exv10w159ws






Exhibit 10.159S




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 1




MODEL 777-300ER PERFORMANCE GUARANTEES




FOR AMERICAN AIRLINES, INC.



	 	 	 
	SECTION	 	CONTENTS
	1

	 	AIRCRAFT MODEL APPLICABILITY
	 
	 	 
	2

	 	FLIGHT PERFORMANCE
	 
	 	 
	3

	 	MANUFACTURER’S EMPTY WEIGHT
	 
	 	 
	4

	 	SOUND LEVELS
	 
	 	 
	5

	 	AIRCRAFT CONFIGURATION
	 
	 	 
	6

	 	GUARANTEE CONDITIONS
	 
	 	 
	7

	 	GUARANTEE COMPLIANCE
	 
	 	 
	8

	 	EXCLUSIVE GUARANTEES






					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 






 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 2





	1	 	AIRCRAFT MODEL APPLICABILITY
	 
	 	 	The guarantees contained in this Attachment (the “Performance Guarantees”) are
applicable to [CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH THE
COMMISSION PURSUANT TO A REQUEST FOR CONFIDENTIAL TREATMENT].
	 
	2	 	FLIGHT PERFORMANCE
	 
	2.1	 	Takeoff
	 
	 	 	The FAA approved takeoff field length at a gross weight at the start
of the ground roll of 775,000 pounds, at a temperature of 30°C, at a
sea level altitude, with an alternate forward center of gravity limit
of 20 percent of the mean aerodynamic chord, and using maximum takeoff
thrust, shall not be more than the following guarantee value:






[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH THE
COMMISSION PURSUANT TO A REQUEST FOR CONFIDENTIAL
TREATMENT]




	2.2	 	Landing
	 
	 	 	The FAA approved landing field length at a gross weight of 554,000
pounds and at a sea level altitude, shall not be more than the
following guarantee value:






[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH THE
COMMISSION PURSUANT TO A REQUEST FOR CONFIDENTIAL
TREATMENT]




	2.3	 	Mission
	 
	2.3.1	 	Mission Payload
	 
	 	 	The payload for a stage length of 7,458 nautical miles in still air (representative
of a Chicago to Hong Kong route) using the conditions and operating rules defined
below, shall not be less than the following guarantee value:





					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 3



 
	 	 	 

	 

	 	[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH THE

COMMISSION PURSUANT TO A REQUEST FOR CONFIDENTIAL

TREATMENT]
	 
	 	 
	Conditions and operating rules:
	 
	 	 
	Stage Length:

	 	The stage length is defined as the sum of the
distances for the climbout maneuver, climb,
cruise, and descent.
	 
	 	 
	Takeoff:

	 	[CONFIDENTIAL PORTION OMITTED AND FILED
SEPARATELY WITH THE COMMISSION PURSUANT TO A
REQUEST FOR CONFIDENTIAL TREATMENT].
	 
	 	 
	 

	 	The takeoff gross weight is not limited by the
airport conditions.
	 
	 	 
	 

	 	Maximum takeoff thrust is used for the takeoff.
	 
	 	 
	 

	 	The takeoff gross weight shall conform to FAA
Regulations.
	 
	 	 
	Climbout Maneuver:

	 	Following the takeoff to 35 feet, the Aircraft
accelerates to 262 KCAS while climbing to 1,500
feet above the departure airport altitude and
retracting flaps and landing gear.
	 
	 	 
	Climb:

	 	The Aircraft climbs from 1,500 feet above the
departure airport altitude to 10,000 feet
altitude at 262 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 to the initial
cruise altitude.
	 
	 	 
	 

	 	The temperature is standard day during climb.
	 
	 	 
	 

	 	Maximum climb thrust is used during climb.






					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 4





	 	 	 

	Cruise:

	 	The Aircraft cruises at 0.84 Mach number.
	 
	 	 
	 

	 	The initial cruise altitude is 28,000 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 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.
	 
	 	 
	Descent:

	 	The Aircraft descends from the final cruise
altitude at 250 KCAS to an altitude of 1,500 feet
above the destination airport altitude.
	 
	 	 
	 

	 	Throughout the descent, the cabin pressure will
be controlled to a maximum rate of descent
equivalent to 300 feet per minute at sea level.
	 
	 	 
	 

	 	The temperature is standard day during descent.
	 
	 	 
	Approach
and Landing Maneuver:

	 	The Aircraft decelerates to the final approach
speed while extending landing gear and flaps,
then descends and lands.
	 
	 	 
	 

	 	The destination airport altitude is 28 feet.
	 
	 	 
	Fixed Allowances:

	 	For the purpose of this guarantee and for the
purpose of establishing compliance with this
guarantee, the following shall be used as fixed
quantities and allowances:
	 
	 	 
	 

	 	Taxi-Out:
	 

	 	[CONFIDENTIAL PORTION OMITTED AND FILED

SEPARATELY WITH THE COMMISSION PURSUANT TO A

REQUEST FOR CONFIDENTIAL TREATMENT]







					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 5





	 	 	 

	 

	 	Takeoff and Climbout Maneuver:
	 

	 	[CONFIDENTIAL PORTION OMITTED AND FILED

SEPARATELY WITH THE COMMISSION PURSUANT TO A

REQUEST FOR CONFIDENTIAL TREATMENT]

	 
	 	 
	 

	 	Approach and Landing Maneuver:
	 

	 	 [CONFIDENTIAL PORTION OMITTED AND FILED

SEPARATELY WITH THE COMMISSION PURSUANT TO A

REQUEST FOR CONFIDENTIAL TREATMENT]

	 
	 	 
	 

	 	Taxi-In (shall be consumed from the reserve

[CONFIDENTIAL PORTION OMITTED AND FILED

SEPARATELY WITH THE COMMISSION PURSUANT TO A

REQUEST FOR CONFIDENTIAL TREATMENT]

	 
	 	 
	 

	 	Usable reserve fuel remaining upon completion of
the approach and landing maneuver: 
 [CONFIDENTIAL
PORTION OMITTED AND FILED SEPARATELY WITH THE
COMMISSION PURSUANT TO A REQUEST FOR CONFIDENTIAL
TREATMENT]
	 
	 	 
	 

	 	[CONFIDENTIAL PORTION OMITTED AND FILED
SEPARATELY WITH THE COMMISSION PURSUANT TO A
REQUEST FOR CONFIDENTIAL TREATMENT].







	2.3.2	 	Mission Block Fuel
	 
	 	 	The block fuel for a stage length of 7,458 nautical miles in still air
(representative of a Chicago to Hong Kong route) with a 70,920 pound payload using
the conditions and operating rules defined below, shall not be more than the
following guarantee value:






NOMINAL: [CONFIDENTIAL PORTION




TOLERANCE: OMITTED AND FILED




GUARANTEE: SEPARATELY WITH THE



					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 6





COMMISSION PURSUANT TO A REQUEST FOR CONFIDENTIAL
TREATMENT]



	 	 	 

	Conditions and operating rules are the same as Paragraph 2.3.1 except as follows:
	 
	 	 
	Block Fuel:

	 	The block fuel is defined as the sum of the fuel used
for taxi-out, takeoff and climbout maneuver, climb,
cruise, descent, approach and landing maneuver, and
taxi-in.
	 
	 	 
	Takeoff:

	 	[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH
THE COMMISSION PURSUANT TO A REQUEST FOR CONFIDENTIAL
TREATMENT].
	 
	 	 
	 

	 	The takeoff gross weight is not limited by the airport
conditions.
	 
	 	 
	Climb:

	 	The Aircraft climbs from 1,500 feet above the departure
airport altitude to 10,000 feet altitude at 262 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 to the initial cruise altitude.
	 
	 	 
	Cruise:

	 	The initial cruise altitude is 30,000 feet.
	 
	 	 
	 

	 	A step climb or multiple step climbs of 2,000 feet
altitude may be used when beneficial to minimize fuel
burn.
	 
	 	 
	Fixed Allowances:

	 	For the purpose of this guarantee and for the purpose of
establishing compliance with this guarantee, the
following shall be used as fixed quantities and
allowances:






					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 7





	 	 	 

	 

	 	Operational Empty Weight, OEW (Paragraph 2.3.4):
	 

	 	[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH

THE COMMISSION PURSUANT TO A REQUEST FOR CONFIDENTIAL

TREATMENT]
	 
	 	 
	 

	 	Taxi-Out:
	 

	 	Fuel 1,050 Pounds

	 
	 	 
	 

	 	Takeoff and Climbout Maneuver:
	 

	 	[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH

THE COMMISSION PURSUANT TO A REQUEST FOR CONFIDENTIAL

TREATMENT]

	 
	 	 
	 

	 	Approach and Landing Maneuver:
	 

	 	[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH

THE COMMISSION PURSUANT TO A REQUEST FOR CONFIDENTIAL

TREATMENT]

	 
	 	 
	 

	 	Taxi-In (shall be consumed from the reserve fuel):
	 

	 	Fuel 350 Pounds

	 
	 	 
	 

	 	Usable reserve fuel remaining upon completion of the
approach and landing maneuver: [CONFIDENTIAL PORTION
OMITTED AND FILED SEPARATELY WITH THE COMMISSION
PURSUANT TO A REQUEST FOR CONFIDENTIAL TREATMENT]






					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 8






	2.3.3	 	Manufacturer’s Empty Weight Basis
	 
	 	 	The Manufacturer’s Empty Weight (MEW) derived in Paragraph 2.3.4 is the basis for
the mission guarantees of Paragraphs 2.3.1 and 2.3.2.





					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 





Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 9




2.3.4 777-300ER Weight Summary — American Airlines



Standard Model Specification MEW



[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH THE COMMISSION PURSUANT
TO A REQUEST FOR CONFIDENTIAL TREATMENT]



[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH THE COMMISSION PURSUANT
TO A REQUEST FOR CONFIDENTIAL TREATMENT]



American Airlines Manufacturer’s Empty Weight (MEW)



Standard and Operational Items Allowance
(Paragraph 2.3.5)



American Airlines Operational Empty Weight (OEW)




	 	 	 	 	 	 	 	 	 	 	 	 	 
	 	 	Quantity	 	 	Pounds	 	 	Pounds	 
	[CONFIDENTIAL
PORTION OMITTED AND
FILED SEPARATELY WITH
THE COMMISSION
PURSUANT TO A REQUEST
FOR CONFIDENTIAL
TREATMENT]
	 	 	 	 	 	 	 	 	 	 	 	 






					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 10





	2.3.5	 	Standard and Operational Items Allowance





	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	 	 	Qty	 	 	Pounds	 	 	Pounds	 	 	Pounds	 
	[CONFIDENTIAL PORTION OMITTED AND FILED
SEPARATELY WITH THE COMMISSION PURSUANT TO A
REQUEST FOR CONFIDENTIAL TREATMENT]
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Standard Items Allowance
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Unusable Fuel
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Oil
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Oxygen Equipment
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Passenger Portable
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Miscellaneous Equipment
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	First Aid Kits
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Crash Axe
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Megaphones
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Flashlights
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Smoke Goggles
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Smoke Hoods
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Fire Gloves
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Galley Structure & Fixed Inserts
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	[CONFIDENTIAL PORTION OMITTED AND FILED
SEPARATELY WITH THE COMMISSION PURSUANT TO A
REQUEST FOR CONFIDENTIAL TREATMENT]
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Operational Items Allowance
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Crew and Crew Baggage
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Flight Crew (Inc. Baggage)
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Cabin Crew (Inc. Baggage)
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Flight Crew Briefcase
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Catering Allowance: Pacific Meal Service
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	First Class
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Business Class
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Economy Class
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Passenger Service Equipment
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Potable Water -.
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Waste Tank Disinfectant
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Emergency Equipment (Incl. Overwater Equip.)
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Slide Rafts
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Life Vests
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Locator Transmitter
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Cargo System
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Containers
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 
	Total Standard and Operational Items Allowance
	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 	 






					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 11





	3	 	MANUFACTURER’S EMPTY WEIGHT
	 
	 	 	The Manufacturer’s Empty Weight (MEW) is guaranteed not to exceed the value in
Section 03-60-00 of Detail Specification TBD plus one percent.
	 
	4	 	SOUND LEVELS
	 
	4.1	 	Community Sound Levels
	 
	4.1.1	 	Certification
	 
	 	 	The Aircraft shall be certified in accordance with the requirements of 14CFR Part
36, Stage 4 and ICAO Annex 16, Volume 1, Chapter 4.
	 
	4.2	 	Interior Sound Levels in Flight






[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH THE COMMISSION
PURSUANT TO A REQUEST FOR CONFIDENTIAL TREATMENT]



					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 





Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 12





	4.3	 	Ramp Sound Levels






[CONFIDENTIAL PORTION OMITTED AND FILED SEPARATELY WITH THE COMMISSION
PURSUANT TO A REQUEST FOR CONFIDENTIAL TREATMENT]




	5	 	AIRCRAFT CONFIGURATION
	 
	5.1	 	The guarantees contained in this Attachment are based on the Aircraft configuration as
defined in the original release of Detail Specification TBD (hereinafter referred to as the
Detail Specification). Appropriate adjustment shall be made for changes in such Detail
Specification approved by the Customer and Boeing or otherwise allowed by the Purchase
Agreement which cause changes to the flight performance, sound levels, and/or weight and
balance of the Aircraft. Such adjustment shall be accounted for by Boeing in its evidence of
compliance with the guarantees.
	 
	5.2	 	The guarantee payload of Paragraph 2.3.1 will be adjusted by Boeing for the effect of the
following on OEW and the Manufacturer’s Empty Weight guarantee of Section 3 will be adjusted
by Boeing for the following in its evidence of compliance with the guarantees:
	 
	 	 	(1) Changes to the Detail Specification or any other changes mutually agreed upon
between the Customer and Boeing or otherwise allowed by the Purchase Agreement.
	 
	 	 	(2) The difference between the component weight allowances given in Appendix IV of
the Detail Specification and the actual weights.
	 
	6	 	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 777-300ER Certification Basis regulations specified in the
Type Certificate Data Sheet T00001SE, dated March 16, 2004.
	 
	6.3	 	In the event a change is made to any law, governmental regulation or requirement, or in the
interpretation of any such law,





					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 13





	 	 	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, 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 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 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 212 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 8.6 pounds per square inch at higher
altitudes, with a nominal Aircraft cabin ventilation rate of 10,300 cubic feet per minute
including passenger cabin recirculation (nominal recirculation is 50 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 of 30 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 6.7 pounds per U.S. gallon.
	 
	6.8	 	Sound pressure levels are measured in decibels (dB) referred to the standard reference
pressure of 20 micro Pascals per ISO 1683-





					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 14





	 	 	1983 (E). Noise data shall be acquired and reduced at preferred one-third octave
band frequencies given in ISO 266-1997(E), for the 24 bands with center frequencies
of 50 Hz to 10,000 Hz, inclusively. Octave band sound pressure levels (OBSPL) at
the eight center band frequencies defined in ISO 266-1997(E) from 63 Hz to 8,000
Hz, inclusively, are determined from the appropriate one-third octave band sound
pressure levels per section 6 of ISO 5129-20001(E). A-weighted (dBA) sound levels
are defined in Section 6 of ISO 5129-2001(E). The one-third octave band sound
pressure levels are weighted per Section 5.4 of IEC 61672-1 to represent typical
human ear response.
	 
	6.9	 	The guarantee for interior sound levels in flight pertains to normal operation of an Aircraft
in cruise during straight and level flight at an altitude of 35,000 feet and 0.84 Mach number.
The Aircraft shall have a complete interior installation including standard thermal/acoustic
insulation, all lining and partition panels, a full ship set of fabric upholstered seats and
floor covering in the passenger cabin and flight deck consisting of a carpet. All BFE
operable equipment, including in-flight entertainment systems, shall be turned off. All
operable galley equipment shall be turned off. The interior configuration is defined in LOPA
B7712788. The pilot’s inboard ear is defined as the captain’s (flight deck left seat) inboard
ear. The procedures used for the measurement of sound levels shall be equivalent to those in
ISO 5129.





					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 15





	6.10	 	The guarantee for ramp sound levels pertains to a parked Aircraft during in-service turn
around with the APU (with optional APU exhaust muffler installed), all environmental control
system packs, environmental control system recirculation fans, electronic equipment cooling
fans and vent fans operating, and with the main propulsion engines and BFE equipment not
operating. The guarantee for ramp sound levels on the 20-meter perimeter pertains to sound
levels measured on a rectangular perimeter 20 meters on either side of the Aircraft
centerline, 20 meters forward of the nose of the fuselage and 20 meters aft of the tail of the
fuselage. The guarantees pertain to APU and environmental control system pack operation at an
outside ambient temperature of 25°C(77°F). The procedures used for the measurement of ramp
sound levels shall be equivalent to those in ICAO Annex 16.
	 
	7	 	GUARANTEE COMPLIANCE
	 
	7.1	 	Compliance with the guarantees of Sections 2, 3 and 4 shall be based on the conditions
specified in those sections, the Aircraft configuration of Section 5 and the guarantee
conditions of Section 6.
	 
	7.2	 	Compliance with the takeoff and landing guarantees, the takeoff portion of the mission
guarantee, and the community sound level guarantees shall be based on the FAA approved
Airplane Flight Manual for the Model 777-300ER.
	 
	7.3	 	Compliance with the takeoff guarantee and the takeoff portion of the mission guarantee shall
be shown using an alternate forward center of gravity limit of 20 percent of the mean
aerodynamic chord.
	 
	7.4	 	Compliance with the climb, cruise and descent portions of the mission guarantee shall be
established by calculations based on flight test data obtained from an aircraft in a
configuration similar to that defined by the Detail Specification.
	 
	7.5	 	The OEW used for compliance with the mission payload guarantee shall be the actual MEW plus
the Standard and Operational Items Allowance in Paragraph 03-60-00 of the Detail
Specification.
	 
	7.6	 	Compliance with the Manufacturer’s Empty Weight guarantee shall be based on information in
the “Weight and Balance Control and Loading Manual — Aircraft Report.”





					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY	 	 





 









 




Attachment to Letter Agreement

No. AAL-PA-1980-LA-1003346

GE90-115BL Engines

Page 16





	7.7	 	The data derived from tests shall be adjusted as required by conventional methods of
correction, interpolation or extrapolation in accordance with established engineering
practices to show compliance with these guarantees.
	 
	7.8	 	Compliance with the guarantee for interior sound levels in flight shall be demonstrated by
Boeing Document D047W263-01. This compliance documentation is based on sound level surveys on
production 777-300ER aircraft acoustically similar to the Buyer’s Aircraft. Compliance with
the guarantee for ramp sound levels shall be demonstrated by Boeing Document D047W227. This
compliance documentation is based on a sound level survey on production 777 aircraft
acoustically similar to the Buyer’s Aircraft. The measured data may be adjusted for sound
level increases resulting from Buyer Furnished Equipment, Boeing Purchased Equipment, and from
changes to the Detail Specification approved by the Customer and Boeing or otherwise allowed
by the Purchase Agreement.
	 
	7.9	 	Compliance shall be based on the performance of the airframe and engines in combination, and
shall not be contingent on the engine meeting its manufacturer’s performance specification.
	 
	8	 	EXCLUSIVE GUARANTEES
	 
	 	 	The only performance guarantees applicable to the Aircraft are those set forth in
this Attachment.






					
	 	 	 	 	 
	P.A. No. 1980

AERO-B-BBA4-M10-1004
	 	 	 	SS10-0587
	 	 	 	 	 
	 
	 	BOEING PROPRIETARY