AD 88-04-02

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AD Number:
88-04-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
PRATT & WHITNEY Models JT8D-209, -217, -217A, -217C, and -219 Engines
Subject:
Anti-rotation Pin Failures
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/04/1988
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Superseded AD: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Superseded By: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: 88-04-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5817

AD NUMBER:   88-04-02

SUBJECT HEADING:   PRATT & WHITNEY Models JT8D-209, -217, -217A, -217C, and -219 Engines

ACTION:  

SUMMARY:  

DATES:   Effective March 4, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
88-04-02 PRATT & WHITNEY: Amendment 39-5817. Applies to Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 turbofan engines.

Compliance is required as indicated, unless already accomplished.

To prevent low pressure turbine (LPT) case penetration as a result of anti-rotation pin failures, accomplish the following:

(a) Radiographic isotope inspect LPT cases installed in JT8D-200 series turbofan engines that incorporate Tinidur (AMS 5637) anti-rotation pins. Engines with new or refurbished (in accordance with the Accomplishment Instructions of paragraph 2.A.(2)(a) of PW service bulletin (SB) 5751, Revision 1, dated September 30, 1987) LPT case assemblies that have incorporated PW SB 5711, Revision 3, dated April 1, 1987, and have been concurrently assembled with new LPT third stage vane anti-rotation pins (Tinidur or Inco 901), are not required to meet the initial and repetitive inspection requirements of this paragraph. Engines requiring the inspection must be inspected in accordance with the Accomplishment Instructions contained in PW Alert SB 5753, Revision 2, dated December 11, 1987, in accordance with the following schedule:

(1) PW JT8D-209 engine LPT cases with 9,300 total cycles in service (CIS) or more on the effective date of this AD; inspect within 2,500 CIS from the effective date of this AD. Thereafter, reinspect in accordance with the requirements of the table below.

(2) PW JT8D-209 engine LPT cases with less than 9,300 total CIS on the effective date of this AD; inspect before the accumulation of 9,300 total CIS, or within 2,500 CIS from the effective date of this AD, whichever occurs later. Thereafter, reinspect in accordance with the requirements of the table below.

(3) PW JT8D-217 engine LPT cases with 7,300 total CIS or more on the effective date of this AD; inspect within 700 CIS from the effective date of this AD. Thereafter, reinspect in accordance with the requirements of the table below.

(4) PW JT8D-217 engine LPT cases with less than 7,300 total CIS on the effective date of this AD; inspect before the accumulation on 7,300 total CIS, or within 700 CIS from the effective date of this AD, whichever occurs later. Thereafter, reinspect in accordance with the requirements of the table below.

(5) PW JT8D-217A engine LPT cases with 3,300 total CIS or more on the effective date of this AD; inspect within 900 CIS from the effective date of this AD. Thereafter, reinspect in accordance with the requirements of the table below.

(6) PW JT8D-217A engine LPT cases with less than 3,300 total CIS on the effective date of this AD; inspect before the accumulation of 3,300 total CIS, or within 900 CIS from the effective date of this AD, whichever occurs later. Thereafter, reinspect in accordance with the requirements of the table below.

(7) PW JT8D-217C/-219 engine LPT cases with 4,200 total CIS or more on the effective date of this AD; inspect within 1,000 cycles from the effective date of this AD. Thereafter, reinspect in accordance with the requirements of the table below.

(8) PW JT8D-217C/-219 engine LPT cases with less than 4,200 total CIS on the effective date of this AD; inspect before the accumulation of 4,200 total CIS, or within 1,000 CIS from the effective date of this AD, whichever occurs later. Thereafter, reinspect in accordance with the requirements of the table below.

THIRD STAGE ANTI-ROTATION PIN REINSPECTION TABLE
Number of fractured, missing, or bent pins	Maximum CIS until reinspection JT8D-209	JT8D-217/-217A/-217C/
-219
0	7,000	1,700
1	6,640	1,610
2	6,280	1,525
3	5,920	1,440
4	5,560	1,350
5	5,200	1,265
6	4,840	1,180
7	4,480	1,090
8	4,120	1,005
9	3,760	920
10	3,400	830
11	3,040	745
12	2,680	660
13	2,320	570
14	1,960	485
15	1,600	400

(b) Remove from service prior to further flight, PW JT8D-209, -217, -217A, -217C, and -219 engines with 44 fractured, missing, or bent LPT third stage vane anti-rotation pins found during the accomplishment of the inspection requirements of paragraph (a) above.

(c) Remove from service within 10 CIS, PW JT8D-209, -217, -217A, -217C, and -219 engines with 16 or more, but less than 44 fractured, missing, or bent LPT third stage vane anti-rotation pins, found during the accomplishment of the inspection requirements of paragraph (a) above.

(d) Modify prior to return to service, in accordance with the Accomplishment Instructions of PW SB 5751, Revision 1, dated September 30, 1987, those engines removed from service in accordance with paragraphs (b) and (c) above.

(e) Modify prior to return to service, in accordance with the Accomplishment Instructions of PW SB 5751, Revision 1, dated September 30, 1987, PW JT8D-209, -217, -217A, -217C, and -219 engines inspected in accordance with paragraph (a) above, at an engine shop visit, and found with 15 or more fractured, missing, or bent LPT third stage vane anti-rotation pins.

(f) Modify PW JT8D-209, -217, -217A, -217C, and -219 engine LPT cases (including LPT cases from those engines referred to in paragraph (a) that were not required to meet the initial and repetitive inspection requirements) at the next LPT module disassembly after the effective date of this AD, in accordance with the Accomplishment Instructions of PW SB 5751, Revision 1, dated September 30, 1987.

(g) Report the following information in writing within 30 days from the date of the inspection to the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Telex Number 949301 FAANE BURL:

(1) Inspection date

(2) Engine serial number (S/N)

(3) LPT case S/N

(4) Engine total time and cycles (if estimate, so note)

(5) LPT case time and cycles since last shop visit (if estimate, so note)

(6) Number of third stage vane anti-rotation pins:
(i) fractured
(ii) missing
(iii) bent

NOTES: (1) For the purpose of this AD, LPT module disassembly occurs when the LPT rotor is separated from the LPT case and vane assembly.

(2) Shop visit is defined as the input of an engine to a repair shop where the subsequent engine maintenance entails:

(a) Separation of a major engine flange (lettered or numbered) other than flanges mating with major sections of the nacelle or reverser. Separation of flanges purely for purposes of shipment, without subsequent internal maintenance, is not a "shop visit."

(b) Removal of a disk, hub, or spool.

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 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.

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 Alert SB 5753, Revision 2, dated December 11, 1987, PW SB 5751, Revision 1, dated September 30, 1987, and PW SB 5711, Revision 3, dated April 1, 1987, identified and described in this document, are 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, Publications Department, P.O. Box 611, Middletown, Connecticut 06457. These documents 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; Rules Docket Number 87-ANE-23, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays.

This amendment becomes effective on March 4, 1988.

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