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94-08-06 Pratt & Whitney: Amendment 39-8878. Docket 91-ANE-47.
Applicability: Pratt & Whitney (PW) JT9D-7R4 series turbofan engines installed on but not limited to Boeing Models 747 and 767 aircraft, and Airbus Models A300 and A310 aircraft.
Compliance: Required as indicated, unless accomplished previously.
To prevent fan blade fracture and uncontained engine failure, resulting in possible damage to the aircraft, accomplish the following:
(a) Perform an initial visual or eddy current inspection of the fan blade set leading edges for leading edge damage within 200 cycles in service (CIS) after the effective date of this AD, and rework or replace fan blades as necessary, in accordance with the Accomplishment Instructions of PW Service Bulletin (SB) No. 72-255, Revision 5, dated January 8, 1990. Perform the fan blade leading edge visual inspections using a strong white light, as well as fingernails and fingertips when inspecting for nicked, eroded, or blunt leading edges.
(b) Thereafter, perform repetitive visual or eddy current fan blade leading edge inspections, at intervals not to exceed 200 CIS, and rework or replace fan blades as necessary, in accordance with the Accomplishment Instructions of PW SB No. 72-255, Revision 5, dated January 8, 1990. Perform the fan blade leading edge visual inspections using a strong white light, as well as fingernails and fingertips when inspecting for nicked, eroded, or blunt leading edges.
(c) For PW Model JT9D-7R4H1 engines, install a new or reworked fan blade set with a 52 degree shroud angle, in accordance with PW SB No. 72-309, Revision 10, dated September 2, 1993, within 1 year after the effective date of this AD.
(d) For PW Models JT9D-7R4D, D1, E, E1, G2, and E4 engines, install a new or reworked fan blade set with a 52 degree shroud angle, in accordance with PW SB No. 72-309, Revision 10, dated September 2, 1993, within 2 years after the effective date of this AD.
(e) Installation of a new orreworked fan blade set with a 52 degree fan blade shroud angle, in accordance with paragraphs (c) or (d) of this AD, constitutes a terminating action to the inspection requirements of paragraphs (a) and (b) of this AD.
(f) 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 the Certification Office.
(g) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(h) The modification and inspections shall bedone in accordance with the following service bulletins:
PW SB No. 72-255
1-2
5
January 8, 1990
3-4
4
August 25, 1988
5
5
January 8, 1990
6-8
3
August 17, 1987
Total Pages: 8.
PW SB No. 72-309
1
10
September 2, 1993
2
8
April 5, 1989
3-4
9
June 12, 1991
5
Original
October 2, 1986
6
1
November 7, 1986
7
5
July 22, 1987
8-10
8
April 5, 1989
11
10
September 2, 1993
12-18
8
April 5, 1989
19-20
10
September 2, 1993
21
8
April 5, 1989
Total Pages: 21.
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, 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.
(i) This amendment becomes effective on July 5, 1994.
