[Federal Register Volume 65, Number 207 (Wednesday, October 25, 2000)]
[Proposed Rules]
[Pages 63817-63820]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-27432]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-214-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 all Airbus Model A310 series 
airplanes. This proposal would require repetitive detailed visual 
inspections to detect cracks propagating from the fastener holes that 
attach the left- and right-hand pick-up angles at frame 40 to the wing 
lower skin and fuselage panel, and

[[Page 63818]]

corrective actions, if necessary. This action is necessary to prevent 
reduced structural integrity of the airplane due to fatigue damage and 
consequent cracking of the pick-up angles at frame 40. This action is 
intended to address the identified unsafe condition.

DATES: Comments must be received by November 24, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-214-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: 
<a href="/cdn-cgi/l/email-protection#c4fde9a5aaa9e9aab4b6a9a7aba9a9a1aab084a2a5a5eaa3abb2"><span class="__cf_email__" data-cfemail="94adb9f5faf9b9fae4e6f9f7fbf9f9f1fae0d4f2f5f5baf3fbe2">[email protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-214-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 for Windows 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 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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the proposed 
AD is being requested.
    <bullet> 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 2000-NM-214-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. 2000-NM-214-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 all Airbus Model A310 series airplanes. The DGAC 
advises that, during unscheduled inspections of these airplanes, 
structural damage was found on the pick-up angles at the junction 
between the wing lower surface and the fuselage skin at frame 40. 
Investigation revealed that the maintenance requirements defined 
currently for Structural Significant Item (SSI) 57-10-19 in the A310 
Airworthiness Limitations Items (ALI's) in Revision 2 of the A310 
Maintenance Review Board (MRB) report are not sufficient to detect 
fatigue damage in a timely manner. Such fatigue damage could result in 
cracking of the pick-up angles at frame 40. This condition, if not 
corrected, could result in reduced structural integrity of the 
airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A310-53A2111, Revision 01, dated 
June 21, 2000. The service bulletin describes procedures for repetitive 
detailed visual inspections to detect cracks propagating from the 
fastener holes that attach the left- and right-hand pick-up angles at 
frame 40 to the wing lower skin and fuselage panel, and corrective 
actions, if necessary. The corrective actions include repair (drilling 
and reaming a crack stop hole in the pick-up angle, performing a 
Rototest inspection and repetitive detailed visual inspections, and 
replacing the pick-up angle with a new angle); or immediate replacement 
of any cracked angle with a new angle; as applicable. The DGAC 
classified this service bulletin as mandatory and issued French 
airworthiness directive 2000-209-310(B), dated June 14, 2000, in order 
to assure 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. 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 the service bulletin described previously.

Cost Impact

    The FAA estimates that 47 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 2 work 
hours per airplane to accomplish the proposed inspection, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the proposed AD on U.S. operators is estimated to be 
$5,640, or $120 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 proposed AD were not adopted. The

[[Page 63819]]

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 Industrie:  Docket 2000-NM-214-AD.

    Applicability: All Model A310 series airplanes, certificated in 
any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (g) 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 prevent reduced structural integrity of the airplane due to 
fatigue damage and consequent cracking of the pick-up angles at 
frame 40, accomplish the following:

Inspections and Corrective Actions

    (a) Perform a detailed visual inspection to detect cracks 
propagating from the fastener holes that attach the left-and right-
hand pick-up angles at frame 40 to the wing lower skin and fuselage 
panel, at the time specified in paragraph (b), (c), (d), (e) or (f) 
of this AD, as applicable. Perform the actions in accordance with 
Figure 2, Sheet 1, ``Synoptic Chart,'' of Airbus Service Bulletin 
A310-53A2111, Revision 01, dated June 21, 2000.
    (1) If no cracking is found during the inspection required by 
paragraph (a) of this AD, repeat the detailed visual inspection 
thereafter at the interval specified in paragraph (a)(1)(i) or 
(a)(1)(ii) of this AD, as applicable.
    (i) For Model A310-200 series airplanes: Except as provided by 
paragraph (d) of this AD, repeat the inspection thereafter at 
intervals not to exceed 1,000 flight cycles or 2,600 flight hours, 
whichever occurs first.
    (ii) For Model A310-300 series airplanes: Except as provided by 
paragraph (d) of this AD, repeat the inspection thereafter at 
intervals not to exceed 850 flight cycles or 2,800 flight hours, 
whichever occurs first.
    (2) If any cracking is found during the inspection required by 
paragraph (a) of this AD, prior to further flight, perform 
applicable corrective actions [including repair (drilling and 
reaming a crack stop hole in the pick-up angle, performing a 
Rototest inspection and repetitive detailed visual inspections at 
the time specified in the service bulletin, and replacing the pick-
up angle with a new angle at the time specified in the service 
bulletin); or immediate replacement of any cracked angle with a new 
angle]. Perform the actions and repetitive inspections in accordance 
with Figure 2, Sheet 1, ``Synoptic Chart,'' of Airbus Service 
Bulletin A310-53A2111, Revision 01, dated June 21, 2000.

    Note 2: Accomplishment of the actions required by paragraph (a) 
of this AD in accordance with Airbus Service Bulletin A310-53A2111, 
dated April 21, 2000, is considered to be acceptable for compliance 
with the requirements of that paragraph.

Compliance Times

    (b) For Model A310-200 series airplanes: Except as provided by 
paragraphs (d), (e), and (f) of this AD, perform the initial 
inspection at the later of the times specified in paragraphs (b)(1) 
and (b)(2) of this AD.
    (1) Prior to the accumulation of 7,900 total flight cycles or 
23,600 total flight hours, whichever occurs first.
    (2) Within 700 flight cycles or 1,200 flight hours after the 
effective date of this AD, whichever occurs first.
    (c) For Model A310-300 series airplanes: Except as provided by 
paragraphs (d), (e), and (f) of this AD, perform the initial 
inspection required by paragraph (a) of this AD at the later of the 
times specified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Prior to the accumulation of 6,700 total flight cycles or 
24,700 total flight hours, whichever occurs first.
    (2) Within 700 flight cycles or 1,200 flight hours after the 
effective date of this AD, whichever occurs first.
    (d) For airplanes that have accumulated more than 18,000 total 
flight cycles or 53,000 total flight hours as of the effective date 
of this AD: Perform the initial inspection required by paragraph (a) 
of this AD within 350 flight cycles or 600 flight hours after the 
effective date of this AD, whichever occurs first. Repeat the 
inspection thereafter at intervals not to exceed 350 flight cycles 
or 600 flight hours, whichever occurs first.
    (e) For airplanes having manufacturer's serial number 0162 
through 0326 inclusive, on which Airbus Service Bulletin A310-53-
2014 has been accomplished prior to the effective date of this AD: 
The initial inspection threshold may be counted from the date of 
accomplishment of Airbus Service Bulletin A310-53-2014.
    (f) For airplanes on which a pick-up angle has been replaced: 
For that pick-up angle only, the initial inspection threshold may be 
counted from the date of installation of the new pick-up angle.

    Note 3: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

Alternative Methods of Compliance

    (g) 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.


[[Page 63820]]



Special Flight Permits

    (h) Special flight permits may be issued in accordance with 
Secs. 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 5: The subject of this AD is addressed in French 
airworthiness directive 2000-209-310(B), dated June 14, 2000.


    Issued in Renton, Washington, on October 19, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-27432 Filed 10-24-00; 8:45 am]
BILLING CODE 4910-13-U


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