AD 86-02-52 R1

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AD Number:
86-02-52 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
PRATT & WHITNEY Models JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and...Show more
Subject:
Combustion Chamber
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/14/1986
Make:
Pratt & Whitney Division
Model:
JT8D-1 | JT8D-11 | JT8D-15 | JT8D-15A | JT8D-17 | JT8D-17A | JT8D-17AR | JT8D-17R | JT8D-1A | JT8D-1...Show more
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Superseded AD: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Superseded By: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: 86-02-52 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5264

AD NUMBER:   86-02-52 R1

SUBJECT HEADING:   PRATT & WHITNEY Models JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR Engines

ACTION:  

SUMMARY:  

DATES:   Effective April 14, 1986.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
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	656975	666980	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 100 cycles 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 accordance with 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.


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