[Federal Register: December 18, 2003 (Volume 68, Number 243)]
[Proposed Rules]
[Page 70479-70482]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18de03-22]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-175-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain Airbus Model A310
series airplanes, that requires repetitive inspections of the fuselage
skin to detect corrosion or fatigue cracking around and under the
chafing plates of the wing root; and corrective actions, if necessary.
That AD also provides an optional terminating action for the repetitive
inspections. This action would reinstate repetitive inspections in
certain areas where corrosion was detected and reworked as required by
the existing AD. The actions specified by the proposed AD are intended
to detect and correct fatigue cracks and corrosion around and under the
chafing plates of the wing root, which could result in reduced
structural integrity of the airplane. This action is intended to
address the identified unsafe condition.
DATES: Comments must be received by January 20, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-175-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. 2002-NM-175-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 Industrie, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. This information may be examined at
[[Page 70480]]
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: Anthony Jopling, Program Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2190; 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:
[sbull] 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.
[sbull] For each issue, state what specific change to the proposed
AD is being requested.
[sbull] 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 2002-NM-175-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. 2002-NM-175-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On April 21, 1998, the FAA issued AD 98-09-20, amendment 39-10501
(63 FR 23377, April 29, 1998), applicable to certain Airbus Model A310
series airplanes, to require repetitive inspections of the fuselage
skin to detect corrosion or fatigue cracks around and under the chafing
plates of the wing root; and corrective actions, if necessary. That AD
also provides an optional terminating action for the repetitive
inspections. That action was prompted by notification from the
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is
the airworthiness authority for France, that it received reports of the
presence of corrosion under the chafing plates and around the fasteners
of the wing root between fuselage frames 36 and 39. The requirements of
that AD are intended to detect and correct fatigue cracks and corrosion
around and under the chafing plates of the wing root, which could
result in reduced structural integrity of the airplane.
Actions Since Issuance of Previous Rule
Although AD 98-09-20 provides an optional terminating action for
repetitive inspections for fatigue cracking around and under the
chafing plates of the wing root, it has been determined that repetitive
inspections for fatigue cracking are still necessary on the left and
right sides of frame 39, stringer 35, if any corrosion was reworked in
this area.
Explanation of Relevant Service Information
Since the issuance of AD 98-09-20, Airbus has issued Service
Bulletin A310-53-2069, Revision 02, dated September 23, 1996; Revision
03, dated October 28, 1997; and Revision 04, dated November 8, 2000.
These service bulletins describe the same procedures as specified in
Airbus Service Bulletin A310-53-2069, Revision 01, dated September 19,
1995, for repetitive inspections to detect corrosion and fatigue cracks
around and under the chafing plates of the wing root between fuselage
frame 36 and frame 39. These service bulletins also include the same
procedures for follow-on and corrective actions as Service Bulletin
A310-53-2069, Revision 01. The corrective actions include reworking
corroded areas, oversizing and reaming holes, installing doublers, and
performing a high frequency eddy current inspection and an x-ray
inspection. Revision 01 of the service bulletin is cited in AD 98-09-20
as the appropriate source of service information.
Airbus has also issued Service Bulletin A310-53-2070, Revision 02,
dated November 8, 2000, which describes procedures for replacement of
the stainless steel chafing plates with new chafing plates made of
aluminum alloy. Accomplishment of this service bulletin eliminates the
need for the repetitive inspections for fatigue cracking, unless
corrosion was detected and reworked on the left and/or right side of
frame 39, stringer 35. If corrosion was detected and reworked in this
area, repetitive inspections for fatigue cracking are still necessary.
The original issue of this service bulletin, dated October 3, 1994, is
cited in AD 98-09-20 as an acceptable source of service information for
the optional terminating action.
The DGAC classified Airbus Service Bulletin A310-53-2069, Revision
04, dated November 8, 2000, as mandatory and issued French
airworthiness directive 2000-514-326(B) R1, dated May 15, 2002, 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
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. 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 supersede AD 98-09-20 to
continue to require repetitive inspections of the fuselage skin to
detect corrosion or fatigue cracking around and under the chafing
plates of the wing root; and corrective actions, if necessary. The
inspections would be required to be accomplished in accordance with
Airbus Service Bulletin A310-53-2069, Revision 04; Revision 03;
Revision 02; or Revision 01; described previously; except as discussed
below. The replacement of the chafing plates would be required to be
accomplished in accordance with Airbus Service Bulletin
[[Page 70481]]
A310-53-2070, Revision 02; Revision 01, dated September 23, 1996; or
Original Issue; described previously; except as discussed below. This
action would reinstate repetitive inspections for fatigue cracking at
frame 39, stringer 35, if corrosion was detected and reworked in this
area.
Differences Among Proposed Rule, Service Information, and French
Airworthiness Directive
Although the service bulletins specify that operators may contact
the manufacturer for disposition of certain repair conditions, this
proposal 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.
Also, operators should note that, although the Accomplishment
Instructions of the referenced service bulletins describe procedures
for reporting inspection results to the manufacturer, this proposed AD
would not require such reporting. The FAA does not need this
information from operators.
Cost Impact
There are approximately 46 airplanes of U.S. registry that would be
affected by this proposed AD. This proposed AD adds no new
requirements. It requires continuation of repetitive inspections for
airplanes where corrosion was detected and reworked at frame 39,
stringer 35. The current costs associated with this proposed AD are
reiterated in their entirety as follows for the convenience of affected
operators:
The inspections that are currently required by AD 98-09-20 take
approximately 68 work hours per airplane to accomplish at an average
labor rate of $65 per work hour. Based on these figures, the cost
impact of the currently required actions is estimated to be $4,420 per
airplane, per inspection cycle.
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. 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 removing amendment 39-10501 (63 FR
23377, April 29, 1998), and by adding a new airworthiness directive
(AD), to read as follows:
Airbus: Docket 2002-NM-175-AD. Supersedes AD 98-09-20, Amendment 39-
10501.
Applicability: Model A310 series airplanes on which Airbus
Modifications 8888 and 8889 have not been accomplished, certificated
in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct fatigue cracking and corrosion around and
under chafing plates of the wing root between fuselage frame 36 and
frame 39, which could result in reduced structural integrity of the
airplane, accomplish the following:
Restatement of Requirements of AD 98-09-20
Repetitive Inspections and Corrective Actions
(a) Except as provided by paragraph (b) of this AD: Within 4
years since date of manufacture, or within 12 months after June 3,
1998 (the effective date of AD 98-09-20, amendment 39-10501),
whichever occurs later, perform an inspection to detect
discrepancies around and under the chafing plates of the wing root,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-53-2069, Revision 04, dated November 8, 2000; Revision
03, dated October 28, 1997; Revision 02, dated September 23, 1996;
or Revision 01, dated September 19, 1995. If any discrepancy is
found, prior to further flight, accomplish follow-on corrective
actions (i.e., removal of corrosion, corrosion protection, high
frequency eddy current inspection, x-ray inspection), as applicable,
in accordance with the applicable service bulletin. Repeat the
inspections thereafter at the intervals specified in the applicable
service bulletin. After the effective date of this AD, repeat the
inspections thereafter at the intervals specified in Revision 04 of
the service bulletin.
(b) If any discrepancy is found during any inspection required
by paragraph (a) of this AD, and Airbus Service Bulletin A310-53-
2069, Revision 04, dated November 8, 2000; Revision 03, dated
October 28, 1997; Revision 02, dated September 23, 1996; or Revision
01, dated September 19, 1995; as applicable; specifies to contact
Airbus for appropriate action: Prior to further flight, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate. Where
differences in the compliance times or corrective actions exist
between the service bulletin and this AD, the AD prevails.
New Requirements of This AD
Optional Terminating Action
(c) Except as provided by paragraph (d) of this AD:
Accomplishment of the replacement of the stainless steel chafing
plates with new chafing plates made of aluminum alloy, in accordance
with Airbus Service Bulletin A310-53-2070, Revision 02, dated
November 8, 2000; Revision 01, dated September 23, 1996; or the
Original Issue, dated October 3, 1994; constitutes terminating
action for the repetitive inspections required by paragraph (a) of
this AD.
Continuation of Repetitive Inspections
(d) Within 30 days after the effective date of this AD: Do a
review of the airplane maintenance records to determine if any
corrosion was detected and reworked on the left and/or right side of
frame 39, stringer 35, during the accomplishment of any corrective
[[Page 70482]]
action or repair specified in paragraphs (a) or (b) of this AD. If
any corrective action or repair has been accomplished in this area,
perform an inspection for fatigue cracking of frame 39, stringer 35,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-53-2069, Revision 04, dated November 8, 2000. Do the
initial inspection at the threshold specified in Figure 1 of the
service bulletin, or within 30 days after the effective date of this
AD, whichever is later. Repeat the inspection thereafter at the
intervals specified in Figure 1 of the service bulletin. If any
discrepancy is found, prior to further flight, accomplish the
applicable follow-on corrective actions in accordance with the
Accomplishment Instructions of the service bulletin.
Submission of Information Not Required
(e) Although the service bulletins referenced in this AD specify
to submit information to the manufacturer, this AD does not include
such a requirement.
Alternative Methods of Compliance
(f) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized
to approve alternative methods of compliance for this AD.
Note 1: The subject of this AD is addressed in French
airworthiness directive 2000-514-326(B) R1, dated May 15, 2002.
Issued in Renton, Washington, on December 10, 2003.
Kevin Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-31179 Filed 12-17-03; 8:45 am]
BILLING CODE 4910-13-U