[Federal Register Volume 66, Number 83 (Monday, April 30, 2001)]
[Proposed Rules]
[Pages 21292-21294]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-10594]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-390-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 F4-605R 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 F4-605R

[[Page 21293]]

airplanes. This proposal would require installation of external 
doublers at frames 29 and 33. This action is necessary to prevent 
fatigue cracking of certain circumferential joints, which could result 
in reduced structural integrity of the fuselage in the vicinity of the 
upper deck cargo door. This action is intended to address the 
identified unsafe condition.

DATES: Comments must be received by May 30, 2001.

ADDRESSES: Submit comments in triplicate to the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-390-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. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the 
Internet must contain ``Docket No. 2000-NM-390-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: Tim Backman, Aerospace 
Engineer, International Branch, ANM-116, FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; 
telephone (425) 227-2797; 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:
     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.
     For each issue, state what specific change to the proposed 
AD is being requested.
     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 2000-NM-390-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 2000-NM-390-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 F4-605R airplanes. The 
DGAC advises that fatigue and damage tolerance analysis conducted on 
airplanes converted from passenger to freighter configuration indicated 
that the upper areas of certain fuselage circumferential joints may not 
reach the airplane design life goal without reinforcement. Additional 
analysis extended this result to include production Model A300-600 
series airplanes equipped with an upper deck cargo door. Premature 
fatigue cracking could result in reduced structural integrity of the 
fuselage in the vicinity of the upper deck cargo door.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A300-53-6119, Revision 01, dated 
September 25, 2000. The service bulletin describes procedures for 
installing external doublers at frames 29 and 33. Accomplishment of the 
actions specified in the service bulletin is intended to adequately 
address the identified unsafe condition. The DGAC classified this 
service bulletin as mandatory and issued French airworthiness directive 
2000-456-323(B), dated November 15, 2000, to ensure 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 accomplishment of 
the actions specified in the service bulletin described previously.

Cost Impact

    The FAA estimates that 32 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 85 work 
hours per airplane to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $1,820 per airplane. Based on these figures, the cost 
impact of the proposed AD on U.S. operators is estimated to be 
$221,440, or $6,920 per airplane.
    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 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

[[Page 21294]]

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-390-AD.

    Applicability: Model A300F4-605R airplanes, certificated 
in any category, except those on which Airbus production 
Modification 12081 or the modification specified by Service Bulletin 
A300-53-6119, Revision 01, dated September 25, 2000, has been 
installed.

    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 (b) 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 fatigue cracking of certain circumferential joints, 
which could result in reduced structural integrity of the fuselage 
in the vicinity of the upper deck cargo door, accomplish the 
following:

Installation of Doublers

    (a) Before the airplane accumulates 10,000 total flight cycles, 
or within 6 months after the effective date of this AD, whichever 
occurs later: Install external doublers at frames 29 and 33, in 
accordance with Airbus Service Bulletin A300-53-6119, Revision 01, 
dated September 25, 2000.

Alternative Methods of Compliance

    (b) 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, 
Transport Airplane Directorate, FAA. 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

    (c) 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 2000-456-323(B), dated November 15, 2000.


    Issued in Renton, Washington, on April 23, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-10594 Filed 4-27-01; 8:45 am]
BILLING CODE 4910-13-U