Airworthiness directives: Airbus,

[Federal Register: July 31, 1998 (Volume 63, Number 147)]

[Proposed Rules]

[Page 40850-40852]

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

[DOCID:fr31jy98-35]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-169-AD]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 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 certain Airbus Model A300 series airplanes. This proposal would require repetitive inspections to detect corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing; and follow-on corrective actions, if necessary. 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 corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, which could result in reduced structural integrity of the fuselage pressure vessel.

DATES: Comments must be received by August 31, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 98-NM-169-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,

[[Page 40851]]

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 98-NM-169-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. 98-NM-169-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 certain Airbus Model A300 series airplanes. The DGAC advises that it has received reports indicating that corrosion was detected on the fuselage skin panels, between frames 55 and 58, from stringers 13 to 31, left and right, in the area surrounding the emergency exits. Investigation revealed that on several airplanes, the corrosion was extensive enough to require partial or complete replacement of the fuselage skin panels. The possible cause of the corrosion of the fuselage skin panels may be attributed to the methods used in the manufacturing of the skin panels. The manufacturing methods have since changed, which has resulted in improved corrosion resistance. Such corrosion of the fuselage skin panels that surround the emergency exits immediately aft of the wing, if not detected and corrected, could result in reduced structural integrity of the fuselage pressure vessel.

Explanation of Relevant Service Information

The manufacturer has issued Airbus Industrie Service Bulletin A300- 53-301, dated September 28, 1995, and Revision 1, dated February 20, 1997, which describes procedures for repetitive visual inspections to detect corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, between frames 55 to 58, and from stringers 13 to 31, left and right; and follow-on corrective actions, if necessary. The follow-on corrective actions include removing the corrosion; measuring the remaining thickness of the fuselage skin; applying (optional) flap peen; and applying corrosion protection finish. Additionally, for any affected area that cannot be reworked within certain allowable limits, the service bulletins describe procedures for repair by installing a doubler, or partially or completely replacing the fuselage skin panel, which would eliminate the need for the repetitive inspections of the affected areas. 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 97-357-231(B), dated November 19, 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 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.

Cost Impact

The FAA estimates that 24 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 $2,880, 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 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.

[[Page 40852]]

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 98-NM-169-AD.

   Applicability: Model A300 series airplanes, as listed in Airbus Industrie Service Bulletin A300-53-301, Revision 1, dated February 20, 1997; 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 (b) 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 corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, which could result in reduced structural integrity of the fuselage pressure vessel, accomplish the following:

   (a) Within 18 months after the effective date of this AD, perform a visual inspection to detect corrosion on the fuselage skin panels that surround the emergency exits immediately aft of the wing, between frames 55 to 58, and from stringers 13 to 31, left and right; in accordance with Airbus Industrie Service Bulletin A300-53- 301, dated September 28, 1995, or Revision 1, dated February 20, 1997.

   (1) If no corrosion is detected, repeat the inspection thereafter at intervals not to exceed 18 months on all areas on the fuselage skin panels that do not have a doubler installed or areas that have not been partially or completely replaced.

   (2) If any corrosion is detected, prior to further flight, accomplish rework and perform a residual thickness measurement, in accordance with the service bulletin.

   (i) If the measurement does not exceed the allowable limits specified by the Accomplishment Instructions of the service bulletin, repeat the inspection thereafter at intervals not to exceed 18 months.

   (ii) If the measurement does exceed the allowable limits specified by the Accomplishment Instructions of the service bulletin, prior to further flight, repair using a doubler, or replace the affected areas of the skin panel the installation of a new skin panel (partially or completely), in accordance with the service bulletin. Accomplishment of either action constitutes terminating action for the repetitive inspections required by this AD for the repaired area or the replaced panel sections only.

   Note 2: Inspections, repairs, and replacements of the fuselage skin panels that surround the emergency exits immediately aft of the wing that have been accomplished prior to the effective date of this AD, in accordance with Airbus Industrie Service Bulletin A300-53- 301, dated September 28, 1995, are considered acceptable for compliance with the applicable action specified in this proposed AD.

   (b) 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.

   (c) 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 4: The subject of this AD is addressed in French airworthiness directive 97-357-231(B), dated November 19, 1997.

   Issued in Renton, Washington, on July 24, 1998. D. L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

   [FR Doc. 98-20437Filed7-30-98; 8:45 am]

   BILLING CODE 4910-13-U