[Federal Register Volume 70, Number 182 (Wednesday, September 21, 2005)]
[Rules and Regulations]
[Pages 55236-55239]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-18522]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22452; Directorate Identifier 2001-NM-336-AD; 
Amendment 39-14277; AD 2005-19-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-301, -321, -322, -
341, and -342 Airplanes; and Model A340-200 and A340-300 Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes; 
and Model A340-200 and A340-300 series airplanes. This AD requires 
repetitive inspections for cracks of the inboard lower flange and 
radius of the left- and right-hand outboard floor beams at frame (FR) 
48, and related investigative and corrective actions if necessary. This 
AD also provides an optional terminating action for the repetitive 
inspections. This AD results from reports that cracks were found during 
fatigue tests at the attachment between the canted lower flange of the 
floor beam and the pressure diaphragm in front of FR48 on both left- 
and right-hand floor beams; and that an additional crack was found in 
the flange radius of the floor beam. We are issuing this AD to detect 
and correct such cracking, which could propagate and result in reduced 
structural integrity of the fuselage.

DATES: Effective October 6, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of October 6, 
2005.
    We must receive comments on this AD by November 21, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.
    You may examine the contents of the AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401, 
Washington, DC. This docket number is FAA-2005-22452; the directorate 
identifier for this docket is 2001-NM-336-AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, ANM-
116, International Branch, FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Although this is a final rule that was not preceded by notice and 
an opportunity for public comment, we invite you to submit any relevant 
written data, views, or arguments regarding this AD. Include ``Docket 
No. FAA-2005-22452; Directorate Identifier 2001-NM-336-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
AD. We will consider all comments received by the closing date and may 
amend the AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of that Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete

[[Page 55237]]

Privacy Act Statement in the Federal Register published on April 11, 
2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified us that an unsafe 
condition may exist on certain Airbus Model A330-301, -321, -322, -341, 
and -342 airplanes; and Model A340-200 and A340-300 series airplanes. 
The DGAC advises that cracks were found during fatigue tests at the 
attachment between the canted lower flange of the floor beam and the 
pressure diaphragm in front of frame (FR) 48 on both left- and right-
hand floor beams. The cracks extended between two fasteners close to 
FR48 on the canted lower flange of the floor beam. In addition, another 
crack was found in the flange radius of the floor beam. Further 
investigation revealed that the cracks resulted from excessive bending 
of the canted lower flange of the floor beam. Fatigue cracks could 
propagate from one fastener to another. This condition, if not 
corrected, could result in reduced structural integrity of the 
fuselage.

Relevant Service Information

    Airbus has issued Service Bulletin A330-53-3014, Revision 05, dated 
June 20, 2003 (for Model A330-301, -321, -322, -341, and -342 
airplanes); and Service Bulletin A340-53-4022, Revision 05, dated June 
16, 2003 (for Model A340-200 and A340-300 series airplanes). The 
service bulletins describe procedures for doing repetitive high-
frequency eddy current (HFEC) inspections for cracks of the inboard 
lower flange and radius of the left- and right-hand outboard floor 
beams at FR48. The service bulletins also describe procedures for 
reporting inspection findings to Airbus. If no cracks are found during 
an HFEC inspection, the service bulletins specify that operators repeat 
the inspection. If any crack is found during any HFEC inspection, the 
service bulletins give procedures for related investigative and 
corrective actions as follows:
    <bullet> For cracks at the radius, the service bulletins specify 
that operators should contact Airbus for repair instructions before 
further flight.
    <bullet> For cracks at the flange, the service bulletins specify 
that operators should measure the total length of the crack. If the 
crack is within certain limits, the service bulletins give procedures 
for stop-drilling the crack before further flight, and for repairing 
the crack within 500 flight cycles after the stop-drilling by 
installing stainless steel doublers under the floor beams. If the crack 
is outside certain limits, the service bulletins specify that operators 
should contact Airbus for repair instructions before further flight.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information and issued French airworthiness directives 
2001-506(B), dated October 17, 2001, and 2001-507(B), dated October 17, 
2001, to ensure the continued airworthiness of these airplanes in 
France.
    Airbus has also issued Service Bulletins A330-53-3013, Revision 03 
dated December 23, 1999 (for Model A330-301, -321, -322, -341, and -342 
airplanes); and Service Bulletin A340-53-4021, Revision 05, dated 
January 27, 2003 (for Model A340-200 and A340-300 series airplanes). 
These service bulletins provide an optional terminating action for the 
repetitive inspections of the inboard lower flange. The terminating 
action is installing new stainless steel doublers under the floor beam 
to limit the bending movement of the canted lower flange. The 
installation involves removing certain fasteners and doing a rotating 
probe inspection for cracks of the fastener holes. If any crack is 
found, the service bulletins specify contacting Airbus for repair 
instructions.

FAA's Determination and Requirements of This AD

    These airplane models 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. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    Therefore, we are issuing this AD to detect and correct cracks 
between the canted lower flange of the floor beam and the pressure 
diaphragm in front of FR48 on both left- and right-hand floor beams; 
and cracks in the flange radius of the floor beam; which could 
propagate and result in reduced structural integrity of the fuselage. 
This AD requires accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Among the AD, the French Airworthiness Directives, and 
the Service Bulletins.''
    Operators should note that, in consonance with the findings of the 
DGAC, this proposed AD allows operators to continue the repetitive 
inspections instead of doing the terminating action. Additionally, in 
certain cases, operators that detect cracking may defer the repair for 
a specified period of time. In making these determinations, we consider 
that, in the case of this AD, long-term continued operational safety is 
adequately assured by doing the repetitive inspections to detect 
cracking before it represents a hazard to the airplane, and by doing 
repairs within the specified time limits.

Differences Among the AD, the French Airworthiness Directives, and the 
Service Bulletins

    The applicability of the French airworthiness directives excludes 
airplanes on which Airbus Service Bulletin A330-53-3013 or A340-53-4021 
was accomplished in service. However, we have not excluded those 
airplanes in the applicability of this AD; rather, this AD includes a 
requirement to accomplish the actions specified in those service 
bulletins. This requirement will ensure that the actions specified in 
the applicable service bulletin and required by this AD are 
accomplished on all affected airplanes. Operators must continue to 
operate the airplane in the configuration required by this AD unless an 
alternative method of compliance is approved. This difference has been 
coordinated with the DGAC.
    The French airworthiness directives specify a compliance time based 
on the time ``since new.'' However, this AD specifies a compliance time 
after the date of issuance of the original standard airworthiness 
certificate or the date of issuance of the original export certificate 
of airworthiness. This decision is based on our determination that 
``since new'' may be interpreted differently by different operators. We

[[Page 55238]]

find that our proposed terminology is generally understood within the 
industry and records will always exist that establish these dates with 
certainty.
    The service bulletins specify that you may contact the manufacturer 
for instructions on how to repair certain conditions, but this AD would 
require you to repair those conditions using a method that we or the 
DGAC (or its delegated agent) approve. In light of the type of repair 
that would be required to address the unsafe condition, and consistent 
with existing bilateral airworthiness agreements, we have determined 
that, for this AD, a repair we, or the DGAC, approve would be 
acceptable for compliance with this AD.
    Although the Accomplishment Instructions of Airbus Service 
Bulletins A330-53-3014, Revision 05, and A340-53-4022, Revision 05, 
provide procedures for reporting certain information to the 
manufacturer, this AD would not require those actions.

Clarification of Optional Terminating Action

    The service bulletins describe procedures for installing a 
stainless steel doubler, which is an optional terminating action for 
the repetitive inspections of both the inboard lower flange and the 
radius. The manufacturer has determined that the crack in the radius is 
a direct consequence of the load re-distribution following cracking of 
the fastener holes. The stainless steel doubler reinforces the area of 
the fastener holes.

Costs of Compliance

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes affected by this AD are currently operated by 
non-U.S. operators under foreign registry; therefore, they are not 
directly affected by this AD action. However, we consider this AD 
necessary to ensure that the unsafe condition is addressed if any 
affected airplane is imported and placed on the U.S. Register in the 
future.
    The following table provides the estimated costs to comply with 
this AD for any affected airplane that might be imported and placed on 
the U.S. Register in the future.

                                                                     Estimated Costs
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                                                          Average labor
                Action                    Work  hours     rate per hour             Parts  cost                         Cost per  airplane
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HFEC inspection, per inspection cycle.                2              $65  None..........................  $130, per inspection cycle.
Optional terminating action...........               18               65  $1,930........................  $3,100.
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FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is 
unnecessary before this AD is issued, and this AD may be made effective 
in less than 30 days after it is published in the Federal Register.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2005-19-12 Airbus: Amendment 39-14277. Docket No. FAA-2005-22452; 
Directorate Identifier 2001-NM-336-AD.

Effective Date

    (a) This AD becomes effective October 6, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330-301, -321, -322, -341, 
and -342 airplanes; and Model A340-211, -212, -213, -311, -312, and 
-313 airplanes; certificated in any category; on which Airbus 
Modification 42418 has not been accomplished in production.

Unsafe Condition

    (d) This AD results from reports that cracks were found during 
fatigue tests at the attachment between the canted lower flange of 
the floor beam and the pressure diaphragm in front of frame (FR) 48 
on both left- and right-hand floor beams; and that an additional 
crack was found in the flange radius of the floor beam. The FAA is 
issuing this AD to detect and correct such cracking,

[[Page 55239]]

which could propagate and result in reduced structural integrity of 
the fuselage.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Repetitive Inspections

    (f) At the applicable times in paragraph (f)(1) or (f)(2) of 
this AD: Do high-frequency eddy current inspection for cracks of the 
inboard lower flange and radius of the left-hand and right-hand 
outboard floor beams at FR48. Do all inspections in accordance with 
the Accomplishment Instructions of the applicable service bulletin 
in Table 1 of this AD. Doing the action in paragraph (h) of this AD 
terminates the repetitive inspection requirements of this paragraph.
    (1) For Airbus Model A330-301, -321, -322, -341, and -342 
airplanes: Do the first inspection before the accumulation of 8,400 
flight cycles since the date of issuance of the original standard 
airworthiness certificate or the date of issuance of the original 
export certificate of airworthiness, or within 6 months after the 
effective date of this AD, whichever occurs later; and repeat the 
inspection thereafter at intervals not to exceed 3,860 total flight 
cycles or 15,050 flight hours, whichever occurs earlier.
    (2) For Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes: Do the first inspection before the accumulation of the 
earlier of 9,200 flight cycles or 70,000 flight hours since the date 
of issuance of the original standard airworthiness certificate or 
the date of issuance of the original export certificate of 
airworthiness, or within 6 months after the effective date of this 
AD, whichever occurs later; and repeat the inspection thereafter at 
intervals not to exceed 3,070 flight cycles.

                                           Table 1.--Service Bulletins
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         For airbus model--                                    Airbus service bulletin--
----------------------------------------------------------------------------------------------------------------
A330-301, -321, -322, -341, and -342  A330-53-3014, Revision 05, dated June 20, 2003.
 airplanes.
A340-211, -212, -213, -311, -312,     A340-53-4022, Revision 05, dated June 16, 2003.
 and -313 airplanes.
----------------------------------------------------------------------------------------------------------------

Related Investigative and Corrective Actions

    (g) If any crack is found during any inspection required by 
paragraph (f) of this AD: Do the applicable actions in paragraph 
(g)(1) and (g)(2) of this AD.
    (1) For cracks at the radius: Before further flight, repair the 
crack according to a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the Direction Ge[aacute]ne[aacute]rale de l'Aviation Civile 
(DGAC) (or its delegated agent).
    (2) For cracks at the flange: Before further flight, measure the 
total length of the crack and do the applicable action in paragraph 
(g)(2)(i) and (g)(2)(ii) of this AD.
    (i) If the crack is less than 12 mm (0.472 inch) in length: 
Before further flight, stop-drill the crack and, within 500 flight 
cycles after stop-drilling the crack, do the action in paragraph (h) 
of this AD.
    (ii) If the crack is greater than or equal to 12 mm (0.472 inch) 
in length: Before further flight, repair the crack according to a 
method approved by either the Manager, International Branch, ANM-
116; or the Direction Ge[aacute]ne[aacute]rale de l'Aviation Civile 
(DGAC) (or its delegated agent).

Optional Terminating Action

    (h) Installing a stainless steel doubler in accordance with 
Airbus Service Bulletin A330-53-3013, Revision 03, December 23, 
1999; or Airbus Service Bulletin A340-53-4021, Revision 05, dated 
January 27, 2003; as applicable; terminates the repetitive 
inspection requirements of paragraph (f) of this AD. If any crack is 
found during this installation while doing the rotating probe 
inspection of the fastener holes: Before further flight, repair the 
crack according to a method approved by either the Manager, 
International Branch, ANM-116; or the DGAC (or its delegated agent).

No Reporting Required

    (i) Although the Accomplishment Instructions of the service 
bulletins identified in Table 1 of this AD describe procedures for 
reporting certain information to the manufacturer, this AD would not 
require those actions.

Alternative Methods of Compliance (AMOCs)

    (j) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.

Related Information

    (k) French airworthiness directives 2001-506(B) and 2001-507(B), 
both dated October 17, 2001, also address the subject of this AD.

Material Incorporated by Reference

    (l) You must use the service information identified in Table 2 
of this AD to perform the actions that are required by this AD, 
unless the AD specifies otherwise. The Director of the Federal 
Register approved the incorporation by reference of these documents 
in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, 
for a copy of this service information. You may review copies at the 
Docket Management Facility, U.S. Department of Transportation, 400 
Seventh Street SW., Room PL-401, Nassif Building, Washington, DC; on 
the Internet at http://dms.dot.gov; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html.

              Table 2.--Material Incorporated by Reference
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                                  Revision
       Service  Bulletin           level                Date
------------------------------------------------------------------------
A330-53-3013...................         03  December 23, 1999.
A330-53-3014...................         05  June 20, 2003.
A340-53-4021...................         05  January 27, 2003.
A340-53-4022...................         05  June 16, 2003.
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    Issued in Renton, Washington, on September 9, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-18522 Filed 9-20-05; 8:45 am]
BILLING CODE 4910-13-P