[Federal Register Volume 69, Number 97 (Wednesday, May 19, 2004)]
[Proposed Rules]
[Pages 28867-28870]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-11288]


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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: 
[email protected]. 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.



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    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