Division Pratt and Whitney Turbine Engines - JT8D - AD/JT8D/43 - Front Compressor Hub - Pratt and Whitney Turbine Engines - JT8D Series

Pratt and Whitney Turbine Engines - JT8D Series

AD/JT8D/43	Front Compressor Hub	12/2009

Applicability:	Pratt & Whitney Aircraft JT8D-1, -1A, -7, and -7A turbofan engines using Front Compressor Front Hub Part Nos. 504101 and 515201.Note 1: Pratt & Whitney Aircraft Alert Service Bulletin (ASB) No. 2944 RevisionNo. 13 dated 22 October 2008 lists the engine and hub serial numbers affected by this AD.
Requirement:	1. To preclude failure of the front compressor front hub as a result of (a) possible surface defects in the blade slots or (b) possible loss of effectiveness of shotpeening in the blade slots accomplish the following on hubs listed in tables I and II of the above ASB.a. Visually inspect the rear face and overhung shelf of the hub rim for cracks emanating out of the base of the acute corner of the dovetail slots, orb. Inspect with an eddy current probe the rear overhung shelf of the hub rim for cracks emanating out of the base of the acute corner of the dovetail slots, orc. Remove all first stage compressor blades and inspect the blade slots of the hub with an eddy current probe for cracks emanating out of the base of the acute corner of the dovetail slots.d. If any crack is found during any of the foregoing inspections replace hub.It is permissible to use any of the three inspection procedures at the end of the preceding inspection period.2. To preclude failure of the front compressor front hub from lack of shotpeening, accomplish the following on hubs listed in table III of the above ASB.a. Visually inspect to determine whether the rim area of the hub has been shotpeened.b. If the inspection confirms that the hub has not been shotpeened then the hub is to be inspected in accordance with Requirements 1.a. through d. of this AD.

Applicability:

Pratt & Whitney Aircraft JT8D-1, -1A, -7, and -7A turbofan engines using Front Compressor Front Hub Part Nos. 504101 and 515201.Note 1: Pratt & Whitney Aircraft Alert Service Bulletin (ASB) No. 2944 RevisionNo. 13 dated 22 October 2008 lists the engine and hub serial numbers affected by this AD.

Requirement:

1. To preclude failure of the front compressor front hub as a result of (a) possible surface defects in the blade slots or (b) possible loss of effectiveness of shotpeening in the blade slots accomplish the following on hubs listed in tables I and II of the above ASB.a. Visually inspect the rear face and overhung shelf of the hub rim for cracks emanating out of the base of the acute corner of the dovetail slots, orb. Inspect with an eddy current probe the rear overhung shelf of the hub rim for cracks emanating out of the base of the acute corner of the dovetail slots, orc. Remove all first stage compressor blades and inspect the blade slots of the hub with an eddy current probe for cracks emanating out of the base of the acute corner of the dovetail slots.d. If any crack is found during any of the foregoing inspections replace hub.It is permissible to use any of the three inspection procedures at the end of the preceding inspection period.2. To preclude failure of the front compressor front hub from lack of shotpeening, accomplish the following on hubs listed in table III of the above ASB.a. Visually inspect to determine whether the rim area of the hub has been shotpeened.b. If the inspection confirms that the hub has not been shotpeened then the hub is to be inspected in accordance with Requirements 1.a. through d. of this AD.

	Later revisions of the above SB, approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 71-07-01 are considered acceptable for compliance with the equivalent Requirements of this AD.Note 2: FAA AD 71-07-01 Amdt. 39-1279 dated 7 September 1971 refers.
Compliance:	Compliance required as indicated on all front compressor front hubs that have accumulated 6000 cycles or more in service.For Requirement 1.a. - Within the next 150 cycles in service and every 150 cycles in service thereafter until the hub is removed.For Requirement 1.b. - Within the next 150 cycles in service, unless already accomplished and every 400 cycles in service thereafter until the hub is removed.For Requirement 1.c. - Within the next 150 cycles in service, unless already accomplished and every 1500 cycles in service thereafter.For Requirement 1.d. - Before further flight.For Requirement 2.a. - Within the next 150 cycles in service.For Requirement 2.b. - At the intervals defined in Requirements 1.a. through 1.d. of this AD.

Later revisions of the above SB, approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 71-07-01 are considered acceptable for compliance with the equivalent Requirements of this AD.Note 2: FAA AD 71-07-01 Amdt. 39-1279 dated 7 September 1971 refers.

Compliance:

Compliance required as indicated on all front compressor front hubs that have accumulated 6000 cycles or more in service.For Requirement 1.a. - Within the next 150 cycles in service and every 150 cycles in service thereafter until the hub is removed.For Requirement 1.b. - Within the next 150 cycles in service, unless already accomplished and every 400 cycles in service thereafter until the hub is removed.For Requirement 1.c. - Within the next 150 cycles in service, unless already accomplished and every 1500 cycles in service thereafter.For Requirement 1.d. - Before further flight.For Requirement 2.a. - Within the next 150 cycles in service.For Requirement 2.b. - At the intervals defined in Requirements 1.a. through 1.d. of this AD.

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