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AD/JT8D/27 Amdt 2 - First Stage Compressor Hub
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AD/JT8D/27 Amdt 2 - First Stage Compressor Hub
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| AD/JT8D/27 Amdt 2 | First Stage Compressor Hub | 7/2005 |
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| Applicability: | Pratt & Whitney (PW) Model JT8D-9, -9A, -11, -15, -15A, -17, -17A, -17R, and-17AR turbofan engines containing front compressor fan hub Part Number (P/N) 817401 with the following serial numbers: J78892 through J80538, K32019 through K34018, L32197 through L34133, or M05722 through M07296; and all serial numbers of fan hubs P/N 594301, 640601, 743301, 749801, 750101, 791801, 806001. |
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| Requirement: | Inspect and / or shotpeen and / or remove from service front compressor fan hub as per Requirements of FAA Airworthiness Directive (AD) 95-10-10.Note: FAA AD 95-10-10 Amendment 39-9227refers. |
| Compliance: | Unless previously accomplished, as per compliance schedule of the FAA AD95-10-10 Amendment 39-9227. |
| This Amendment becomes effective on 7 July 2005. | |
| Background: | Fracture of the front compressor fan hub can result in an uncontained engine failure and damage to the aircraft. The requirements of this AD are aimed at prevention of the hub fracture and resultant uncontained engine failure.The current amendment deletes reference to the manufacturer’s document and refers to the FAA AD as part of the harmonisation with the engine certificating Authority requirements.Amendment 1 of this Directive became effective on 9 December 1993. |
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James Coyne
Delegate of the Civil Aviation Safety Authority
25 May 2005