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###### Department of Transportation

###### Federal Aviation Administration 

          - 14 CFR Part 39 
          - [Docket No. 2000-NM-77-AD; Amendment 39-11798; AD 2000-12-20] 
          - RIN 2120-AA64 

# AGENCY:

Federal Aviation Administration, DOT. 

# ACTION:

Final rule. 

# SUMMARY:

This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires modification of the position 1 flap screw jack. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fracture of the lead screw of the position 1 flap screw jack, which could result in failure of the tie bar and possible disconnection of the flap structure from the airplane. 

# DATES:

Effective July 28, 2000. 

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of July 28, 2000. 

# ADDRESSES:

The service information referenced in this AD may be obtained from Airbus Industrie, 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 Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. 

# FOR FURTHER INFORMATION CONTACT:

                        Norman B. Martenson, Manager, International Branch, ANM-116, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington                               ( print page 39078)                            98055-4056; telephone (425) 227-2110; fax (425) 227-1149.                     

# SUPPLEMENTARY INFORMATION:

                    A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Airbus Model A310 series airplanes was published in the                     **Federal Register**                     on April 19, 2000 (65 FR 20921). That action proposed to require modification of the position 1 flap screw jack.                 

## 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. 

## Conclusion 

The FAA has determined that air safety and the public interest require the adoption of the rule as proposed. 

## Cost Impact 

The FAA estimates that 41 airplanes of U.S. registry will be affected by this AD, that it will take approximately 2 work hours per airplane to accomplish the required modification, and that the average labor rate is $60 per work hour. Required parts will cost approximately $105 per airplane. Based on these figures, the cost impact of the required modification AD on U.S. operators is estimated to be $9,225, or $225 per airplane. 

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. 

## 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 adding the following new airworthiness directive: 

**2000-12-20 Airbus Industrie:**                             Amendment 39-11798. Docket 2000-NM-77-AD.                        

*Applicability:*                             Model A310 series airplanes, certificated in any category, except those airplanes on which Airbus Modification 10855 or Airbus Service Bulletin A310-27-2075 has been accomplished.                         

# Note 1:

This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 prevent fracture of the lead screw of the position 1 flap screw jack, which could result in failure of the tie bar and possible disconnection of the flap structure from the airplane, accomplish the following: 

## Modification 

(a) Within 18 months after the effective date of this AD, modify the position 1 flap screw jack in accordance with Airbus Service Bulletin A310-27-2075, Revision 02, dated February 8, 2000. 

# Note 2:

Modifications accomplished prior to the effective date of this AD, in accordance with Airbus Service Bulletin A310-27-2075, dated November 18, 1994, or Revision 01, dated July 20, 1995, are considered acceptable for compliance with the modification specified by this AD.

# Note 3:

The Airbus service bulletin references Lucas/Liebherr Service Bulletin 537-27-M537-15, dated May 12, 1994, as an additional source of service information for accomplishing the applicable action required by this AD.

## Spares 

(b) As of the effective date of this AD, no person shall install on any airplane a position 1 flap screw jack having part number 537G0000-02, unless modified in accordance with this AD. 

## Alternative Methods of Compliance 

(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 4:

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 

(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. 

## Incorporation by Reference 

                            (e) The modification shall be done in accordance with Airbus Service Bulletin A310-27-2075, Revision 02, dated February 8, 2000. 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 5:

The subject of this AD is addressed in French airworthiness directive 1999-510-299(B), dated December 29, 1999.

(f) This amendment becomes effective on July 28, 2000. 

Issued in Renton, Washington, on June 12, 2000. 

Donald L. Riggin, 

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. 

[FR Doc. 00-15307 Filed 6-22-00; 8:45 am] 

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