[Federal Register Volume 63, Number 225 (Monday, November 23, 1998)]
[Proposed Rules]
[Pages 64661-64664]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31173]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-249-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 and A300-600 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
[[Page 64662]]
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 inspections to
detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment
fittings at the lower flange, and repair, if necessary. This action
would establish repetitive inspection intervals for certain inspections
required by the existing AD. This action also would add a requirement
to modify Gear Rib 5 of the MLG attachment fittings, which constitutes
terminating action for the repetitive inspections. 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 December 23, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-249-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 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 98-NM-249-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. 98-NM-249-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On January 23, 1998, the FAA issued AD 98-03-06, amendment 39-10298
(63 FR 5224, February 2, 1998), applicable to certain Airbus Model A300
and A300-600 series airplanes, to require 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 action was prompted by
issuance of mandatory continuing airworthiness information by a foreign
civil airworthiness authority. The requirements of that AD are intended
to detect and correct 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 98-03-06, the manufacturer has issued
Airbus Service Bulletins A300-57-0234, Revision 01 (for Model A300
series airplanes), and A300-57-6087, Revision 01 (for Model A300-600
series airplanes), both dated March 11, 1998. Airbus Service Bulletin
A300-57-0234, Revision 01, limits the effectivity of the existing AD,
however, these service bulletins add no additional airplanes to the
effectivity. These service bulletins recommend repetitive intervals for
accomplishing detailed visual and high frequency eddy current
inspections to detect cracks in 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 98-151-247(B), dated April 8, 1998, in
order to assure the continued airworthiness of these airplanes in
France.
The manufacturer also has issued Airbus Service Bulletins A300-57-
0235 (for Model A300 series airplanes), and A300-57-6088 (for Model
A300-600 series airplanes), both dated August 5, 1998. These service
bulletins describe procedures for modification of Gear Rib 5 of the MLG
attachment fittings at the lower flange by increasing the depth,
diameter, and corner radius of the spotface of specified fastener
holes. Accomplishment of this modification would eliminate the need for
the repetitive inspections described previously. The DGAC approved
these service bulletins.
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 98-03-06 to
continue to require inspections to detect cracks in Gear Rib 5 of MLG
attachment fittings at the lower flange, and repair, if necessary. The
proposed AD also would establish repetitive inspection intervals for
certain inspections. In addition, the proposal would require
modification of Gear Rib 5 of the MLG attachment fittings, which
constitutes terminating action for the repetitive inspections. The
actions would be required to be accomplished in accordance with the
[[Page 64663]]
service bulletins described previously, except as discussed below.
Differences Between the Proposed AD and the Related Service
Bulletins
Operators should note that, although the service bulletins
described previously specify that appropriate corrective action may be
obtained by contacting the manufacturer for disposition of certain
repair conditions, this proposal would require that any such repairs be
accomplished in accordance with a method approved by either the FAA or
the Direction Generale de l'Aviation Civile (or its delegated agent).
Operators also should note that this AD proposes to mandate, prior
to the accumulation of 21,000 total flight cycles or within 2 years
after the effective date of the AD, whichever occurs later, the
modification of Gear Rib 5 of the MLG attachment fittings as described
in Airbus Service Bulletins A300-57-6088 and A300-57-0235.
Accomplishment of this modification would constitute terminating action
for the repetitive inspections.
The FAA has determined that long-term continued operational safety
will be better assured by modifications or design changes to remove the
source of the problem, rather than by repetitive inspections. Long-term
inspections may not be providing the degree of safety assurance
necessary for the transport airplane fleet. This, coupled with a better
understanding of the human factors associated with numerous repetitive
inspections, has led the FAA to consider placing less emphasis on
special procedures and more emphasis on design improvements. The
proposed modification requirement is in consonance with these
considerations.
Cost Impact
There are approximately 164 airplanes of U.S. registry that would
be affected by this proposed AD.
The inspection currently required by AD 98-03-06, and retained in
this proposed AD, takes 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 currently required inspection on
U.S. operators is estimated to be $59,040, or $360 per airplane, per
inspection cycle.
The modification that is proposed in this AD action would take
approximately 62 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts would cost
approximately $10,270 per airplane. Based on these figures, the cost
impact of the new actions proposed by this AD on U.S. operators is
estimated to be $2,294,360, or $13,990 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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-10298 (63 FR
5224, February 2, 1998), and by adding a new airworthiness directive
(AD), to read as follows:
Airbus Industrie: Docket 98-NM-249-AD. Supersedes AD 98-03-06,
Amendment 39-10298.
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;
certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
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 (e) 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:
(a) For Model A300 series airplanes that have accumulated more
than 27,000 flight cycles as of March 9, 1998 (the effective date of
AD 98-03-06, amendment 39-10298): Except as provided by paragraph
(b) of this AD, within 40 flight cycles after March 9, 1998, perform
a detailed visual inspection to detect cracks in Gear Rib 5 of the
MLG attachment fittings at the lower flange, in accordance with
Airbus Service Bulletin A300-57-0234, Revision 01, dated March 11,
1998. Thereafter, repeat the inspection at intervals not to exceed
40 flight cycles, until the initial inspections required by
paragraph (b) are accomplished.
(b) For all airplanes: 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 (b)(1)
or (b)(2) of this AD, as applicable. Repeat the inspections
thereafter at intervals not to exceed 1,500 flight cycles.
Accomplishment of the inspections required by this paragraph
terminates the inspections required by paragraph (a) of this AD.
(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
[[Page 64664]]
accumulation of 18,000 total flight cycles, or within 1,500 flight
cycles after March 9, 1998, whichever occurs later.
Note 2: Accomplishment of the initial detailed visual and HFEC
inspections in accordance with Airbus Service Bulletin A300-57A0234
or A300-57A6057, both dated August 5, 1997, as applicable, is
considered acceptable for compliance with the initial inspections
required by paragraph (a) or (b) of this AD.
(c) If any crack is detected during any inspection required by
this AD, prior to further flight, 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).
(d) Prior to the accumulation of 21,000 total flight cycles, or
within 2 years after the effective date of this AD, 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 (for
Model A300-600 series airplanes), or A300-57-0235 (for Model A300
series airplanes), both dated August 5, 1998, as applicable.
Accomplishment of this modification constitutes terminating action
for the repetitive inspection requirements of this AD.
(e) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(f) 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 4: The subject of this AD is addressed in French
airworthiness directive 98-151-247 (B), dated April 8, 1998.
Issued in Renton, Washington, on November 16, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-31173 Filed 11-20-98; 8:45 am]
BILLING CODE 4910-13-U
