AD 98-11-19 ACTIVE

This document corrects a typographical error that appeared in airworthiness directive (AD) 98-11-19 that was published in the Federal Register on May 28, 1998 (63 FR 29096). The typographical error in the applicability statement of the AD resulted in a reference to an engine model that does not exist. This AD is applicable to certain Airbus Model A310 and A300-600 series airplanes. This AD requires a visual inspection to detect cracks in the aft mount beam assembly of the engine; and replacement of any cracked beam with a new beam or beam assembly; and a fluorescent penetrant inspection to detect cracks in the aft mount beam assembly of the engine, and various follow-on actions.

Final rule; correction.

98-11-19 AIRBUS INDUSTRIE: Amendment 39-10544. Docket 96-NM-172-AD.

"Applicability: Model A310 and A300-600 series airplanes, equipped with Pratt & Whitney Model JT9D-7R4D1, JT9D-7R4E1, JT9D-7R4H1, PW4152, PW4156A, or PW4158 engines; certificated in any category."

NOTE 1: This AD applies to each airplane 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 airplanes 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 (c) 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 toaddress it.

Compliance: Required as indicated, unless accomplished previously.

To detect and correct cracking in the aft mount beam assembly of the engine, which could result in reduced structural integrity of the aft mount beam assembly, accomplish the following:

(a) Within 500 flight hours after the effective date of this AD, perform a visual inspection to detect cracks in the aft mount beam assembly of the engine, in accordance with Part 1 of the Accomplishment Instructions of Pratt & Whitney Alert Service Bulletin PW7R4 A71- 129, Revision 1, dated August 30, 1995, or Pratt & Whitney Alert Service Bulletin PW4NAC A71-149, Revision 1, dated August 30, 1995; as applicable.

(1) If no crack is detected, no further action is required by this paragraph.

(2) If any crack is detected, prior to further flight, replace the cracked beam with a new beam or beam assembly, in accordance with the applicable service bulletin.

(b) Within 4,000 flight cycles after the effective date of this AD, perform a fluorescent penetrant inspection to detect cracks in the aft mount beam assembly of the engine, in accordance with Part 2 of the Accomplishment Instructions of Pratt & Whitney Alert Service Bulletin PW7R4 A71-129, Revision 1, dated August 30, 1995, or Pratt & Whitney Alert Service Bulletin PW4NAC A71-149, Revision 1, dated August 30, 1995; as applicable.

(1) If no crack is detected, prior to further flight, perform an eddy current inspection to detect cracks in the aft mount beam assembly of the engine, in accordance with the applicable service bulletin.

(i) If no crack is detected, prior to further flight, reidentify the beam in accordance with the applicable service bulletin.

(ii) If any crack is detected, prior to further flight, replace the cracked beam with a new beam or beam assembly, in accordance with the applicable service bulletin.

(2) If any crack is detected, prior to further flight, replace the cracked beam with a new beam or beam assembly, in accordance with the applicable service bulletin.

NOTE 2: Accomplishment of the actions required by paragraphs (a) and (b) of this AD in accordance with Pratt & Whitney Service Bulletin PW4MD11 A71-102, Revision 3, dated August 30, 1995, is considered to be acceptable for compliance with those paragraphs.

(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, International Branch, ANM-116, 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, International Branch, ANM-116.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

(d) 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 airplane to a location where the requirements of this AD can be accomplished.

(e) The actions shall be done in accordance with the following Pratt & Whitney Alert Service Bulletins, which contain the following list of effective pages:

Service Bulletin
Referenced and Date
Page Number
Shown on Page
Revision Level
Shown on Page
Date
Shown on Page
PW7R4 A71-129,
Revision 1,
August 30, 1995
1, 4, 12, 17-21,
23, 25-32

2, 3, 5-11, 13-16,
22, 24
1

Original
August 30, 1995

May 30, 1995
PW4NAC A71-149,
Revision 1,
August 30, 1995
1, 2, 4, 12, 17-21
25-32
3, 5-11, 13-16
22-24
1

Original
August 30, 1995

May 30, 1995

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, Connecticut 06108.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.

NOTE 4: The subject of this AD is addressed in French airworthiness directive 96-020- 195(B), dated January 31, 1996.

(f) This amendment becomes effective on July 2, 1998.

Airworthiness Directive (AD) 98-11-19, amendment 39-10544, applicable to certain Airbus Model A310 and A300-600 series airplanes, was published in the Federal Register on May 28, 1998 (63 FR 29096). That AD requires a visual inspection to detect cracks in the aft mount beam assembly of the engine, and replacement of any cracked beam with a new beam or beam assembly. That AD also requires a fluorescent penetrant inspection to detect cracks in the aft mount beam assembly of the engine, and various follow-on actions.

As published, that AD contained a typographical error in the applicability statement: the applicability statement indicated that the AD is applicable to Model A310 and A300-600 series airplanes, equipped with Pratt & Whitney engines of various models, including Model PW4151. The designation should be Model PW4152. The engine model designated PW4151 in the applicability statement of the published AD does not exist.

Since no other part of the regulatory information has been changed, the final rule is not being republished.

The effective date of this AD remains July 2, 1998.
39.13 - [Corrected]

On page 29097, in the second column, the applicability statement of AD 98-11-19 is corrected to read as follows:
* * * * *
"Applicability: Model A310 and A300-600 series airplanes, equipped with Pratt & Whitney Model JT9D-7R4D1, JT9D-7R4E1, JT9D-7R4H1, PW4152, PW4156A, or PW4158 engines; certificated in any category." * * * *

The service information referenced in this AD may be obtained from Pratt & Whitney, 400 Main Street, East Hartford, Connecticut 06108. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.