AD 96-16-07

This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80C2 series turbofan engines. This action supersedes priority letter AD 96-09-01 that currently requires borescope inspections of the rear right hand mount link to determine if the serial number matches those listed in applicable service bulletins as improperly manufactured, and replacement, if necessary, with a serviceable part. This action references a newly revised service bulletin and bases the compliance time on the effective date of this superseding AD for engines installed on McDonnell Douglas MD-11 series aircraft. This amendment is prompted by the availability of the newly revised service bulletin. The actions specified by this AD are intended to prevent rear right hand mount link failure, which could result in engine separation from the aircraft.

Final rule; request for comments.

96-16-07 General Electric Company: Amendment 39-9707. Docket No. 96-ANE-16. Supersedes Priority Letter AD 96-09-01, issued April 15, 1996.

Applicability: General Electric Company (GE) CF6-80C2 series turbofan engines identified by Serial Numbers (S/N's) listed in GE CF6-80C2 Service Bulletin (SB) No. 72-835, Revision 1, dated May 2, 1996. These engines are installed on but not limited to Airbus A300 and A310 series, and McDonnell Douglas MD-11 series aircraft.

NOTE: 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 (d) 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 rear right hand mount link failure, which could result in engine separation from the aircraft, accomplish the following:

(a) No further action is required for operators that have complied with priority letter AD 96-09-01.

(b) For engines installed on Airbus A300 and A310 series aircraft, accomplish the following:

(1) Prior to further flight, borescope inspect the rear right hand mount link in accordance with the Accomplishment Instructions of GE CF6-80C2 SB No. 72-835, Revision 1, dated May 2, 1996, to determine if the link S/N is listed in that SB.

(2) If the link S/N does not match those listed in that SB, no further action is required.

(3) If the link S/N matches those listed in that SB, prior to further flight remove the rear right hand mount link from service and replace with a serviceable part in accordance with the Accomplishment Instructions of GE CF6-80C2 SB No. 72-835, Revision 1, dated May 2, 1996.

(c) For engines installed on McDonnell Douglas MD-11 series aircraft, accomplish the following:
(1) Within 15 days after the effective date of this AD, borescope inspect the rear right hand mount link in accordance with the Accomplishment Instructions of GE CF6-80C2 SB No. 72- 835, Revision 1, dated May 2, 1996, to determine if the S/N is listed in that SB.

(2) If the S/N does not match those listed in that SB, no further action is required.

(3) If the S/N matches those listed in that SB, within 60 days after the effective date of this AD, remove the rear right hand mount link from service and replace with a serviceable part in accordance with the Accomplishment Instructions of GE CF6-80C2 SB No. 72-835, Revision 1, dated May 2, 1996.

(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 the Engine Certification Office.

(e) 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.

(f) The actions required by this AD shall be done in accordance with the following SB:

Document No.
Pages
Revision
Date
GE CF6-80C2 SB
No. 72-835
1-16
1
May 2, 1996
Total pages: 16.

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 General Electric Technical Services, Attn: Leader for Distribution/Microfilm, 10525 Chester Road, Cincinnati, OH 45215; phone (513) 672-8400 ext. 114, fax (513) 672-8422. 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 supersedes priority letter AD 96-09-01, issued April 15, 1996.

(h) This amendment becomes effective on August 28, 1996.

On April 15, 1996, the Federal Aviation Administration (FAA) issued priority letter airworthiness directive (AD) 96-09-01, applicable to General Electric Company (GE) CF6-80C2 series turbofan engines, which requires borescope inspections of the rear right hand mount link to determine if the serial number matches those listed in applicable service bulletins as improperly manufactured, and replacement, if necessary, with a serviceable part. That action was prompted by reports of rear right hand mount links that were not properly heat treated during manufacture. Rear right hand mount links that are not properly heat treated are susceptible to failure due to insufficient strength. That condition, if not corrected, could result in rear right hand mount link failure, which could result in engine separation from the aircraft.

Since the issuance of that priority letter AD, GE has issued CF6-80C2 Service Bulletin (SB) No. 72-835, Revision 1, dated May 2, 1996. This AD references this new revision, and bases the compliance time on the effective date of this superseding AD for engines installed on McDonnell Douglas MD-11 series aircraft.

Since an unsafe condition has been identified that is likely to exist or develop on other engines of this same type design, this AD supersedes priority letter AD 96-09-01 to require the following:

For certain engines installed on Airbus A300 and A310 series aircraft, prior to further flight, borescope inspect the rear right hand mount link to determine if the link S/N is listed in GE CF6- 80C2 SB No. 72-835, Revision 1, dated May 2, 1996. If the link S/N matches those listed in that SB, prior to further flight, remove the rear right hand mount link from service and replace with a serviceable part.

For certain engines installed on McDonnell Douglas MD-11 series aircraft, within 15 days after the effective date of this AD, borescope inspect the rear right hand mount link to determine if the link S/N is listed in GE CF6-80C2 SB No. 72-835, Revision 1, dated May 2, 1996. If the link S/N matches those listed in that SB, within 60 days after the effective date of this AD, remove the rear right hand mount link from service and replace with a serviceable part.

Engines installed on Airbus A300 and A310 series aircraft have higher certification mount loads than those installed on McDonnell Douglas MD-11 aircraft, and therefore require immediate inspection. The actions are required to be accomplished in accordance with the service bulletin described previously.

Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days.

Comments Invited

Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified under the caption "ADDRESSES." All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available, both before and after the closing date for comments, in the RulesDocket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must submit a self-addressed, stamped postcard on which the following statement is made: "Comments to Docket Number 96-ANE-16." The postcard will be date stamped and returned to the commenter.

The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

The FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and is not a "significant regulatory action" under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39 - AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 USC 106(g), 40113, 44701. 39.13 - [AMENDED]

2. Section 39.13 is amended by adding the following new airworthiness directive: