AD 86-09-01 R1

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AD Number:
86-09-01 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
PRATT & WHITNEY Models JT9D-3A, -7, -7A, -7AH, -7H, -7F, -7J, -20, -59A, -70A, -7Q, and -7Q3 Series Engines
Subject:
Turbine Vane Antirotation Pin Failure
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/06/1988
Make:
Pratt & Whitney Division
Model:
JT9D-20 | JT9D-3A | JT9D-59A | JT9D-7 | JT9D-70A | JT9D-7A | JT9D-7AH | JT9D-7F | JT9D-7H | JT9D-7J ...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Superseded AD: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Superseded By: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: 86-09-01 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5928

AD NUMBER:   86-09-01 R1

SUBJECT HEADING:   PRATT & WHITNEY Models JT9D-3A, -7, -7A, -7AH, -7H, -7F, -7J, -20, -59A, -70A, -7Q, and -7Q3 Series Engines

ACTION:  

SUMMARY:  

DATES:   Effective July 6, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
86-09-01 R1 PRATT & WHITNEY: Amendment 39-5268 as amended by Amendment 39-5928. Applies to Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7AH, -7H, -7F, -7J, -20, -59A, -70A, -7Q, and -7Q3 series turbofan engines.

Compliance is required as indicated, unless already accomplished.

To prevent low pressure turbine (LPT) case penetration that can result from turbine vane antirotation pin failure, accomplish the following:

(a) Radioisotope inspect, and remove from service or reinspect stainless steel (AMS 5735) antirotation pins in LPT cases installed in PW JT9D-3A, -7, -7A, -7AH, -7H, -7F, -7J, and -20 turbofan engines as follows:

(1) Radioisotope inspect for broken LPT stages three, four, five, and six turbine vane antirotation pins in accordance with the Accomplishment Instructions contained in PW Service Bulletin (SB) 5735, dated February 20, 1987, within the next 750 hours time in service (TIS) after the effective date of this AD or within 4,000 hours TIS since the last LPT module shop visit, whichever occurs later.

(2) Remove from service, prior to further flight, engines with LPT cases found to contain more than 18 pins broken in any stage, or with any number of broken pins which results in a circumferential gap between any two vanes that exceeds 0.500 inch as measured on the film and replace the pins in accordance with paragraph (b) below.

(3) Reinspect thereafter and remove from service in accordance with the requirements of Table I in PW SB 5735, dated February 20, 1987. LPT cases found to have no broken pins do not require reinspection prior to pin replacement in accordance with paragraph (b) below.

(b) Remove from service the entire set of stainless steel (AMS 5735) antirotation pins in LPT cases installed in PW JT9D-3A, -7, -7A, -7AH, -7H, -7F, -7J, and -20 turbofan engines, and replace with nickel alloy (AMS 5660/5661) pins in accordance with the Accomplishment Instructions contained in PW SB 5292, Revision 3, dated June 24, 1985, when removed from service as required by paragraph (a) above; or at the next LPT module shop visit after May 13, 1986; or by December 31, 1989, whichever occurs first.

(c) Incorporate additional LPT antirotation pins in the fourth, fifth, and sixth stage stator locations on PW JT9D-59A, -70A, -7Q, and -7Q3 turbofan engines at the next LPT module shop visit after May 13, 1986, or by December 31, 1989, whichever occurs first, in accordance with the Accomplishment Instructions contained in PW SB 5507, Revision 3, dated December 5, 1984.

NOTES: (1) Compliance with this AD requires that the entire set of the antirotation pins must be replaced, since it has been determined that partial incorporation of pins in accordance with PW SB 5292, Revision 3, dated June 24, 1985, or earlier revisions of the SB, may not preclude failure of the pins. LPT modules incorporating partial sets of pins in accordance with the requirements of PW SB 5292, Revision 3, dated June 24, 1985, or earlier revisions of the SB are subject to the requirements of this AD.

(2) For the purpose of this AD, an LPT module shop visit occurs when the LPT rotor is removed from the case and vane assembly.

(3) Incorporation of the requirements of the FAA approved revisions of the PW SB's listed below constitutes an equivalent means of compliance with the respective paragraphs of this AD that reference these SB's:

1. PW SB 5292, Revision 4, dated April 8, 1987, or Revision 5, dated October 26, 1987.

2. PW SB 5735, Revision 1, dated June 12, 1987, or Revision 2, dated March 7, 1988.

3. PW SB 5507, Revision 4, dated June 16, 1987.

(d) 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.

(e) Upon request, an equivalent means of compliance may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803.

(f) 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 times specified in this AD.

PW SB 5735, dated February 20, 1987, 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 these documents from the manufacturer may obtain copies upon request to Pratt & Whitney, Publication Department, P.O. Box 611, Middletown, Connecticut 06457.

This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 85-ANE-21, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays.

This amendment, 39-5928, amends Amendment 39-5268, (51 FR 12509; April 11, 1986), AD 86-09-01.

This amendment, 39-5928, becomes effective on July 6, 1988.

FOOTER: