Airworthiness Directives; Airbus Model A310 Series Airplanes

[Federal Register Volume 63, Number 82 (Wednesday, April 29, 1998)]
[Rules and Regulations]
[Pages 23377-23378]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11070]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-248-AD; Amendment 39-10501; AD 98-09-20]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series Airplanes

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 
repetitive inspections of the fuselage skin to detect corrosion or 
fatigue cracking around and under the chafing plates of the wing root; 
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 and corrosion around and 
under chafing plates of the wing root, which could result in reduced 
structural integrity of the airplane.

DATES: Effective June 3, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 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 certain Airbus Model A310 series 
airplanes was published in the Federal Register on February 24, 1998 
(63 FR 9163). That action proposed to require repetitive inspections of 
the fuselage skin to detect corrosion or fatigue cracking around and 
under the chafing plates of the wing root; and corrective actions, if 
necessary.

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.

[[Page 23378]]

Cost Impact

    The FAA estimates that 36 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 68 work hours per 
airplane to accomplish the required inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $146,880, or 
$4,080 per airplane, per inspection cycle.
    Should an operator elect to accomplish the optional terminating 
action rather than continue the repetitive inspections, it will take 
approximately 45 work hours per airplane to accomplish the 
modification, at an average labor rate of $60 per work hour. Required 
parts will cost approximately $2,229 per airplane. Based on these 
figures, the cost impact of this optional terminating action is 
estimated to be $4,929 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:

98-09-20  Airbus Industrie: Amendment 39-10501. Docket 96-NM-248-AD.

    Applicability: Model A310 series airplanes on which Airbus 
Modifications 8888 and 8889 have 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 (d) 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 and corrosion around and 
under chafing plates of the wing root between fuselage frame (FR) 36 
and FR 39, which could result in reduced structural integrity of the 
airplane, accomplish the following:
    (a) Except as provided by paragraph (b) of this AD: Within 4 
years since date of manufacture, or within 12 months after the 
effective date of this AD, whichever occurs later, perform an 
inspection to detect discrepancies around and under the chafing 
plates of the wing root, in accordance with paragraph B. of the 
Accomplishment Instructions of Airbus Service Bulletin A310-53-2069, 
Revision 1, dated September 19, 1995. If any discrepancy is found, 
prior to further flight, accomplish follow-on corrective actions 
(i.e., removal of corrosion, corrosion protection, high frequency 
eddy current inspection, x-ray inspection), as applicable, in 
accordance with the service bulletin. Repeat the inspections, as 
applicable, thereafter, at intervals specified in the service 
bulletin.
    (b) If any discrepancy is found as a result of an inspection 
required by paragraph (a) of this AD, and Airbus Service Bulletin 
A310-53-2069, Revision 1, dated September 19, 1995, specifies to 
contact Airbus for an appropriate action: Prior to further flight, 
repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate. 
Where differences in the compliance times or corrective actions 
exist between the service bulletin and this AD, the AD prevails.
    (c) Accomplishment of the replacement of the chafing plates in 
accordance with Airbus Service Bulletin A310-53-2070, dated October 
3, 1994, constitutes terminating action for the repetitive 
inspection requirement of this AD.
    (d) 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. 
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.

    (e) 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.
    (f) The actions shall be done in accordance with Airbus Service 
Bulletin A310-53-2069, Revision 1, dated September 19, 1995 and 
Airbus Service Bulletin A310-53-2070, dated October 3, 1994. 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 96-008-175(B), dated January 3, 1996.

    (g) This amendment becomes effective on June 3, 1998.

    Issued in Renton, Washington, on April 21, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-11070 Filed 4-28-98; 8:45 am]
BILLING CODE 4910-13-U

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T05:03:09.299076+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

45c2e88df8255cc7c4f4f912fe72503934b49e8dbd5d2b969166dc165a086b8d

Text SHA-256

3565cbd3aeb5ab54b2ddce68de90c115e2d0573bd3dfdba8ebf85af47395865e