AD 96-15-06

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AD Number:
96-15-06
Document Type:
AD Final Rules
Docket Number:
96-ANE-19
Subject Heading:
PRATT & WHITNEY Model JT8D-200 Series Engines
Subject:
First Stage Fan Hubs
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/03/1996
Make:
Pratt & Whitney Division
Model:
JT8D-209 | JT8D-217 | JT8D-217A | JT8D-217C | JT8D-219
Product Type:
Engine
Product Subtype:
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 96-15-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   96-ANE-19

AMENDMENT:   39-9714

AD NUMBER:   96-15-06

SUBJECT HEADING:   PRATT & WHITNEY Model JT8D-200 Series Engines

ACTION:  

SUMMARY:  

DATES:   Effective September 3, 1996.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   96-15-06 PRATT & WHITNEY: Amendment 39-9714. Docket 96-ANE-19.
Applicability: Pratt & Whitney (PW) JT8D-200 series turbofan engines incorporating affected first stage fan hubs, Part Number (P/N) 5000501-01, identified by any of the following Serial Numbers:
T50693, T50823,
T50827, R32926,
R32960, P66756.
These engines are installed on but not limited to McDonnell Douglas MD-80 series aircraft.
NOTE: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To prevent the initiation and propagation of a fatigue crack, fracture of the fan hub, uncontained engine failure, and damage to the aircraft, accomplish the following:
(a) Prior to further flight, remove from service all affected first stage fan hubs, P/N 5000501-01, identified by Serial Numbers listed in the applicability paragraph of this AD, and replace with serviceable parts.
(b) An alternative method of compliance or adjustment of compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office.
NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office.
(c) This amendment becomes effective September 3, 1996, to all persons except those persons to whom it was made immediately effective by priority letter AD 96-15-06, issued July 16, 1996, which contained the requirements of this amendment.

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