Common use of GUARANTEE CONDITIONS Clause in Contracts

GUARANTEE CONDITIONS. 5.1. All guaranteed performance data are based on the ICAO International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes. 5.2. The FAA Regulations (FAR) referred to in this Attachment are, unless otherwise specified, the 747-400 Certification Basis regulations specified in the Type Certificate Data Sheet A20WE, Revision B, dated June 8, 1989. 5.3. Requirement, or in the interpretation of any such law, governmental regulation or requirement that affects the certification basis for the Aircraft as described in Paragraph 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 79 Attachment to Letter Agreement No. 6-1162-DSF-082 CF6-80C2BIF Engines Page 15 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, 235 mph tires, with 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. The improved climb performance procedure will be used for takeoff as required. 5.5. 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 100 kilowatts total electrical load. Normal operation of the air conditioning system shall be defined as pack switches in the "Normal" position, the temperature control switches in the "Auto" position that results in a nominal cabin temperature of 75 degrees F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.9 pounds per square inch, with a nominal Aircraft cabin ventilation rate of 5,600 cubic feet per minute including passenger cabin recirculation. The APU is turned off unless otherwise specified. 5.6. The climb, cruise and descent portions of the mission guarantees are based on an Aircraft center of gravity location of 20 percent of the mean a aerodynamic chord. 5.7. Performance, where applicable, is based on a fuel Lower Heating value (LHV) of 18,580 BTU per pound and a fuel density of 6.75 pounds per U.S. gallon.

GUARANTEE CONDITIONS. 5.1. 3.1 All guaranteed performance data are based on the ICAO International Standard Atmosphere (ISA) and specified variations therefrom; altitudes unless otherwise specified. Altitudes are pressure altitudes. 5.2. 3.2 The FAA Regulations (FAR) referred to in this Attachment are, unless otherwise specified, the 747-400 Certification Basis regulations specified in the Aircraft Type Certificate Data Sheet A20WE, Revision B, dated June 8, 1989.Sheet. * Indicates that material has been omitted and confidential treatment has been requested therefor. All such omitted material has been filed separately with the SEC pursuant to Rule 24b-2. -------------------------------------------------------------------------------- ATTACHMENT "G" PERFORMANCE * GUARANTEE -------------------------------------------------------------------------------- 5.3. Requirement, or in the interpretation of any such law, governmental regulation or requirement that affects the certification basis for the Aircraft as described in Paragraph 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 79 Attachment to Letter Agreement No. 6-1162-DSF-082 CF6-80C2BIF Engines Page 15 Attachment shall be appropriately modified to reflect any such change. 5.4. 3.3 The takeoff portion of the mission and landing guarantees are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 235 mph tires, and with automatic anti-skid operative, and with the Aircraft center of gravity at the most forward limit operative 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 offoff unless otherwise specified. The improved climb performance procedure will be used for takeoff as required. The landing data is based on the use of automatic spoilers. 5.5. 3.4 The cruise specific air range, speed and the climb, cruise and descent portions of the mission guarantees include allowances for normal electrical 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 100 kilowatts 37 kW total electrical loadand hydraulic loads. Normal operation of the air conditioning system shall be defined as pack switches operation in the "Normal" positionautomatic mode, with the temperature control switches in the "Auto" position that results in set to maintain a nominal cabin temperature of 75 degrees F(Degree)F, and all air conditioning systems operating normally. This operation nominally allows a sea level cabin altitude to be maintained up to 19,500ft and a maximum cabin pressure differential of 8.9 7.8 pounds per square inchinch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 5,600 cubic feet 1,100 cu.ft per minute min at 35,000 ft including passenger cabin recirculationrecirculation (nominal recirculation is 42 % not considering gasper flow). The APU is turned off unless u▇▇▇▇▇ otherwise specified. 5.6. 3.5 The cruise specific air range, speed and the climb, cruise cruise, and descent portions of the mission guarantees are based on an Aircraft center of gravity location of 20 percent 15% of the mean a aerodynamic chord. 5.7. 3.6 Performance, where applicable, is based on a fuel Lower Heating value Value (LHV) of 18,580 BTU per pound and a fuel density of 6.75 6.70 pounds per U.S. gallon.

GUARANTEE CONDITIONS. 5.1. 6.1 All guaranteed performance data are based on the ICAO International Standard Atmosphere (ISA) and specified variations therefrom; altitudes are pressure altitudes. 5.2. 6.2 The FAA Regulations Federal Aviation Administration (FARFAA) regulations referred to in this Attachment are, unless otherwise specified, the 747737-400 900ER Certification Basis regulations specified in the Type Certificate Data Sheet A20WEA16WE, Revision B40, dated June 8April 27, 19892007. 5.3. Requirement6.3 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 Paragraph 5.2Paragraphs 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 79 Attachment to Letter Agreement No. 6-1162-DSF-082 CF6-80C2BIF Engines Page 15 Attachment shall be appropriately modified to reflect any such change. 5.4. 6.4 The takeoff and landing guarantees, and the takeoff portion of the mission guarantees guarantee are based on hard surface, level and dry runways with no wind or obstacles, no clearway or stopway, 235 225 mph tires, with Category 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 offoff unless otherwise specified. The improved climb performance procedure will be used for takeoff as required. The landing performance is based on the use of automatic spoilers. 5.5. 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 100 50 kilowatts total electrical load. Normal operation of the air conditioning system shall be defined as pack switches in the "NormalAuto" position, the temperature control switches in the "Auto" position that results in a nominal cabin temperature of 75 degrees 75°F, and all air conditioning systems operating normally. This operation allows a maximum cabin pressure differential of 8.9 8.35 pounds per square inchinch at higher altitudes, with a nominal Aircraft cabin ventilation rate of 5,600 3,300 cubic feet per minute including passenger cabin recirculationrecirculation (nominal recirculation is 47 percent). The APU is turned off unless otherwise specified. 5.6. 6.6 The climb, cruise and descent portions of the mission guarantees guarantee are based on an Aircraft center of gravity location location, as determined by Boeing, not to be aft of 20 19.7 percent of the mean a aerodynamic chord. 5.7. 6.7 Performance, where applicable, is based on a fuel Lower Heating value Value (LHV) of Attachment to Letter Agreement 6-1162-SCR-112 CFM56-7B26E Engines Page #PageNum# 18,580 BTU per pound and a fuel density of 6.75 6.70 pounds per U.S. gallon.