Airworthiness Directives; Airbus Model A320 Series Airplanes

[Federal Register Volume 62, Number 66 (Monday, April 7, 1997)]
[Rules and Regulations]
[Pages 16473-16474]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-8422]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-105-AD; Amendment 39-9988; AD 97-07-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A320 series airplanes, that requires 
modification of an area on the front spar of the wing center section by 
installing shims and new fasteners to reinforce pressure floor 
fittings. This amendment is prompted by a report from the manufacturer 
indicating that full-scale fatigue testing on the test model revealed 
fatigue cracking in this area. The actions specified by this AD are 
intended to prevent fatigue cracking in this area, which can reduce the 
structural integrity of fuselage frame 36 and the wing center section.

DATES: Effective May 12, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 12, 1997.

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: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; fax (206) 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 A320 series 
airplanes was published in the Federal Register on January 21, 1997 (62 
FR 2982). That action proposed to require modification of an area on 
the front spar of the wing center section by installing shims and new 
fasteners to reinforce pressure floor fittings.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.

Conclusion

    After careful review of the available data, including the comments 
noted above, 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 5 Airbus Model A320 series airplanes of U.S. 
registry will be affected by this AD, that it will take approximately 
13 work hours per airplane to accomplish the required actions, and that 
the average labor rate is $60 per work hour. Required parts will cost 
approximately $576 per airplane. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $6,780, or $1,356 
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 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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:

[[Page 16474]]

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:

97-07-14  Airbus Industrie: Amendment 39-9988. Docket 96-NM-105-AD.
    Applicability: Model A320 series airplanes as listed in Airbus 
Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992; 
certificated in any category.

    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 (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 prevent fatigue cracking in the rib flange of the front spar 
side of the wing center section, and consequent reduced structural 
integrity of fuselage frame 36 and the wing center section, 
accomplish the following:
    (a) Prior to the accumulation of 16,000 total landings, or 
within 3 months after the effective date of this AD, whichever 
occurs later, modify the rib flange on the front spar of the wing 
center section by installing shims and new fasteners to reinforce 
pressure floor fittings, in accordance with Airbus Service Bulletin 
A320-57-1013, Revision 1, dated September 29, 1992.

    Note 2: Modification of the rib flange accomplished prior to the 
effective date of this AD in accordance with Airbus Service Bulletin 
A320-57-1013, dated April 12, 1989, is considered acceptable for 
compliance with the modification required by this 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, standardization Branch, ANM-113, 
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, 
Standardization Branch, ANM-113.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (c) Special flight permits may be issued in accordance with 
Secs. 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.
    (d) The modification shall be done in accordance with Airbus 
Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992, 
which contains the following list of effective pages:

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                 Page No.                  Revision level shown on page             Date shown on page          
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1-3......................................  1...........................  September 29, 1992.                    
4-11.....................................  Original....................  April 12, 1989.                        
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    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.
    (e) This amendment becomes effective on May 12, 1997.

    Issued in Renton, Washington, on March 27, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-8422 Filed 4-4-97; 8:45 am]
BILLING CODE 4910-13-U

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