[Federal Register: September 12, 2005 (Volume 70, Number 175)]
[Proposed Rules]
[Page 53739-53743]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12se05-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22384; Directorate Identifier 2005-NM-131-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 Series Airplanes,
Model A300 B4 Series Airplanes, Model A310-200 Series Airplanes, Model
A310-300 Series Airplanes, and Model A300 B4-600, B4-600R, and F4-600R
Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively
Called A300-600 Series Airplanes)
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus transport category airplanes. This proposed AD would
require repetitive eddy current inspections for cracks of the stiffener
fittings of the fuselage at frame (FR) 12A, and corrective actions if
necessary. This proposed AD also provides a terminating action for the
inspections. This proposed AD results from reports of cracks on the
upper attachment fitting of the stiffener fitting at FR12A. We are
proposing this AD to prevent failure of the stiffener fittings, which
could result in the reduced structural integrity of the floor and rods
around FR12A.
DATES: We must receive comments on this proposed AD by October 12,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
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 Jacques Leborgne, Airbus Customer Service Directorate, 1
Rond Point Maurice Bellonte, 31707 Blagnac
[[Page 53740]]
Cedex, France, fax (+33) 5 61 93 36 14, for service information
identified in this proposed AD for Model A300 B2 series airplanes and
Model A300 B4 series airplanes. Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for service information
identified in this proposed AD for Model A310-200 series airplanes,
Model A310-300 series airplanes, and Model A300-600 series airplanes.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Include the docket number ``FAA-
2005-22384; Directorate Identifier 2005-NM-131-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. We will consider all comments received by the closing date and may
amend the proposed 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 proposed 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 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 A300 B2 and A300 B4 series
airplanes, Model A310-200 and -300 series airplanes, and Model A300-600
series airplanes.
The DGAC advises that there are reports of cracks on the upper
attachment fitting of the stiffener fitting on the floor beam at frame
(FR) 12A, right-hand and left-hand sides of the fuselage. The DGAC
states that the cracks are due to a combined effect of the
pressurization of the cabin and bending induced by thermal effects
which generates a longitudinal force in the floor beam, causing a high
level of fatigue in the fitting. This condition, if not corrected,
could result in failure of the stiffener fittings, and consequent
reduced structural integrity of the floor and rods around FR12A.
Relevant Service Information
Airbus has issued Service Bulletin A300-53-0365, Revision 01 (for
Model A300 B2 and A300 B4 series airplanes); Service Bulletin A300-53-
6138, Revision 01 (for Model A300-600 series airplanes); and Service
Bulletin A310-53-2117, Revision 01 (for Model A310-200 and A310-300
series airplane); all dated April 4, 2005. The service bulletins
describe procedures for repetitive eddy current inspections for cracks
of the stiffener fittings of the fuselage at FR12A, and corrective
action if necessary. Doing the corrective action eliminates the need
for the repetitive inspection. The corrective action includes replacing
the existing fitting on FR12A with a FR12A crossbeam and installing a
new web between FR12A and FR13 at stringer 26.
The service bulletins refer to Airbus Service Bulletin A300-53-
0364, Revision 02, dated September 24, 2004 (for Model A300 B2 and B4
series airplanes); Service Bulletin A300-53-6137, Revision 03, dated
April 4, 2005 (for Model A300-600 series airplanes); and Service
Bulletin A310-53-2116, Revision 02, dated September 24, 2004 (for Model
A310-200 and -300 series airplane); as the appropriate sources of
service information for doing the corrective action.
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 directive F-
2005-084, dated May 25, 2005, to ensure the continued airworthiness of
these airplanes in France.
FAA's Determination and Requirements of the Proposed 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 airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Between
the Proposed AD and Service Bulletins.''
Differences Between the Proposed AD and Service Bulletins
Unlike the procedures described in Airbus Service Bulletins A300-
53-0365, Revision 01; A300-53-6138, Revision 01; and A310-53-2117,
Revision 01; this proposed AD would not permit further flight if cracks
are detected in the stiffener fittings of the fuselage at FR12A. We
have determined that, because of the safety implications and
consequences associated with that cracking, any cracked fitting must be
replaced before further flight.
The service bulletins specify to contact the manufacturer for
fastener requirements if stiffener fitting FR12A has been replaced, but
this proposed AD would require contacting the FAA or the DGAC (or its
delegated agent). 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 proposed
AD, requirements that we or the DGAC approve would be acceptable for
compliance with this proposed AD.
Operators should note that, although the Accomplishment
Instructions of the referenced service bulletins describe procedures
for reporting results, this proposed AD would not require those
actions. We do not need this information from operators.
[[Page 53741]]
Difference Between French Airworthiness Directive and This Proposed AD
The applicability of French airworthiness directive F-2005-084,
dated May 25, 2005, excludes airplanes that accomplished Airbus Service
Bulletin A300-53-0364, dated December 1, 2003; Revision 01, dated May
5, 2004; or Revision 02, dated September 24, 2004; or Airbus Service
Bulletin A300-53-6137, dated December 1, 2003; Revision 01, dated May
5, 2004; Revision 02, dated September 24, 2004; or Revision 03, dated
April 4, 2005; or Airbus Service Bulletin A310-53-2116, dated December
1, 2003; Revision 01, dated May 5, 2004; or Revision 02, dated
September 24, 2004; in service. However, we have not excluded those
airplanes in the applicability of this proposed AD; rather, this
proposed AD includes a requirement to accomplish the actions specified
in the latest revision of the service bulletins, as applicable. This
requirement would ensure that the actions specified in the service
bulletins and required by this proposed AD are accomplished on all
affected airplanes. Operators must continue to operate the airplane in
the configuration required by this proposed AD unless an alternative
method of compliance is approved.
Costs of Compliance
This proposed AD would affect about 202 airplanes of U.S. registry.
The proposed inspection would take between 57 and 64 work hours per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the estimated cost of the proposed inspection for U.S.
operators is between $748,410 and $840,320, or between $3,705 and
$4,160 per airplane, per inspection cycle.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the 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. 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 proposed 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2005-22384; Directorate Identifier 2005-NM-
131-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
12, 2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to Airbus Model A300 B2-1A,
B2-1C, B2K-3C, and B2-203 airplanes; Model A300 B4-2C, B4-103, and
B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-
605R and F4-622R airplanes; Model A300 C4-605R Variant F airplanes;
Model A310-203, -204, -221, and -222 airplanes; and Model A310-304,
-322, -324, and -325 airplanes; certificated in any category; except
for airplanes on which AIRBUS Modification 12662 has been done in
production.
Unsafe Condition
(d) This AD results from reports of cracks on the upper
attachment fitting of the stiffener fitting at frame (FR) 12A. We
are issuing this AD to prevent failure of the stiffener fittings,
which could result in the reduced structural integrity of the floor
and rods around FR12A.
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.
Inspections
(f) At the applicable initial inspection threshold specified in
Table 1 of this AD or within the applicable grace period specified
in Table 2 of this AD, whichever occurs later: Do an eddy current
inspection for cracks of the stiffener fittings of the fuselage at
FR12A, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A300-53-0365, Revision 01 (for Model A300 B2-1A,
B2-1C, B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103,
and B4-203 airplanes); Service Bulletin A300-53-6138, Revision 01
(for Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, Model
A300 B4-605R and B4-622R airplanes, Model A300 F4-605R and F4-622R
airplanes, and Model A300 C4-605R Variant F airplanes); or Service
Bulletin A310-53-2117, Revision 01 (for Model A310-203, -204, -221,
and -222 airplanes, and Model A310-304, -322, -324, and -325
airplanes); all dated April 4, 2005; as applicable.
Repeat the inspection thereafter at intervals not to exceed the
applicable compliance time specified in Table 1 of this AD until the
actions specified in paragraph (h) of this AD are done.
[[Page 53742]]
Table 1.--Compliance Times for Initial and Repetitive Inspections
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Do the initial inspection prior to the And repeat at intervals not to
For airplanes identified as-- accumulation of-- exceed--
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Configuration 01 in Airbus 19,300 total flight cycles............... 11,450 flight cycles.
Service Bulletin A300-53-0365,
Revision 01, dated April 4, 2005.
Configuration 02 in Airbus 15,500 total flight cycles............... 9,200 flight cycles.
Service Bulletin A300-53-0365,
Revision 01, dated April 4, 2005.
Configuration 01 in Airbus 19,300 total flight cycles............... 11,450 flight cycles.
Service Bulletin A300-53-6138,
Revision 01, dated April 4, 2005.
Configuration 02 in Airbus 17,600 total flight cycles............... 11,450 flight cycles.
Service Bulletin A300-53-6138,
Revision 01, dated April 4, 2005.
Configuration 03 in Airbus 12,700 total flight cycles............... 8,000 flight cycles.
Service Bulletin A300-53-6138,
Revision 01, dated April 4, 2005.
Configuration 04 in Airbus 10,200 total flight cycles............... 6,400 flight cycles.
Service Bulletin A300-53-6138,
Revision 01, dated April 4, 2005.
Configuration 01 in Airbus 19,300 total flight cycles............... 11,450 flight cycles.
Service Bulletin A310-53-2117,
Revision 01, dated April 4, 2005.
Configuration 02 in Airbus 17,600 total flight cycles............... 11,450 flight cycles.
Service Bulletin A310-53-2117,
Revision 01, dated April 4, 2005.
Configuration 03 in Airbus 12,700 total flight cycles............... 8,000 flight cycles.
Service Bulletin A310-53-2117,
Revision 01, dated April 4, 2005.
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Table 2.--Grace Period for the Initial Inspection
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For Airbus model-- Grace period is--
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A300 B2-1A, B2-1C, B2K-3C, and B2-203 Within 2,500 flight cycles
airplanes. after the effective date of
this AD.
A300 B4-2C, B4-103, and B4-203 Within 2,000 flight cycles
airplanes; A300 B4-601, B4-603, B4- after the effective date of
620, and B4-622 airplanes; A300 B4- this AD.
605R and B4-622R airplanes; A300 F4-
605R and F4-622R airplanes; A300 C4-
605R Variant F airplanes; A310-203, -
204, -221, and -222 airplanes; and
A310-304, -322, -324, and -325
airplanes.
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Corrective Action
(g) If any cracking is found during any inspection required by
paragraph (f) of this AD, before further flight, do the replacement
and installation specified in paragraph (h) of this AD.
Terminating Action
(h) Replacing the existing fitting on FR12A with a FR12A
crossbeam and installing a new web between FR12A and FR13 at
stringer 26 in accordance with Airbus Service Bulletin A300-53-0364,
Revision 02, dated September 24, 2004 (for Model A300 B2-1A, B2-1C,
B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103, and B4-
203 airplanes); Service Bulletin A300-53-6137, Revision 03, dated
April 4, 2005 (for Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-
605R and F4-622R airplanes, and Model A300 C4-605R Variant F
airplanes); or Service Bulletin A310-53-2116, Revision 02, dated
September 24, 2004 (for Model A310-203, -204, -221, and -222
airplanes, and Model A310-304, -322, -324, and -325 airplanes); as
applicable; and except as required by paragraph (i) of this AD;
constitutes terminating action for the requirements of this AD.
(i) Where the service bulletins specify to contact the
manufacturer for certain information, before further flight, do the
terminating action according to a method approved by either the
Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate; or the DGAC (or its delegated agent).
Actions Accomplished According to Previous Issue of Service Bulletin
(j) Actions accomplished before the effective date of this AD
according to the Airbus service bulletins specified in Table 3 of
this AD are considered acceptable for compliance with the
corresponding actions specified in this AD.
Table 3.--Previous Issues of Service Bulletins
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Airbus Service Bulletin Revision level Date
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A300-53-0364.......................... Original......................... December 1, 2003.
A300-53-0364.......................... 01............................... May 5, 2004.
A300-53-0365.......................... Original......................... December 1, 2003.
A300-53-6137.......................... Original......................... December 1, 2003.
A300-53-6137.......................... 01............................... May 5, 2004.
A300-53-6137.......................... 02............................... September 24, 2004.
A300-53-6138.......................... Original......................... December 1, 2003.
A310-53-2116.......................... Original......................... December 1, 2003.
A310-53-2116.......................... 01............................... May 5, 2004.
A310-53-2117.......................... Original......................... December 1, 2003.
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[[Page 53743]]
No Reporting Required
(k) Although the service bulletins referenced in this AD specify to
submit certain information to the manufacturer, this AD does not
include that requirement.
Alternative Methods of Compliance (AMOCs)
(l) The Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA, has the authority to approve AMOCs for this AD, if
requested in accordance with the procedures found in 14 CFR 39.19.
Related Information
(m) French airworthiness directive F-2005-084, dated May 25, 2005,
also addresses the subject of this AD.
Issued in Renton, Washington, on August 24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-17980 Filed 9-9-05; 8:45 am]
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