[Federal Register Volume 64, Number 149 (Wednesday, August 4, 1999)]
[Proposed Rules]
[Pages 42289-42291]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-20067]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-119-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-301, and Model A340-
211, -212, -311, and -312 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Airbus Model A330-301, and
Model A340-211, -212, -311, and -312 series airplanes. This proposal
would require repetitive detailed visual inspections of the fuselage
belly fairing support structure to detect cracks; and corrective
action, if necessary. This proposal also would provide for an optional
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 detect and correct fatigue cracking of
the fuselage belly fairing support structure, which could result in
reduced structural integrity of the fuselage belly fairing support
structure.
DATES: Comments must be received by September 3, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-119-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 99-NM-119-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-119-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on certain Airbus Model A330-301, and Model A340-
211, -212, -311, and -312 series airplanes. The DGAC advises that,
during fatigue tests, cracks were found in the fuselage belly fairing
support structure. This condition, if not corrected, could result in
reduced structural integrity of the fuselage belly fairing support
structure.
Explanation of Relevant Service Information
Airbus has issued Service Bulletins A330-53-3029, dated June 26,
1995 (for Model A330 series airplanes), and A340-53-4038, Revision 1,
dated February 6, 1996 (for Model A340 series
[[Page 42290]]
airplanes), which describe procedures for performing repetitive
detailed visual inspections of particular parts of the fuselage belly
fairing support structure for cracks, and repair, if necessary.
Airbus also has issued Service Bulletins A330-53-3012, dated June
26, 1995 (for Model A330 series airplanes), and A340-53-4020, dated
June 26, 1996 (for Model A340 series airplanes), which describe
procedures for modification of the fuselage belly fairing support
structure. The modification involves removing certain parts and
replacing the parts with new, improved parts. Accomplishment of this
modification would eliminate the need for the repetitive inspections
specified in Airbus Service Bulletins A330-53-3029 (for Model A330
series airplanes) and A340-53-4038 (for Model A340 series airplanes).
Accomplishment of the actions specified in the service bulletins is
intended to adequately address the identified unsafe condition. The
DGAC classified Airbus Service Bulletins A330-53-3029 and A340-53-4038
as mandatory and issued French airworthiness directives 95-256-023(B)
R1 and 95-258-037(B) R1, both dated December 17, 1997, 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
Sec. 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 require accomplishment of
the actions specified in Airbus service bulletins described previously,
except as discussed below. This proposed AD also would provide for
optional terminating action for the repetitive inspections.
Operators should note that, in consonance with the findings of the
DGAC, the FAA has determined that the repetitive inspections proposed
by this AD can be allowed to continue in lieu of accomplishment of a
terminating action. In making this determination, the FAA considers
that, in this case, long-term continued operational safety will be
adequately assured by accomplishing the repetitive inspections to
detect cracking before it represents a hazard to the airplanes.
Differences Between Proposed Rule and Service Bulletin
Operators should note that, unlike the inspection procedures
described in Airbus Service Bulletins A330-53-3029 (for Model A330
series airplanes) and A340-53-4038 (for Model A340 series airplanes),
this proposed AD would not permit further flight if cracking is
detected. The FAA has determined that, because of the safety
implications and consequences associated with such cracking, any
structure that is found to be cracked must be repaired prior to further
flight, in accordance with the applicable service bulletins.
Cost Impact
Currently, there are no Airbus Model A330-301 series airplanes on
the U.S. Register. However, should an affected airplane be imported and
placed on the U.S. Register in the future, it would take approximately
5 work hours to accomplish the proposed inspection, at an average labor
rate of $60 per work hour. Based on these figures, the cost impact of
the proposed AD on U.S. operators is estimated to be $300 per airplane,
per inspection cycle.
Also, there are no Airbus Model A340-211, -212, -311, and -312
series airplanes on the U.S. Register. However, should an affected
airplane be imported and placed on the U.S. Register in the future, it
would take approximately 6 work hours to accomplish the proposed
inspection, at an average labor rate of $60 per work hour. Based on
these figures, the cost impact of the proposed AD on U.S. operators is
estimated to be $360 per airplane, per inspection cycle.
Should an affected airplane be imported and placed on the U.S.
Register and an operator elect to accomplish the optional terminating
action rather than continue the repetitive inspections, it would take
approximately between 10 and 178 hours per airplane (for Model A330
series airplanes), or between 10 and 188 hours per airplane (for Model
A340 series airplanes), at an average labor rate of $60 per work hour.
Required parts would cost approximately between $1,313 and $13,262 (for
Model A330 series airplanes) or between $1,049 and $14,311 (for Model
A340 series airplanes), per airplane. Based on these figures, the cost
impact of this optional terminating action is estimated to be between
$1,913 and $23,942 (for Model A330 series airplanes) or between $1,649
and $25,591 (for Model A340 series airplanes), per airplane.
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 adding the following new
airworthiness directive:
Airbus Industrie: Docket 99-NM-119-AD.
Applicability: Model A330-301 series airplanes, except those
airplanes on which Airbus Modification 42332 (reference Airbus
Service Bulletin A330-53-3012, dated June 26, 1995) has been
accomplished; and Model
[[Page 42291]]
A340-211, -212, -311, and -312 series airplanes, except those
airplanes on which Airbus Modification 42331 or 42332 (reference
Airbus Service Bulletin A340-53-4020, dated June 26, 1995), 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) 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 detect and correct fatigue cracking of the fuselage belly
fairing support structure, which could result in reduced structural
integrity of the fuselage belly fairing support structure,
accomplish the following:
Repetitive Inspection
(a) Prior to the accumulation of 4,000 total flight cycles, or
within 500 flight hours after the effective date of this AD,
whichever occurs later, perform a detailed visual inspection of the
fuselage belly fairing support structure for cracks, in accordance
with Airbus Service Bulletin A330-53-3029, dated June 26, 1995 (for
Model A330 series airplanes); or A340-53-4038, Revision 1, dated
February 6, 1996 (for Model A340 series airplanes); as applicable.
Thereafter, repeat the inspection at intervals not to exceed 2,800
flight cycles.
Repair
(b) If any crack is found during any inspection required by
paragraph (a) of this AD, prior to further flight, repair in
accordance with Airbus Service Bulletin A330-53-3012, dated June 26,
1995 (for Model A330 series airplanes); or A340-53-4020, dated June
26, 1995 (for Model A340 series airplanes); as applicable.
Accomplishment of this action constitutes terminating action for the
repetitive inspections required by this AD for only that repaired
part.
Optional Terminating Action
(c) Modification of the belly fairing support structure in
accordance with Airbus Service Bulletin A330-53-3012, dated June 26,
1995 (for Model A330 series airplanes); or A340-53-4020, dated June
26, 1995 (for Model A340 series airplanes); as applicable;
constitutes terminating action for the requirements of this AD.
Alternative Methods of Compliance
(d) 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 2: 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 3: The subject of this AD is addressed in French
airworthiness directives 95-256-023(B) R1 and 95-258-037(B) R1, both
dated December 17, 1997.
Issued in Renton, Washington, on July 29, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-20067 Filed 8-3-99; 8:45 am]
BILLING CODE 4910-13-U
