[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]
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