GUARANTEE CONDITIONS. 6.1 All guaranteed performance data are based on the International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes. 6.2 The Federal Aviation Administration (FAA) regulations referred to in this Attachment are, unless otherwise specified, the 737-900ER Certification Basis regulations specified in the Type Certificate Data Sheet A16WE, Revision 40, dated April 27, 2007. 6.3 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 4.1 or 6.2, 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. 6.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantee are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 225 mph tires, with Category H brakes and anti-skid operative, and with the Aircraft center of gravity at the most forward limit unless otherwise specified. The takeoff performance is based on no engine bleed for air conditioning or thermal anti-icing and the Auxiliary Power Unit (APU) turned off unless otherwise specified. Unbalanced field length calculations and the improved climb performance procedure will be used for takeoff as required. The landing performance is based on the use of automatic spoilers. 6.5 The climb, cruise and descent portions of the mission guarantees include allowances for normal power extraction and engine bleed for normal operation of the air conditioning system. Normal electrical power extraction shall be defined as not less than a 50 kilowatts total electrical load. 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 75°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.35 pounds per square inch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 3,300 cubic feet per minute including passenger cabin recirculation (nominal recirculation is 47 percent). The APU is turned off unless otherwise specified.
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GUARANTEE CONDITIONS. 6.1 All guaranteed performance data are based on the International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes.
6.2 The Federal Aviation Administration (FAA) regulations referred to in this Attachment are, unless otherwise specified, the 737-900ER Certification Basis regulations specified in the Type Certificate Data Sheet A16WE, Revision 40, dated April 27, 2007. * Indicates that certain information contained herein has been omitted and filed separately with the Securities and Exchange Commission. Confidential treatment has been requested with respect to the omitted portions.
6.3 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 4.1 or 6.2, 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.
6.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantee are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 225 mph tires, with Category H P brakes and anti-skid operative, and with the Aircraft center of gravity at the most forward limit unless otherwise specified. The takeoff performance is based on no engine bleed for air conditioning or thermal anti-icing and the Auxiliary Power Unit (APU) turned off unless otherwise specified. Unbalanced field length calculations and the The improved climb performance procedure will be used for takeoff as required. The landing performance is based on the use of automatic spoilers.
6.5 The climb, cruise and descent portions of the mission guarantees guarantee include allowances for normal power extraction and engine bleed for normal operation of the air conditioning system. Normal electrical power extraction shall be defined as not less than a 50 kilowatts total electrical load. 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 75°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.35 pounds per square inch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 3,300 cubic feet per minute including passenger cabin recirculation (nominal recirculation is 47 percent). The APU is turned off unless otherwise specified.
6.6 The climb, cruise and descent portions of the mission guarantee are based on an Aircraft center of gravity location, as determined by Boeing, not to be aft of 19.7 percent of the mean aerodynamic chord.
6.7 Performance, where applicable, is based on a fuel Lower Heating Value (LHV) of 18,580 BTU per pound and a fuel density of 6.70 pounds per U.S. gallon.
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GUARANTEE CONDITIONS. 6.1 5.1 All guaranteed performance data are based on the International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes.
6.2 5.2 The Federal Aviation Administration (FAA) regulations referred to in this Attachment are, unless otherwise specified, the 737-900ER Certification Basis regulations specified in the Type Certificate Data Sheet A16WE, Revision 40, dated April 27, 2007.
6.3 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 P.A. No. PA-1951 AERO-B-BBA4-M12-0362C SS12-0153 Attachment to Letter Agreement ▇▇. ▇▇▇-▇▇-▇▇▇▇-▇▇-▇▇▇▇▇▇▇ *** that affects the certification basis for the Aircraft as described in Paragraphs 4.1 or 6.2Paragraph 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.
6.4 5.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantee guarantees are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 225 *** mph tires, with Category H P brakes and anti-skid operative, and with the Aircraft center of gravity at the most forward limit unless otherwise specified. The takeoff performance is based on no engine bleed for air conditioning or thermal anti-icing and the Auxiliary Power Unit (APU) turned off unless otherwise specified***. Unbalanced field length calculations and the improved climb performance procedure will be used for takeoff as required. The landing performance is based on the use of automatic spoilers.
6.5 5.5 The enroute one-engine-inoperative altitude guarantee is based on engine bleed for air conditioning with one pack operating. No engine bleed for thermal anti-icing is provided unless otherwise specified. The APU is turned off unless otherwise specified.
5.6 The speed, altitude capability, and cruise range guarantees, and the climb, cruise and descent portions of the mission guarantees include allowances for normal power extraction and engine bleed for normal operation of the air conditioning system. Normal electrical power extraction shall be defined as not less than a 50 *** kilowatts total electrical load. 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 75***°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.35 *** pounds per square inch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 3,300 *** cubic feet per minute including passenger cabin recirculation (nominal recirculation is 47 *** percent). ***.
5.7 The APU speed, altitude capability, and cruise range guarantees, and the climb, cruise and descent portions of the mission guarantees are based on an Aircraft center of gravity location of *** percent of the mean aerodynamic chord.
5.8 Performance, where applicable, is turned off unless otherwise specified.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. PA-1951 AERO-B-BBA4-M12-0362C SS12-0153 Attachment to Letter Agreement ▇▇. ▇▇▇-▇▇-▇▇▇▇-▇▇-▇▇▇▇▇▇▇ ***
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GUARANTEE CONDITIONS. 6.1 5.1 All guaranteed performance data are based on the International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes.
6.2 5.2 The Federal Aviation Administration (FAA) regulations referred to in this Attachment are, unless otherwise specified, Code of Federal Regulations 14, Part 25 amended by Amendments 25-1 through 25-117, subject to the 737-900ER Certification Basis regulations specified in approval of the Type Certificate Data Sheet A16WE, Revision 40, dated April 27, 2007Federal Aviation Administration.
6.3 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 4.1 or 6.2Paragraph 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.
6.4 5.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantee guarantees are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 225 mph [***] tires, with Category H brakes and anti-skid operative, and with the . The takeoff performance is based on an Aircraft alternate center of gravity at of 17.6 percent of the most forward limit mean aerodynamic chord unless otherwise specified. The takeoff performance is based on no engine bleed power extraction for normal operation of the air conditioning or with thermal anti-icing turned off and the Auxiliary Power Unit (APU) turned off unless otherwise specified. Unbalanced field length calculations and the improved climb performance procedure will be used for takeoff as required. The landing performance is based on the use of automatic spoilers.
6.5 5.5 The enroute one-engine-inoperative altitude guarantee is based on engine power extraction for engine and wing thermal anti-icing, and air conditioning with two packs operating. The APU is turned off unless otherwise specified.
5.6 The altitude capability and cruise range guarantees, and the climb, cruise and descent portions of the mission guarantees include allowances for normal power extraction and engine bleed power extraction for normal operation of the air conditioning system. Normal electrical power extraction shall be defined as not less than a 50 kilowatts total electrical load. 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 75°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.35 pounds per square inch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 3,300 cubic feet per minute including passenger cabin recirculation (nominal recirculation No engine power extraction for thermal anti-icing is 47 percent)provided unless otherwise specified. The APU is turned off unless otherwise specified.
5.7 Long Range Cruise (LRC) speed is defined to be the highest speed where cruise fuel mileage is 99 percent of the maximum cruise fuel mileage.
5.8 The altitude capability and cruise range 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 28 percent of the mean aerodynamic chord.
5.9 The runway loading guarantees are based on the aircraft being configured with two 4-wheel main landing gears and a dual wheel nose gear, with the main gear wheel spacing (center-to-center) of [***] in the inboard/outboard direction and [***] the forward/aft direction and equal loading for all of the main gear tires.
5.10 Performance, where applicable, is based on a fuel Lower Heating Value [***] per pound and a fuel density of [***] per U.S. gallon ([***]).
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GUARANTEE CONDITIONS. 6.1 5.1 All guaranteed performance data are based on the International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes.
6.2 5.2 The Federal Aviation Administration (FAA) regulations referred to in this Attachment are, unless otherwise specified, the 737-900ER Certification Basis regulations specified in the Type Certificate Data Sheet A16WE, Revision 40, dated April 27, 2007.. AERO-B-BBA4-M12-0320C SS12-0153 Attachment to Letter Agreement ▇▇. ▇▇▇-▇▇-▇▇▇▇▇-▇▇-▇▇▇▇▇▇▇ ***
6.3 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 4.1 or 6.2Paragraph 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.
6.4 5.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantee guarantees are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 225 *** mph tires, with Category H P brakes and anti-skid operative, and with the Aircraft center of gravity at the most forward limit unless otherwise specified. The takeoff performance is based on no engine bleed for air conditioning or thermal anti-icing and the Auxiliary Power Unit (APU) turned off unless otherwise specified***. Unbalanced field length calculations and the improved climb performance procedure will be used for takeoff as required. The landing performance is based on the use of automatic spoilers.
6.5 5.5 The enroute one-engine-inoperative altitude guarantee is based on engine bleed for air conditioning with one pack operating. No engine bleed for thermal anti-icing is provided unless otherwise specified. The APU is turned off unless otherwise specified.
5.6 The speed, altitude capability, and cruise range guarantees, and the climb, cruise and descent portions of the mission guarantees include allowances for normal power extraction and engine bleed for normal operation of the air conditioning system. Normal electrical power extraction shall be defined as not less than a 50 *** kilowatts total electrical load. 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 75***°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.35 *** pounds per square inch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 3,300 *** cubic feet per minute including passenger cabin recirculation (nominal recirculation is 47 *** percent). ***.
5.7 The APU speed, altitude capability, and cruise range guarantees, and the climb, cruise and descent portions of the mission guarantees are based on an Aircraft center of gravity location of *** percent of the mean aerodynamic chord.
5.8 Performance, where applicable, is turned off unless otherwise specified.based on a fuel Lower Heating Value (LHV) of *** BTU per pound and a fuel density of *** pounds per U.S. gallon. AERO-B-BBA4-M12-0320C SS12-0153 Attachment to Letter Agreement ▇▇. ▇▇▇-▇▇-▇▇▇▇▇-▇▇-▇▇▇▇▇▇▇ ***
Appears in 1 contract
GUARANTEE CONDITIONS. 6.1 5.1 All guaranteed performance data are based on the International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes.
6.2 5.2 The Federal Aviation Administration (FAA) regulations referred to in this Attachment are, unless otherwise specified, the 737-900ER Certification Basis regulations specified in the Type Certificate Data Sheet A16WE, Revision 4041, dated April 27July 31, 2007.
6.3 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 AERO-B-BBA4-M12-0320C SS12-0153 Attachment to Letter Agreement No. UAL-PA-03784-LA-1207868 *** that affects the certification basis for the Aircraft as described in Paragraphs 4.1 or 6.2Paragraph 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.
6.4 5.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantee guarantees are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 225 *** mph tires, with Category H P brakes and anti-skid operative, and with the Aircraft center of gravity at the most forward limit unless otherwise specified. The takeoff performance is based on no engine bleed for air conditioning or thermal anti-icing and the Auxiliary Power Unit (APU) turned off unless otherwise *** specified. Unbalanced field length calculations and the improved climb performance procedure will be used for takeoff as required. The landing performance is based on the use of automatic spoilers.
6.5 5.5 The enroute one-engine-inoperative altitude guarantee is based on engine bleed for air conditioning with one pack operating. No engine bleed for thermal anti-icing is provided unless otherwise specified. ***.
5.6 The speed, altitude capability, and cruise range guarantees, and the climb, cruise and descent portions of the mission guarantees include allowances for normal power extraction and engine bleed for normal operation of the air conditioning system. Normal electrical power extraction shall be defined as not less than a 50 *** kilowatts total electrical load. 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 75***°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.35 *** pounds per square inch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 3,300 *** cubic feet per minute including passenger cabin recirculation (nominal recirculation is 47 *** percent). ***.
5.7 The APU speed, altitude capability, and cruise range guarantees, and the climb, cruise and descent portions of the mission guarantees are based on an Aircraft center of gravity location of *** percent of the mean aerodynamic chord.
5.8 Performance, where applicable, is turned off unless otherwise specified.based on a fuel Lower Heating Value (LHV) of *** BTU per pound and a fuel density of *** pounds per U.S. gallon. AERO-B-BBA4-M12-0320C SS12-0153 Attachment to Letter Agreement ▇▇. ▇▇▇-▇▇-▇▇▇▇▇-▇▇-▇▇▇▇▇▇▇ ***
Appears in 1 contract
GUARANTEE CONDITIONS. 6.1 5.1 All guaranteed performance data are based on the International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes.
6.2 5.2 The Federal Aviation Administration (FAA) regulations referred to in this Attachment are, unless otherwise specified, the 737-900ER Certification Basis regulations specified in the Type Certificate Data Sheet A16WE, Revision 4041, dated April 27July 31, 2007.. P.A. No. PA-1951 AERO-B-BBA4-M12-0362C SS12-0153 Attachment to Letter Agreement ▇▇. ▇▇▇-▇▇-▇▇▇▇-▇▇-▇▇▇▇▇▇▇ ***
6.3 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 4.1 or 6.2Paragraph 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.
6.4 5.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantee guarantees are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 225 *** mph tires, with Category H P brakes and anti-skid operative, and with the Aircraft center of gravity at the most forward limit unless otherwise specified. The takeoff performance is based on no engine bleed for air conditioning or thermal anti-icing and the Auxiliary Power Unit (APU) turned off unless otherwise specified***. Unbalanced field length calculations and the improved climb performance procedure will be used for takeoff as required. The landing performance is based on the use of automatic spoilers.
6.5 5.5 The enroute one-engine-inoperative altitude guarantee is based on engine bleed for air conditioning with one pack operating. No engine bleed for thermal anti-icing is provided unless otherwise specified. The APU is turned off unless otherwise specified.
5.6 The speed, altitude capability, and cruise range guarantees, and the climb, cruise and descent portions of the mission guarantees include allowances for normal power extraction and engine bleed for normal operation of the air conditioning system. Normal electrical power extraction shall be defined as not less than a 50 *** kilowatts total electrical load. 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 75***°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.35 *** pounds per square inch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 3,300 *** cubic feet per minute including passenger cabin recirculation (nominal recirculation is 47 *** percent). ***.
5.7 The APU speed, altitude capability, and cruise range guarantees, and the climb, cruise and descent portions of the mission guarantees are based on an Aircraft center of gravity location of *** percent of the mean aerodynamic chord.
5.8 Performance, where applicable, is turned off unless otherwise specified.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. PA-1951 AERO-B-BBA4-M12-0362C SS12-0153 Attachment to Letter Agreement ▇▇. ▇▇▇-▇▇-▇▇▇▇-▇▇-▇▇▇▇▇▇▇ ***
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GUARANTEE CONDITIONS. 6.1 4.1 All guaranteed performance data are based on the International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes.
6.2 4.2 The Federal Aviation Administration (FAA) regulations referred to in this Attachment are, unless otherwise specified, the 737-900ER 737-*** Certification Basis regulations specified in the Type Certificate Data Sheet A16WE, Revision 40, dated April 27, 2007***.
6.3 4.3 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 4.1 or 6.2Paragraph 4.2, 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 Attachment to Letter Agreement ▇▇. ▇▇▇-▇▇-▇▇▇▇▇-▇▇-▇▇▇▇▇▇▇ CFM56-7B*** Engines guarantees set forth in this Attachment shall be appropriately modified to reflect any such change.
6.4 4.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantee guarantees are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 225 *** mph tires, with Category H *** brakes and anti-skid operative, *** minute takeoff thrust, and with the Aircraft center of gravity at the most forward limit unless otherwise specified. The takeoff performance is based on no engine bleed for air conditioning or thermal anti-icing and the Auxiliary Power Unit (APU) turned off unless otherwise specified. Unbalanced field length calculations and the improved climb performance procedure will be used for takeoff as required. The landing performance is based on the use of automatic spoilers.
6.5 4.5 The climb, cruise and descent portions of the mission guarantees include allowances for normal power extraction and engine bleed for normal operation of the air conditioning system. Normal electrical power extraction shall be defined as not less than a 50 *** kilowatts total electrical load. 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 75***°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.35 *** pounds per square inch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 3,300 *** cubic feet per minute including passenger cabin recirculation (nominal recirculation is 47 *** percent). The APU is turned off unless otherwise specified.
4.6 The climb, cruise and descent portions of the mission guarantees are based on an Aircraft center of gravity location of *** percent of the mean aerodynamic chord.
4.7 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. Attachment to Letter Agreement ▇▇. ▇▇▇-▇▇-▇▇▇▇▇-▇▇-▇▇▇▇▇▇▇ CFM56-7B*** Engines
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GUARANTEE CONDITIONS. 6.1 5.1 All guaranteed performance data are based on the International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes.
6.2 5.2 The Federal Aviation Administration (FAA) regulations referred to in this Attachment are, unless otherwise specified, the 737767-900ER 300 Certification Basis regulations specified in the Type Certificate Data Sheet A16WEA1NM, Revision 4023, dated April 27May 10, 20072004.
6.3 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 4.1 or 6.2Paragraph 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.
6.4 5.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantee guarantees are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 225 mph tires, with Category H D brakes and anti-skid operative, and with the Aircraft center of gravity at the most forward limit unless otherwise specified. The takeoff performance is based on no engine bleed for air conditioning or thermal anti-icing and the Auxiliary Power Unit (APU) turned off unless otherwise specified. Unbalanced field length calculations and the The improved climb performance procedure will be used for takeoff as required. The landing performance is based on the use of automatic spoilers.
6.5 5.5 The climb, cruise and descent portions of the mission guarantees include fuel mileage guarantee includes allowances for normal power extraction and engine bleed for normal operation of the air conditioning system. Normal electrical power extraction shall be defined as not less than a 50 140 kilowatts total electrical load. 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 75°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.35 8.6 pounds per square inch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 3,300 1,600 cubic feet per minute including passenger cabin recirculation (nominal recirculation is 47 0 percent). The APU is turned off unless otherwise specified.
5.6 The cruise fuel mileage guarantee is based on an Aircraft center of gravity location of 17 percent of the mean aerodynamic chord.
5.7 Performance, where applicable, is based on a fuel Lower Heating Value (LHV) of 18,580 BTU per pound.
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GUARANTEE CONDITIONS. 6.1 5.1 All guaranteed performance data are based on the International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes.
6.2 5.2 The Federal Aviation Administration (FAA) regulations referred to in this Attachment are, unless otherwise specified, Code of Federal Regulations 14, Part 25 amended by Amendments 25-1 through 25-117, subject to the 737-900ER Certification Basis regulations specified in approval of the Type Certificate Data Sheet A16WE, Revision 40, dated April 27, 2007Federal Aviation Administration.
6.3 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 4.1 3.1 or 6.25.2, 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.
6.4 5.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantee guarantees are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 225 *** mph tires, and with Category H brakes and anti-skid operative, and with the Aircraft center of gravity at the most forward limit unless otherwise specified. The takeoff performance is based on no an Aircraft alternate forward center of gravity limit of *** percent of the mean aerodynamic chord. The takeoff performance is based on engine bleed power extraction for normal operation of the air conditioning or with thermal anti-icing and the Auxiliary Power Unit (APU) turned off unless otherwise specified. and *** Unbalanced field length calculations and the improved climb performance procedure will be used for takeoff as required. .
5.5 The landing performance 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-ice is provided unless otherwise specified. ***
5.6 The all-engine altitude capability guarantees, and the use of automatic spoilers.
6.5 The climb, cruise and descent portions of the mission guarantees include allowances for normal power extraction and engine bleed power extraction for normal operation of the air conditioning system. Normal electrical power extraction shall be defined as not less than a 50 kilowatts total electrical load. 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 75***°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.35 pounds per square inch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 3,300 cubic feet per minute including passenger cabin recirculation (nominal recirculation is 47 percent). The APU is turned off unless otherwise specified.No engine power extraction for thermal anti-icing is
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