[Federal Register: May 19, 2004 (Volume 69, Number 97)]
[Proposed Rules]
[Page 28867-28870]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19my04-18]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-279-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 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 A310 series
airplanes. This proposal would require repetitive inspections for
fatigue cracking of the area around the fasteners of the landing plate
of the aileron access doors of the bottom skin panel of the wings, and
related corrective action. The proposal also provides for an optional
terminating action, which would end the repetitive inspections. This
action is necessary to prevent fatigue cracking of the area around the
fasteners of the landing plate of the aileron access doors and the
bottom skin panel of the wings, which could result in reduced
structural integrity of the wings. This action is intended to address
the identified unsafe condition.
DATES: Comments must be received by June 18, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-279-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-279-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Airbus, 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: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; 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 action may be changed in
light of the comments received.
Submit comments using the following format:
Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
For each issue, state what specific change to the proposed
AD is being requested.
Include justification (e.g., reasons or data) for each
request.
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 action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2003-NM-279-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. 2003-NM-279-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, has notified the FAA
that an unsafe condition may exist on certain Airbus Model A310 series
airplanes. The DGAC advises that full-scale fatigue testing of a Model
A310 airplane on which Airbus Modification 5106 had been done revealed
skin cracking in the modified area. The cracking had initiated from one
of the attachment holes of the landing plate of the aileron access
door. In addition, during routine maintenance of a post-modification
5106 Model A310 airplane, a 62-millimeter crack was found on the right-
hand wing in the
[[Page 28868]]
bottom skin panel. Fatigue cracking of the area around the fasteners of
the landing plate of the aileron access doors and the bottom skin panel
of the wings could result in reduced structural integrity of the wings.
The manufacturer has developed an inspection program for Model A310
series airplanes on which Airbus Modification 5106 has been done. The
manufacturer is also conducting a review of the inspection program
developed for airplanes on which Airbus Modification 5106 has not been
done.
Related Rulemaking
On December 8, 1998, the FAA issued AD 98-26-01, amendment 39-10942
(63 FR 69179, December 16, 1998) applicable to all Airbus Model A310
series airplanes. That AD requires various inspections to detect
fatigue cracks at certain locations on the fuselage, horizontal
stabilizer, wings and tail; repair or modification, if necessary; and
installation of doublers. The actions specified by that AD are intended
to prevent reduced structural integrity of the fuselage, horizontal
stabilizer, and wings.
Explanation of Relevant Service Information
Airbus has issued the following service information:
Airbus Service Bulletin A310-57-2004, Revision 2, dated
March 5, 1990, which describes procedures for modification of the
landing plate of the access door of the bottom skin panel of the left
and right wings. The modification includes removing the existing
clearance fit bolts from the landing plate of the aileron access door
on the left and right wings, and installing reamed oversized
interference fit bolts. Accomplishment of the modification eliminates
the need for the repetitive inspections.
Airbus Service Bulletin A310-57-2081, dated June 11, 2002,
which describes procedures for modification of the access door and the
bottom skin panel of the left and right wings. The modification
includes a high frequency eddy current inspection of the fastener holes
of the modification areas for cracking, and repair per Service Bulletin
A310-57-2082, if cracking is found. The service bulletin also specifies
contacting the manufacturer for repair instructions if cracking is
found outside the modification areas. If no cracking is found, the
service bulletin describes procedures for cutting the landing plate of
the aileron access door into three parts, cold expanding of the
fastener holes of the landing plate, installing an interference plug;
installing an external reinforcement plate, cold expanding of the
attachment holes of the reinforcement plate, and installing
interference fit fasteners.
Airbus Service Bulletin A310-57-2082, dated June 11, 2002,
which describes procedures for a high frequency eddy current inspection
for cracking of the area around the fasteners of the landing plate of
the aileron access doors of the bottom skin panel of the left and right
wings, and related corrective action. The related corrective action
includes doing a permanent repair (installing a repair plate and new
landing plates), or a temporary repair (crack-stop drilling) followed
by repetitive inspections until a permanent repair is done.
Accomplishment of the actions specified in the service information
is intended to adequately address the identified unsafe condition. The
DGAC classified this service information as mandatory and issued French
airworthiness directive 2003-242(B), dated June 25, 2003, to ensure the
continued airworthiness of these airplanes in France.
FAA's Conclusions
This airplane model is manufactured in France and is 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 us informed of the
situation described above. We have 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 the service information described previously,
except as discussed below. This proposed AD also would provide for
optional terminating action for the repetitive inspections.
Consistent with the findings of the DGAC, the proposed AD would
allow repetitive inspections to continue in lieu of the terminating
action. In making this determination, we considered that long-term
continued operational safety in this case will be adequately ensured by
repetitive inspections to find cracking before it represents a hazard
to the airplane.
Differences Among French Airworthiness Directive, Service Information,
and Proposed AD
Unlike the procedures described in Service Bulletin A310-57-2082,
and the French airworthiness directive, this proposed AD would not
permit further flight if cracks are found in the area around the
fasteners of the landing plate of the aileron access doors of the
wings. The service bulletin specifies the option of a temporary repair
(crack-stop drilling) if cracking is found in the landing plate and
wing skin panel, and follow-on repetitive inspections until a permanent
repair is done. We have determined that, because of the safety
implications and consequences associated with such cracking, no
temporary repair is allowed and a permanent repair must be done before
further flight. However, under the provisions of paragraph (e) of the
proposed AD, we may approve requests for a temporary repair provided
that data are submitted to substantiate that (1) the crack is not part
of multi-site damage, (2) crack growth is easily detectable, and (3)
established inspection procedures would detect cracked structure at
intervals permitting a permanent repair to be done before reduced
structural integrity of the wings can occur.
Service Bulletin A310-57-2081 specifies that operators may contact
the manufacturer for disposition of certain repair conditions, but this
proposed AD would require operators to repair those conditions per a
method approved by either the FAA or the DGAC (or its delegated agent).
In light of the type of repair that would be required to address the
unsafe condition, and consistent with existing bilateral airworthiness
agreements, we have determined that, for this proposed AD, a repair
approved by either the FAA or the DGAC would be acceptable for
compliance with this proposed AD.
For airplanes on which Airbus Modification 5106 has been done, the
French airworthiness directive specifies an inspection threshold of a
certain number of flights ``since new.'' However, this proposed AD
specifies an inspection threshold of a certain number of flight cycles
since the date of issuance of the original Airworthiness Certificate or
the date of issuance of the original Export Certificate of
Airworthiness, whichever is first. This decision is based on our
determination that ``since new'' may be interpreted differently by
different operators. We
[[Page 28869]]
find that our proposed terminology is generally understood within the
industry and records will always exist that establish these dates with
certainty.
Cost Impact
We estimate that 46 airplanes of U.S. registry would be affected by
this proposed AD, that it would take about 2 work hours per airplane to
do the proposed inspection, and that the average labor rate is $65 per
work hour. Based on these figures, the cost impact of the inspection
proposed by this AD on U.S. operators is estimated to be $5,980, or
$130 per airplane, per inspection cycle.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this AD were not adopted. The cost impact figures
discussed in AD rulemaking actions represent only the time necessary to
perform the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations proposed herein would 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 proposal would not have federalism implications
under Executive Order 13132.
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: Docket 2003-NM-279-AD.
Applicability: Model A310 series airplanes, certificated in any
category; on which Airbus Modification 12525 has not been done
during production.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue cracking of the area around the fasteners of
the landing plate of the aileron access doors and the bottom skin
panel of the wings, which could result in reduced structural
integrity of the wings, accomplish the following:
Repetitive Inspections
(a) For airplanes on which Airbus Modification 5106 (Airbus
Service Bulletin A310-57-2004, Revision 2, dated March 5, 1990) has
not been done as of the effective date of this AD: Within 2,000
flight cycles after the effective date of this AD, or within 3,000
flight cycles after the last inspection done per paragraph (k) of AD
98-26-01, amendment 39-10942 (63 FR 69179, December 16, 1998),
whichever is first; do a high frequency eddy current (HFEC)
inspection for cracking of the area around the fasteners of the
landing plate of the wing bottom skin panel No. 2 of the left and
right wings. Do the inspection per the Accomplishment Instructions
of Airbus Service Bulletin A310-57-2082, dated June 11, 2002. If no
cracking is found, repeat the inspection thereafter at intervals not
to exceed 1,900 flight cycles, until accomplishment of the
terminating action specified in paragraph (d) of this AD.
(b) For airplanes on which Airbus Modification 5106 has been
done as of the effective date of this AD: Do the HFEC inspection
required by paragraph (a) of this AD at the applicable time
specified in paragraph (b)(1), (b)(2), (b)(3), or (b)(4) of this AD.
If no cracking is found, repeat the inspection thereafter at
intervals not to exceed 1,900 flight cycles, until accomplishment of
the terminating action specified in paragraph (d) of this AD.
(1) For airplanes that have accumulated fewer than 17,000 total
flight cycles since the date of issuance of the original
Airworthiness Certificate or the date of issuance of the original
Export Certificate of Airworthiness, whichever is first, as of the
effective date of this AD: Inspect prior to the accumulation of
18,000 total flight cycles.
(2) For airplanes that have accumulated 17,000 or more total
flight cycles, but fewer than 19,001 total flight cycles since the
date of issuance of the original Airworthiness Certificate or the
date of issuance of the original Export Certificate of
Airworthiness, whichever is first, as of the effective date of this
AD: Inspect within 2,000 flight cycles after the effective date of
this AD.
(3) For airplanes that have accumulated 19,001 or more total
flight cycles, but fewer than 21,001 total flight cycles since the
date of issuance of the original Airworthiness Certificate or the
date of issuance of the original Export Certificate of
Airworthiness, whichever is first, as of the effective date of this
AD: Inspect with 1,200 flight cycles after the effective date of
this AD.
(4) For airplanes that have accumulated 21,001 or more total
flight cycles since the date of issuance of the original
Airworthiness Certificate or the date of issuance of the original
Export Certificate of Airworthiness, whichever is first, as of the
effective date of this AD: Inspect within 500 flight cycles after
the effective date of this AD.
Corrective Action
(c) If any cracking is found during any inspection required by
paragraph (a) or (b) of this AD: Before further flight, do the
actions required by either paragraph (c)(1) or (c)(2) of this AD.
(1) Do a permanent repair of the area by doing the applicable
corrective actions per the Accomplishment Instruction of Airbus
Service Bulletin A310-57-2082, dated June 11, 2002. Accomplishment
of the permanent repair terminates the repetitive inspections
required by this AD for the repaired area only.
(2) Do the terminating action specified in paragraph (d) of this
AD.
Optional Terminating Action
(d) Modification of the landing plate of the aileron access
doors of the wing bottom skin panel No. 2 of the left and right
wings by doing all the actions, per the Accomplishment Instructions
of Airbus Service Bulletin A310-57-2081, dated June 11, 2002,
terminates the requirements of this AD. Where the service bulletin
specifies contacting the manufacturer for disposition of certain
repair conditions that may be associated with the modification
procedure, this AD requires that the repair be done per a method
approved by either the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile, or its delegated agent.
Alternative Methods of Compliance
(e) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, is authorized to approve alternative methods of
compliance for this AD.
Note 1: The subject of this AD is addressed in French
airworthiness directive 2003-242(B), dated June 25, 2003.
[[Page 28870]]
Issued in Renton, Washington, on May 11, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-11288 Filed 5-18-04; 8:45 am]
BILLING CODE 4910-13-P