[Federal Register Volume 65, Number 95 (Tuesday, May 16, 2000)]
[Proposed Rules]
[Pages 31113-31115]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-12248]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-105-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model 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 all Airbus Model A300-600 series 
airplanes. This proposal would require repetitive high frequency eddy 
current (HFEC) or rototest inspections to detect cracking in the area 
surrounding the frame feet attachment holes between fuselage frames 
(FR) 41 and FR46; installation of new fasteners for certain airplanes; 
and follow-on corrective actions, 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 prevent cracking of the center section 
of the fuselage, which could result in rupture of the frame foot and 
reduced structural integrity of the airplane.

DATES: Comments must be received by June 15, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-105-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, 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

[[Page 31114]]

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 2000-NM-105-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-105-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 A300-600 series airplanes. The 
DGAC advises that, during an inspection performed in accordance with 
Structure Significant Item (SSI) Task 53-15-54, cracking was detected 
in the area surrounding the frame feet attachment holes at fuselage 
frames (FR) 43 through FR46 between stringers 24 and 30 on the right-
hand side, and at FR45 on the left-hand side. The cracking occurred on 
an airplane that had accumulated 26,100 total flight cycles and 32,160 
total flight hours. Such cracking of the center section of the 
fuselage, if not detected and corrected, could result in rupture of the 
frame foot and reduced structural integrity of the airplane.

Explanation of Relevant Service Information

    The manufacturer has issued Airbus Service Bulletin A300-53-6122, 
dated February 9, 2000, which describes procedures for repetitive high 
frequency eddy current (HFEC) or rototest inspections to detect 
cracking of the frame feet attachment holes between FR41 and FR46; 
installation of new fasteners for certain airplanes; and follow-on 
corrective actions, if necessary. The follow-on corrective actions 
involve subsequent performing rotating probe inspections and repairing 
certain cracking conditions. The repair involves reaming out cracks, 
cold working fastener holes, and installing oversized fasteners. The 
DGAC classified this service bulletin as mandatory and issued French 
airworthiness directive 2000-060-303(B), dated February 9, 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 
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 repetitive HFEC or 
rototest inspections to detect cracking in the area surrounding the 
frame feet attachment holes between FR41 and FR46; installation of new 
fasteners for certain airplanes; and follow-on corrective actions, if 
necessary. The actions would be required to be accomplished in 
accordance with the service bulletin described previously, except as 
discussed below.

Differences Between Proposed Rule and Service Bulletin

    Operators should note that, although the service bulletin specifies 
that the manufacturer may be contacted for disposition of certain 
conditions, this proposal would require the repair of those conditions 
to be accomplished in accordance with a method approved by the FAA or 
the DGAC (or its delegated agent). In light of the type of repair that 
would be required to address the identified unsafe condition, and in 
consonance with existing bilateral airworthiness agreements, the FAA 
has determined that, for the proposed AD, a repair approved by either 
the FAA or the DGAC would be acceptable for compliance with this 
proposed AD.

Cost Impact

    The FAA estimates that 75 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 6 work 
hours per airplane to accomplish the proposed inspections, 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 
$27,000, or $360 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 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.

[[Page 31115]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Airbus Industrie: Docket 2000-NM-105-AD.

    Applicability: All Model 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 
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 prevent cracking of the center section of the fuselage, which 
could result in rupture of the frame foot and reduced structural 
integrity of the airplane, accomplish the following:

High Frequency Eddy Current (HFEC) or Rototest Inspection

    (a) Perform a HFEC or rototest inspection to detect cracking in 
the area surrounding the frame feet attachment holes between 
fuselage frames (FR) 41 and FR46 from stringers 24 to 28, left- and 
right-hand sides, in accordance with Airbus Service Bulletin A300-
53-6122, dated February 9, 2000, at the time specified in paragraph 
(a)(1) or (a)(2), as applicable.
    (1) For airplanes on which Task 53-15-54 in Maintenance Review 
Board Document (MRBD), Revision 3, dated April 1998, has NOT been 
accomplished as of the effective date of this AD: Perform the 
inspection at the later of the times specified in paragraphs 
(a)(1)(i) and (a)(1)(ii) of this AD.
    (i) Prior to the accumulation of the total flight-cycle or 
flight-hour threshold, whichever occurs first, specified in 
paragraph 1.E. (``Compliance'') of the service bulletin; or
    (ii) Within the applicable grace period specified in paragraph 
1.E. (``Compliance'') of the service bulletin.
    (2) For airplanes on which Task 53-15-54 in Maintenance Review 
Board Document (MRBD), Revision 3, dated April 1998, has been 
accomplished as of the effective date of this AD: Perform the next 
repetitive inspection at the later of the times specified in 
paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.
    (i) Within the flight-cycle or flight-hour interval, whichever 
occurs first, specified in paragraph 1.E. (``Compliance'') of the 
service bulletin, following the latest inspection accomplished in 
accordance with the MRBD; or
    (ii) Within the grace period specified in paragraph 1.E. 
(``Compliance'') of the service bulletin.
    (b) For airplanes on which no cracking is detected during the 
inspection required by paragraph (a) of this AD, prior to further 
flight, install new fasteners as applicable, in accordance with 
Airbus Service Bulletin A300-53-6122, dated February 9, 2000; and 
repeat the inspection required by paragraph (a) of this AD 
thereafter at intervals not to exceed the applicable intervals 
specified in paragraph 1.E. (``Compliance'') of the service 
bulletin.

Corrective Actions

    (c) For airplanes on which cracking is detected during any 
inspection required by this AD: Prior to further flight, except as 
required by paragraph (d) of this AD, accomplish corrective actions 
(e.g., performing rotating probe inspections, reaming out cracks, 
cold working fastener holes, and installing oversized fasteners) in 
accordance with Airbus Service Bulletin A300-53-6122, dated February 
9, 2000. Repeat the inspection required by paragraph (a) of this AD 
thereafter at intervals not to exceed the applicable intervals 
specified in paragraph 1.E. (``Compliance'') of the service 
bulletin.
    (d) If cracking is detected during any inspection required by 
this AD, and the service bulletin specifies to contact the 
manufacturer for an appropriate corrective action: Prior to further 
flight, repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Direction Generale de l'Aviation Civile (DGAC) (or it's 
delegated agent).

Alternative Methods of Compliance

    (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.

Special Flight Permits

    (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 2000-060-303(B), dated February 9, 2000.


    Issued in Renton, Washington, on May 10, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-12248 Filed 5-15-00; 8:45 am]
BILLING CODE 4910-13-U