[Federal Register Volume 63, Number 114 (Monday, June 15, 1998)]
[Rules and Regulations]
[Pages 32608-32609]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15679]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-194-AD; Amendment 39-10586; AD 98-12-33]
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 
repetitive inspections to detect fatigue cracking on the connecting 
angle between frame 56 and the right-hand frame support at stringer 38; 
and replacement of the connecting angle, if necessary. This amendment 
also provides for an optional terminating action for the repetitive 
inspections.
    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 cracking on the connecting angle, which could result in reduced 
structural integrity of the airplane.

DATES: Effective July 20, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 20, 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 certain Airbus Model A320 series 
airplanes was published in the Federal Register on April 14, 1998 (63 
FR 18156). That action proposed to require repetitive inspections to 
detect fatigue cracking on the connecting angle between frame 56 and 
the right-hand frame support at stringer 38; and replacement of the 
connecting angle, if necessary. That action also proposed to provide 
for an optional terminating action for the repetitive inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received.
    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 5 airplanes of U.S. registry will be 
affected by this AD. It will take approximately 1 work hour per 
airplane to accomplish the required inspection, at an average labor 
rate of $60 per work hour. Based on this figure, the cost impact of the 
inspection required by this AD on U.S. operators is estimated to be 
$300, or $60 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.
    Should an operator elect to perform the optional terminating 
replacement provided by this AD, it would take approximately 3 work 
hours per airplane to accomplish the modification, at an average labor 
rate of $60 per work hour. Required parts would cost $136 or $153 per 
airplane, depending on the service kit purchased. Based on these 
figures, the cost impact of the optional terminating modification 
provided by this AD on U.S. operators is estimated to be as low as 
$1,580, or $316 per airplane, and as high as $1,665, or $333 per 
airplane.

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

[[Page 32609]]

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:

98-12-33 Airbus  Industrie: Amendment 39-10586. Docket 97-NM-194-AD.

    Applicability: Model A320 series airplanes, on which Airbus 
Modification 20941 (reference Airbus Service Bulletin A320-53-1011, 
dated December 9, 1994) has not been accomplished, 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 (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 detect and correct fatigue cracking on the connecting angle 
between frame 56 and the right-hand frame support at stringer 38, 
which could result in reduced structural integrity of the airplane, 
accomplish the following:
    (a) Prior to the accumulation of 20,000 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever occurs later, perform a visual inspection for fatigue 
cracking on the connecting angle between frame 56 and the right-hand 
frame support at stringer 38, in accordance with Airbus Service 
Bulletin A320-53-1084, Revision 1, dated November 28, 1995.
    (1) If no cracking is detected, accomplish either paragraph 
(a)(1)(i) or (a)(1)(ii) of this AD.
    (i) Prior to further flight, replace the connecting angle 
between frame 56 and the right-hand frame support at stringer 38 
with a new part, in accordance with Airbus Service Bulletin A320-53-
1011, dated December 9, 1994; or
    (ii) Repeat the visual inspection thereafter at intervals not to 
exceed 12,000 flight cycles.
    (2) If any cracking is detected, prior to further flight, 
replace the connecting angle between frame 56 and the right-hand 
frame support at stringer 38 with a new part, in accordance with 
Airbus Service Bulletin A320-53-1011, dated December 9, 1994.
    (b) Accomplishment of the replacement of the connecting angle 
constitutes terminating action for the repetitive inspection 
requirements of this AD.
    (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 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.

    (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.
    (e) The actions shall be done in accordance with the following 
Airbus service bulletins, which contain the specified effective 
pages:

----------------------------------------------------------------------------------------------------------------
 Service bulletin referenced and                               Revision level shown on                          
               date                  Page No. shown on page             page               Date shown on page   
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A320-53-1084, Revision 1,          1, 2.....................  1.......................  Nov. 28, 1995.          
 November 28, 1995.                3-11.....................  Original................  Dec. 9, 1994.           
A320-53-1011, December 9, 1994...  1-11.....................  Original................  Dec. 9, 1994.           
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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 96-237-090(B), dated October 23, 1996, and 
Erratum to French airworthiness directive 96-237-090(B), dated 
February 26, 1997.
    (f) This amendment becomes effective on July 20, 1998.

    Issued in Renton, Washington, on June 5, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-15679 Filed 6-12-98; 8:45 am]
BILLING CODE 4910-13-U