[Federal Register Volume 68, Number 243 (Thursday, December 18, 2003)]
[Proposed Rules]
[Pages 70479-70482]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31179]


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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).

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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: 
[email protected]. 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