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###### Department of Transportation

###### Federal Aviation Administration 

          - 14 CFR Part 39 
          - [Docket No. 2002-NM-211-AD; Amendment 39-13819; AD 2004-20-14] 
          - RIN 2120-AA64 

# AGENCY:

Federal Aviation Administration, DOT. 

# ACTION:

Final rule. 

# SUMMARY:

This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B4 series airplanes and all Airbus Model A300-600 series airplanes. That AD currently requires a one-time high frequency eddy current inspection to detect cracking of the splice fitting at fuselage frame (FR) 47 between stringers 24 and 25; and corrective actions if necessary. This amendment requires new repetitive inspections of an expanded area and adds airplanes to the applicability in the existing AD. The actions specified by this AD are intended to detect and correct cracking of the splice fitting at fuselage FR 47, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition. 

# DATES:

Effective November 17, 2004. 

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 17, 2004. 

# ADDRESSES:

                        The service information referenced in this AD may be obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to:                         *http://www.archives.gov/​federal_​register/​code_​of_​federal_​regulations/​ibr_​locations.html.*

# FOR FURTHER INFORMATION CONTACT:

Tim Backman, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2797; fax (425) 227-1149. 

# SUPPLEMENTARY INFORMATION:

                    A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 2001-03-14, amendment 39-12118 (66 FR 10957, February 21, 2001), was published as a supplemental notice of proposed rulemaking (NPRM) in the                     **Federal Register**                     on August 4, 2004 (69 FR 47035). The proposal is applicable to all Airbus Model A300 series airplanes and all Airbus Model A300-600 series airplanes. The action proposed to require new repetitive high frequency eddy current inspections to detect cracking of an expanded area, and corrective actions, if necessary; and to add airplanes to the applicability in the existing AD.                 

## Comments 

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public. 

## Clarification of Service Information Requirements for Paragraph (b) of This AD 

In our response to comments in the Preamble of the supplemental NPRM, we stated our intent to revise paragraphs (a), (b), and (c) of the supplemental NPRM to refer to Revision 02 of the referenced Airbus service bulletins as the appropriate sources of service information for accomplishment of the required actions. (Revision 01 of those service bulletins was referenced in the original NPRM for accomplishment of the required actions.) However, while we revised paragraphs (a) and (c) of the supplemental NPRM, we inadvertently omitted the revision to paragraph (b). Therefore, we have revised paragraph (b) of this final rule to reference Revision 02 of Airbus Service Bulletin A300-53-6123 as the appropriate source of service information for the required actions in that paragraph. 

## Conclusion 

                    After careful review of the available data, the FAA has determined that air safety and the public interest require the adoption of the rule with the change                           ( print page 60810)                        described previously. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD.                 

## Cost Impact 

There are approximately 92 airplanes of U.S. registry that will be affected by this AD. 

The inspection of an expanded area that is required in this AD will take approximately 29 work hours per airplane to accomplish, at an average labor rate of $65 per work hour. Based on these figures, the cost impact of the required inspection on U.S. operators is estimated to be $173,420, or $1,885 per airplane, per inspection cycle. 

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions. 

## Regulatory Impact 

The regulations adopted herein will 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 final rule does not have federalism implications under Executive Order 13132. 

                    For the reasons discussed above, I certify that this action (1) Is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it 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 

2. Section 39.13 is amended by removing amendment 39-12118 ( 66 FR 10957, February 21, 2001), and by adding a new airworthiness directive (AD), amendment 39-13819, to read as follows: 

**2004-20-14 Airbus:**                             Amendment 39-13819. Docket 2002-NM-211-AD. Supersedes AD 2001-03-14, Amendment 39-12118.                         

*Applicability:*                             All Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes; and all Model A300 B4 series airplanes; certificated in any category.                         

*Compliance:*                             Required as indicated, unless accomplished previously.                         

To detect and correct cracking of the splice fitting at fuselage frame (FR) 47, which could result in reduced structural integrity of the airplane, accomplish the following: 

## Repetitive Inspections 

(a) For airplanes defined in Airbus Service Bulletin A300-53-0350, Revision 02, dated November 12, 2002: Do a high frequency eddy current (HFEC) inspection to detect cracking of the splice fitting at fuselage FR 47 between stringers 24 and 26 (left- and right-hand sides), at the applicable times specified in paragraph (a)(1) or (a)(2) of this AD. Repeat the inspection thereafter at the earlier of the flight-cycle/flight-hour intervals specified in the applicable column in Table 2 of Figure 1 and Sheet 1 of the Accomplishment Instructions of the service bulletin. Do the inspections in accordance with the service bulletin, excluding Appendix 01. 

(1) For airplanes that have accumulated 20,000 or more total flight cycles as of the effective date of this AD: Do the initial inspection at the later of the times specified in paragraphs (a)(1)(i) and (a)(1)(ii) of this AD: 

(i) At the earlier of the flight-cycle/flight-hour intervals after the effective date of this AD, as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of the service bulletin. 

(ii) Within 750 flight cycles or 1,500 flight hours after the effective date of this AD, whichever is first. 

(2) For airplanes that have accumulated fewer than 20,000 total flight cycles as of the effective date of this AD: Do the initial inspection at the later of the times specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. 

(i) At the earlier of the flight-cycle/flight-hour intervals after the effective date of this AD, as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of the service bulletin. 

(ii) Within 1,800 flight cycles or 3,000 flight hours after the effective date of this AD, whichever is first. 

(b) For airplanes defined in Airbus Service Bulletin A300-53-6123, Revision 02, dated November 12, 2002: Do the HFEC inspection required by paragraph (a) of this AD at the applicable times specified in paragraph (b)(1) or (b)(2) of this AD. Repeat the inspection thereafter at the earlier of the flight-cycle/flight-hour intervals specified in the applicable column in Table 2 of Figure 1 and Sheet 1 of the Accomplishment Instructions of the service bulletin. Do the inspections in accordance with the service bulletin, excluding Appendix 01. 

(1) For airplanes that have accumulated 10,000 or more total flight cycles as of the effective date of this AD: Do the initial inspection within 750 flight cycles or 1,900 flight hours after the effective date of this AD, whichever is first. 

(2) For airplanes that have accumulated fewer than 10,000 total flight cycles as of the effective date of this AD: Do the initial inspection at the later of the times specified in paragraphs (b)(2)(i) and (b)(2)(ii) of this AD. 

(i) At the earlier of the flight-cycle/flight-hour intervals after the effective date of this AD, as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of the service bulletin. 

(ii) Within 1,500 flight cycles or 3,800 flight hours after the effective date of this AD, whichever is first. 

## Repair 

(c) Repair any cracking found during any inspection required by this AD before further flight, in accordance with Airbus Service Bulletin A300-53-0350 or A300-53-6123, both Revision 02, both excluding Appendix 01, both dated November 12, 2002; as applicable. Where the service bulletins specify to contact Airbus in case of certain crack findings, this AD requires that a repair be accomplished before further flight in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent). 

## Credit for Previous Issues of Airbus Service Bulletin 

(d) Accomplishment of the actions before the effective date of this AD in accordance with Airbus Service Bulletin A300-53-0350 or A300-53-6123, Revision 01, dated December 18, 2001; is considered acceptable for compliance with the corresponding actions specified in this AD. 

## Alternative Methods of Compliance 

                            (e) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD.                                   ( print page 60811)    

## Incorporation by Reference 

                            (f) Unless otherwise specified in this AD, the actions shall be done in accordance with Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002; and Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002; as applicable. 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, 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 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to:                             *http://www.archives.gov/​federal_​register/​code_​of_​federal_​regulations/​ibr_​locations.html.*

# Note 1:

The subject of this AD is addressed in French airworthiness directive 2002-184(B), dated April 3, 2002. 

## Effective Date 

(g) This amendment becomes effective on November 17, 2004. 

Issued in Renton, Washington, on September 30, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. 

[FR Doc. 04-22564 Filed 10-12-04; 8:45 am] 

BILLING CODE 4910-13-P