[Federal Register Volume 79, Number 125 (Monday, June 30, 2014)]
[Proposed Rules]
[Pages 36666-36669]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-15254]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 /
Proposed Rules
[[Page 36666]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0425; Directorate Identifier 2013-NM-180-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 supersede Airworthiness Directive (AD) 2012-06-
19, for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -
302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model
A340-200 and -300 series airplanes. AD 2012-06-19 currently requires
repetitive inspections of the main fitting and sliding tube of the nose
landing gear (NLG) for defects, damage, and cracks; and corrective
actions if necessary. Since we issued AD 2012-06-19, we have determined
that additional airplanes are affected by the identified unsafe
condition. This proposed AD would add airplanes to the applicability.
This proposed AD would require an inspection of the part number and
serial number of the NLG main fitting and NLG sliding tube; for
affected parts, a magnetic particle inspection (MPI) for cracks, and
flap peening and replacement if necessary. This proposed AD would also
require, for certain parts, additional inspections for damage and
cracking. We are proposing this AD to detect and correct cracks,
defects, or damage of the main fitting or sliding tube, which could
result in consequent NLG collapse.
DATES: We must receive comments on this proposed AD by August 14, 2014.
ADDRESSES: You may send comments 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--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 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-2014-
0425; or in person at the Docket Operations office 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-2014-0425;
Directorate Identifier 2013-NM-180-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
On March 15, 2012, we issued AD 2012-06-19, Amendment 39-17000 (77
FR 22188, April 13, 2012). AD 2012-06-19 requires actions intended to
address an unsafe condition on certain Airbus Model A330-201, -202, -
203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -
343 airplanes; and Model A340-200 and -300 series airplanes.
Since we issued AD 2012-06-19, Amendment 39-17000 (77 FR 22188,
April 13, 2012), we have determined that additional airplanes are
affected by the identified unsafe condition.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0179, dated August 7, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -
341, -342, and -343 airplanes; and Model A340-200 and -300 series
airplanes. The MCAI states:
During the overhaul of two different Nose Landing Gear (NLG)
units, cracks were found on the main fitting of one and the sliding
tube of the other. Investigations concluded that the cracks
initiated as a result of residual stress in the parts, following
damage due to impact during towing incidents.
A subsequent review of the reported incidents identified a
specific group of NLG main fittings and sliding tubes that may have
sustained impact damage as a result of towing incidents.
This condition, if not detected and corrected could lead to NLG
collapse.
[[Page 36667]]
To address this potential unsafe condition, EASA issued AD 2010-
0034 [(http://ad.easa.europa.eu/blob/easa_ad_2010_0034_Corrected_superseded.pdf/AD_2010-0034_1) [which corresponds to
FAA AD 2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012)]
to require accomplishment of a one-time Magnetic Particles
Inspection (MPI), followed by repetitive Detailed Visual Inspections
(DVI) of the main fittings and sliding tubes of the affected NLG
units identified by Part Number (P/N) and Serial Number (S/N) in the
Applicability section of that AD and, depending on findings,
accomplishment of applicable corrective actions.
Since that [EASA] AD was issued, it has been found necessary to
address the issue at the level of NLG detail parts and no longer at
NLG assembly level, as some detail parts have been transferred from
an aeroplane to another. Airbus revised the applicable Service
Bulletins (SB), which now list the affected NLG main fittings and
sliding tubes.
For the reasons described above, this [EASA] AD retains
[certain] requirements of EASA AD 2010-0034 which is superseded and
requires [an inspection of the part number and serial number of the
NLG main fitting and NLG sliding tube, and for affected parts,] a
one-time MPI [for cracks], followed by repetitive DVI [for cracking,
damage to paint, sealant, cadmium, and base metal] of the affected
NLG main fittings and sliding tubes and, depending on inspection
results, accomplishment of corrective actions [e.g., flap peening
and replacing cracked parts]. This AD also extends the applicability
to A330 freighters.
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-2014-
0425.
Relevant Service Information
Airbus has issued Service Bulletin A330-32-3233, Revision 02, dated
January 27, 2014; and Service Bulletin A340-32-4275, Revision 01, dated
July 5, 2013. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
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 92 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
The actions that are required by AD 2012-06-19, Amendment 39-17000
(77 FR 22188, April 13, 2012), and retained in this proposed AD take
about 4 work-hours per product, at an average labor rate of $85 per
work-hour. Required parts cost about $0 per product. Based on these
figures, the estimated cost of the actions that are required by AD
2012-06-19 is $31,280 per product.
We also estimate that it would take about 10 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $0 per
product. Based on these figures, we estimate the cost of this proposed
AD on U.S. operators to be $78,200, or $850 per product.
In addition, we estimate that any necessary follow-on actions would
take about 114 work-hours and require parts costing $435,000, for a
cost of $444,690 per product. We have no way of determining the number
of aircraft that might need these actions.
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 proposed 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 removing Airworthiness Directive (AD)
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), and
adding the following new AD:
Airbus: Docket No. FAA-2014-0425; Directorate Identifier 2013-NM-
180-AD.
(a) Comments Due Date
We must receive comments by August 14, 2014.
(b) Affected ADs
This AD supersedes AD 2012-06-19, Amendment 39-17000 (77 FR
22188, April 13, 2012).
(c) Applicability
This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and
-313 airplanes; certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports of a cracked nose landing gear
(NLG) main fitting and sliding tube during overhaul of the NLGs
following damage due to impact during towing incidents. We are
issuing this AD to detect and correct cracks, defects, or damage of
the main fitting or sliding tube, which could result in consequent
NLG collapse.
[[Page 36668]]
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Detailed Inspection and Corrective Actions
This paragraph restates the requirements of paragraph (g) of AD
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012) with
revised service information. For Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes; and Model A340-211, -212, -213, -311, -312, and -313
airplanes; if fitted with the NLG identified in table 1 to paragraph
(g) of this AD: Within 900 flight hours after April 30, 2012 (the
effective date of AD 2012-06-19), do a detailed inspection of the
NLG main fitting and sliding tube for any cracks, defects, and
damage of the paint or surface protection, including paint removal
and cracking of the surface treatment. Before further flight after
doing the detailed inspection of the NLG, remove the labels, paint,
surface protection coatings, and cadmium from the NLG main fitting;
do a detailed inspection for any damage to the surface that will
impair the magnetic particle inspection (MPI); and, if any defects
are found, before further flight, remove any defects by polishing.
Do all actions specified in paragraph (g) of this AD in accordance
with the Accomplishment Instructions of the applicable service
information specified in paragraph (g)(1) or (g)(2) of this AD.
(1) For Model A330 airplanes: Airbus Mandatory Service Bulletin
A330-32-3233, dated October 22, 2009; or Airbus Service Bulletin
A330-32-3233, Revision 02, dated January 27, 2014.
(2) For Model A340 airplanes: Airbus Mandatory Service Bulletin
A340-32-4275, dated October 22, 2009; or Airbus Service Bulletin
A340-32-4275, Revision 01, dated July 5, 2013.
Table 1 to Paragraph (g) of This AD--Applicable NLG and Serial Numbers
------------------------------------------------------------------------
Part No. Serial No.
------------------------------------------------------------------------
D23285200.................................. B2
D23285101-7................................ B58
D23285101-10............................... B75
D23581100-1................................ B124
D23581100-1................................ B159
D23581100-7................................ B386
D23581100-7................................ B398
D23581100-7................................ B400
D23581100-7................................ B403
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(h) Retained Magnetic Particle Inspection
This paragraph restates the requirements of paragraph (h) of AD
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), with
revised service information. Before further flight after doing the
actions required in paragraph (g) of this AD: Do an MPI for cracking
of the NLG main fitting and sliding tube, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraph (g)(1) or (g)(2) of this AD.
(1) If no crack is detected during the MPI required by paragraph
(h) of this AD: Before further flight, flap peen the inspected area
where the paint and cadmium has been removed, and replace the
protective coatings, in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraph (g)(1) or (g)(2) of this AD.
(2) If any crack is detected during the MPI required by
paragraph (h) of this AD: Before further flight, replace the damaged
part with a new or serviceable part, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraph (g)(1) or (g)(2) of this AD.
(i) New Requirement of This AD: Identification
Within 1,000 flight hours after the effective date of this AD,
identify the part number and serial number of the NLG main fitting
and NLG sliding tube, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-32-3233, Revision 02,
dated January 27, 2014; or Airbus Service Bulletin A340-32-4275,
Revision 01, dated July 5, 2013; as applicable. A review of airplane
maintenance records is acceptable in lieu of this identification if
the part number and the serial number of the NLG main fitting and
NLG sliding tube can be conclusively determined from that review.
(j) New Requirement of This AD: MPI
If, during the identification required by paragraph (i) of this
AD, it is determined any NLG main fitting or NLG sliding tube is
installed and the fitting or tube has a part number and serial
number listed in Airbus Service Bulletin A330-32-3233, Revision 02,
dated January 27, 2014; or Airbus Service Bulletin A340-32-4275,
Revision 01, dated July 5, 2013; as applicable: Within 1,000 flight
hours after the effective date of this AD, do an MPI for cracks of
the affected parts, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-32-3233, Revision 02,
dated January 27, 2014; or Airbus Service Bulletin A340-32-4275,
Revision 01, dated July 5, 2013; as applicable. Accomplishing the
MPI required by this paragraph terminates the inspections required
by paragraphs (g) and (h) of this AD.
(1) If any crack is detected during the MPI required by
paragraph (j) of this AD, before further flight, replace any cracked
part (NLG main fitting and NLG sliding tube) with a serviceable one,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-32-3233, Revision 02, dated January 27, 2014; or
Airbus Service Bulletin A340-32-4275, Revision 01, dated July 5,
2013; as applicable.
(2) If no crack is detected during the MPI required by paragraph
(j) of this AD, before further flight, do a flap peening to
introduce compressive residual stress and corrosion protection, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-32-3233, Revision 02, dated January 27, 2014; or
Airbus Service Bulletin A340-32-4275, Revision 01, dated July 5,
2013; as applicable.
(k) New Requirement of This AD: Detailed Inspection
Within 900 flight hours after doing the flap peening required by
paragraph (j)(2) of this AD, do a detailed inspection for damage to
paint, damage to the sealant around the labels, damage to the
cadmium or base metal, and for cracking of the affected parts; in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-32-3233, Revision 02, dated January 27, 2014; or
Airbus Service Bulletin A340-32-4275, Revision 01, dated July 5,
2013; as applicable. Repeat the inspection thereafter at intervals
not to exceed 900 flight hours.
(1) If damage to the paint, damage to the sealant around the
labels, or damage to the cadmium or base metal, is detected during
any detailed inspection required by paragraph (k) of this AD, before
further flight, do an MPI for cracking of the affected parts, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-32-3233, Revision 02, dated January 27, 2014; or
Airbus Service Bulletin A340-32-4275, Revision 01, dated July 5,
2013; as applicable.
(2) If any cracking is detected during any inspection required
by paragraph (k) or (k)(1) of this AD, before further flight,
replace any cracked part with a serviceable part, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A330-32-
3233, Revision 02, dated January 27, 2014; or Airbus Service
Bulletin A340-32-4275, Revision 01, dated July 5, 2013; as
applicable.
(l) Terminating Action
Replacement of a part as required by paragraph (j)(1) or (k)(2)
of this AD is terminating action for the repetitive detailed
inspections required by paragraph (k) of this AD for that part,
provided that the part number and serial number of the replacement
part is not listed in Airbus Service Bulletin A330-32-3233, Revision
02, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275,
Revision 01, dated July 5, 2013; as applicable.
(m) Parts Installation Limitation
As of the effective date of this AD, installation of an NLG main
fitting or NLG sliding tube having a part number and serial number
listed in Airbus Service Bulletin A330-32-3233, Revision 02, dated
January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision
01, dated July 5, 2013; as applicable; is allowed, provided that the
NLG main fitting and NLG sliding tube has not accumulated more than
900 flight hours since the most recent inspection accomplished in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-32-3233, Revision 02, dated January 27, 2014; or
Airbus Service Bulletin A340-32-4275, Revision 01, dated July 5,
2013; as applicable.
(n) Credit for Previous Actions
This paragraph provides credit for inspections required by
paragraphs (j) and (k) of this AD and the flap peening required by
paragraph (j)(2) of this AD, if those actions were performed before
the effective date of
[[Page 36669]]
this AD using the service information specified in paragraph (n)(1),
(n)(2), or (n)(3) of this AD.
(1) Airbus Service Bulletin A330-32-3233, dated October 22,
2009.
(2) Airbus Service Bulletin A330-32-3233, Revision 01, dated
July 5, 2013.
(3) Airbus Service Bulletin A340-32-4275, dated October 22,
2009.
(o) 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 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) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or by the Design Approval Holder with a State of
Design Authority's design organization approval, as applicable). You
are required to ensure the product is airworthy before it is
returned to service.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0179, dated August 7, 2013, 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-
2014-0425.
(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 19, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-15254 Filed 6-27-14; 8:45 am]
BILLING CODE 4910-13-P