[Federal Register Volume 64, Number 250 (Thursday, December 30, 1999)]
[Proposed Rules]
[Pages 73439-73441]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-33949]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-337-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of 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 requires modification of Gear Rib 5 of the MLG 
attachment fittings, which constitutes terminating action for the 
repetitive inspections. This action would expand the current inspection 
area for certain airplanes. This proposal is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by the proposed AD are 
intended to prevent fatigue cracking of the MLG attachment fittings, 
which could result in reduced structural integrity of the airplane.

DATES: Comments must be received by January 31, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-337-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments

[[Page 73440]]

submitted will be available, both before and after the closing date for 
comments, in the Rules Docket for examination by interested persons. A 
report summarizing each FAA-public contact concerned with the substance 
of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-337-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 99-NM-337-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On September 2, 1999, the FAA issued AD 99-19-26, amendment 39-
11313 (64 FR 49966, September 15, 1999), applicable to certain Airbus 
Model A300 and A300-600 series airplanes, 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. That AD also requires modification of Gear Rib 5 of the MLG 
attachment fittings, which constitutes terminating action for the 
repetitive inspections. That action was prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The requirements of that AD are intended to 
prevent fatigue cracking of the MLG attachment fittings, which could 
result in reduced structural integrity of the airplane.

Explanation of Relevant Service Information

    Since the issuance of AD 99-19-26, the manufacturer has issued 
Airbus Service Bulletins A300-57A0234, Revision 03, including Appendix 
01, dated September 2, 1999 (for Model A300 series airplanes); and 
A300-57A6087, Revision 02, including Appendix 01, dated June 24, 1999 
(for Model A300-600 series airplanes). These service bulletins expand 
the current inspection area for accomplishing the repetitive detailed 
visual and high frequency eddy current inspections to include holes 43, 
48, 49, 50, 52, and 54 of Gear Rib 5 of the main landing gear (MLG) 
attachment fittings at the lower flange.
    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, classified these service bulletins 
as mandatory and issued French airworthiness directive 1998-151-247(B) 
R2, dated June 16, 1999, in order to assure the continued airworthiness 
of these airplanes in France.

FAA's Conclusions

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would supersede AD 99-19-26 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. It also would continue to require 
modification of Gear Rib 5 of the MLG attachment fittings, which 
constitutes terminating action for the repetitive inspections. This 
proposed AD would expand the current inspection area for certain 
airplanes. The inspections would be required to be accomplished in 
accordance with the service bulletins described previously.

Cost Impact

    There are approximately 164 airplanes of U.S. registry that would 
be affected by this proposed AD.
    The modification that is currently required by AD 99-19-26, and 
retained in this proposed 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 proposed in this AD action 
would 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 proposed 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 current or proposed 
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 proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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.

[[Page 73441]]

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), to read as follows:

Airbus Industrie: 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:

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.
    (d)(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.

    Note 6: The subject of this AD is addressed in French 
airworthiness directive 1998-151-247(B), dated June 16, 1999.

    Issued in Renton, Washington, on December 23, 1999.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-33949 Filed 12-29-99; 8:45 am]
BILLING CODE 4910-13-U