AD 98-12-24

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AD Number:
98-12-24
Document Type:
AD Final Rules
Docket Number:
98-NM-182-AD
Subject Heading:
Airworthiness Directives; Airbus Model A310 Series Airplanes Equipped With General Electric Model CF...Show more
Subject:
Inspect Aft Engine Mounts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/25/1998
Make:
Airbus
Model:
A310-203 | A310-221 | A310-222 | A310-304 | A310-322 | A310-324 | A310-325
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39 [63 FR 31614 NO. 111 06/10/98]
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 98-12-24
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   98-NM-182-AD

AMENDMENT:   39-10578

AD NUMBER:   98-12-24

SUBJECT HEADING:   Airworthiness Directives; Airbus Model A310 Series Airplanes Equipped With General Electric Model CF6-80A3 Series Engines

ACTION:   Final rule; request for comments.

SUMMARY:   This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310 series airplanes. This action requires a one-time inspection to detect cracked or broken links of the aft engine mounts, and replacement of any cracked or broken link with a serviceable link. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct cracking of the links of the aft engine mounts, which could result in failure of the aft engine attachment and consequent separation of the engine from the airplane.

DATES:   Effective June 25, 1998. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 25, 1998. Comments for inclusion in the Rules Docket must be received on or before July 10, 1998.

ADDRESSES:   Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 98-NM-182-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined 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.

FOR FURTHER INFORMATION CONTACT:   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.

SUPPLEMENTARY INFORMATION:  
The Direction Générale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition may exist on certain Airbus Model A310 series airplanes. The DGAC advises that, during a routine maintenance inspection of a General Electric Model CF6-80A3 series engine for an Airbus Model A310 series airplane, a crack was discovered on the left-hand link of the aft engine mount assembly. The crack measured 10 mm in length and was located at the upper end of the link, at the gearing location. The cause of the crack is still under investigation. This condition, if not corrected, could result in failure of the aft engine attachment and consequent separation of the engine from the airplane.

Explanation of Relevant Service Information
Airbus has issued All Operators Telex (AOT) 71 06, dated October 21, 1997, which describes procedures for a one-time detailed visual inspection to detect cracked or broken links of the aft engine mounts, and replacement of any cracked or broken link with a serviceable link. The DGAC classified this AOT as mandatory and issued French telegraphic airworthiness directive T97-324-234(B), dated October 22, 1997, and airworthiness directive 97-324-234(B), dated November 5, 1997; in order to assure the continued airworthiness of these airplanes in France.

FAA's Conclusions
This airplane model is manufactured in France and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.

Explanation of Requirements of Rule
Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, this AD is being issued to detect and correct cracking of the links of the aft engine mounts, which could result in failure of the aft engine attachment and consequent separation of the engine from the airplane. This AD requires accomplishment of the actions specified in the AOT described previously. This AD also requires that operators report results of inspection findings (positive and negative) to Airbus.

Interim Action
This is considered to be interim action until final action is identified, at which time the FAA may consider further rulemaking.

Determination of Rule's Effective Date
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 shall 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 Rules Docket 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 rule must submit a self-addressed, stamped postcard on which the following statement is made: "Comments to Docket Number 98-NM-182-AD." The postcard will be date stamped and returned to the commenter.

Regulatory Impact
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 that it 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 U.S.C. 106(g), 40113, 44701.
§ 39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive:

REGULATORY TEXT:  
98-12-24 AIRBUS INDUSTRIE: Amendment 39-10578. Docket 98-NM-182-AD.

Applicability: Model A310 series airplanes, equipped with General Electric Model CF6-80A3 series 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 to address it.

Compliance: Required as indicated, unless accomplished previously.

To detect and correct cracking of the links of the aft engine mounts, which could result in failure of the aft engine attachment and consequent separation of the engine from the airplane, accomplish the following:

(a) Within 5 days after the effective date of this AD, perform a one-time detailed visual inspection to detect cracked or broken links of the aft engine mounts, in accordance with Airbus All Operators Telex (AOT) 71 06, dated October 21, 1997. If any cracked or broken link is detected, prior to further flight, replace the cracked or broken link with a serviceable link, in accordance with the AOT.

(b) Within 10 days after the effective date of this AD, submit a report of the inspection results (positive and negative) to Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.

(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 2: 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 Airbus All Operators Telex 71 06, dated October 21, 1997. 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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 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.

NOTE 3: The subject of this AD is addressed in French telegraphic airworthiness directive T97-324-234(B), dated October 22, 1997, and airworthiness directive 97-324-234(B), dated November 5, 1997.

(f) This amendment becomes effective on June 25, 1998.

FOOTER: