AD 86-02-52 R1 ACTIVE

86-02-52 R1 PRATT & WHITNEY: Amendment 39-5264. Applies to Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR model turbofan engines overhauled by Aerothrust Corporation of Miami, Florida, with the following serial numbers:

648779
654034
657429
667109
688132
649019
654072
657480
667127
688418
649218
654344
657591
667130
688440
649255
654595
657699
667144
688441
649281
654799
657714
667203
688444
649283
654806
657742
667204
688445
649285
654857
665873
667216
688473
649347
654909
666661
674268
688504
649581
654975
666685
674465
688505
649655
655366
666716
674564
688509
653453
655813
666738
674611
688839
653509
655920
666764
687309
688844
653512
655967
666804
687323
689877
653526
656047
666850
687413
689935
653571
656089
666853
687715
696688
653645
656120
666878
687727
696720
653699
656854
666976
687806
702937
653838
656975666980
687836
702938
653854
657066
666989
687840
702975
653992
657112
666993
687841

653996
657201
667042

657258
667059

Compliance is required as indicated unless already accomplished.

To prevent fracture of the combustion chamber which could result in an uncontained engine failure, accomplish the following:

NOTES: 1) For the initial inspection, time since inspection (TSI) is defined as hours or cycles since installation by Aerothrust. Thereafter, for the repetitive inspections, TSI is defined as hours or cycles since the last inspection.

2) For the initial inspection, the cumulative crack length at the 2-3 seam weld is that present at the time of installation by Aerothrust as determined by individual chamber x-ray film records on file at Aerothrust.

3) Investigation is continuing and pending the results, additional engine serial numbers may be added to this AD.

(a) Remove from service within the next 100 hours or 100cycles time in service from the effective date of this AD, whichever occurs first, chambers with greater than 8 inches but less than or equal to 12 inches cumulative crack length at installation by Aerothrust.

(b) Remove from service, prior to further flight, chambers with greater than 12 inches cumulative crack length at installation by Aerothrust.

(c) Inspect combustion chamber 2-3 seam welds in accordance with PW Service Bulletin Number 5639, dated November 15, 1985, or FAA approved equivalent, per the following schedule:

(1) Inspect chambers with 3 inches or less cumulative crack length as follows:

(i) Prior to accumulating 2,000 hours or 1,500 cycles TSI, whichever occurs first; or

(ii) For chambers with greater than 1,900 hours or 1,400 cycles TSI on the effective date of this AD, inspect within the next 100 hours or 100 cycles time in service, whichever occurs first.

(2) Inspect chambers with greater than 3 inches but less than or equal to 6 inches cumulative crack length as follows:

(i) Prior to accumulating 1,500 hours or 1,000 cycles TSI, whichever occurs first; or

(ii) For chambers with greater than 1,400 hours or 900 cycles TSI on the effective date of this AD, inspect within the next 100 hours or 100 cycles time in service, whichever occurs first.

(3) Inspect chambers with greater than 6 inches but less than or equal to 8 inches cumulative crack length as follows:

(i) Prior to accumulating 250 hours or 200 cycles TSI, whichever occurs first; or

(ii) For chambers with greater than 150 hours or 100 cycles TSI on the effective date of this AD, inspect within the next 100 hours or 100 cycles time in service, whichever occurs first.

(4) Chambers for which the cumulative crack length at installation by Aerothrust cannot be confirmed must be inspected within the next 100 hours or 100 cycles time in service, whichever occurs first.

(d) Reinspect chambers, thereafter, in accordancewith the appropriate inspection interval of paragraphs (c)(1) through (c(3), as determined by the crack length at last inspection or at installation by Aerothrust, whichever crack length is greater. Remove from service, prior to further flight, any chambers with greater than 8 inches cumulative crack length at reinspection.

Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished.

Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, New England Region.

Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD.

Pratt & Whitney Service Bulletin Number 5639, dated November 15, 1985, identified and described in this document is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Pratt & Whitney, East Hartford, Connecticut. This document may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, Rules Docket Number 86-ANE-3, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m.

This amendment becomes effective April 14, 1986, as to all persons except those persons to whom it was made immediately effective by TAD T86-02-52, issued January 29, 1986, which contained this amendment.

TAD T86-02-52 superseded TAD T85-17-51R1 for the engines affected by this TAD, and this TAD supersedes TAD T86-02-51.