[Federal Register Volume 63, Number 75 (Monday, April 20, 1998)]
[Proposed Rules]
[Pages 19425-19427]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-10279]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-74-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 series 
airplanes and all Model A310 and A300-600 series airplanes. This 
proposal would require repetitive

[[Page 19426]]

inspections for wear damage of the aft attachment fittings of the 
articulated seats and dummy tracks in the passenger compartment; and 
repair, if necessary. 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 wear damage of the aft attachment 
fittings of the articulated seats and dummy tracks. This condition, if 
not detected and corrected, could cause the floor panels to sag and 
result in failure of flight control systems and consequent reduced 
controllability of the airplane.

DATES: Comments must be received by May 20, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-74-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, 
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-74-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-74-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 series airplanes, and 
all Model A310 and A300-600 series airplanes. The DGAC advises that it 
has received reports indicating that, on in-service airplanes, wear 
damage was found between frames 38.2 and 40 and between frames 54 and 
54.2 on the aft attachment fittings of the articulated seats and dummy 
tracks in the passenger compartment. Investigation has revealed that, 
under certain load conditions, such as take-off and landing, the 
sliders of the articulated seats may cause excessive wear of the dummy 
track slot contact surface. This excessive wear restricts the sliding 
movement of the articulated seats and can lead to cracking and rupture 
of the attachment fitting. This condition, if not detected and 
corrected, could cause the floor panels to sag and result in failure of 
flight control systems and consequent reduced controllability of the 
airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A300-53-0329, Revision 01 (for 
Model A300); A300-53-6105, Revision 01 (for Model A300-600); and A310-
53-2101, Revision 01 (for Model A310); all dated October 17, 1997. 
These service bulletins describe procedures for repetitive detailed 
visual inspections for wear damage of the aft attachment fittings of 
the articulated seats and dummy tracks between frames 38.2 and 40 and 
between frames 54 and 54.2 in the passenger compartment; and repair, if 
necessary. 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 97-116-222(B), dated May 21, 
1997, in order to assure the continued airworthiness of these airplanes 
in France.

FAA's Conclusions

    These airplanes model are manufactured in France and are 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 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 Service Bulletin

    Operators should note that, unlike the procedures described in 
Airbus Service Bulletins A300-53-0329, Revision 01 (for Model A300); 
Airbus A300-53-6105, Revision 01 (for Model A300-600), and Airbus A310-
53-2101, Revision 01 (for Model A310), all dated October 17, 1997, this 
proposed AD would not permit further flight if wear damage is detected 
on the aft attachment fittings on the articulated seats and dummy 
tracks in the passenger compartment. The FAA has determined that, 
because of the safety implications and consequences associated with 
such wear damage, any subject attachment fitting that is found to 
exhibit wear damage must be repaired prior to further flight.
    In addition, operators should note that, although the referenced 
service bulletins specify that the manufacturer may be contacted for 
disposition of certain repair conditions, this proposal would require 
the repair of those conditions to be accomplished in

[[Page 19427]]

accordance with a method approved by the FAA.

Cost Impact

    The FAA estimates that 126 airplanes of U.S. registry would be 
affected by this proposed AD. It would take approximately 48 work hours 
per airplane to accomplish the proposed inspection, at an average labor 
rate of $60 per work hour. Based on these figures, the cost impact of 
the proposed AD on U.S. operators is estimated to be $362,880, or 
$2,880 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.

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-74-AD.

    Applicability: Model A300 series airplanes on which Airbus 
Modification 3599 or 3135 (reference Airbus Service Bulletin A300-
53-0188) has been accomplished, and all Model A310 and A300-600 
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 
otherwise 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 (e) 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 wear damage of the aft attachment fittings 
of the articulated seats and dummy tracks in the passenger 
compartment, which could cause the floor panels to sag and result in 
failure of flight control systems and consequent reduced 
controllability of the airplane, accomplish the following:
    (a) Perform a detailed visual inspection for wear damage of the 
aft attachment fittings of the articulated seats and dummy tracks in 
the passenger compartment, in accordance with Airbus Service 
Bulletins A300-53-0329, Revision 01 (for Airbus Model A300 series 
airplanes); A300-53-6105, Revision 01 (for Airbus Model A300-600 
series airplanes); or A310-53-2101, Revision 01 (for Airbus Model 
A310 series airplanes), all dated October 17, 1997; at the 
applicable time specified in paragraph (a)(1) or (a)(2) of this AD.
    (1) For airplanes that have accumulated less than 12,000 total 
flight cycles as of the effective date of this AD: Inspect prior to 
the accumulation of 6,000 total flight cycles, or within 18 months 
after the effective date of this AD, whichever occurs later.
    (2) For airplanes that have accumulated 12,000 or more total 
flight cycles as of the effective date of this AD: Inspect within 12 
months after the effective date of this AD.
    (b) If no wear damage is detected during the inspection required 
by paragraph (a) of this AD, repeat the detailed visual inspection 
thereafter at intervals not to exceed 6,000 flight cycles.
    (c) If any wear damage measuring 2 mm (0.078 in.) or less is 
detected during the inspection required by paragraph (a) of this AD, 
prior to further flight, repair in accordance with Airbus Service 
Bulletins A300-53-0329, Revision 01 (for Airbus Model A300 series 
airplanes); A300-53-6105, Revision 01 (for Airbus Model A300-600 
series airplanes); or A310-53-2101, Revision 01 (for Airbus Model 
A310 series airplanes); all dated October 17, 1997. Repeat the 
detailed visual inspection thereafter at intervals not to exceed 
6,000 flight cycles.
    (d) If any wear damage measuring more than 2 mm (0.078 in.) is 
detected during the inspection required by paragraph (a) of this AD, 
prior to further flight, repair in accordance with a method approved 
by the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate. Repeat the detailed visual inspection 
thereafter at intervals not to exceed 6,000 flight cycles.
    (e) 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. 
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.

    (f) 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 97-116-222(B), dated May 21, 1997.

    Issued in Renton, Washington, on April 13, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-10279 Filed 4-17-98; 8:45 am]
BILLING CODE 4910-13-U