[Federal Register Volume 63, Number 102 (Thursday, May 28, 1998)]
[Proposed Rules]
[Pages 29153-29155]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-14040]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-116-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300, A310, and A300-600 
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 A300, A310, 
and A300-600 series airplanes. This proposal would require repetitive 
detailed visual inspections to detect cracks in the pylon thrust and 
sideload fitting of the wing, and replacement of any cracked pylon 
thrust and sideload fitting with a new fitting. This proposal is 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign civil airworthiness authority. The actions specified by 
the proposed AD are intended to detect and correct cracks in the pylon 
thrust and sideload fitting of the wing, which could result in reduced 
structural integrity of the airplane.

DATES: Comments must be received by June 29, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-116-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    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,

[[Page 29154]]

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 notice may be changed in 
light of the comments received.
    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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 98-NM-116-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. 98-NM-116-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 certain Airbus Model A300, A310, and A300-600 
series airplanes. The DGAC advises that during a zonal inspection on a 
Model A310 series airplane, a cracked pylon thrust and sideload fitting 
was detected on an in-service airplane which had accumulated 2,170 
total flight cycles. Further investigation revealed that the cracks 
were caused by improper mounting of the fitting to the wing reinforcing 
plate and built-in stresses due to a surface flaw in the titanium 
thrust and sideload fitting. Such cracks in the pylon thrust and 
sideload fitting of the wing, if not corrected, could result in reduced 
structural integrity of the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A300-57-0232, Revision 01 (for 
Model A300 series airplanes); A310-57-2075, Revision 01 (for Model A310 
series airplanes); and A300-57-6079, Revision 02 (for Model A300-600 
series airplanes); all dated January 12, 1998; which describe 
procedures for repetitive detailed visual inspections to detect cracks 
in the pylon thrust and sideload fitting of the wing, and replacement 
of any cracked pylon thrust and sideload fitting with a new fitting. 
Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition. The 
DGAC classified these service bulletins as mandatory and issued French 
airworthiness directive 97-358-232(B), dated November 19, 1997, in 
order to assure the continued airworthiness of these airplanes in 
France.

FAA's Conclusions

    These airplane models are manufactured in France and are 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 bulletins described previously, 
except as discussed below.

Differences Between Proposed Rule and Foreign AD

    The proposed AD would differ from the parallel French airworthiness 
directive in that it would not allow for adjustment in compliance time 
based on airplane utilization. In developing an appropriate compliance 
time for this AD, the FAA considered not only the manufacturer's 
recommendation, but the degree of urgency associated with addressing 
the subject unsafe condition, and the average utilization of the 
affected fleet. In light of these factors, the FAA finds an 18-month 
compliance time for initiating the required actions to be warranted, in 
that it represents an appropriate interval of time allowable for 
affected airplanes to continue to operate without compromising safety.

Cost Impact

    The FAA estimates that 126 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 3 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 
$22,680, or $180 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.

Regulatory Impact

    The regulations proposed herein would not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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.

[[Page 29155]]

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 98-NM-116-AD.

    Applicability: Model A300 series airplanes, as listed in Airbus 
Service Bulletin A300-57-0232, Revision 01, dated January 12, 1998; 
Model A310 series airplanes, as listed in Airbus Service Bulletin 
A310-57-2075, Revision 01, dated January 12, 1998; and Model A300-
600 series airplanes, as listed in Airbus Service Bulletin A300-57-
6079, Revision 02, dated January 12, 1998; 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 (c) 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 detect and correct cracks in the pylon thrust and sideload 
fitting of the wing, which could result in reduced structural 
integrity of the airplane, accomplish the following:
    (a) Prior to the accumulation of 2,800 total flight cycles, or 
within 18 months after the effective date of this AD, whichever 
occurs later, perform a detailed visual inspection to detect cracks 
in the pylon thrust and sideload fitting of the wing, in accordance 
with Airbus Service Bulletin A300-57-0232, Revision 01 (for Model 
A300 series airplanes); A310-57-2075, Revision 01 (for Model A310 
series airplanes); or A300-57-6079, Revision 02 (for Model A300-600 
series airplanes); all dated January 12, 1998; as applicable. Repeat 
the detailed visual inspection thereafter at intervals not to exceed 
2,800 flight cycles.
    (b) If any crack is detected during any inspection required by 
paragraph (a), prior to further flight, replace the pylon thrust and 
sideload fitting with a new fitting in accordance with Airbus 
Service Bulletin A300-57-0232, Revision 01 (for Model A300 series 
airplanes); A310-57-2075, Revision 01 (for Model A310 series 
airplanes); or A300-57-6079, Revision 02 (for Model A300-600 series 
airplanes); all dated January 12, 1998; as applicable. Thereafter, 
continue the inspections in accordance with the requirements of 
paragraph (a) of this AD.
    (c) 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

    (d) Special flight permits may be issued in accordance with 
sections 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 3: The subject of this AD is addressed in French 
airworthiness directive 97-358-232(B), dated November 19, 1997.

    Issued in Renton, Washington, on May 20, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-14040 Filed 5-27-98; 8:45 am]
BILLING CODE 4910-13-P