# AD 86-02-52 R1: Combustion Chamber - Type: Airworthiness directive - Status: Current - Products: Pratt & Whitney Division JT8D-1, JT8D-11, JT8D-15, JT8D-15A, JT8D-17, JT8D-17A, JT8D-17AR, JT8D-17R, JT8D-1A, JT8D-1B, JT8D-7, JT8D-7A and 3 more - Effective: April 14, 1986 - Amendment: 39-5264 - Data sheets: TCDS E2EA - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/5CD04BDFC2D97D6E8625685F0070E43B.0001 - Page: https://openairdocs.org/ad/86-02-52-R1 ## The airworthiness directive 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. --- From OpenAirDocs.org, an independent open copy of FAA data. Only the Federal Register edition on govinfo.gov is the official legal text of an AD.