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93-14-20: 93-14-20 PRATT & WHITNEY: Amendment 39-8645. Docket No. 91-ANE-05.
Applicability: Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 turbofan engines installed on, but not limited to Boeing 747, McDonnell Douglas DC-10, and Airbus A300 aircraft, in which the following high pressure turbine (HPT) stage 2 vane assemblies, identified by vane cluster assembly part numbers, are installed: 743772, 774872, 806272, 807372, 807772, 807072, and 808372.
Compliance: Required as indicated, unless previously accomplished.
To prevent uncontained HPT stage 2 blade fractures or lenticular airseal failures, accomplish the following:
(a) For engines that have not incorporated the requirements of PW Service Bulletin (SB) 5566, Revision 5, dated August 10, 1990, and the requirements of PW SB 5428, Revision 3, dated March 12, 1984, borescope inspect the HPT stage 2 vanes in accordance with the Accomplishment Instructions of PW SB 5667, Revision 2, dated June 11, 1992, and in accordance withthe criteria identified in the applicable PW Maintenance Manual (MM) listed in paragraph (c) of this AD, prior to accumulating 1,000 hours time in service (TIS) since vane installation, or within the next 125 hours TIS after the effective date of this AD, whichever occurs later, and remove from service, prior to further flight, second stage turbine vanes exhibiting distress beyond serviceable limits.
(b) For engines that have incorporated the requirements of PW SB 5566, Revision 5, dated August 10, 1990, and PW SB 5428, Revision 3, dated March 12, 1984, borescope inspect the HPT stage 2 vanes in accordance with the Accomplishment Instructions of PW SB 5667, Revision 2, dated June 11, 1992, and in accordance with the criteria identified in the applicable PW MM listed in paragraph (c) of this AD, prior to accumulating 2,000 hours total part TIS since new on the entire set of vanes, or within 1,000 hours TIS since vane installation, or within the next 125 hours TIS after the effectivedate of this AD, whichever occurs later, and remove from service, prior to further flight, second stage turbine vanes exhibiting distress beyond serviceable limits.
(c) Thereafter, inspect the HPT stage 2 vanes in accordance with the criteria identified in the following PW MMs, and remove from service, prior to further flight, HPT stage 2 vanes exhibiting distress beyond serviceable limits.
Engine Models
MM Part Number/
Revision Date
Section/Table
JT9D-7Q/7Q3
783777/December 25, 1989
72-00-00/604A
JT9D-59A/-70A
783778/April 25, 1990
72-00-00/605A
JT9D-59A
783779/September 15, 1989
72-00-00/605
(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from Engine Certification Office.
(e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(f) The inspections shall be done in accordance with the following service document:
Document No.
Pages
Issue
Date
PW SB No. 5667
1-6
Revision 2
June 11, 1992
Total pages: 6
This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Pratt & Whitney, Publications Department, 400 Main Street, East Hartford, CT 06108. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(g) This amendment becomes effective on August 27, 1993.
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96-18-08 R1: 96-18-08 R1 PRATT & WHITNEY: Amendment 39-10857. Docket 95-ANE-37. Revises AD 96-18-08, Amendment 39-9732.
Applicability: Pratt & Whitney Models PW2037, PW2037(M), PW2040, PW2240, and PW2337 turbofan engines, installed on but not limited to, Boeing 757 series and Ilyushin IL96 series aircraft.
Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (o) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To prevent high pressure turbine (HPT) or low pressure turbine (LPT) failure, which may result in an uncontained engine failure and possible damage to the aircraft, accomplish the following:
(a) Remove from service 1st stage HPT disks, Part Number (P/N) 1A5301, prior to exceeding 5,000 total part cycles since new (TPC), if installed with blade retaining plate, P/N 1A6998, and replace with serviceable parts. If blade retaining plate, P/N 1A6998, has not been installed on disk, P/N 1A5301, the disk may accumulate 15,000 TPC prior to removal from service.
(b) Remove from service 1st stage HPT blade retaining plates, P/N 1A6998, prior to exceeding 5,000 TPC, and replace with serviceable parts. If rework is accomplished prior to exceeding 5,000 TPC in accordance with the Accomplishment Instructions of PW Alert Service Bulletin (ASB) No. PW2000 A72-82, Revision 1, dated April 25, 1986; Revision 2, dated July 17, 1986; Revision 3, dated November 7, 1986; or Revision 4, dated June 18, 1987, and reidentified as assembly P/N 1B2373, the blade retaining plate may accumulate 15,000 TPC prior to removal from service.
(c) Remove from service 2nd stage HPT blade retaining plates, P/N 1B0450, prior to exceeding 7,000 TPC, and replace with serviceable parts.
(d) Remove from service 2nd stage HPT blade retaining plates, P/N 1B0945 (assembly P/N 1B0947), and replace with serviceable parts, in accordance with the Accomplishment Instructions of PW ASB No. PW2000 A72-228, Revision 2, dated May 10, 1988; Revision 3, dated August 25, 1988; or Revision 4, dated November 9, 1988, as follows:
(1) Prior to exceeding 5,000 TPC, for retaining plates that have not been inspected in accordance with the Accomplishment Instructions of the above ASB prior to 3,000 TPC.
(2) Prior to exceeding 8,000 TPC, for retaining plates that have been inspected in accordance with the Accomplishment Instructions of the above ASB prior to 3,000 TPC.
(e) Remove from service 2nd stage HPT hubs, P/N's 1A8302, 1B1002, 1B1202, or 1B4902 prior to exceeding 7,500 TPC, and replace with serviceable hubs. Hubs may accumulate 15,000 TPC prior to removal from service if they are inspected at intervals that do not exceed 6,000 cycles in service since last inspection, in accordance with the Accomplishment Instructions of PW Service Bulletin (SB) No. PW2000 72-450, Original, dated March 13, 1992; Revision 1, dated March 26, 1992; Revision 2, dated April 7, 1992; Revision 3, dated May 29, 1992; Revision 4, dated August 28, 1992; ASB No. PW2000 72-450, Revision 5, dated May 28, 1994; or Revision 6, dated July 9, 1996.
(f) Remove from service all suspect 2nd stage HPT hubs, P/N 1B6602, prior to exceeding 7,500 TPC, and replace with serviceable hubs. The suspect hubs are identified at the assembly level, P/N 1B6232, in Section 1, Planning Informationcontained in PW SB No. PW2000 72-501, dated September 30, 1993. Hubs may accumulate 15,000 TPC prior to removal from service if hub assemblies are inspected prior to 7,500 TPC to verify scarf cut blades are installed and to inspect the blade platform rail fillet radii dimensions, in accordance with the Accomplishment Instructions of PW SB No. PW2000 72-501, dated September 30, 1993. Hub assemblies found with non-scarf cut blades must be reinspected at intervals not to exceed 6,000 TPC since last inspection. Blades found with under minimum rail fillet radii dimensions must be scrapped.
(g) Remove from service HPT lenticular airseal, P/N 1A8209, prior to exceeding 4,000 TPC, and replace with serviceable airseals. Airseals may accumulate 15,000 TPC prior to removal from service if:
(1) Inspected prior to exceeding 4,000 TPC, and thereafter inspected at intervals not to exceed 250 cycles in service since last inspection, in accordance with Compliance Paragraph E of the Accomplishment Instructions of PW ASB No. PW2000 A72-220, Revision 3, dated April 13, 1989, or Revision 4, dated September 20, 1989; or
(2) The 2nd stage HPT case and vane assembly is reworked and reidentified prior to exceeding 4,000 TPC, in accordance with the Accomplishment Instructions of PW SB No. PW2000 72-233, Revision 2, dated September 27, 1988, or Revision 3, dated May 30, 1989.
(h) For PW2037, PW2037(M), and PW2337 model engines, remove from service 4th stage LPT disks, P/N's 8A1024, 8A1534, or 8A2137 prior to exceeding 17,000 TPC, and replace with serviceable disks.
(i) For PW2040 and PW2240 model engines, remove from service 4th stage LPT disks, P/N's 8A1534 or 8A2137, prior to exceeding 15,000 TPC, and replace with serviceable disks.
(j) Remove from service 3rd stage LPT airsealing ring supports, P/N 8A1783, and replace with serviceable parts, as follows:
(1) For PW2040 and PW2240 model engines, prior to exceeding 15,000 TPC.
(2) For PW2037, PW2037(M), and PW2337 model engines, prior to exceeding 17,000 TPC. Airsealing ring supports may accumulate 20,000 TPC prior to removal from service if they were fluorescent penetrant inspected in accordance with Section 72-53-00 of PW2000 Engine Manual, P/N 1A6231.
(k) For PW2037, PW2037(M), and PW2337 model engines, remove from service prior to exceeding 17,000 TPC, and replace with serviceable parts, as follows:
(1) 4th stage LPT airseal, P/N's 8A1014 or 8A1805.
(2) 5th stage LPT airseal, P/N's 8A1015 or 8A1806.
(3) 7th stage LPT airseal, P/N's A8A1017, A8A1808, 8A2097, or A8A2097.
(l) Parts listed in paragraph (k) of this AD may accumulate 20,000 TPC prior to removal from service if they were fluorescent penetrant inspected for cracks between 12,000 TPC and 17,000 TPC in accordance with Section 72-53-00 of PW2000 Engine Manual, P/N 1A6231.
(m) For PW2040 and PW2240 model engines, remove from service prior to exceeding 15,000 TPC, and replace with serviceable parts, as follows:(1) 4th stage LPT airseal, P/N's 8A1014 or 8A1805.
(2) 5th stage LPT airseal, P/N's 8A1015 or 8A1806.
(3) 7th stage LPT airseal, P/N's A8A1017, A8A1808, 8A2097, or A8A2097.
(n) Parts listed in paragraph (m) of this AD may accumulate the following TPC prior to removal if they were fluorescent penetrant inspected for cracks between 10,000 TPC and 15,000 TPC in accordance with Section 72-53-00 of PW2000 Engine Manual, P/N 1A6231:
(1) 4th stage LPT airseal, P/N's 8A1014 or 8A1805, prior to exceeding 18,000 TPC.
(2) 5th stage LPT airseal, P/N's 8A1015 or 8A1806, prior to exceeding 19,000 TPC.
(3) 7th stage LPT airseal, P/N's A8A1017, A8A1808, 8A2097, or A8A2097, prior to exceeding 20,000 TPC.
(o) An alternative method of compliance or adjustment of the initial compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. Operators shall submit their requests through an appropriate FAA PrincipalMaintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office.
Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Engine Certification Office.
(p) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished.
(q) The actions required by this AD shall be done in accordance with the following PW service documents:
Document No
Pages
Revision
Date
ASB No. PW2000 A72-82
1
1
April 25, 1986
2-6
Original
June 7, 1985
7-9
1
April 25, 1986
10
Original
June 7, 1985
11
1
April 25, 1986
Total Pages: 11.
ASB No. PW2000 A72-82
1
2
July 17, 1986
2-6
Original
June 7, 1985
7-9
1
April 25, 1986
10
Original
June 7, 198511
2
July 17, 1986
Total Pages: 11.
ASB No. PW2000 A72-82
1-4
3
November 7, 1986
5,6
Original
June 7, 1985
7-14
3
November 7, 1986
Total Pages: 14
ASB No. PW2000 A72-82
1
4
June 18, 1987
2-4
3
November 7, 1986
5,6
Original
June 7, 1985
7-12
3
November 7, 1986
13
4
June 18, 1987
14
3
November 7, 1986
Total Pages: 14.
ASB No. PW2000 A72-228
1
2
May 10, 1988
2
Original
July 6, 1987
3
2
May 10, 1988
4
1
March 29, 1988
5-26
2
May 10, 1988
Total Pages: 26.
ASB No. PW2000 A72-228
1
3
August 25, 1988
2
Original
July 6, 1987
3
2
May 10, 1988
4
3
August 25, 1988
5-19
2
May 10, 1988
20
3
August 25, 1988
21,22
2
May 10, 1988
23
3
August 25, 1988
24-26
2
May 10, 1988
Total Pages: 26.
ASB No. PW2000 A72-228
1
4
November 9, 1988
2
Original
July 6, 1987
3
4
November 9, 1988
4
3
August 25, 1988
5-19
2May 10, 1988
20
3
August 25, 1988
21,22
2
May 10, 1988
23
3
August 25, 1988
24-26
4
November 9, 1988
Total Pages: 26.
SB No. PW2000 72-450
1-26
Original
March 13, 1992
Total Pages: 26.
SB No. PW2000 72-450
1
1
March 26, 1992
2-11
Original
March 13, 1992
12,13
1
March 26, 1992
14,15
Original
March 13, 1992
16,17
1
March 26, 1992
18-21
Original
March 13, 1992
22,23
1
March 26, 1992
24,25
Original
March 13, 1992
26
1
March 26, 1992
Total Pages: 26.
SB No. PW2000 72-450
1
2
April 7, 1992
2,3
Original
March 13, 1992
4,5
2
April 7, 1992
6-11
Original
March 13, 1992
12
1
March 26, 1992
13
2
April 7, 1992
14,15
Original
March 13, 1992
16,17
1
March 26, 1992
18-21
Original
March 13, 1992
22,23
1
March 26, 1992
24,25
Original
March 13, 1992
26
1
March 26, 1992
Total Pages: 26.
SB No. PW2000 72-450
1-5
3
May29, 1992
6-11
Original
March 13, 1992
12
1
March 26, 1992
13
3
May 29, 1992
14
Original
March 13, 1992
15-29
3
May 29, 1992
Total Pages: 29.
SB No. PW2000 72-450
1
4
August 28, 1992
2-5
3
May 29, 1992
6-11
Original
March 13, 1992
12
1
March 26, 1992
13
3
May 29, 1992
14
Original
March 13, 1992
15
4
August 28, 1992
16
3
May 29, 1992
17
4
August 28, 1992
18-29
3
May 29, 1992
Total Pages: 29.
ASB No. PW2000 72-450
1
5
May 28, 1994
2
4
May 28, 1994
3-5
3
May 29, 1992
6-11
Original
March 13, 1992
12
1
March 26, 1992
13
3
May 29, 1992
14
Original
March 13, 1992
15
4
August 28, 1992
16
3
May 29, 1992
17
4
August 28, 1992
18-29
3
May 29, 1992
Total Pages: 29.
ASB No. PW2000 72-450
1
6
July 9, 1996
2
4
May 28, 1994
3-5
3
May 29, 1992
6-11
Original
March 13, 1992
12
1
March 26, 1992
133
May 29, 1992
14
Original
March 13, 1992
15
4
August 28, 1992
16
3
May 29, 1992
17
4
August 28, 1992
18-28
3
May 29, 1992
29
6
July 9, 1996
Total Pages: 29.
SB No PW72-501
1-12
Original
September 30, 1993
Total Pages: 12.
ASB No. PW2000 A72-220
1
3
April 13, 1989
2
1
July 29, 1987
3-26
3
April 13, 1989
Total Pages: 26.
ASB No. PW2000 A72-220
1
4
September 20, 1989
2
1
July 29, 1987
3-6
3
April 13, 1989
7-9
4
September 20, 1989
10-16
3
April 13, 1989
17-27
4
September 20, 1989
Total Pages: 27.
SB No. PW2000 72-233
1,2
2
September 27, 1988
3-7
Original
August 7, 1987
8
1
January 22, 1988
9,10
2
September 27, 1988
Total Pages: 10.
SB No. PW2000 72-233
1-4
3
May 30, 1989
5
Original
August 7, 1987
6
3
May 30, 1989
7
Original
August 7, 1987
8
1
January 22, 1988
9,10
3
May 30, 1989
Total Pages: 10.The incorporation by reference of these service documents was approved previously by the Director of the Federal Register as of November 29, 1996 (61 FR 50984, September 30, 1996). Copies may be obtained from Pratt & Whitney, Publications Department, Supervisor Technical Publications Distribution, M/S 132-30, 400 Main St., East Hartford, CT 06108; telephone (860) 565-7700, fax (860) 565-4503. Copies may be inspected at the FAA, New England Region, Office of Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(r) This amendment becomes effective on November 10, 1998.
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