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###### Department of Transportation

###### Federal Aviation Administration 

          - 14 CFR Part 39 
          - [Docket No. 2000-NM-105-AD] 
          - RIN 2120-AA64 

# 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 A300-600 series airplanes. This proposal would require repetitive high frequency eddy current (HFEC) or rototest inspections to detect cracking in the area surrounding the frame feet attachment holes between fuselage frames (FR) 41 and FR46; installation of new fasteners for certain airplanes; 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 prevent cracking of the center section of the fuselage, which could result in rupture of the frame foot and reduced structural integrity of the airplane. 

# DATES:

Comments must be received by June 15, 2000. 

# ADDRESSES:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2000-NM-105-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, 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                           ( print page 31114)                        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 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 2000-NM-105-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. 2000-NM-105-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. 

## Discussion 

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 all Airbus Model A300-600 series airplanes. The DGAC advises that, during an inspection performed in accordance with Structure Significant Item (SSI) Task 53-15-54, cracking was detected in the area surrounding the frame feet attachment holes at fuselage frames (FR) 43 through FR46 between stringers 24 and 30 on the right-hand side, and at FR45 on the left-hand side. The cracking occurred on an airplane that had accumulated 26,100 total flight cycles and 32,160 total flight hours. Such cracking of the center section of the fuselage, if not detected and corrected, could result in rupture of the frame foot and reduced structural integrity of the airplane. 

## Explanation of Relevant Service Information 

The manufacturer has issued Airbus Service Bulletin A300-53-6122, dated February 9, 2000, which describes procedures for repetitive high frequency eddy current (HFEC) or rototest inspections to detect cracking of the frame feet attachment holes between FR41 and FR46; installation of new fasteners for certain airplanes; and follow-on corrective actions, if necessary. The follow-on corrective actions involve subsequent performing rotating probe inspections and repairing certain cracking conditions. The repair involves reaming out cracks, cold working fastener holes, and installing oversized fasteners. The DGAC classified this service bulletin as mandatory and issued French airworthiness directive 2000-060-303(B), dated February 9, 2000, 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 repetitive HFEC or rototest inspections to detect cracking in the area surrounding the frame feet attachment holes between FR41 and FR46; installation of new fasteners for certain airplanes; and follow-on corrective actions, if necessary. The actions would be required to be accomplished in accordance with the service bulletin described previously, except as discussed below. 

## Differences Between Proposed Rule and Service Bulletin 

Operators should note that, although the service bulletin specifies that the manufacturer may be contacted for disposition of certain conditions, this proposal would require the repair of those conditions to be accomplished in accordance with a method approved by the FAA or the DGAC (or its delegated agent). In light of the type of repair that would be required to address the identified unsafe condition, and in consonance with existing bilateral airworthiness agreements, the FAA has determined that, for the proposed AD, a repair approved by either the FAA or the DGAC would be acceptable for compliance with this proposed AD. 

## Cost Impact 

The FAA estimates that 75 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 6 work hours per airplane to accomplish the proposed inspections, 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 $27,000, or $360 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 a substantial direct effect 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, it is determined that this proposal would not have federalism implications under Executive Order 13132. 

                    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. 

      ( print page 31115)    
§ 39.13 

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

**Airbus Industrie:**                                 Docket 2000-NM-105-AD.                            

*Applicability:*                                 All Model 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 (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 center section of the fuselage, which could result in rupture of the frame foot and reduced structural integrity of the airplane, accomplish the following: 

## High Frequency Eddy Current (HFEC) or Rototest Inspection 

(a) Perform a HFEC or rototest inspection to detect cracking in the area surrounding the frame feet attachment holes between fuselage frames (FR) 41 and FR46 from stringers 24 to 28, left- and right-hand sides, in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000, at the time specified in paragraph (a)(1) or (a)(2), as applicable. 

(1) For airplanes on which Task 53-15-54 in Maintenance Review Board Document (MRBD), Revision 3, dated April 1998, has NOT been accomplished as of the effective date of this AD: Perform the inspection at the later of the times specified in paragraphs (a)(1)(i) and (a)(1)(ii) of this AD. 

(i) Prior to the accumulation of the total flight-cycle or flight-hour threshold, whichever occurs first, specified in paragraph 1.E. (“Compliance”) of the service bulletin; or 

(ii) Within the applicable grace period specified in paragraph 1.E. (“Compliance”) of the service bulletin. 

(2) For airplanes on which Task 53-15-54 in Maintenance Review Board Document (MRBD), Revision 3, dated April 1998, has been accomplished as of the effective date of this AD: Perform the next repetitive inspection at the later of the times specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. 

(i) Within the flight-cycle or flight-hour interval, whichever occurs first, specified in paragraph 1.E. (“Compliance”) of the service bulletin, following the latest inspection accomplished in accordance with the MRBD; or 

(ii) Within the grace period specified in paragraph 1.E. (“Compliance”) of the service bulletin. 

(b) For airplanes on which no cracking is detected during the inspection required by paragraph (a) of this AD, prior to further flight, install new fasteners as applicable, in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000; and repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed the applicable intervals specified in paragraph 1.E. (“Compliance”) of the service bulletin. 

## Corrective Actions 

(c) For airplanes on which cracking is detected during any inspection required by this AD: Prior to further flight, except as required by paragraph (d) of this AD, accomplish corrective actions (e.g., performing rotating probe inspections, reaming out cracks, cold working fastener holes, and installing oversized fasteners) in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000. Repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed the applicable intervals specified in paragraph 1.E. (“Compliance”) of the service bulletin. 

                                (d) If cracking is detected during any inspection required by this AD, and the service bulletin specifies to contact the manufacturer for an appropriate corrective  action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Ge                                                                ne                                                                rale de l'Aviation Civile (DGAC) (or it's delegated agent).                             

## Alternative Methods of Compliance 

(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. 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.

## Special Flight Permits 

(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. 

# Note 3:

The subject of this AD is addressed in French airworthiness directive 2000-060-303(B), dated February 9, 2000.

Issued in Renton, Washington, on May 10, 2000. 

Donald L. Riggin, 

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. 

[FR Doc. 00-12248 Filed 5-15-00; 8:45 am] 

BILLING CODE 4910-13-U