[Federal Register Volume 63, Number 39 (Friday, February 27, 1998)]
[Rules and Regulations]
[Pages 9934-9935]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-4400]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-152-AD; Amendment 39-10360; AD 98-04-49]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320-111, -211, -212, -
214, -231, -232, and -233 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 all Airbus Model A320-111, -211, -212, -214, -231, -232, 
and -233 series airplanes, that requires repetitive ultrasonic 
inspections to detect fatigue cracking in the wing/fuselage joint 
cruciform fittings, and corrective actions, if necessary. 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 detect and correct fatigue cracks 
on the wing/fuselage joint cruciform fittings, which could result in 
reduced structural integrity of the wing/fuselage.

DATES: Effective April 3, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 3, 1998.

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, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 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 all Airbus Model A320-111, -211, -
212, -214, -231, -232, and -233 series airplanes was published in the 
Federal Register on December 1, 1997 (62 FR 63476). That action 
proposed to require repetitive ultrasonic inspections to detect fatigue 
cracking in the wing/fuselage joint cruciform fittings, and corrective 
actions, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    All of the commenters support 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 132 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 8 work hours per 
airplane to accomplish the required inspection, at an average labor 
rate of $60 per work hour. Based on these figures, the cost impact of 
the inspection required by this AD on U.S. operators is estimated to be 
$63,360, or $480 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:

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:

98-04-49  Airbus Industrie: Amendment 39-10360. Docket 97-NM-152-AD.

    Applicability: Model A320-111, -211, -212, -214, -231, -232, and 
-233 series airplanes, all serial numbers, 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

[[Page 9935]]

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 fatigue cracks on the wing/fuselage joint 
cruciform fittings, which could result in reduced structural 
integrity of the wing/fuselage, accomplish the following:
    (a) Prior to the accumulation of 28,000 total landings, or 
within 60 days after the effective date of this AD, whichever occurs 
later, perform an ultrasonic inspection to detect fatigue cracking 
in the wing/fuselage joint cruciform fittings, in accordance with 
Airbus Service Bulletin A320-57-1051, Revision 01, dated March 21, 
1996.
    (1) If no cracking is detected, repeat the inspection thereafter 
at intervals not to exceed 20,000 landings.
    (2) If any crack is detected, prior to further flight, repair it 
in accordance with the service bulletin. Thereafter, repeat the 
inspection at the times specified in paragraph (a)(2)(i) or 
(a)(2)(ii) of this AD, as applicable.
    (i) If the crack that was detected and repaired was greater than 
2.5 mm: Repeat the inspection prior to the accumulation of 32,000 
landings since accomplishment of the repair; and thereafter at 
intervals not to exceed 32,000 landings.
    (ii) If the crack that was detected and repaired was less than 
or equal to 2.5 mm: Repeat the inspection prior to the accumulation 
of 28,000 landings since accomplishment of the repair; and 
thereafter at intervals not to exceed 20,000 landings.
    (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 request 
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.

    (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.
    (d) The actions shall be done in accordance with Airbus Service 
Bulletin A320-57-1051, Revision 01, dated March 21, 1996, which 
contains the specified effective pages:

------------------------------------------------------------------------
                                     Revision level      Date shown on  
             Page No.                 shown on page           page      
------------------------------------------------------------------------
1-29, 31-37, 39-40...............  1.................  Mar. 21, 1996.   
30, 38...........................  Original..........  Mar. 30, 1993.   
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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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 96-299-094(B), dated December 18, 1996.

    (e) This amendment becomes effective on April 3, 1998.

    Issued in Renton, Washington, on February 13, 1998.
Stewart R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification. 
Service.
[FR Doc. 98-4400 Filed 2-26-98; 8:45 am]
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