Airworthiness directives: Airbus,

[Federal Register: July 7, 1998 (Volume 63, Number 129)]

[Proposed Rules]

[Page 36622-36624]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr07jy98-18]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-307-AD]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

SUMMARY: This document proposes the adoption of a new airworthiness directive (AD) that is applicable to all Airbus Model A300, A310, and A300-600 series airplanes. This proposal would require repetitive visual inspections to detect cracked or broken door stop fittings on the fuselage frame of the forward passenger doors, and replacement of any cracked or broken fitting with a new fitting. This proposal is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by the proposed AD are intended to detect and correct

[[Page 36623]]

cracked or broken door stop fittings of the forward passenger doors, which could result in failure of the door stop fittings, consequent reduced structural integrity of the door support structure, and sudden loss of cabin pressure in the passenger compartment.

DATES: Comments must be received by August 6, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 97-NM-307-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal holidays.

The service information referenced in the proposed rule 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.

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:

Comments Invited

Interested persons are invited to participate in the making of the proposed 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 above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this notice may be changed in light of the comments received.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with the substance of this proposal will be filedin 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 97-NM-307-AD.'' The postcard will be date stamped and returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 97-NM-307-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

Discussion

The Direction Generale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition may exist on all Airbus Model A300, A310, and A300-600 series airplanes. The DGAC advises that, during full scale fatigue testing of Airbus Model A330 and A340 series airplanes, cracked and broken door stop fittings were discovered on the fuselage frame of the left and right forward passenger doors. The broken door stops were found between 27,000 and 60,000 simulated flight cycles. As a result of these findings, another analysis of fatigue loading on Model A300, A310, and A300-600 series airplanes was performed. The results of this analysis demonstrated that similar fractures also may occur on these airplanes because of the design similarities. Such cracked or broken door stop fittings, if not detected and corrected, could result in failure of the door stop fittings, consequent reduced structural integrity of the door support structure, and sudden loss of cabin pressure in the passenger compartment.

Explanation of Relevant Service Information

Airbus has issued Service Bulletins A300-53-0309 (for Model A300 series airplanes); A310-53-2087 (for Model A310 series airplanes); and A300-53-6060 (for Model A300-600 series airplanes); all dated March 19, 1997; which describe procedures for repetitive visual inspections to detect cracked or broken door stop fittings on the fuselage frame of the forward passenger doors, and replacement of any cracked or broken fitting with a new fitting. Accomplishment of the actions specified in the service bulletins is intended to adequately address the identified unsafe condition. The DGAC classified these service bulletins as mandatory and issued French airworthiness directive 97-124-223(B), dated June 4, 1997, in order to assure the continued airworthiness of these airplanes in France.

FAA's Conclusions

These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of Sec. 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 Proposed 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, the proposed AD would require accomplishment of the actions specified in the service bulletins described previously, except as discussed below.

Differences Between Proposed Rule and Service Bulletin

Operators should note that, although the Airbus service bulletins reference the Master Minimum Equipment List (MMEL) for appropriate compliance times for repair of cracked or broken door stop fittings, this proposed AD would not permit further flight if cracks are detected in the door stop fittings. The FAA has determined that, because of the safety implications and consequences associated with such cracking, any subject door stop fitting that is found to be cracked, must be replaced prior to further flight.

Cost Impact

The FAA estimates that 103 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 2 work hours per airplane to accomplish the proposed inspection, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $12,360, or $120 per airplane, per inspection cycle.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the proposed requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted.

Regulatory Impact

The regulations proposed herein would not have substantial direct effects

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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 proposal would not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this proposed regulation (1) is not a ``significant regulatory action'' under Executive Order 12866; (2) is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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.

   Sec. 39.13 [Amended]

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

   Airbus Industrie: Docket 97-NM-307-AD.

   Applicability: All Model A300, A310, and A300-600 series airplanes; 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 cracked or broken door stop fittings of the forward passenger doors, which could result in failure of the door stop fittings, consequent reduced structural integrity of the door support structure, and sudden loss of cabin pressure in the passenger compartment, accomplish the following:

   (a) Prior to the accumulation of the total flight cycles specified in the ``Threshold'' column of paragraph 1.B.(5) of the Planning Information of Airbus Service Bulletin A300-53-0309 (for Model A300 series airplanes); A310-53-2087 (for Model A310 series airplanes); or A300-53-6060 (for Model A300-600 series airplanes); all dated March 19, 1997; as applicable; or within 200 flight cycles after the effective date of this AD, whichever occurs later; accomplish paragraphs (a)(1) and (a)(2) of this AD.

   (1) Perform a visual inspection of the left and right forward passenger door stop fittings to detect cracked or broken door stop fittings, in accordance with the applicable service bulletin. And

   (2) Thereafter, repeat the visual inspection at the intervals specified in the ``Intervals'' column of paragraph 1.B.(5) of the Planning Information of the applicable service bulletin.

   (b) If any cracked or broken door stop fitting is detected during any inspection required by paragraph (a)(1) or (a)(2) of this AD, prior to further flight, replace the door stop fitting with a new fitting in accordance with Airbus Service Bulletin A300-53-0309 (for Model A300 series airplanes); A310-53-2087 (for Model A310 series airplanes); or A300-53-6060 (for Model A300-600 series airplanes); all dated March 19, 1997; as applicable. Thereafter, repeat the visual inspections at the intervals specified in the ``Intervals'' column of paragraph 1.B.(5) of the Planning Information of the applicable service bulletin.

   (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.

   Note 3: The subject of this AD is addressed in French airworthiness directive 97-124-223(B), dated June 4, 1997.

   Issued in Renton, Washington, on June 30, 1998. Stewart R. Miller, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

   [FR Doc. 98-17958Filed7-6-98; 8:45 am]

   BILLING CODE 4910-13-P