AD 98-21-31

This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 series airplanes. This action requires incorporating into the FAA-approved maintenance program certain torque values for installing certain nuts and bolts of the engine attachment fittings; and follow-on actions, if necessary. 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 prevent cracking of the nuts and bolts of the engine attachment fittings due to overtorquing; such cracking could propagate and result in separation of the engine from the airplane.

Final rule; request for comments.

98-21-31 AIRBUS INDUSTRIE: Amendment 39-10839. Docket 98-NM-288-AD.

Applicability: All Model A300 series airplanes equipped with CF6-50C2 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 (e) 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 cracking of the nuts and bolts of the engine attachment fittings due to overtorquing, which could result in crack propagation and consequent separation of the engine from the airplane, accomplish the following:

(a) For all airplanes: Within 10 flight cycles after the effective date of this AD, incorporate the torque value range for the nuts and bolts of the engine forward and aft attachment fittings into the FAA-approved maintenance program, to indicate the correct range specified by Airbus All Operators Telex (AOT) A300/AOT 71-07, dated September 8, 1998.

(b) For airplanes on which an engine has been replaced between October 1, 1997, and 10 days after the effective date of this AD; if either

the incorrect torque value range was incorporated for the nuts and bolts of the engine attachment fittings, as specified in the October 1, 1997, revision of the Airbus Industrie A300 Airplane Maintenance Manual (AMM); or

maintenance records do not indicate incorporation of the correct torque values, as specified in Airbus All Operators Telex (AOT) A300/AOT 71-07, dated September 8, 1998: Within 10 flight cycles after the effective date of this AD, accomplish either paragraph (b)(1) or (b)(2) of this AD.

(1) Replace all nuts and bolts with new parts, in accordance with the AOT. Or

(2) Remove all nuts and bolts; perform a penetrant inspection to detect cracking of the nuts and bolts, in accordance with the AOT; and accomplish paragraph (b)(2)(i) or (b)(2)(ii), as applicable, of this AD.

(i) If no crack is detected, prior to further flight, reinstall the nuts and bolts that were removed for the inspection. Within 50 flight cycles, replace all nuts and bolts with new parts, in accordance with the AOT.

(ii) If any crack is detected in any nut or bolt, prior to further flight, replace the cracked nut or bolt with a new part and reinstall the uncracked nuts and bolts. Within 50 flight cycles, replace (with a new part) any nut and boltthat has not been replaced within the last 50 flight cycles, in accordance with the AOT.

(c) For airplanes on which an engine has been replaced between October 1, 1997, and 10 days after the effective date of this AD, using the correct torque value range for the nuts and bolts of the engine attachment fittings, as specified in Airbus All Operators Telex (AOT) AOT/A300 71-07, dated September 8, 1998: No further action is required by this AD.

(d) As of the effective date of this AD, no person shall reinstall, on any airplane, any nut or bolt that has been replaced with a new part in accordance with paragraph (b) of this AD.

(e) 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 thensend 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.

(f) 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.

(g) Except for the maintenance program revision provided for in paragraph (a) of this AD, the actions shall be done in accordance with Airbus All Operators Telex (AOT) A300/AOT 71-07, dated September 8, 1998. 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 airworthiness directive T98-376-260 (B).

(h) This amendment becomes effective on November 2, 1998.

The Direction G n rale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, recently notified the FAA that an unsafe condition may exist on certain Airbus Model A300 series airplanes. The DGAC advises that the October 1, 1997, revision of the Airbus Industrie A300 Airplane Maintenance Manual provided an incorrect, excessive torque value range of 450-500 foot pounds, instead of the correct range of 320-340 foot pounds, for installation of the nuts and bolts of the forward and aft attachment fittings for CF6-50C2 engines. Such overtorquing could result in cracking of the nuts and bolts, which, if allowed to propagate, could cause separation of the engine from the airplane.

Explanation of Relevant Service Information
Airbus has issued All Operators Telex (AOT) A300/AOT 71-07, dated September 8, 1998. The AOT describes procedures for a one-time inspection of the engine change job card to determine the torque value range specified for installing the nuts and bolts of the engine forward and aft fittings. Additionally, for airplanes for which the maintenance program is determined to contain incorrect torque values, the AOT describes procedures for correcting the job card, and either replacing all nuts and bolts with new parts or inspecting the nuts and bolts for cracks and eventually replacing all nuts and bolts with new parts. The DGAC approved this AOT and issued French airworthiness directive T98-376-260 (B) 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 ofthe 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 prevent cracking of the nuts and bolts of the engine attachment fittings due to overtorquing, which could result in crack propagation and consequent separation of the engine from the airplane. This AD requires incorporating into the FAA-approved maintenance program certain torque values for installing certain nuts and bolts; and accomplishing follow-on actions specified in the AOT, if necessary.

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 hereonare 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-288-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: