[Federal Register Volume 80, Number 114 (Monday, June 15, 2015)]
[Proposed Rules]
[Pages 34098-34101]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-14229]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-1981; Directorate Identifier 2014-NM-204-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 A330-200 Freighter, A330-200, A330-300, A340-200,
and A340-300 series airplanes. This proposed AD was prompted by reports
that the inner bore of some main landing gear (MLG) unit bogie beams
were insufficiently re-protected against corrosion after inspection or
maintenance actions were accomplished. This proposed AD would require,
for certain MLG units, determining which revision of the component
maintenance manual (CMM) was used to accomplish the most recent MLG
unit overhaul; a detailed inspection for missing or damaged paint, and
if necessary, a detailed inspection of the cadmium plating for
discrepancies, measurement of the depth of the cadmium plating, a
general visual inspection of the base metal for corrosion or damage, a
detailed inspection of repaired areas for cracking or corrosion; and
corrective actions if necessary. We are proposing this AD to detect and
correct corrosion in the bore of each MLG unit bogie beam, which could
result in collapse of a MLG unit, and subsequent damage to the airplane
and injury to occupants.
DATES: We must receive comments on this proposed AD by July 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 Airbus service information identified in this proposed AD,
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 45 80; email [email protected]; Internet
http://www.airbus.com. For Messier-Dowty service information contact
Messier-Dowty Limited, Cheltenham Road, Cloucester, GL2 9QH, England;
telephone +44(0) 1452 712424; fax+ 44(0) 1452 713821; Internet http://www.messier-dowtycom). 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-
1981; 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: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM 116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
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-2015-1981;
Directorate Identifier
[[Page 34099]]
2014-NM-204-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 2014-0222, dated October 6, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330-200 Freighter, A330-200, A330-300, A340-200, and A340-300 series
airplanes. The MCAI states:
From in-service experience, it was found that the inner bore of
some bogie beams had been insufficiently re-protected against
corrosion after inspection and/or possible maintenance actions
accomplished in this area (absence of corrosion inhibitor and damage
to paint have been found in some specific areas).
This condition, if not detected and corrected, could lead to
corrosion on the bore of the bogie beam, potentially resulting in
Main Landing Gear (MLG) collapse, ultimately resulting in damage to
the aeroplane and injury to the occupants.
To address this potential unsafe condition, Airbus issued Alert
Operators Transmission (AOT) A32L004-14, providing inspection
instructions for some aeroplane configurations.
For the reasons described above, this [EASA] AD requires
identification of the MLG units that are possibly affected, [a
detailed] inspection [for missing or damaged paint] of the MLG Bogie
Beam bore and, depending on findings, accomplishment of the
applicable corrective actions.
This [EASA] AD also prohibits the installation of MLG units that
have been overhauled by using instructions from an earlier
Components Maintenance Manual (CMM) revision.
Required actions also include a detailed inspection of the cadmium
plating for discrepancies (gray in color), measurement of the depth of
the cadmium plating if necessary, and a general visual inspection of
the base metal for corrosion or damage, and a detailed inspection of
repaired areas for cracking or corrosion. Corrective actions include
removing cadmium plating and repairing any cracked, corroded, or
damaged areas; re-applying cadmium plating and paint; and re-applying
temporary corrosion protection to the bores of the MLG bogie beams.
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-
1981.
Related Service Information Under 1 CFR Part 51
Airbus has issued Alert Operators Transmission A32L004-14, dated
July 28, 2014, including Appendices 1, 2, 3, and 4, which are not
dated. This service information describes procedures for inspections of
the bogie beam bore of the MLG.
Messier-Dowty has issued the following service information, which
describes procedures for inspections of the internal diameter of the
bogie beam for corrosion.
Service Bulletin A33/34-32-272, including Appendices A, B,
C, and D, dated November 16, 2007.
Service Bulletin A33/34-32-272, Revision 1, including
Appendices A, B, C, and D, dated September 22, 2008.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section of this
NPRM.
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 these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 89 airplanes of U.S.
registry.
We also estimate that it would take about 12 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 $90,780, or $1,020
per product.
We have received no definitive data that would enable us to provide
cost estimates for any necessary follow-on actions.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed AD has
been detailed in the Costs of Compliance section of this document and
includes time for reviewing instructions, as well as completing and
reviewing the collection of information. Therefore, all reporting
associated with this proposed AD is mandatory. Comments concerning the
accuracy of this burden and suggestions for reducing the burden should
be directed to the FAA at 800 Independence Ave. SW., Washington, DC
20591, ATTN: Information Collection Clearance Officer, AES-200.
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;
[[Page 34100]]
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-2015-1981; Directorate Identifier 2014-NM-
204-AD.
(a) Comments Due Date
We must receive comments by July 30, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A330-201, A330-202, A330-203, A330-223, A330-223F,
A330-243, A330-243F, A330-301, A330-302, A330-303, A330-321, A330-
322, A330-323, A330-341, A330-342, and A330-343 airplanes; all
manufacturer serial numbers; except those on which Airbus
Modification 58896 has been embodied in production or embodied
through Airbus Service Bulletin A330-32-3237.
(2) Model A340-211, A340-212, A340-213, A340-311, A340-312, and
A340-313 airplanes; all manufacturer serial numbers; except those on
which Airbus Modification 58896 has been embodied in production or
embodied through Airbus Service Bulletin A340-32-4279.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports that the inner bore of some main
landing gear (MLG) unit bogie beams were insufficiently re-protected
against corrosion after inspection or maintenance actions were
accomplished. We are issuing this AD to detect and correct corrosion
in the bore of each MLG unit bogie beam, which could result in
collapse of a MLG unit, and subsequent damage to the airplane and
injury to occupants.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Identification of Affected MLG Units
Within 12 months after the effective date of this AD: For MLG
units having a 201252 series or 201490 series part number, determine
the revision of the Airbus component maintenance manual (CMM) used
to do the most recent MLG unit overhaul. If it is determined that
the Airbus CMM revision specified in paragraph (g)(1) or (g)(2) of
this AD was used to accomplish the most recent MLG unit overhaul:
Within 12 months after the effective date of this AD, clean the area
between the bogie pivot pin and the bogie beam bore of each MLG unit
and do a detailed inspection for missing or damaged paint, in
accordance with the instructions of Airbus Alert Operators
Transmission A32L004-14 dated July 28, 2014.
(1) For MLG units having a part number in the 201252 series:
Airbus CMM 32-11-74, Revision 25 or earlier.
(2) For MLG units having a part number in the 201490 series:
Airbus CMM 32-12-05, Revision 20 or earlier.
(h) Inspection of Cadmium Plating
If, during the inspection required by paragraph (g) of this AD,
any missing or damaged paint is found: Before further flight, do a
detailed inspection of the cadmium plating for discrepancies,
measure the depth of the plating as applicable, and do a general
visual inspection of the base metal for corrosion or damage. If any
discrepancy, damage, or corrosion is found, before further flight,
do all applicable corrective actions, and do a detailed inspection
of repaired areas for cracking or corrosion, in accordance with
Airbus Alert Operators Transmission A32L004-14, dated July 28, 2014,
except where Airbus Alert Operators Transmission A32L004-14, dated
July 28, 2014, specifies to contact Messier-Dowty if cracking or
corrosion is found in a repaired area, before further flight, 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).
(i) Reporting Requirement
At the applicable time specified in paragraph (i)(1) or (i)(2)
of this AD, report the findings of the inspection required by
paragraph (g) of this AD to Airbus, Customer Services Engineering--
SEEL1, Attn: Philippe Kerangueven, Product Leader A330/A340, ATA-32,
Landing Gear Systems, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; phone +33 (0) 5 67 19 18 42; fax +33 0 5 67 19 12-05;
email [email protected]. The report must include the
information specified in Appendix 2 of Airbus Alert Operators
Transmission A32L004-14, dated July 28, 2014.
(1) If the inspection was done on or after the effective date of
this AD: Within 90 days after that inspection.
(2) If the inspection was done before the effective date of this
AD: Within 90 days after the effective date of this AD.
(j) Optional Method of Compliance
Accomplishment of the boroscope inspection of the internal
diameter of the bogie beam for corrosion or damage to the protective
treatments, measurement of the depth of the protective treatments as
applicable, and accomplishment of all applicable corrective actions,
in accordance with the Accomplishment Instructions of Messier-Dowty
Service Bulletin A33/34-32-272, dated November 16, 2007; or Revision
1, including Appendices A, B, C, and D, dated September 22, 2008;
are acceptable for the corresponding actions required by paragraphs
(g) and (h) of this AD for that MLG unit, provided the actions in
the Messier-Dowty Service Bulletins identified in paragraphs (j)(1)
through (j)(5) of this AD have not been accomplished on that MLG
unit. Where Messier-Dowty Service Bulletin A33/34-32-272, dated
November 16, 2007; or Revision 1, including Appendices A, B, C, and
D, dated September 22, 2008; specify to contact Messier-Dowty for
repair information, the repair 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.
(1) Messier-Dowty Service Bulletin A33/34-32-285, dated July 9,
2010.
(2) Messier-Dowty Service Bulletin A33/34-32-285, Revision 1,
dated October 4, 2011.
(3) Messier-Dowty Service Bulletin A33/34-32-285, Revision 2,
dated October 4, 2012.
(4) Messier-Dowty Service Bulletin A33/34-32-285, Revision 3,
dated September 11, 2013.
(5) Messier-Dowty Service Bulletin A33/34-32-285, Revision 4,
dated January 23, 2014.
Note 1 to paragraph (j) of this AD: Inspections done using the
instructions in Messier-Dowty Service Bulletin A33/34-32-285,
Revision 5, dated August 14, 2014, do not affect the optional method
of compliance provided by this paragraph.
(k) Parts Installation Limitation
As of the effective date of this AD, any overhauled MLG unit
having a 201252 series or 201490 series part number may be installed
on an airplane, provided the most recent MLG overhaul was done using
an Airbus CMM that is not specified in paragraph (g)(1) or (g)(2) of
this AD, or, prior to installation, the MLG unit passes the
inspection required by paragraph (g) of this AD.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International
[[Page 34101]]
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 Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; 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.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0222, dated October 6,
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-2015-1981.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; 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 June 3, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-14229 Filed 6-12-15; 8:45 am]
BILLING CODE 4910-13-P