AD 2000-07-26

[Federal Register Volume 65, Number 75 (Tuesday, April 18, 2000)]
[Rules and Regulations]
[Pages 20715-20717]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-9112]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-304-AD; Amendment 39-11682; AD 2000-07-26]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 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 A300 series airplanes, that requires 
a

[[Page 20716]]

one-time detailed visual inspection to detect corrosion on the outer 
surface of the fuselage skin panel; application of corrosion preventive 
protection; and corrective action, 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 corrosion of the fuselage 
skin panel, which could result in cracking and consequent reduced 
structural integrity of the airplane.

DATES: Effective May 23, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 23, 2000.

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 A300 series 
airplanes was published in the Federal Register on January 3, 2000 (65 
FR 91). That action proposed to require a one-time detailed visual 
inspection to detect corrosion on the outer surface of the fuselage 
skin panel; application of corrosion preventive protection; and 
corrective action, if necessary.

Comment Received

    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.

Request to Reference Latest Service Bulletin Revision

    One commenter, the manufacturer, requests that the proposed AD be 
revised to refer to Airbus Service Bulletin A300-53-0328, Revision 01, 
including Appendix 01, dated March 15, 2000, for accomplishment of the 
inspection. The original issue of the service bulletin, dated March 5, 
1999, was referenced in the proposed AD as the appropriate source of 
service information. The commenter notes that the original issue of the 
service bulletin references a 30-month interval rather than the correct 
5-year interval for certain follow-on repetitive inspections that are 
covered by the Corrosion Prevention Control Program (CPCP). The 
commenter suggests that referencing Revision 01 of the service 
bulletin, in which the correct interval is specified, will avoid 
confusion on the part of operators.
    The FAA concurs. The FAA has reviewed the procedures described in 
Airbus Service Bulletin A300-53-0328, Revision 01, including Appendix 
01, dated March 15, 2000, and has determined that they are equivalent 
to those described in the original issue of the service bulletin, 
except for certain cleaning procedures. The final rule has been revised 
to refer to Revision 01 of the service bulletin as the appropriate 
source of service information. However, a ``NOTE'' has been included in 
the final rule to provide credit for previous accomplishment of the 
actions required by this AD in accordance with the original issue of 
the service bulletin.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 3 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 4 or 22 work hours 
per airplane, depending on the airplane configuration, 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 $240 or $1,320 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 a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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:

2000-07-26  Airbus Industrie: Amendment 39-11682. Docket 99-NM-304-
AD.
    Applicability: Model A300 series airplanes, certificated in any 
category; except those on which Airbus Modification 04201 has been 
accomplished.

    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.

[[Page 20717]]

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 corrosion of the fuselage skin panel, 
which could result in cracking and consequent reduced structural 
integrity of the airplane, accomplish the following:

Inspection

    (a) Perform a one-time detailed visual inspection of the outer 
surface of the fuselage skin panel between fuselage frames FR39 and 
FR40, and between stringers 27 and 33, for corrosion; in accordance 
with Airbus Service Bulletin A300-53-0328, Revision 01, including 
Appendix 01, both dated March 15, 2000. Perform the inspection at 
the applicable time specified in paragraph (a)(1), (a)(2), or (a)(3) 
of this AD. If any corrosion is found, prior to further flight, 
repair (i.e., rework corroded areas, or repair or replace panels, as 
applicable) in accordance with the service bulletin, except as 
provided by paragraph (b) of this AD. Temporary repairs must be 
replaced with permanent repairs prior to accumulation of the life 
limits specified in the service bulletin.
    (1) For airplanes for which the date of manufacture was less 
than 15 years before the effective date of this AD: Inspect within 
18 months after the effective date of this AD.
    (2) For airplanes for which the date of manufacture was at least 
15 but less than 20 years before the effective date of this AD: 
Inspect within 12 months after the effective date of this AD.
    (3) For airplanes for which the date of manufacture was 20 or 
more years before the effective date of this AD: Inspect within 6 
months after the effective date of this AD.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (b) Where Airbus Service Bulletin A300-53-0328, Revision 01, 
dated March 15, 2000, specifies that Airbus may be contacted for a 
repair, prior to further flight, replace the skin panel with a new 
or serviceable skin panel in accordance with the service bulletin.

    Note 3: Accomplishment of the actions required by this AD in 
accordance with Airbus Service Bulletin A300-53-0328, dated March 5, 
1999, prior to the effective date of this AD, is acceptable for 
compliance with the requirements of this AD.

Alternative Methods of Compliance

    (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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (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.

Incorporation by Reference

    (e) The actions shall be done in accordance with Airbus Service 
Bulletin A300-53-0328, Revision 01, including Appendix 01, dated 
March 15, 2000. 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 5: The subject of this AD is addressed in French 
airworthiness directive 1999-209-281(B), dated May 19, 1999.
    (f) This amendment becomes effective on May 23, 2000.


    Issued in Renton, Washington, on April 6, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-9112 Filed 4-17-00; 8:45 am]
BILLING CODE 4910-13-U