AD 2001-16-13

[Federal Register Volume 66, Number 164 (Thursday, August 23, 2001)]
[Rules and Regulations]
[Pages 44295-44297]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-21103]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-70-AD; Amendment 39-12382; AD 2001-16-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Model A330 series airplanes. This action requires 
a one-time roto-test inspection of fastener holes of certain fuselage 
joints for cracks and reinforcement of the fuselage between frames 31 
and 37.1. If cracks are detected, this action requires a follow-up high 
frequency eddy current (HFEC) inspection and repair. This action is 
necessary to prevent fatigue cracking of the fuselage longitudinal 
buttstrap, which could result in reduced structural integrity of the 
fuselage. This action is intended to address the identified unsafe 
condition.

DATES: Effective September 7, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 7, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before September 24, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket Number 2001-NM-70-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:
<a href="/cdn-cgi/l/email-protection#261f0b47484b0b4f475445494b4b4348526640474708414950"><span class="__cf_email__" data-cfemail="6851450906054501091a0b0705050d061c280e0909460f071e">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-70-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 this AD 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; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
Renton, Washington 98055-4056; telephone (425) 227-2125; fax (425) 227-
1149.

SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, notified the 
FAA

[[Page 44296]]

that an unsafe condition may exist on certain Airbus Model A330 series 
airplanes. The DGAC advises that during fatigue testing on the 
fuselage, cracks were detected in the longitudinal buttstrap at 
stringer 9 after 60,051 simulated flights, at frame 31 after 87,876 
simulated flights, and at frame 37.1 after 69,570 simulated flights. 
This condition, if not corrected, could result in propagation of 
existing cracks and initiation of additional cracks of the fuselage 
longitudinal buttstrap, which could result in reduced structural 
integrity of the airplane.

Explanation of Relevant Service Information

    Airbus Industrie has issued Service Bulletin A330-53-3090, Revision 
02, dated January 9, 2001, which describes procedures for a one-time 
roto-test inspection for cracks at fastener holes of the affected 
fuselage joints and installation of additional doublers and wedges to 
reinforce the circumferential joint at frames 31/37.1 and of the 
longitudinal joint at stringer 9 on both the left-hand and right-hand 
sides. If cracks are detected by the roto-test inspection, the service 
bulletin also describes procedures for an additional high frequency 
eddy current (HFEC) inspection to determine the length of the cracks. 
The DGAC classified this service bulletin as mandatory and issued 
French airworthiness directive 2001-075(B), dated March 7, 2001, 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 21.19) 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 the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design that may be 
registered in the United States at some time in the future, this AD is 
being issued to prevent fatigue cracking of the fuselage longitudinal 
buttstrap, which could result in reduced structural integrity of the 
fuselage. This AD requires a roto-test inspection of fastener holes of 
certain fuselage joints for cracks and reinforcement of the fuselage 
structure between frames 31 and 37.1. If cracks are detected, this 
action requires a follow-up HFEC inspection and corrective action. The 
actions are required to be accomplished in accordance with the service 
bulletin described previously, except as described below.

Differences Between Proposed Rule and Foreign Airworthiness 
Directive

    Operators should note that, although the service bulletin specifies 
that the manufacturer may be contacted for instructions regarding 
repair of cracks, this AD requires the repair of cracks to be 
accomplished per a method approved by either 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 this AD, a repair method approved by either the 
FAA or the DGAC would be acceptable for compliance with this AD.

Cost Impact

    None of the Model A330 series airplanes affected by this action are 
on the U.S. Register. All airplanes included in the applicability of 
this rule currently are operated by non-U.S. operators under foreign 
registry; therefore, they are not directly affected by this AD action. 
However, the FAA considers that this rule is necessary to ensure that 
the unsafe condition is addressed in the event that any of these 
subject airplanes are imported and placed on the U.S. Register in the 
future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 321 work hours 
to accomplish the required actions, at an average labor rate of $60 per 
work hour. The cost of required parts is approximately $6,187. Based on 
these figures, the cost impact of this AD would be $25,447 per 
airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
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 under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Submit comments using the following format:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> 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 rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-70-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a

[[Page 44297]]

``significant regulatory action'' under Executive Order 12866; (2) is 
not a ``significant rule'' under DOT Regulatory Policies and Procedures 
(44 FR 11034, February 26, 1979); and (3) 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 final 
evaluation has been prepared for this action and it is contained in the 
Rules Docket. A copy of it may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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:

2001-16-13  Airbus Industrie: Amendment 39-12382. Docket 2001-NM-70-
AD.

    Applicability: Model A330 airplanes, serial numbers 301, 321, 
322, 323, 341, 342, and 343, certificated in any category; except 
airplanes on which Airbus Industrie Modification 46636 has been 
accomplished in production or which have been modified in service in 
accordance with Airbus Service Bulletin A330-53-3090, dated March 9, 
1999; Revision 01, dated July 6, 1999; or Revision 02, dated January 
9, 2001.

    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 (d) 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 the fuselage longitudinal 
buttstrap, which could result in reduced structural integrity of the 
fuselage, accomplish the following:

Inspection

    (a) Prior to the accumulation of 15,000 total flight cycles: 
Perform a roto-test inspection to detect cracks of the fastener 
holes at frame 31, frame 37.1, and stringer 9, in accordance with 
Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 
2001.

Reinforcement

    (b) If no cracks are detected during the inspection performed in 
accordance with paragraph (a) of this AD, prior to further flight, 
reinforce the fuselage structure between frames 31 and 37.1, in 
accordance with Airbus Service Bulletin A330-53-3090, Revision 02, 
dated January 9, 2001.

Follow-up Inspection

    (c) If any crack is detected during the inspection performed in 
accordance with paragraph (a) of this AD, prior to further flight, 
perform a high frequency eddy current (HFEC) inspection to determine 
the crack length, in accordance with Airbus Service Bulletin A330-
53-3090, Revision 02, dated January 9, 2001. Prior to further 
flight, repair the crack in accordance with a method approved by 
either the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate; or the Direction Generale de l'Aviation Civile 
(or its delegated agent).

Alternative Methods of Compliance

    (d) 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

    (e) 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.

Incorporation by Reference

    (f) Except as required by paragraph (c) of this AD, the actions 
shall be done in accordance with Airbus Service Bulletin A330-53-
3090, Revision 02, dated January 9, 2001. This incorporation by 
reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 2001-075(B), dated March 17, 2001.

Effective Date

    (g) This amendment becomes effective on September 7, 2001.

    Issued in Renton, Washington, on August 15, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21103 Filed 8-22-01; 8:45 am]
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