Airworthiness Directives; Airbus Airplanes, 91062-91066 [2016-28802]
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Federal Register / Vol. 81, No. 242 / Friday, December 16, 2016 / Proposed Rules
cabin floor beam junction at certain fuselage
frame locations. We are issuing this AD to
detect and correct cracking in the cabin floor
beam junction at certain fuselage frame
locations, which could result in reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
Before exceeding 36,900 total flight cycles
since first flight of the airplane, or within
2,100 flight cycles after the effective date of
this AD, whichever occurs later: Do a
detailed inspection for cracking of the frame
to cabin floor beam junction on the aft and
forward sides at frame (FR) 35.1 and FR 35.2
on the left-hand and right-hand sides, in
accordance with the Accomplishment
Instructions of the Airbus service information
specified in paragraphs (g)(1), (g)(2), (g)(3),
and (g)(4) of this AD. Repeat the inspection
of the frame to cabin floor beam junction on
the aft and forward sides at FR 35.1 and FR
35.2 on the left-hand and right-hand sides
thereafter at intervals not to exceed 15,300
flight cycles.
(1) Airbus Service Bulletin A320–53–1317,
dated December 15, 2015 (FR 35.1 right-hand
side).
(2) Airbus Service Bulletin A320–53–1318,
dated October 9, 2015 (FR 35.1 left-hand
side).
(3) Airbus Service Bulletin A320–53–1319,
dated October 9, 2015 (FR 35.2 right-hand
side).
(4) Airbus Service Bulletin A320–53–1320,
dated October 9, 2015 (FR 35.2 left-hand
side).
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(h) Repair
If any crack is found during any inspection
required by paragraph (g) of this AD: 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).
Although the service information specified in
paragraph (g) of this AD specifies to contact
Airbus for repair instructions, and specifies
that action as ‘‘RC’’ (Required for
Compliance), this AD requires repair as
specified in this paragraph. Repair of an
airplane as required by this paragraph does
not constitute terminating action for the
repetitive actions required by paragraph (g) of
this AD, unless specified otherwise in the
instructions provided by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA.
(i) 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
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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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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.
(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) Required for Compliance (RC): Except
as required by paragraph (h) of this AD: If
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0105, dated
June 6, 2016, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2016–9498.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://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
December 2, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–29676 Filed 12–15–16; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–8428; Directorate
Identifier 2014–NM–032–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposal to supersede Airworthiness
Directive (AD) 2011–17–09 for all
Airbus Model A330–200, –200
Freighter, and –300 series airplanes; and
AD 2012–25–12 for all Airbus Model
A330–200 and –300 series airplanes.
The notice of proposed rulemaking
(NPRM) proposed to require revising the
maintenance or inspection program, as
applicable, to incorporate new or
revised airworthiness limitation
requirements. The NPRM was prompted
by revisions to certain airworthiness
limitations items (ALI) documents,
which specify more restrictive
instructions and/or airworthiness
limitations. This action revises the
NPRM by proposing to require revising
the maintenance or inspection program,
as applicable, to incorporate more
restrictive, instructions and/or
airworthiness limitations that the
manufacturer has recently issued. We
are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this SNPRM by January 30, 2017.
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
https://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 SNPRM, contact
SUMMARY:
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Airbus service information identified in
this final rule, 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
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
For Messier-Bugatti-Dowty service
information identified in this SNPRM,
contact Messier-Bugatti USA, One
Carbon Way, Walton, KY 41094;
telephone 859–525–8583; fax 859–485
8827; email americascsc@
safranmbd.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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
8428; 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 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:
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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–2015–8428; Directorate Identifier
2014–NM–032–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 https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
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substantive verbal contact we receive
about this proposed AD.
Discussion
We issued an NPRM to amend 14 CFR
part 39 to supersede AD 2011–17–09,
Amendment 39–16773 (76 FR 53305,
August 26, 2011) (‘‘AD 2011–17–09’’);
and AD 2012–25–12, Amendment 39–
17293 (77 FR 75825, December 26,
2012) (‘‘AD 2012–25–12’’). AD 2011–
17–09 applies to all Airbus Model
A330–200 series airplanes, –200
Freighter, and –300 series airplanes. AD
2012–25–12 applies to all Airbus Model
A330–200 and –300 series airplanes.
The NPRM published in the Federal
Register on January 13, 2016 (81 FR
1570) (‘‘the NPRM’’). The NPRM was
prompted by revisions to certain
airworthiness limitations items (ALI)
documents, which specify more
restrictive instructions and/or
airworthiness limitations. The NPRM
proposed to require revising the
maintenance or inspection program, as
applicable, to incorporate new or
revised airworthiness limitation
requirements.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive, 2014–0009, dated January 8,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A330–200, –200 Freighter, and
–300 series airplanes; and Model A340–
200, –300, –500, and –600 series
airplanes. The MCAI states:
The airworthiness limitations for Airbus
aeroplanes are currently published in
Airworthiness Limitations Section (ALS)
documents.
The instructions and airworthiness
limitations applicable to the Safe Life
Airworthiness Limitation Items (SL ALI) are
given in Airbus A330 ALS Part 1 and A340
ALS Part 1, which are approved by EASA.
The revision 07 of Airbus A330 and A340
ALS Part 1 introduces more restrictive
instructions and/or airworthiness limitations.
Failure to comply with this revision could
result in an unsafe condition.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2012–0179, which is superseded, and
requires accomplishment of the actions
specified in Airbus A330 or A340 ALS Part
1 revision 07.
In addition, this [EASA] AD also
supersedes EASA AD 2011–0122–E and
EASA AD 2011–0212, whose requirements
have been transferred into Airbus A330 and
A340 ALS Part 1 revision 07.
The unsafe condition is fatigue
cracking, accidental damage, and
corrosion in certain principal structural
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elements, and possible failure of certain
life limited parts, which could result in
reduced structural integrity of the
airplane.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
8428.
Actions Since the NPRM Was Issued
Since we issued the NPRM, Airbus
has issued Airbus A330 ALS Part 1, Safe
Life Airworthiness Limitation Items
(SL–ALI), Revision 08, dated April 11,
2016, which specifies more restrictive
instructions and/or airworthiness
limitations.
Related Rulemaking
We are considering similar
rulemaking for Model A340–200, –300,
–500, and –600 series airplanes that
would revise the maintenance or
inspection program, as applicable, to
incorporate more restrictive instructions
and/or airworthiness limitations.
Currently, there are no U.S.-registered
Model A340 series airplanes.
Airworthiness Limitations Based on
Type Design
The FAA recently became aware of an
issue related to the applicability of ADs
that require incorporation of an ALS
revision into an operator’s maintenance
or inspection program.
Typically, when these types of ADs
are issued by civil aviation authorities
of other countries, they apply to all
airplanes covered under an identified
type certificate (TC). The corresponding
FAA AD typically retains applicability
to all of those airplanes.
In addition, U.S. operators must
operate their airplanes in an airworthy
condition, in accordance with 14 CFR
91.7(a). Included in this obligation is the
requirement to perform any
maintenance or inspections specified in
the ALS, and in accordance with the
ALS as specified in 14 CFR 43.16 and
91.403(c), unless an alternative has been
approved by the FAA.
When a TC is issued for a type design,
the specific ALS, including revisions, is
a part of that type design, as specified
in 14 CFR 21.31(c).
The sum effect of these operational
and maintenance requirements is an
obligation to comply with the ALS
defined in the type design referenced in
the manufacturer’s conformity
statement. This obligation may
introduce a conflict with an AD that
requires a specific ALS revision if new
airplanes are delivered with a later
revision as part of their type design.
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Federal Register / Vol. 81, No. 242 / Friday, December 16, 2016 / Proposed Rules
To address this conflict, the FAA has
approved alternative methods of
compliance (AMOCs) that allow
operators to incorporate the most recent
ALS revision into their maintenance/
inspection programs, in lieu of the ALS
revision required by the AD. This
eliminates the conflict and enables the
operator to comply with both the AD
and the type design.
However, compliance with AMOCs is
normally optional, and we recently
became aware that some operators
choose to retain the AD-mandated ALS
revision in their fleet-wide
maintenance/inspection programs,
including those for new airplanes
delivered with later ALS revisions, to
help standardize the maintenance of the
fleet. To ensure that operators comply
with the applicable ALS revision for
newly delivered airplanes containing a
later revision than that specified in an
AD, we plan to limit the applicability of
ADs that mandate ALS revisions to
those airplanes that are subject to an
earlier revision of the ALS, either as part
of the type design or as mandated by an
earlier AD.
This SNPRM therefore applies to
Model A330–200, –200 Freighter, and
–300 series airplanes with an original
certificate of airworthiness or original
export certificate of airworthiness that
was issued on or before the date of
approval of the ALS revision identified
in this SNPRM. Operators of airplanes
with an original certificate of
airworthiness or original export
certificate of airworthiness issued after
that date must comply with the
airworthiness limitations specified as
part of the approved type design and
referenced on the TC data sheet.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Related Service Information Under 1
CFR Part 51
Airbus has issued Airbus A330 ALS
Part 1, SL–ALI, Revision 08, dated April
11, 2016. Messier-Bugatti-Dowty has
issued Service Letter A33–34 A20,
Revision 7, including Appendices A
through F, dated July 20, 2012. This
service information describes Safe Life
Airworthiness Limitation Items SL–ALI
for the landing gear. This service
information is distinct since it was
issued by two different manufacturers
for different purposes.
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.
Comments
We gave the public the opportunity to
participate in developing this proposed
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AD. We considered the comments
received.
Request To Specify New Service
Information
Air France requested that we revise
paragraph (i) of the proposed AD to
include Messier-Bugatti-Dowty Service
Letter A33–34 A20, Revision 7,
including Appendices A through F,
dated July 20, 2012, as the required
service information.
We agree with the commenter’s
request. The changes in Messier-BugattiDowty Service Letter A33–34 A20,
Revision 7, including Appendices A
through F, dated July 20, 2012, do not
specify additional work. We have
revised paragraph (i) of this proposed
AD to specify using Messier-Dowty
Service Letter A33–34 A20, Revision 5,
including Appendices A through F,
dated July 31, 2009; or Messier-BugattiDowty Service Letter A33–34 A20,
Revision 7, including Appendices A
through F, dated July 20, 2012.
Requests To Specify Airbus A330
Variations
Air France requested that we revise
paragraph (k) of the proposed AD to list
all of the Airbus A330 variations to
Airbus A330 ALS Part 1, SL–ALS,
Revision 07, dated September 23, 2013,
applicable at the effective date of this
AD. Air France submitted a list of the
requested variations.
American Airlines (AAL) requested
that we add three Airbus A330
variations to paragraph (k) of the
proposed AD. AAL stated that the
NPRM does not include two variation
documents that AAL currently utilizes
as part of its approved maintenance
program.
We partially agree with the
commenters’ requests. Airbus has issued
A330 ALS Part 1, SL–ALI, Revision 08,
dated April 11, 2016. Therefore, the
variations for Airbus A330 ALS Part 1,
SL–ALI, Revision 07, dated September
23, 2013, are no longer applicable to this
SNPRM.
We have changed paragraph (k) of this
proposed AD to reference Airbus A330
ALS Part 1, SL–ALI, Revision 08, dated
April 11, 2016. We have also changed
paragraph (c) of this proposed AD to
reference the date of April 11, 2016, for
the certificate of airworthiness.
FAA’s Determination and Requirements
of This SNPRM
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
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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.
Certain changes described above
expand the scope of the NPRM. As a
result, we have determined that it is
necessary to reopen the comment period
to provide additional opportunity for
the public to comment on this SNPRM.
This SNPRM would require revisions
to certain operator maintenance
documents to include new actions (e.g.,
inspections). Compliance with these
actions is required by 14 CFR 91.403(c).
For airplanes that have been previously
modified, altered, or repaired in the
areas addressed by this SNPRM, the
operator may not be able to accomplish
the actions described in the revisions. In
this situation, to comply with 14 CFR
91.403(c), the operator must request
approval for an AMOC according to
paragraph (m)(1) of this proposed AD.
The request should include a
description of changes to the required
actions that will ensure the continued
damage tolerance of the affected
structure.
Costs of Compliance
We estimate that this SNPRM affects
82 airplanes of U.S. registry.
The actions that are required by AD
2011–17–09, and retained in this
SNPRM, take about 1 work-hour per
product, at an average labor rate of $85
per work-hour. Based on these figures,
the estimated cost of the actions that are
required by AD 2011–17–09 is $85 per
product.
The actions that are required by AD
2012–25–12, and retained in this
SNPRM, take about 16 work-hours per
product (2 main landing gear (MLG)
bogie beams per airplane), at an average
labor rate of $85 per work-hour.
Required parts cost about $255,000 per
MLG bogie beam. Based on these
figures, the estimated cost of the actions
that are required by AD 2012–25–12 is
up to $256,360 per MLG bogie beam.
We also estimate that it would take
about 1 work-hour per product to
comply with the basic requirements of
this SNPRM. The average labor rate is
$85 per work-hour. Based on these
figures, we estimate the cost of this
SNPRM on U.S. operators to be $6,970,
or $85 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,
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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
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2011–17–09, Amendment 39–16773 (76
■
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FR 53305, August 26, 2011); and AD
2012–25–12, Amendment 39–17293 (77
FR 75825, December 26, 2012); and
adding the following new AD:
Airbus: Docket No. FAA–2015–8428;
Directorate Identifier 2014–NM–032–AD.
(a) Comments Due Date
We must receive comments by January 30,
2017.
(b) Affected ADs
This AD replaces AD 2011–17–09,
Amendment 39–16773 (76 FR 53305, August
26, 2011) (‘‘AD 2011–17–09’’); and AD 2012–
25–12, Amendment 39–17293 (77 FR 75825,
December 26, 2012) (‘‘AD 2012–25–12’’).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1), (c)(2), and
(c)(3) of this AD, certificated in any category,
with an original certificate of airworthiness
or original export certificate of airworthiness
issued on or before April 11, 2016.
(1) Airbus Model A330–201, –202, –203,
–223, and –243 airplanes.
(2) Airbus Model A330–223F and –243F
airplanes.
(3) Airbus Model A330–301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 05, Periodic inspections.
(e) Reason
This AD was prompted by revisions to
certain airworthiness limitations items (ALI)
documents, which specify more restrictive
instructions and/or airworthiness limitations.
We are issuing this AD to detect and correct
fatigue cracking, accidental damage, or
corrosion in principal structural elements,
and possible failure of certain life limited
parts, which could result in reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Maintenance Program Revision,
With New Terminating Action
This paragraph restates the requirements of
paragraph (h) of AD 2011–17–09, with new
terminating action. Within 3 months after
September 30, 2011 (the effective date of AD
2011–17–09): Revise the maintenance
program by incorporating Airbus A330 ALS
Part 1, ‘‘Safe Life Airworthiness Limitation
Items (SL–ALI), Revision 05, dated July 29,
2010. Comply with all Airbus A330 ALS Part
1, SL–ALI, Revision 05, dated July 29, 2010,
at the times specified therein. Accomplishing
the actions specified in paragraph (k) of this
AD terminates the requirements of this
paragraph.
(h) Retained Limitation of No Alternative
Intervals or Limits, With No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2011–17–09, with no
changes. Except as provided by paragraph
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91065
(m) of this AD, after accomplishment of the
actions specified in paragraph (g) of this AD,
no alternatives to the maintenance tasks,
intervals, or limitations specified in
paragraph (g) of this AD may be used.
(i) Retained Bogie Beam Replacement, With
Specific Delegation Approval Language,
New Terminating Action, and New Service
Information
This paragraph restates the requirements of
paragraph (g) of AD 2012–25–12, with
specific delegation approval language and
terminating action and new service
information. For airplanes identified in
paragraphs (c)(1) and (c)(3) of this AD: At the
later of the times specified in paragraphs
(i)(1) and (i)(2) of this AD, replace all main
landing gear (MLG) bogie beams having part
number (P/N) 201485300, 201485301,
201272302, 201272304, 201272306, or
201272307, except those that have serial
number (S/N) S2A, S2B, or S2C, as identified
in Messier-Dowty Service Letter A33–34 A20,
Revision 5, including Appendices A through
F, dated July 31, 2009; or Messier-BugattiDowty Service Letter A33–34 A20, Revision
7, including Appendices A through F, dated
July 20, 2012; with a new or serviceable part,
using a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, or the European
Aviation Safety Agency (EASA) (or its
delegated agent). As of the effective date of
this AD, the applicable MLG bogie beams
specified in this paragraph must be replaced
using a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA Design Organization
Approval (DOA). Accomplishing the actions
specified in paragraph (k) of this AD
terminates the requirements of this
paragraph.
(1) At the applicable time specified in
paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of
this AD.
(i) For Model A330–201, –202, –203, –223,
–243 series airplanes, weight variant
(WV)02x, WV05x (except WV058), and
WV06x series: Before the accumulation of a
life limit of 50,000 landings or 72,300 total
flight hours, whichever occurs first from the
first installation of a MLG bogie beam on the
airplane.
(ii) For Model A330–201, –202, –203, –223,
–243 WV058 series airplanes: Before the
accumulation of a life limit of 50,000
landings or 57,900 total flight hours,
whichever occurs first from the first
installation of a MLG bogie beam on the
airplane.
(iii) For Model A330–301, –302, –303,
–321, –322, –323, –341, –342, –343 series
airplanes, WV00x, WV01x, WV02x, and
WV05x series: Before the accumulation of a
life limit of 46,000 landings or 75,000 total
flight hours, whichever occurs first from the
first installation of a MLG bogie beam on the
airplane.
(2) Within 6 months after January 30, 2013
(the effective date of AD 2012–25–12).
(j) Retained Parts Installation Limitation,
With New Terminating Action
This paragraph restates the requirements of
paragraph (h) of AD 2012–25–12, with new
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terminating action. For airplanes identified
in paragraphs (c)(1) and (c)(3) of this AD, as
of January 30, 2013 (the effective date of AD
2012–25–12), a MLG bogie beam having any
part number identified in paragraph (i) of this
AD may be installed on an airplane, provided
its life has not exceeded the life limit
specified in paragraphs (i)(1)(i), (i)(1)(ii), and
(i)(1)(iii) of this AD, and is replaced with a
new or serviceable part before reaching the
life limit specified in paragraphs (i)(1)(i),
(i)(1)(ii), and (i)(1)(iii) of this AD.
Accomplishing the actions specified in
paragraph (k) of this AD terminates the
requirements of this paragraph.
(k) New Maintenance or Inspection Program
Revision
Within 3 months after the effective date of
this AD: Revise the maintenance or
inspection program, as applicable, by
incorporating the information in Airbus A330
ALS Part 1, SL–ALI, Revision 08, dated April
11, 2016. The initial compliance times for the
actions specified in Airbus A330 ALS Part 1,
SL–ALI, Revision 08, dated April 11, 2016,
are at the times specified in Airbus A330
ALS Part 1, SL–ALI, Revision 08, dated April
11, 2016, or within 3 months after the
effective date of this AD, whichever occurs
later. Accomplishing the actions specified in
this paragraph terminates the requirements
specified in paragraphs (g) through (j) of this
AD.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(l) New Limitation of No Alternative Actions
or Intervals
After the maintenance or inspection
program, as applicable, has been revised, as
required by paragraph (k) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions or
intervals are approved as an AMOC in
accordance with the procedures specified in
paragraph (m)(1) of this AD.
(m) 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: 9-ANM-116AMOC-REQUESTS@faa.gov. 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: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
VerDate Sep<11>2014
18:25 Dec 15, 2016
Jkt 241001
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
this AD to address the unsafe condition
on these products.
We must receive comments on
this proposed AD by January 30, 2017.
DATES:
[Docket No. FAA–2016–9439; Directorate
Identifier 2016–NM–170–AD]
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
https://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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone: 562–797–1717;
Internet: https://
www.myboeingfleet.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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9439.
RIN 2120–AA64
Examining the AD Docket
(n) Related Information
(1) For Airbus 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 airworthiness.A330–
A340@airbus.com; Internet https://
www.airbus.com.
(2) For Messier-Bugatti-Dowty service
information identified in this AD, contact
Messier-Bugatti USA, One Carbon Way.
Walton, KY 41094; telephone 859–525–8583;
fax 859–485 8827; email americascsc@
safranmbd.com.
(3) 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
November 22, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–28802 Filed 12–15–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8
airplanes. This proposed AD was
prompted by a report indicating that
during an airplane inspection in
production, the variable frequency
starter generator (VFSG) power feeder
cables were found to contain terminal
lugs incorrectly installed common to
terminal blocks located in the wing
front spar. This proposed AD would
require a general visual inspection of
the wings, section 16, terminal lugs at
the terminal power block of the VFSG
power feeder cable for correct
installation and if required, applicable
corrective actions. We are proposing
SUMMARY:
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
ADDRESSES:
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9439; 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 Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Brendan Shanley, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–
917–6492; fax: 425–917–6590; email:
brendan.shanley@faa.gov.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\16DEP1.SGM
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]]>Agencies
[Federal Register Volume 81, Number 242 (Friday, December 16, 2016)]
[Proposed Rules]
[Pages 91062-91066]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-28802]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-8428; Directorate Identifier 2014-NM-032-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening
of comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposal to supersede Airworthiness
Directive (AD) 2011-17-09 for all Airbus Model A330-200, -200
Freighter, and -300 series airplanes; and AD 2012-25-12 for all Airbus
Model A330-200 and -300 series airplanes. The notice of proposed
rulemaking (NPRM) proposed to require revising the maintenance or
inspection program, as applicable, to incorporate new or revised
airworthiness limitation requirements. The NPRM was prompted by
revisions to certain airworthiness limitations items (ALI) documents,
which specify more restrictive instructions and/or airworthiness
limitations. This action revises the NPRM by proposing to require
revising the maintenance or inspection program, as applicable, to
incorporate more restrictive, instructions and/or airworthiness
limitations that the manufacturer has recently issued. We are proposing
this AD to address the unsafe condition on these products.
DATES: We must receive comments on this SNPRM by January 30, 2017.
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 https://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 SNPRM, contact
[[Page 91063]]
Airbus service information identified in this final rule, 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 airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com.
For Messier-Bugatti-Dowty service information identified in this
SNPRM, contact Messier-Bugatti USA, One Carbon Way, Walton, KY 41094;
telephone 859-525-8583; fax 859-485 8827; email
americascsc@safranmbd.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 https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8428; 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
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-2015-8428;
Directorate Identifier 2014-NM-032-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 https://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
We issued an NPRM to amend 14 CFR part 39 to supersede AD 2011-17-
09, Amendment 39-16773 (76 FR 53305, August 26, 2011) (``AD 2011-17-
09''); and AD 2012-25-12, Amendment 39-17293 (77 FR 75825, December 26,
2012) (``AD 2012-25-12''). AD 2011-17-09 applies to all Airbus Model
A330-200 series airplanes, -200 Freighter, and -300 series airplanes.
AD 2012-25-12 applies to all Airbus Model A330-200 and -300 series
airplanes. The NPRM published in the Federal Register on January 13,
2016 (81 FR 1570) (``the NPRM''). The NPRM was prompted by revisions to
certain airworthiness limitations items (ALI) documents, which specify
more restrictive instructions and/or airworthiness limitations. The
NPRM proposed to require revising the maintenance or inspection
program, as applicable, to incorporate new or revised airworthiness
limitation requirements.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive, 2014-0009, dated January 8, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200, -200 Freighter, and -300 series airplanes; and Model A340-
200, -300, -500, and -600 series airplanes. The MCAI states:
The airworthiness limitations for Airbus aeroplanes are
currently published in Airworthiness Limitations Section (ALS)
documents.
The instructions and airworthiness limitations applicable to the
Safe Life Airworthiness Limitation Items (SL ALI) are given in
Airbus A330 ALS Part 1 and A340 ALS Part 1, which are approved by
EASA.
The revision 07 of Airbus A330 and A340 ALS Part 1 introduces
more restrictive instructions and/or airworthiness limitations.
Failure to comply with this revision could result in an unsafe
condition.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2012-0179, which is superseded, and requires
accomplishment of the actions specified in Airbus A330 or A340 ALS
Part 1 revision 07.
In addition, this [EASA] AD also supersedes EASA AD 2011-0122-E
and EASA AD 2011-0212, whose requirements have been transferred into
Airbus A330 and A340 ALS Part 1 revision 07.
The unsafe condition is fatigue cracking, accidental damage, and
corrosion in certain principal structural elements, and possible
failure of certain life limited parts, which could result in reduced
structural integrity of the airplane.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8428.
Actions Since the NPRM Was Issued
Since we issued the NPRM, Airbus has issued Airbus A330 ALS Part 1,
Safe Life Airworthiness Limitation Items (SL-ALI), Revision 08, dated
April 11, 2016, which specifies more restrictive instructions and/or
airworthiness limitations.
Related Rulemaking
We are considering similar rulemaking for Model A340-200, -300, -
500, and -600 series airplanes that would revise the maintenance or
inspection program, as applicable, to incorporate more restrictive
instructions and/or airworthiness limitations. Currently, there are no
U.S.-registered Model A340 series airplanes.
Airworthiness Limitations Based on Type Design
The FAA recently became aware of an issue related to the
applicability of ADs that require incorporation of an ALS revision into
an operator's maintenance or inspection program.
Typically, when these types of ADs are issued by civil aviation
authorities of other countries, they apply to all airplanes covered
under an identified type certificate (TC). The corresponding FAA AD
typically retains applicability to all of those airplanes.
In addition, U.S. operators must operate their airplanes in an
airworthy condition, in accordance with 14 CFR 91.7(a). Included in
this obligation is the requirement to perform any maintenance or
inspections specified in the ALS, and in accordance with the ALS as
specified in 14 CFR 43.16 and 91.403(c), unless an alternative has been
approved by the FAA.
When a TC is issued for a type design, the specific ALS, including
revisions, is a part of that type design, as specified in 14 CFR
21.31(c).
The sum effect of these operational and maintenance requirements is
an obligation to comply with the ALS defined in the type design
referenced in the manufacturer's conformity statement. This obligation
may introduce a conflict with an AD that requires a specific ALS
revision if new airplanes are delivered with a later revision as part
of their type design.
[[Page 91064]]
To address this conflict, the FAA has approved alternative methods
of compliance (AMOCs) that allow operators to incorporate the most
recent ALS revision into their maintenance/inspection programs, in lieu
of the ALS revision required by the AD. This eliminates the conflict
and enables the operator to comply with both the AD and the type
design.
However, compliance with AMOCs is normally optional, and we
recently became aware that some operators choose to retain the AD-
mandated ALS revision in their fleet-wide maintenance/inspection
programs, including those for new airplanes delivered with later ALS
revisions, to help standardize the maintenance of the fleet. To ensure
that operators comply with the applicable ALS revision for newly
delivered airplanes containing a later revision than that specified in
an AD, we plan to limit the applicability of ADs that mandate ALS
revisions to those airplanes that are subject to an earlier revision of
the ALS, either as part of the type design or as mandated by an earlier
AD.
This SNPRM therefore applies to Model A330-200, -200 Freighter, and
-300 series airplanes with an original certificate of airworthiness or
original export certificate of airworthiness that was issued on or
before the date of approval of the ALS revision identified in this
SNPRM. Operators of airplanes with an original certificate of
airworthiness or original export certificate of airworthiness issued
after that date must comply with the airworthiness limitations
specified as part of the approved type design and referenced on the TC
data sheet.
Related Service Information Under 1 CFR Part 51
Airbus has issued Airbus A330 ALS Part 1, SL-ALI, Revision 08,
dated April 11, 2016. Messier-Bugatti-Dowty has issued Service Letter
A33-34 A20, Revision 7, including Appendices A through F, dated July
20, 2012. This service information describes Safe Life Airworthiness
Limitation Items SL-ALI for the landing gear. This service information
is distinct since it was issued by two different manufacturers for
different purposes.
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.
Comments
We gave the public the opportunity to participate in developing
this proposed AD. We considered the comments received.
Request To Specify New Service Information
Air France requested that we revise paragraph (i) of the proposed
AD to include Messier-Bugatti-Dowty Service Letter A33-34 A20, Revision
7, including Appendices A through F, dated July 20, 2012, as the
required service information.
We agree with the commenter's request. The changes in Messier-
Bugatti-Dowty Service Letter A33-34 A20, Revision 7, including
Appendices A through F, dated July 20, 2012, do not specify additional
work. We have revised paragraph (i) of this proposed AD to specify
using Messier-Dowty Service Letter A33-34 A20, Revision 5, including
Appendices A through F, dated July 31, 2009; or Messier-Bugatti-Dowty
Service Letter A33-34 A20, Revision 7, including Appendices A through
F, dated July 20, 2012.
Requests To Specify Airbus A330 Variations
Air France requested that we revise paragraph (k) of the proposed
AD to list all of the Airbus A330 variations to Airbus A330 ALS Part 1,
SL-ALS, Revision 07, dated September 23, 2013, applicable at the
effective date of this AD. Air France submitted a list of the requested
variations.
American Airlines (AAL) requested that we add three Airbus A330
variations to paragraph (k) of the proposed AD. AAL stated that the
NPRM does not include two variation documents that AAL currently
utilizes as part of its approved maintenance program.
We partially agree with the commenters' requests. Airbus has issued
A330 ALS Part 1, SL-ALI, Revision 08, dated April 11, 2016. Therefore,
the variations for Airbus A330 ALS Part 1, SL-ALI, Revision 07, dated
September 23, 2013, are no longer applicable to this SNPRM.
We have changed paragraph (k) of this proposed AD to reference
Airbus A330 ALS Part 1, SL-ALI, Revision 08, dated April 11, 2016. We
have also changed paragraph (c) of this proposed AD to reference the
date of April 11, 2016, for the certificate of airworthiness.
FAA's Determination and Requirements of This SNPRM
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.
Certain changes described above expand the scope of the NPRM. As a
result, we have determined that it is necessary to reopen the comment
period to provide additional opportunity for the public to comment on
this SNPRM.
This SNPRM would require revisions to certain operator maintenance
documents to include new actions (e.g., inspections). Compliance with
these actions is required by 14 CFR 91.403(c). For airplanes that have
been previously modified, altered, or repaired in the areas addressed
by this SNPRM, the operator may not be able to accomplish the actions
described in the revisions. In this situation, to comply with 14 CFR
91.403(c), the operator must request approval for an AMOC according to
paragraph (m)(1) of this proposed AD. The request should include a
description of changes to the required actions that will ensure the
continued damage tolerance of the affected structure.
Costs of Compliance
We estimate that this SNPRM affects 82 airplanes of U.S. registry.
The actions that are required by AD 2011-17-09, and retained in
this SNPRM, take about 1 work-hour per product, at an average labor
rate of $85 per work-hour. Based on these figures, the estimated cost
of the actions that are required by AD 2011-17-09 is $85 per product.
The actions that are required by AD 2012-25-12, and retained in
this SNPRM, take about 16 work-hours per product (2 main landing gear
(MLG) bogie beams per airplane), at an average labor rate of $85 per
work-hour. Required parts cost about $255,000 per MLG bogie beam. Based
on these figures, the estimated cost of the actions that are required
by AD 2012-25-12 is up to $256,360 per MLG bogie beam.
We also estimate that it would take about 1 work-hour per product
to comply with the basic requirements of this SNPRM. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this SNPRM on U.S. operators to be $6,970, or $85 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,
[[Page 91065]]
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 removing Airworthiness Directive (AD)
2011-17-09, Amendment 39-16773 (76 FR 53305, August 26, 2011); and AD
2012-25-12, Amendment 39-17293 (77 FR 75825, December 26, 2012); and
adding the following new AD:
Airbus: Docket No. FAA-2015-8428; Directorate Identifier 2014-NM-
032-AD.
(a) Comments Due Date
We must receive comments by January 30, 2017.
(b) Affected ADs
This AD replaces AD 2011-17-09, Amendment 39-16773 (76 FR 53305,
August 26, 2011) (``AD 2011-17-09''); and AD 2012-25-12, Amendment
39-17293 (77 FR 75825, December 26, 2012) (``AD 2012-25-12'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
with an original certificate of airworthiness or original export
certificate of airworthiness issued on or before April 11, 2016.
(1) Airbus Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Airbus Model A330-223F and -243F airplanes.
(3) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 05, Periodic
inspections.
(e) Reason
This AD was prompted by revisions to certain airworthiness
limitations items (ALI) documents, which specify more restrictive
instructions and/or airworthiness limitations. We are issuing this
AD to detect and correct fatigue cracking, accidental damage, or
corrosion in principal structural elements, and possible failure of
certain life limited parts, which could result in reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Maintenance Program Revision, With New Terminating Action
This paragraph restates the requirements of paragraph (h) of AD
2011-17-09, with new terminating action. Within 3 months after
September 30, 2011 (the effective date of AD 2011-17-09): Revise the
maintenance program by incorporating Airbus A330 ALS Part 1, ``Safe
Life Airworthiness Limitation Items (SL-ALI), Revision 05, dated
July 29, 2010. Comply with all Airbus A330 ALS Part 1, SL-ALI,
Revision 05, dated July 29, 2010, at the times specified therein.
Accomplishing the actions specified in paragraph (k) of this AD
terminates the requirements of this paragraph.
(h) Retained Limitation of No Alternative Intervals or Limits, With No
Changes
This paragraph restates the requirements of paragraph (i) of AD
2011-17-09, with no changes. Except as provided by paragraph (m) of
this AD, after accomplishment of the actions specified in paragraph
(g) of this AD, no alternatives to the maintenance tasks, intervals,
or limitations specified in paragraph (g) of this AD may be used.
(i) Retained Bogie Beam Replacement, With Specific Delegation Approval
Language, New Terminating Action, and New Service Information
This paragraph restates the requirements of paragraph (g) of AD
2012-25-12, with specific delegation approval language and
terminating action and new service information. For airplanes
identified in paragraphs (c)(1) and (c)(3) of this AD: At the later
of the times specified in paragraphs (i)(1) and (i)(2) of this AD,
replace all main landing gear (MLG) bogie beams having part number
(P/N) 201485300, 201485301, 201272302, 201272304, 201272306, or
201272307, except those that have serial number (S/N) S2A, S2B, or
S2C, as identified in Messier-Dowty Service Letter A33-34 A20,
Revision 5, including Appendices A through F, dated July 31, 2009;
or Messier-Bugatti-Dowty Service Letter A33-34 A20, Revision 7,
including Appendices A through F, dated July 20, 2012; with a new or
serviceable part, using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
or the European Aviation Safety Agency (EASA) (or its delegated
agent). As of the effective date of this AD, the applicable MLG
bogie beams specified in this paragraph must be replaced using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA
Design Organization Approval (DOA). Accomplishing the actions
specified in paragraph (k) of this AD terminates the requirements of
this paragraph.
(1) At the applicable time specified in paragraphs (i)(1)(i),
(i)(1)(ii), and (i)(1)(iii) of this AD.
(i) For Model A330-201, -202, -203, -223, -243 series airplanes,
weight variant (WV)02x, WV05x (except WV058), and WV06x series:
Before the accumulation of a life limit of 50,000 landings or 72,300
total flight hours, whichever occurs first from the first
installation of a MLG bogie beam on the airplane.
(ii) For Model A330-201, -202, -203, -223, -243 WV058 series
airplanes: Before the accumulation of a life limit of 50,000
landings or 57,900 total flight hours, whichever occurs first from
the first installation of a MLG bogie beam on the airplane.
(iii) For Model A330-301, -302, -303, -321, -322, -323, -341, -
342, -343 series airplanes, WV00x, WV01x, WV02x, and WV05x series:
Before the accumulation of a life limit of 46,000 landings or 75,000
total flight hours, whichever occurs first from the first
installation of a MLG bogie beam on the airplane.
(2) Within 6 months after January 30, 2013 (the effective date
of AD 2012-25-12).
(j) Retained Parts Installation Limitation, With New Terminating Action
This paragraph restates the requirements of paragraph (h) of AD
2012-25-12, with new
[[Page 91066]]
terminating action. For airplanes identified in paragraphs (c)(1)
and (c)(3) of this AD, as of January 30, 2013 (the effective date of
AD 2012-25-12), a MLG bogie beam having any part number identified
in paragraph (i) of this AD may be installed on an airplane,
provided its life has not exceeded the life limit specified in
paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD, and is
replaced with a new or serviceable part before reaching the life
limit specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii)
of this AD. Accomplishing the actions specified in paragraph (k) of
this AD terminates the requirements of this paragraph.
(k) New Maintenance or Inspection Program Revision
Within 3 months after the effective date of this AD: Revise the
maintenance or inspection program, as applicable, by incorporating
the information in Airbus A330 ALS Part 1, SL-ALI, Revision 08,
dated April 11, 2016. The initial compliance times for the actions
specified in Airbus A330 ALS Part 1, SL-ALI, Revision 08, dated
April 11, 2016, are at the times specified in Airbus A330 ALS Part
1, SL-ALI, Revision 08, dated April 11, 2016, or within 3 months
after the effective date of this AD, whichever occurs later.
Accomplishing the actions specified in this paragraph terminates the
requirements specified in paragraphs (g) through (j) of this AD.
(l) New Limitation of No Alternative Actions or Intervals
After the maintenance or inspection program, as applicable, has
been revised, as required by paragraph (k) of this AD, no
alternative actions (e.g., inspections) or intervals may be used
unless the actions or intervals are approved as an AMOC in
accordance with the procedures specified in paragraph (m)(1) of this
AD.
(m) 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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: As of the effective date of
this AD, 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 the EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(n) Related Information
(1) For Airbus 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 airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(2) For Messier-Bugatti-Dowty service information identified in
this AD, contact Messier-Bugatti USA, One Carbon Way. Walton, KY
41094; telephone 859-525-8583; fax 859-485 8827; email
americascsc@safranmbd.com.
(3) 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 November 22, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-28802 Filed 12-15-16; 8:45 am]
BILLING CODE 4910-13-P
