[Federal Register Volume 80, Number 30 (Friday, February 13, 2015)]
[Proposed Rules]
[Pages 7992-7994]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-02535]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0084; Directorate Identifier 2014-NM-181-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Airbus
Model A300 B4-600 series airplanes; and Airbus Model A300 B4-600R
series airplanes. This proposed AD was prompted by reports indicating
that, on airplanes that received a certain repair following crack
findings, cracks can re-initiate. This proposed AD would require
repetitive inspections for cracking of the frame (FR) 40 forward
fittings for airplanes previously repaired. We are proposing this AD to
detect and correct cracking on the FR 40 forward fittings, which could
result in rupture of the forward fittings and reduction of in-flight
structural strength.
DATES: We must receive comments on this proposed AD by March 30, 2015.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0084; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0084;
Directorate Identifier 2014-NM-181-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0199, dated September 05, 2014 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A300 B4-2C, B4-103, and B4-203 airplanes; Airbus Model A300 B4-600
series airplanes; and Airbus Model A300 B4-600R series airplanes. The
MCAI states:
During routine inspection on an A300-600 aeroplane, a crack was
found in the right-hand frame (FR) 40 forward fitting between
stringer (STRG) 32 and STRG 33. The subject aeroplane had previously
been modified, as a crack prevention measure, in accordance with
Airbus SB A300-57-6053 (mod 10453).
To ensure the structural integrity of FR 40, pending completion
of the full root cause analysis using a refined Finite Element Model
(FEM), EASA issued AD 2009-0094 [dated April 21, 2009, http://ad.easa.europa.eu/ad/2009-0094], to require, a one-time Detailed
Visual Inspection (DVI) of A300 and A300-600 aeroplanes on which
Airbus SB A300-53-0297 or SB A300-57-6053, as applicable, was
embodied as a crack prevention measure.
Thereafter, cracks were found during maintenance check in the FR
40 forward fitting on two aeroplanes, one A300 with Airbus SB A300-
53-0297 embodied and one A300-600 with Airbus SB A300-57-6053
embodied. EASA AD 2009-0094 had been accomplished on both
aeroplanes.
Consequently, EASA issued AD 2011-0163 [dated August 30, 2011,
http://ad.easa.europa.eu/ad/2011-0163], superseding EASA AD 2009-
0094, to require, for aeroplanes modified preventively, repetitive
DVI of the FR 40 forward fitting (without nut removal),
accomplishment of a one-time Eddy Current (EC) inspection or liquid
penetrant inspection of this area (with nut removal) and, depending
on findings, the accomplishment of associated corrective actions.
A detailed FEM study was recently completed which demonstrated
that, on aeroplanes repaired following crack findings in accordance
with the instructions of Airbus SB A300-53-0297 or SB A300-57-6053
at any revision, as applicable, cracks can re-initiate.
For the reasons described above, this [EASA] AD requires
repetitive inspections of the FR 40 forward fitting for aeroplanes
repaired in accordance with the instructions of Airbus SB A300-53-
0297 or SB A300-57-6053 following crack findings.
The corrective actions include a repair using a method approved by
the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA).
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0084.
[[Page 7993]]
Relevant Service Information Under 1 CFR Part 51
We reviewed the following Airbus service information:
Airbus A300 Alert Operators Transmission (AOT) A53W002-14,
dated April 02, 2014.
Airbus A300 AOT A57W003-14, Revision 01, dated April 17,
2014.
Airbus A300 Alert Operators Transmission (AOT) A53W002-14, dated
April 02, 2014, describes procedures for repetitive inspections of the
FR40 forward fitting on A300 aircraft post MOD 10453S20571. Airbus A300
AOT A57W003-14, Revision 01, dated April 17, 2014, describes procedures
for repetitive inspections of the FR40 forward fitting on A300-600
aircraft pre MOD 10221S20394 and post MOD 10453S20571. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI. This service information is
reasonably available; see ADDRESSES for ways to access this service
information.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 26 airplanes of U.S.
registry.
We also estimate that it would take about 3 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $6,630, or $255
per product.
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 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 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);
3. Will not affect intrastate aviation in Alaska; and
4. 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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
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 FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2015-0084; Directorate Identifier 2014-NM-
181-AD.
(a) Comments Due Date
We must receive comments by March 30, 2015.
(b) Affected ADs
None
(c) Applicability
(1) This AD applies to the airplanes identified in paragraphs
(c)(1)(i) and (c)(1)(ii) of this AD, certificated in any category.
(i) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes, all
manufacturer serial numbers (MSN), on which modification 10453 has
been embodied as a repair following a crack finding, as specified in
Airbus Service Bulletin A300-53-0297 (modification 10453).
(ii) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
and B4-622R airplanes, all MSN as specified in Airbus Service
Bulletin A300-57-6053.
(2) This AD does not apply to airplanes that have been modified,
as a preventive measure, as specified in Airbus Service Bulletin
A300-53-0297 or A300-57-6053 (modification 10453), as applicable to
airplane model.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports indicating that, on airplanes
that received a certain repair following crack findings, cracks can
re-initiate. We are issuing this AD to detect and correct cracking
on the frame (FR) 40 forward fittings, which could result in rupture
of the forward fittings and reduction of in-flight structural
strength.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Within 300 flight cycles after the effective date of this AD, do
a detailed inspection of the forward fitting at FR 40 without nut
removal to detect cracks on both left-hand and right-hand sides of
the airplane, in accordance with Airbus A300 Alert Operators
Transmission (AOT) A53W002-14, dated April 2, 2014 (for Airbus Model
A300 B4-2C, B4-103, and B4-203 airplanes); or Airbus A300AOT
A57W003-14, Revision 01, dated April 17, 2014 (for Airbus Model A300
B4-600 series airplanes, and Airbus Model A300 B4-600R series
airplanes); as applicable. If any crack is detected, repair before
further flight using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). Repeat the inspection thereafter at
intervals not to exceed 300 flight cycles.
(h) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local
[[Page 7994]]
Flight Standards District Office, as appropriate. If sending
information directly to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.
(i) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0199, dated September 5,
2014, for related information. This MCAI may be found in the AD
docket on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2015-0084.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email [email protected];
Internet http://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on January 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-02535 Filed 2-12-15; 8:45 am]
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