[Federal Register Volume 63, Number 198 (Wednesday, October 14, 1998)]
[Proposed Rules]
[Pages 55063-55065]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-27477]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-153-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD), applicable to certain Airbus Model A300-600 series 
airplanes, that would have required repetitive inspections to detect 
cracks in the angle fitting at frame 40 of the center wing box, and 
corrective actions, if necessary; and eventual modification of that 
angle fitting, which would terminate the repetitive inspections. That 
proposal was prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. This new action 
revises certain compliance times in the proposed rule. The actions 
specified by this new proposed AD are intended to prevent cracks in the 
center wing box angle fitting, which could result in the failure of the 
center wing box at frame 40, and consequent reduced structural 
integrity of the airplane.

DATES: Comments must be received by November 9, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 97-NM-153-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 97-NM-153-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. 97-NM-153-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to 
certain Airbus Model A300-600 series airplanes, was published as a 
notice of proposed rulemaking (NPRM) in the Federal Register on March 
4, 1998 (63 FR 10576). That NPRM would have required repetitive 
inspections to detect cracks in the angle fitting at frame 40 of the 
center wing box, and corrective

[[Page 55064]]

actions, if necessary; and eventual modification of that angle fitting, 
which would terminate the repetitive inspections. That NPRM was 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign civil airworthiness authority. The actions specified by 
that NPRM are intended to prevent cracks in the center wing box angle 
fitting, which could result in the failure of the center wing box at 
frame 40, and consequent reduced structural integrity of the airplane.

Actions Since Issuance of Previous Proposal

    Since the issuance of that NPRM, the FAA has become aware of a 
typographical error that appeared in Table 1 of the proposal. The 
initial inspection threshold for airplanes having an average flight 
time (AFT) of 5.50-5.99 should be 3,200 flight cycles instead of 2,300 
flight cycles. Table 1 of this supplemental NPRM has been revised 
accordingly.

Comment Received

    Due consideration has been given to the comment received in 
response to the NPRM.

Request for Correction to Compliance Time

    One commenter requests a correction to another compliance time that 
appeared in Table 1 of the proposed AD. The initial inspection interval 
for airplanes having an AFT of 2.10-2.49, should be 5,300 flight cycles 
instead of 6,300 flight cycles. The commenter notes that the data 
listed in Table 1 of the proposal did not match the data the 
manufacturer submitted to the FAA on October 17, 1997.
    The FAA concurs with the commenter's request to correct the 
compliance time listed in the original NPRM. Table 1 of this 
supplemental NPRM has been revised accordingly.

Conclusion

    Since this change expands the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.

Cost Impact

    The FAA estimates that 54 Model A300-600 series airplanes of U.S. 
registry would be affected by this proposed AD.
    It would take approximately 36 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 inspection 
proposed by this AD on U.S. operators is estimated to be $116,640, or 
$2,160 per airplane, per inspection cycle.
    It would take approximately 754 work hours per airplane to 
accomplish the proposed modification, at an average labor rate of $60 
per work hour. Required parts would cost approximately $11,605 per 
airplane. Based on these figures, the cost impact of the modification 
proposed by this AD on U.S. operators is estimated to be $3,069,630, or 
$56,845 per airplane.
    The cost impact figures discussed above are 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: Docket 97-NM-153-AD.

    Applicability: Model A300-600 series airplanes on which Airbus 
Modification 10453 has not been installed; 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 prevent cracks in the center wing box angle fitting, which 
could result in the failure of the center wing box at frame 40, and 
consequent reduced structural integrity of the airplane, accomplish 
the following:
    (a) Prior to the accumulation of the threshold specified in 
Table 1 of this AD, as applicable, or within 1,500 flight cycles 
after the effective date of this AD, whichever occurs later: Perform 
a detailed visual, eddy current, or liquid penetrant inspection to 
detect cracking in the angle fitting of frame 40 (both left and 
right), with the nut removed, in accordance with Airbus Service 
Bulletin A300-57-6052, Revision 1, dated July 22, 1996. Thereafter, 
repeat the inspections at the interval specified in Table 1 of this 
AD, as applicable, until the actions required by paragraph (c) of 
this AD have been accomplished.

[[Page 55065]]



                                                     Table 1
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                                                                                                 Eddy current/
                                                                            Visual inspection   liquid penetrant
 Average flight time (AFT): flight hours/flight cycles   Threshold (flight   interval (flight      inspection
                                                              cycles)            cycles)        interval (flight
                                                                                                    cycles)
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2.10-2.49..............................................              5,900              4,700              5,300
2.50-2.99..............................................              5,600              4,400              4,900
3.00-3.49..............................................              5,200              4,100              4,600
3.50-3.99..............................................              4,800              3,800              4,200
4.00-4.49..............................................              4,400              3,500              3,900
4.50-4.99..............................................              4,000              3,200              3,500
5.00-5.49..............................................              3,600              2,800              3,200
5.50-5.99..............................................              3,200              2,500              2,800
6.00-6.50..............................................              2,800              2,200              2,500
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    (b) Except as provided by paragraph (d) of this AD, if any crack 
is found during an inspection required by paragraph (a) of this AD, 
prior to further flight, accomplish follow-on corrective actions in 
accordance with the procedures specified in Airbus Service Bulletin 
A300-57-6052, Revision 1, dated July 22, 1996.
    (c) Within 4 years after the effective date of this AD, modify 
the angle fitting at frame 40 (both left and right) in accordance 
with Airbus Service Bulletin A300-57-6053, Revision 1, dated October 
31, 1995. Accomplishment of the modification constitutes terminating 
action for the repetitive inspections required by paragraph (a) of 
this AD.
    (d) If any crack is found during an inspection required by 
paragraph (a) of this AD, and the applicable service bulletin 
specifies to contact the manufacturer for an appropriate action: 
Prior to further flight, repair in accordance with a method approved 
by the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate.
    (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 
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 3: The subject of this AD is addressed in French 
airworthiness directive (CN) 95-111-181(B) R1, dated October 23, 
1996.

    Issued in Renton, Washington, on October 7, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-27477 Filed 10-13-98; 8:45 am]
BILLING CODE 4910-13-U