Airworthiness Directives; Airbus Model A300 and A300-600 Series Airplanes

[Federal Register Volume 65, Number 46 (Wednesday, March 8, 2000)]
[Rules and Regulations]
[Pages 12077-12080]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-5331]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-337-AD; Amendment 39-11616; AD 2000-05-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 and A300-600 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A300 and A300-600 series 
airplanes, that currently requires repetitive inspections to detect 
cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings 
at the lower flange, and repair, if necessary. That AD also

[[Page 12078]]

requires modification of Gear Rib 5 of the MLG attachment fittings, 
which constitutes terminating action for the repetitive inspections. 
This amendment expands the current inspection area for certain 
airplanes. 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 MLG attachment fittings, which could result in 
reduced structural integrity of the airplane.

DATES: Effective April 12, 2000.
    The incorporation by reference of certain publications, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of April 12, 2000.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of October 20, 1999 (64 FR 49966, September 15, 
1999).

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) by superseding AD 99-19-26, 
amendment 39-11313 (64 FR 49966, September 15, 1999), which is 
applicable to certain Airbus Model A300 and A300-600 series airplanes, 
was published in the Federal Register on December 30, 1999 (64 FR 
73439). The action proposed to continue to require repetitive 
inspections to detect cracks in Gear Rib 5 of the main landing gear 
(MLG) attachment fittings at the lower flange, and repair, if 
necessary; and modification of Gear Rib 5 of the MLG attachment 
fittings, which would constitute terminating action for the repetitive 
inspections. That action also proposed to expand the current inspection 
area for certain airplanes.

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

    There are approximately 164 airplanes of U.S. registry that will be 
affected by this AD.
    The modification that is currently required by AD 99-19-26, and 
retained in this AD, takes approximately 62 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Required 
parts cost approximately $10,270 per airplane. Based on these figures, 
the cost impact of the currently required inspections on U.S. operators 
is estimated to be $2,294,360, or $13,990 per airplane.
    The new expanded inspections that are required in this AD action 
will take approximately 6 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Based on these figures, the 
cost impact of the requirements of this AD on U.S. operators is 
estimated to be $59,040, or $360 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 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 removing amendment 39-11313 (64 FR 
49966, September 15, 1999), and by adding a new airworthiness directive 
(AD), amendment 39-11616, to read as follows:

2000-05-07  Airbus Industrie: Amendment 39-11616. Docket 99-NM-337-
AD. Supersedes AD 99-19-26, Amendment 39-11313.
    Applicability: Model A300 series airplanes, as listed in Airbus 
Service Bulletin A300-57-0234, Revision 01, dated March 11, 1998; 
and Model A300-600 series airplanes, as listed in Airbus Service 
Bulletin A300-57-6087, Revision 01, dated March 11, 1998; except 
airplanes on which Airbus Modification 11912 has been installed in 
production, or on which Airbus Modification 11932 has 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)(1) 
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 main landing gear (MLG) 
attachment fittings, which could result in reduced structural 
integrity of the airplane, accomplish the following:

[[Page 12079]]

Repetitive Inspections

    (a) Perform a detailed visual and a high frequency eddy current 
(HFEC) inspection to detect cracks in Gear Rib 5 of the MLG 
attachment fittings at the lower flange, in accordance with Airbus 
Service Bulletin A300-57-6087, Revision 01, dated March 11, 1998 
(for Model A300-600 series airplanes); or A300-57-0234, Revision 01, 
dated March 11, 1998 (for Model A300 series airplanes); as 
applicable; at the time specified in paragraph (a)(1) or (a)(2) of 
this AD, as applicable. After the effective date of this AD, only 
Airbus Service Bulletin A300-57A0234, Revision 02, dated June 24, 
1999, or Revision 03, including Appendix 01, dated September 2, 1999 
(for Model A300 series airplanes); or A300-57A6087, Revision 02, 
including Appendix 01, dated June 24, 1999 (for Model A300-600 
series airplanes); as applicable; shall be used. Repeat the 
inspections thereafter at intervals not to exceed 1,500 flight 
cycles.

Detailed Visual Inspection

    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.''

    (1) For airplanes that have accumulated 20,000 or more total 
flight cycles as of March 9, 1998: Inspect within 500 flight cycles 
after March 9, 1998.
    (2) For airplanes that have accumulated less than 20,000 total 
flight cycles as of March 9, 1998: Inspect prior to the accumulation 
of 18,000 total flight cycles, or within 1,500 flight cycles after 
March 9, 1998, whichever occurs later.

    Note 3: Accomplishment of the initial detailed visual and HFEC 
inspections in accordance with Airbus Service Bulletin A300-57A0234 
or A300-57A6057, both dated August 1, 1997, as applicable, is 
considered acceptable for compliance with the initial inspections 
required by paragraph (a) of this AD.

Repair

    (b) If any crack is detected during any inspection required by 
this AD, prior to further flight, accomplish the requirements of 
paragraphs (b)(1) or (b)(2) of this AD, as applicable.
    (1) If a crack is detected at one hole only, and the crack does 
not extend out of the spotface of the hole, repair in accordance 
with Airbus Service Bulletin A300-57A0234, Revision 02, dated June 
24, 1999, or Revision 03, including Appendix 01, dated September 2, 
1999 (for Model A300 series airplanes); or A300-57A6087, Revision 
02, including Appendix 01, dated June 24, 1999 (for Model A300-600 
series airplanes); as applicable.
    (2) If a crack is detected at more than one hole, or if any 
crack at any hole extends out of the spotface of the hole, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate, or the 
Direction Generale de l'Aviation Civile (or its delegated agent).

Terminating Modification

    (c) Prior to the accumulation of 21,000 total flight cycles, or 
within 2 years after October 20, 1999 (the effective date of AD 99-
19-26, amendment 39-11313), whichever occurs later: Modify Gear Rib 
5 of the MLG attachment fittings at the lower flange in accordance 
with Airbus Service Bulletin A300-57-6088, Revision 01, including 
Appendix 01 (for Model A300-600 series airplanes), or A300-57-0235, 
Revision 01, including Appendix 01 (for Model A300 series 
airplanes), all dated February 1, 1999, as applicable. 
Accomplishment of this modification constitutes terminating action 
for the repetitive inspection requirements of this AD.

    Note 4: Accomplishment of the modification required by paragraph 
(d) of this AD prior to the effective date of this AD in accordance 
with Airbus Service Bulletin A300-57-6088 or A300-57-0235, both 
dated August 1, 1998; as applicable; is acceptable for compliance 
with the requirements of that paragraph.

Alternative Methods of Compliance

    (d)(1) 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.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 99-19-26, amendment 39-11313, are approved as 
alternative methods of compliance with this AD.

    Note 5: 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

    (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.

Incorporation by Reference

    (f) Except as provided by paragraph (b)(2) of this AD, the 
actions shall be done in accordance with Airbus Service Bulletin 
A300-57-6087, Revision 01, dated March 11, 1998; Airbus Service 
Bulletin A300-57A6087, Revision 02, including Appendix 01, dated 
June 24, 1999; Airbus Service Bulletin A300-57-0234, Revision 01, 
dated March 11, 1998; Airbus Service Bulletin A300-57A0234, Revision 
02, dated June 24, 1999; Airbus Service Bulletin A300-57A0234, 
Revision 03, including Appendix 01, dated September 2, 1999; Airbus 
Service Bulletin A300-57-6088, Revision 01, including Appendix 01, 
dated February 1, 1999; and Airbus Service Bulletin A300-57-0235, 
Revision 01, including Appendix 01, dated February 1, 1999; as 
applicable.
    (1) The incorporation by reference of Airbus Service Bulletin 
A300-57A6087, Revision 02, including Appendix 01, dated June 24, 
1999; Airbus Service Bulletin A300-57A0234, Revision 02, dated June 
24, 1999; and Airbus Service Bulletin A300-57A0234, Revision 03, 
including Appendix 01, dated September 2, 1999; is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) The incorporation by reference of Airbus Service Bulletin 
A300-57-6087, Revision 01, dated March 11, 1998; Airbus Service 
Bulletin A300-57-0234, Revision 01, dated March 11, 1998; Airbus 
Service Bulletin A300-57-6088, Revision 01, including Appendix 01, 
dated February 1, 1999; and Airbus Service Bulletin A300-57-0235, 
Revision 01, including Appendix 01, dated February 1, 1999; was 
approved previously by the Director of the Federal Register as of 
October 20, 1999 (64 FR 49966, September 15, 1999).
    (3) 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 6: The subject of this AD is addressed in French 
airworthiness directive 1998-151-247(B), dated June 16, 1999.

    (g) This amendment becomes effective on April 12, 2000.


[[Page 12080]]


    Issued in Renton, Washington, on February 29, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-5331 Filed 3-7-00; 8:45 am]
BILLING CODE 4910-13-U

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