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TASK 05-11-00-200-801
1 . General.
A.Specified rotating parts and static structure parts have been identified by the Federal Aviation Administration (FAA) to be life-limited in relation to the time in service. The fan, high pressure compressor, combustor, high pressure turbine, and low pressure turbine have life-limited parts.
B.FAA-certified commercial engine in military service are not necessarily operated in accordance with the type design certification basis of the Federal Aviation Regulations contained in CFR Title 14.
2 . Necessary Records.
A.Keep an accurate history for the total operation of each part. The total cycles are the main record that must be kept. The operators must make sure the total cycles of the life-limited parts are not more than the cyclic life limits.
B.The maximum life limits for all parts, in any condition, are specified in the sections that follow. Keep an accurate history of cycles, on all parts, in two forms: the total number of cycles operated and the number of cycles remaining. We recommend that the operators also keep records of the number of cycles operated in each engine model, since some life-limited parts are common to two or more engine models.
C.A cycle is defined as:
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A flight that has a start, takeoff, landing, and a shutdown.
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A flight consisting of a takeoff and landing (no engine shutdown and restart).
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A touch-and-go landing or simulated touch-and-go landing (no weight on wheels) for pilot training.
D.The life limits in this chapter are total cycles which must be counted for each part from its first entry into service. Any Service Bulletin that is issued for a life-limited part will specify the effects on the life limits.
E.Some life-limited parts are common to two or more engine models. A part common to multiple engine models can have different life cycle limits depending on the engine application. If a life-limited part was previously used on a GEnx-2B engine, the life cycle limits are contained in the GEnx-2B Engine Manual GEK 114119. Use one of these methods to find the remaining available life cycles for life-limited parts of multiple engine models:
CAUTION:
IF THE NUMBER OF CYCLES OPERATED IN EACH ENGINE MODEL IS NOT RECORDED, YOU MUST USE METHOD A TO CALCULATE THE REMAINING CYCLES AVAILABLE OF A PART. A PART CAN HAVE MORE CYCLES THAN THE PERMITTED LIFE LIMIT INTERVAL IF METHOD A IS NOT USED. IF A PART HAS MORE CYCLES THAN THE PERMITTED LIFE LIMIT INTERVAL, DAMAGE TO THE ENGINE CAN OCCUR. IT IS THE OPERATOR'S RESPONSIBILITY TO KEEP ACCURATE RECORDS OF PART OPERATION.
(1)If only the cycles and not the engine model have been recorded, use Method A. Refer to Figure 801.
CAUTION:
IF THE NUMBER OF CYCLES OPERATED IN EACH ENGINE MODEL IS NOT RECORDED, YOU MUST USE METHOD A TO CALCULATE THE REMAINING CYCLES AVAILABLE OF A PART. A PART CAN HAVE MORE CYCLES THAN THE PERMITTED LIFE LIMIT INTERVAL IF METHOD A IS NOT USED. IF A PART HAS MORE CYCLES THAN THE PERMITTED LIFE LIMIT INTERVAL, DAMAGE TO THE ENGINE CAN OCCUR. IT IS THE OPERATOR'S RESPONSIBILITY TO KEEP ACCURATE RECORDS OF PART OPERATION.
(2)If the cycles and associated engine model for each part have been recorded, use Method B. Refer to Figure 802.
(3)Commercial-service use of GEnx series engines or engine parts thereof that have operated in military applications is prohibited unless specific prior FAA (Engine Certification Office, ANE- 140) approval is granted.
F.Fan Blade Repairs
(1)Approval of repairs of fan blade composite material in the root section of the fan blade up to the inner annulus flow path line must be coordinated with the FAA Engine Certification Office. Substantiation of these repairs must show that compliance to Special Conditions No. 33-006-SC is maintained.
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Figure 801   Method A to Calculate Total Available Life Cycles
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Figure 802   Method B to Calculate Total Available Life Cycles