[Federal Register Volume 63, Number 186 (Friday, September 25, 1998)]
[Rules and Regulations]
[Pages 51279-51281]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25473]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-192-AD; Amendment 39-10797; AD 98-20-30]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 Series Airplanes 
Equipped With a Bulk Cargo Door

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 series airplanes equipped with a 
bulk cargo door, that requires repetitive inspections to detect fatigue 
cracking of the upper frame flanges; and repair, if necessary. This 
amendment also requires modification of the upper frame flanges of the 
bulk cargo door, which constitutes 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 prevent fatigue cracking of the upper frame flanges, which could 
result in reduced structural integrity of the airplane.

DATES: Effective October 30, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 30, 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 series 
airplanes equipped with a bulk cargo door was published in the Federal 
Register on August 7, 1998 (63

[[Page 51280]]

FR 42286). That action proposed to require repetitive inspections to 
detect fatigue cracking of the upper frame flanges; and repair, if 
necessary. That action also proposed to require modification of the 
upper frame flanges of the bulk cargo door, which constitutes 
terminating action for the repetitive inspections.

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 8 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 these figures, the cost impact of the inspection required by 
this AD on U.S. operators is estimated to be $480, or $60 per airplane, 
per inspection cycle.
    It will take approximately 4 work hours per airplane to accomplish 
the required modification, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of the modification 
required by this AD on U.S. operators is estimated to be $1,920, or 
$240 per airplane.
    The cost impact figures discussed above are 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:

98-20-30  Airbus Industrie: Amendment 39-10797. Docket 97-NM-192-AD.

    Applicability: Model A320 series airplanes, equipped with a bulk 
cargo door (Airbus Modification 20029), 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 prevent fatigue cracking of the upper frame flanges, 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 1,200 flight cycles after the effective date of this AD, 
whichever occurs later: Perform a high frequency eddy current 
inspection to detect fatigue cracking of the upper frame flanges, in 
accordance with Airbus Service Bulletin A320-53-1022, Revision 1, 
dated June 18, 1992.
    (1) If no cracking is detected, accomplish either paragraph 
(a)(1)(i) or (a)(1)(ii) of this AD.
    (i) Repeat the eddy current inspection thereafter at intervals 
not to exceed 1,200 flight cycles until accomplishment of the 
requirements of paragraph (b) of this AD. Or
    (ii) Prior to further flight, modify the upper frame flanges, in 
accordance with Airbus Service Bulletin A320-53-1021, Revision 1, 
dated April 13, 1992. This modification constitutes terminating 
action for the requirements of this AD.
    (2) If any cracking is detected, prior to further flight, repair 
in accordance with Airbus Service Bulletin A320-53-1021, Revision 1, 
dated April 13, 1992.
    Accomplishment of the repair constitutes terminating action for 
the requirements of this AD.
    (b) Prior to the accumulation of 26,000 total flight cycles, or 
within 6,000 flight cycles after the effective date of this AD, 
whichever occurs later: Perform a high frequency eddy current 
inspection to detect fatigue cracking of the upper frame flanges, in 
accordance with Airbus Service Bulletin A320-53-1021, Revision 1, 
dated April 13, 1992.
    (1) If no cracking is detected, prior to further flight, modify 
the upper frame flanges, in accordance with the service bulletin. 
Accomplishment of this modification constitutes terminating action 
for the requirements of this AD.
    (2) If any cracking is detected, prior to further flight, repair 
in accordance with the service bulletin. Accomplishment of the 
repair constitutes terminating action for the 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 
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.
    (e) The inspections, repairs, and modification shall be done in 
accordance with the following Airbus service bulletins, which 
contain the specified effective pages:

[[Page 51281]]



----------------------------------------------------------------------------------------------------------------
 Service bulletin referenced   Page number shown    Revision level shown on
           and date                 on page                   page                     Date shown on page
----------------------------------------------------------------------------------------------------------------
A320-53-1022,................                1-6  1..........................  June 18, 1992.
Revision 1,..................                       .........................  .................................
June 18, 1992................               7, 8  Original...................  October 17, 1991.
A320-53-1021,................            1, 4-24  1..........................  April 13, 1992
Revision 1,..................                       .........................
April 13, 1992...............               2, 3  Original...................  October 17, 1991
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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 96-238-091(B), dated October 23, 1996.

    (f) This amendment becomes effective on October 30, 1998.

    Issued in Renton, Washington, on September 17, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-25473 Filed 9-24-98; 8:45 am]
BILLING CODE 4910-13-P