AD 92-19-04 ACTIVE

92-19-04 AIRBUS INDUSTRIE: Amendment 39-8362. Docket No. 91-NM-252-AD.

Applicability: Model A300-B4-620, A310-221, A310-222, and A310-322 series airplanes, equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, or JT9D-7R4H1 series engines; and Model A300-B4-622, A300-B4-622R, and A310-324 series airplanes, equipped with Pratt and Whitney PW 4152 or PW 4158 series engines, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent reduced structural integrity of the airplane, accomplish the following:

(a) Accomplish the requirements of paragraphs (a)(1), (a)(2), and (a)(3) of this AD as follows: For airplanes equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, and JT9D-7R4H1 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW7R4 71-90, Revision 2, dated May 14, 1992, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter JT9/71-00/SS:JDS:0-12-3-1. For airplanes equipped with Pratt and Whitney PW 4152 and PW 4158 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW4NAC 71-86, Revision 2, dated February 28, 1992, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter 4000/71.00/SS:TJF:0-12-03-1.

(1) Prior to the accumulation of 500 hours time-in-service after the effective date of this AD, perform a visual inspection to detect cracks or a broken link in the forward engine mount thrust link, in accordance with Part 1 of the applicable service bulletin.
(i) If no crack or broken link is found, repeat the visual inspection thereafter at intervals not to exceed 1,000 landings until the requirements of paragraph (a)(2) of this AD are accomplished.
(ii) If any crack or a broken link is found as a result of the visual inspection, prior to further flight, replace the link with a serviceable part that has been inspected in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (a) of this AD.

(2) At the next engine removal or within 4,000 hours time-in-service after the effective date of this AD, whichever occurs first, perform a initial etch inspection to detect cracks or a broken link in the forward engine mount thrust link, in accordance with the applicable service bulletin.
(i) If no crack is found as a result of the initial etch inspection, reinstall the link assembly in accordance with the applicable service bulletin. No further action is required.
(ii) If any crack or broken link is found as a result of the initial etch inspection, prior to further flight, replace the link with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (a) of this AD.

(3) Replacement of the forward engine mount thrust link in accordance with the applicable service bulletin constitutes terminating action for the requirements of this AD.

(b) Accomplish the requirements in paragraphs (b)(1), (b)(2), (b)(3), and (b)(4) of this AD as follows: For airplanes equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, and JT9D-7R4H1 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW7R4 71-100, Revision 1, dated July 25, 1991, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter JT9/71-00/SS:0-12-3-1. For airplanes equipped with Pratt and Whitney PW 4152 and PW 4158 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW4NAC 71-105, Revision 1, dated July 25, 1991, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter 4000/71-00/SS:TJF:0-12-03-1.

(1) Prior to the accumulation of 500 hours time-in-service after the effective date of this AD, perform a visual inspection to detect cracks or forging laps in the aft engine mount beam assembly, in accordance with Part 1 of the applicable service bulletin.
(i) If no crack or forging lap is found as a result of the visual inspection, repeat the visual inspection thereafter at intervals not to exceed 1,000 landings until the requirements of paragraph (b)(2) of this AD are accomplished.
(ii) If any crack is found as a result of the visual inspection, prior to further flight, perform a dip etch and a spot fluorescent penetrant inspection to confirm the findings of cracks or forging laps, in accordance with Part 2 of the applicable service bulletin. If any finding of cracks or forging laps is confirmed, prior to further flight, replace the defective beam assembly with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (b) of this AD. As of the effective date of this AD, none of the aft beam assemblies listed in the applicable service bulletin shall be installed on any airplane.

(2) Except as provided by paragraph (b)(3) of this AD, at the next engine removal or within 4,000 hours time-in-service after the effective date of this AD, whichever occurs first, perform a dip etch and a fluorescent penetrant inspection to detect cracks or forging laps in the aft engine mount beam assembly, in accordance with Part 2 of the applicable service bulletin.
(i) If no crack or forging lap is found as a result of the dip etch and fluorescent penetrant inspection, reinstall the beam assembly in accordance with the applicable service bulletin. No further action is required.
(ii) If any crack or forging lap is found as a result of the dip etch and fluorescent penetrant inspection, prior to further flight, replace the beam assembly with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (b) ofthis AD.

(3) If the requirements of paragraph (b)(2) of this AD result in a dual engine removal, the dip etch and fluorescent penetrant inspection of one of the two aft engine mounts may be deferred to the next 4,000 hours time-in-service or engine removal, whichever occurs first, provided no crack or forging lap is found while accomplishing the visual inspections required by paragraph (b)(1) of this AD. If those inspections are deferred, repeat the visual inspection of the deferred aft engine mount, as required by paragraph (b)(1) of this AD, at intervals not to exceed 1,000 landings.

(4) Replacement of the aft engine mount beam assembly, in accordance with the applicable service bulletin, constitutes terminating action for the requirements of paragraph (b) of this AD.

(c) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch.

NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch.

(d) 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.

(e) The inspection and replacement shall be done in accordance with the following Pratt and Whitney service bulletins, as applicable, which contain the specified effective pages:

Service Bulletin
Referenced and Date

Page Number
Revision Level
Shown on Page
Date
Shown on Page
PW4NAC 71-105,
Revision 1,
July 25, 1991,
1-19
1
July 25, 1991,

1-2

3, 6, 8,
11-16, 18
2

1
February 28, 1992

July 25, 1991PW4NAC 71-86,
Revision 2,
February 28, 1992
4-5, 7,
9-10, 17
Original
May 10, 1991

1, 16-20

2, 4-5, 7,
10
2

Original
May 14, 1992

May 10, 1991
PW7R4 71-90,
Revision 2,
May 14, 1992
3, 6, 8-9,
11-15
1
July 25, 1991
PW7R4 71-100,
Revision 1,
July 25, 1991
1, 4, 6-18

2-3, 5
1

Original
July 25, 1991

May 10, 1991

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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(f) This amendment becomes effective on November 17, 1992.