except during a step climb when maximum climb thrust may be used.
Climb. The Aircraft climbs from 1,500 feet above the departure airport altitude to 10,000 feet altitude at 283 KCAS. The Aircraft then accelerates at a rate of climb of 500 feet per minute to a climb speed of 356 KCAS. The climb continues at 356 KCAS until 0.84 Mach number is reached. The climb continues at 0.84 Mach number to the initial cruise altitude. The temperature is ISA+10 degrees C during climb. Maximum climb thrust is used during climb. Cruise: The Aircraft cruises at 0.84 Mach number. The initial cruise altitude is 29,000 feet. A step climb or multiple step climbs of 4,000 feet altitude may be used when beneficial to minimize fuel burn.
Climb. The Aircraft climbs from 1,500 feet above the departure airport altitude to 10,000 feet altitude at 250 KCAS. The Aircraft then accelerates at a rate of climb of 500 feet per minute to the recommended climb speed for minimum block fuel. The climb continues at the recommended climb speed for minimum block fuel until 0.85 Mach number is reached. The climb continues at 0.85 Mach number to the initial cruise altitude. The temperature is ISA+10°C during climb. Maximum climb thrust is used during climb. Cruise: The Aircraft cruises at the Long Range Cruise (LRC) speed. The initial cruise altitude is 39,000 feet. A step climb or multiple step climbs of 2,000 feet altitude may be used when beneficial to minimize fuel burn. The temperature is ISA+10°C during cruise. The cruise thrust is not to exceed maximum cruise thrust except during a step climb when maximum climb thrust may be used.
Climb. The Aircraft climbs from *** feet above the departure airport altitude to *** feet altitude at *** KCAS. The Aircraft then accelerates at a rate of climb of *** feet per minute to the recommended climb speed for minimum block fuel. The climb continues at the recommended climb speed for minimum block fuel until *** Mach number is reached. The climb continues at *** Mach number to the initial cruise altitude. The temperature is standard day during climb. Maximum climb thrust is used during climb. Cruise: The Aircraft cruises at *** Mach number. Boeing / United Air Lines, Inc. Proprietary
Climb cruise and descent performance associated with the Guarantees shall include allowances for normal electrical load and for normal engine air bleed and power extraction associated with maximum cabin differential pressure as defined in Section 21-30.31 of the Specification. Cabin air conditioning management during performance demonstration as described in Paragraph 8.3 may be such as to optimize the Aircraft performance while meeting the minimum air conditioning requirements defined above. Unless otherwise stated no air shall be bled from the engines for anti-icing. Cruise performance at [DELETED] ft and above is based on a center of gravity position of [DELETED] % MAC, unless otherwise stated.
Climb. The Aircraft climbs from *** feet above the departure airport altitude to *** feet altitude at *** KCAS. The Aircraft then accelerates at a rate of climb of *** feet per minute to the recommended climb speed for minimum ***. The climb continues at the recommended climb speed for minimum *** until *** Mach number is reached.
Climb. The Aircraft climbs from *** feet above the departure airport altitude to *** feet altitude at *** KCAS. The Aircraft then accelerates at a rate of climb of *** feet per minute to the recommended climb speed for minimum block fuel. The climb continues at the recommended climb speed for minimum block fuel until *** Mach number is reached. The climb continues at *** Mach number to the initial cruise altitude. The temperature is standard day during climb. Maximum climb thrust is used during climb. Cruise: The Aircraft cruises at *** Mach number. The initial cruise altitude is *** feet. A step climb or multiple step climbs of *** feet altitude may be used when beneficial to minimize fuel burn. The temperature is standard day during cruise. BOEING / UNITED AIR LINES, INC. PROPRIETARY P.A. No. 3860 AERO-B-BBA4-M09-0774C SS09-0285 Attachment A2 UAL-PA-03860-LA-1209430 Trent 1000-*** Engines The cruise thrust is not to exceed maximum cruise thrust except during a step climb when maximum climb thrust may be used.
