Airworthiness Directives; Airbus Airplanes, 24035-24039 [2017-10266]
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Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations
that is likely to exist or develop on
products identified in this rulemaking
action.
(d) Subject
Joint Aircraft System Component (JASC)
7230, Turbine Engine Compressor Section.
Regulatory Findings
(e) Reason
This AD was prompted by CICs that were
weld repaired and have a higher probability
of cracking due to increased residual stresses
as a result of the weld repair process. We are
issuing this AD to prevent CIC failure, engine
separation and loss of the airplane.
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
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 AD:
(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 to the extent that it justifies
making a regulatory distinction, 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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–10–06 Rolls-Royce plc: Amendment
39–18880; Docket No. FAA–2017–0114;
Directorate Identifier 2017–NE–03–AD.
(a) Effective Date
This AD is effective June 9, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Rolls-Royce plc (RR)
RB211 Trent 768–60, RB211 Trent 772–60,
and RB211 Trent 772B–60 turbofan engines
that have a compressor intermediate case
(CIC) that was repaired using RR Repair
FRSC005.
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(g) Required Actions
(1) Inspect repaired CICs during the next
shop visit, or within 6,000 engine flight
cycles, whichever occurs first, after the
effective date of this AD, using paragraph
3.B.(1)(c) of the Accomplishment
Instructions, of RR Alert Non-Modification
Service Bulletin (NMSB) RB.211–72–AH976,
Revision 2, dated March 16, 2017.
(2) If a CIC fails inspection required by
paragraph (g)(1) of this AD, either repair the
CIC using paragraph 3.B.(2)(b) of the
Accomplishment Instructions, of RR Alert
NMSB RB.211–72–AH976, Revision 2, dated
March 16, 2017, or, replace the CIC with a
part eligible for installation, before next
flight.
(h) Definitions
For the purpose of this AD, a shop visit is
the induction of an engine into the shop for
maintenance or overhaul that requires the
separation of major mating engine module
flanges. The separation of engine flanges
solely for the purpose of transporting the
engine without subsequent engine
maintenance does not constitute an engine
shop visit.
(i) Installation Prohibition
After the effective date of this AD, do not
install an affected intermediate module on an
engine unless the CIC has passed the
inspection required by paragraph (g)(1) of
this AD.
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(j) Credit for Previous Actions
You may take credit for the inspections
and corrective action required by paragraph
(g) of this AD, if you performed these actions
before the effective date of this AD using RR
Alert NMSB RB.211–72–AH976, original
issue, dated November 3, 2016 or RR Alert
NMSB RB.211–72–AH976, Revision 1, dated
November 17, 2016.
(k) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use
the procedures found in 14 CFR 39.19 to
make your request. You may email your
request to: ANE-AD-AMOC@faa.gov.
(l) Related Information
(1) For more information about this AD,
contact Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
PO 00000
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24035
7754; fax: 781–238–7199; email:
Robert.Green@faa.gov.
(2) Refer to MCAI European Aviation
Safety Agency (EASA), AD 2017–0071, dated
April 26, 2017, for more information. You
may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov by
searching for and locating it in Docket No.
FAA–2017–0114.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Rolls-Royce plc Alert Non-Modification
Service Bulletin RB.211–72–AH976, Revision
2, dated March 16, 2017.
(ii) Reserved.
(3) For Rolls-Royce plc service information
identified in this AD, contact Rolls-Royce
plc, Corporate Communications, P.O. Box 31,
Derby, England, DE24 8BJ; phone: 011–44–
1332–242424; fax: 011–44–1332–249936;
email: https://www.rolls-royce.com/contact/
civil_team.jsp; Internet: https://
customers.rolls-royce.com/public/
rollsroycecare.
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call 781–238–7125.
(5) You may view this service information
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
May 4, 2017.
Robert J. Ganley,
Acting Assistant Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10438 Filed 5–24–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–8428; Directorate
Identifier 2014–NM–032–AD; Amendment
39–18898; AD 2017–10–24]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2011–17–
SUMMARY:
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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. AD
2011–17–09 required revisions to
certain operator maintenance
documents to include new inspections.
AD 2012–25–12 required replacing
certain main landing gear (MLG) bogie
beams before reaching new reduced life
limits. This new AD requires revising
the maintenance or inspection program,
as applicable, to incorporate new, more
restrictive, or revised instructions and/
or airworthiness limitation
requirements. This AD was prompted by
revisions to certain airworthiness
limitation item (ALI) documents, which
specify more restrictive instructions
and/or airworthiness limitations. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective June 29,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 29, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of January 30, 2013 (77 FR
75825, December 26, 2012).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of September 30, 2011 (76 FR
53305, August 26, 2011).
ADDRESSES: For 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.A330A340@airbus.com; Internet https://
www.airbus.com.
For Messier-Bugatti-Dowty service
information identified in this final rule,
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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
8428.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
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:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) 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 applied to all
Airbus Model A330–200, –200
Freighter, and –300 series airplanes. AD
2012–25–12 applied to all Airbus Model
A330–200 and –300 series airplanes.
The SNPRM published in the Federal
Register on December 16, 2016 (81 FR
91062). We preceded the SNPRM with
a notice of proposed rulemaking
(NPRM) that published in the Federal
Register on January 13, 2016 (81 FR
1570). The NPRM was prompted by a
determination that more restrictive
instructions and/or airworthiness
limitations should be incorporated into
the maintenance or inspection program,
as applicable. The NPRM proposed to
require revising the maintenance or
inspection program, as applicable, to
incorporate new or revised
airworthiness limitation requirements.
The SNPRM proposed 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 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.
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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, or
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.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the SNPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
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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 Appendixes A
through F, dated July 20, 2012. This
service information describes 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.
Costs of Compliance
We estimate that this AD affects 82
airplanes of U.S. registry.
The actions that are required by AD
2011–17–09, and retained in this AD,
take about 1 work-hour per product, at
an average labor rate of $85 per workhour. 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 AD,
take about 16 work-hours, at an average
labor rate of $85 per work-hour, with
required parts cost of 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 AD. The average labor rate is $85
per work-hour. Based on these figures,
we estimate the cost of this AD on U.S.
operators to be $6,970, or $85 per
product.
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 AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government. For the reasons
discussed above, I certify that this AD:
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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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.
Authority for This Rulemaking
§ 39.13
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
■
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[Amended]
2.The FAA amends § 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:
2017–10–24 Airbus: Amendment 39–18898;
Docket No. FAA–2015–8428; Directorate
Identifier 2014–NM–032–AD.
(a) Effective Date
This AD is effective June 29, 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’’).
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24037
(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 limitation item
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
Airworthiness Limitations Section (ALS) Part
1, Safe Life Airworthiness Limitation Items
(SL–ALI), Revision 05, dated July 29, 2010.
Comply with all ALIs in 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 Additional
Exception
This paragraph restates the requirements of
paragraph (i) of AD 2011–17–09, with
additional exception. Except as provided by
paragraphs (k) and (m)(1) 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
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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 Appendixes A through
F, dated July 31, 2009; or Messier-BugattiDowty Service Letter A33–34 A20, Revision
7, including Appendixes 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 Airbus’s
EASA Design Organization Approval (DOA).
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
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
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 it 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.
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(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 alternative
method of compliance (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 manager of the International Branch,
send it to the attention of the person
identified in paragraph (n)(2) of this AD.
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: 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
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0009, dated
January 8, 2014, 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–
2015–8428.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
PO 00000
Frm 00040
Fmt 4700
Sfmt 4700
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.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on June 29, 2017.
(i) Airbus A330 Airworthiness Limitations
Section Part 1, Safe Life Airworthiness
Limitation Items, Revision 08, dated April
11, 2016.
(ii) Messier-Bugatti-Dowty Service Letter
A33–34 A20, Revision 7, including
Appendixes A through F, dated July 20,
2012.
(4) The following service information was
approved for IBR on January 30, 2013 (77 FR
75825, December 26, 2012).
(i) Messier-Dowty Service Letter A33–34
A20, Revision 5, including Appendixes A
through F, dated July 31, 2009.
(ii) Reserved.
(5) The following service information was
approved for IBR on September 30, 2011 (76
FR 53305, August 26, 2011).
(i) Airbus A330 Airworthiness Limitations
Section, Part 1, Safe Life Airworthiness
Limitation Items, Revision 05, dated July 29,
2010. The revision level of this document is
indicated only on the title page and in the
Record of Revisions; the revision date of this
document is not indicated on the title page
of this document.
(ii) Reserved.
(6) 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.A330A340@airbus.com; Internet https://
www.airbus.com.
(7) 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.
(8) 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.
(9) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
E:\FR\FM\25MYR1.SGM
25MYR1
Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations
Issued in Renton, Washington, on May 10,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10266 Filed 5–24–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–8849; Directorate
Identifier 2015–NM–174–AD; Amendment
39–18892; AD 2017–10–18]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A330–223F, –223, –321,
–322, and –323 airplanes. This AD was
prompted by fatigue load analysis that
determined the need for reduced
inspection intervals and updated torque
values of the bolts. This AD requires
repetitive torque checks of the forward
engine mount bolts, an inspection of the
forward mount assembly, and
replacement of the bolts or repair of the
forward mount assembly as necessary.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective June 29,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 29, 2017.
ADDRESSES: For 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. 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–2016–8849.
SUMMARY:
VerDate Sep<11>2014
15:57 May 24, 2017
Jkt 241001
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–2016–
8849; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A330–223F,
–223, –321, –322, and –323 airplanes.
The NPRM published in the Federal
Register on August 30, 2016 (81 FR
59535). The NPRM was prompted by
fatigue load analysis that determined
the need for reduced inspection
intervals (for torque checks required by
AD 2013–14–04, Amendment 39–17509
(78 FR 68352, November 14, 2013) (‘‘AD
2013–14–04’’)) and updated torque
values of the bolts. The NPRM proposed
to require repetitive torque checks to
determine if there are any loose or
broken forward engine mount bolts,
and, if necessary, replacement of all four
forward engine mount bolts and
associated nuts, inspection of the
forward mount assembly, and repair.
We are issuing this AD to detect and
correct loose and broken bolts, which
could lead to engine detachment in
flight and damage to the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2015–0214,
dated October 19, 2015 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A330–223F, –223,
–321, –322, and –323 airplanes. The
MCAI states:
The forward mount engine pylon bolts,
Part Number (P/N) 51U615, fitted on Airbus
PO 00000
Frm 00041
Fmt 4700
Sfmt 4700
24039
A330 aeroplanes with Pratt & Whitney (PW)
PW4000 engines, are made from MP159
material. Analysis made by PW identified
that MP159 material pylon bolts do not meet
the full life cycle torque check interval
requirement, in a bolt-out condition.
Consequently, PW issued Alert Service
Bulletin (ASB) PW4G–100–A71–32, and the
U.S. Federal Aviation Administration (FAA),
as Engine Certification Authority, issued
FAA AD 2006–16–05 [Amendment 39–14705
(71 FR 44185, August 4, 2006) (‘‘AD 2006–
16–05’’)] to require repetitive torque checks
of MP159 material forward mount pylon
bolts fitted on certain PW4000 series engines.
However, the engine mount system is
considered to be part of aeroplane
certification rather than the engine
certification. Following further fatigue load
analysis by Airbus of the A330 engine mount
system, it was determined that the torque
check interval for MP159 material forward
mount pylon bolts, as required by FAA AD
2006–16–05 (2,700 flight cycles (FC)),
provided an insufficient level of safety for
Airbus A330 aeroplanes.
This condition, if not detected and
corrected, could ultimately lead to
detachment of the engine from the aeroplane,
possibly resulting in damage to the aeroplane
and/or injury to persons on the ground.
Consequently, EASA issued AD 2012–0094
[which corresponds to FAA AD 2013–14–04]
to require accomplishment of repetitive
torque checks of the forward mount pylon
bolts installed on affected A330 aeroplanes
and, depending on findings, replacement of
all four bolts and associated nuts, in
accordance with PW ASB PW4G–100–A71–
32 Revision 01 and Airbus Service Bulletin
(SB) A330–71–3028.
Since that AD was issued, it has been
concluded that a new torque value must be
applied.
Consequently, Airbus issued SB A330–71–
3028 Revision 02 and PW issued ASB
PW4G–100–A71–32 Revision 02 to update
the torque value. Additional forward mount
inspections are also provided in case of one
or more forward engine mount bolts is found
loose, broken or missing.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2012–0094, which is superseded,
introduces a new torque value, and requires
additional inspections and, depending on
findings, corrective action(s).
Corrective actions include repetitive
torque checks to determine if there are
any loose or broken forward engine
mount bolts on both engines, and, if
necessary, replacement of all four
forward engine mount bolts and
associated nuts, inspection of the
forward mount assembly, and repair.
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–2016–
8849.
Comments
We gave the public the opportunity to
participate in developing this AD. The
E:\FR\FM\25MYR1.SGM
25MYR1
]]>Agencies
[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)]
[Rules and Regulations]
[Pages 24035-24039]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10266]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-8428; Directorate Identifier 2014-NM-032-AD;
Amendment 39-18898; AD 2017-10-24]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2011-17-
[[Page 24036]]
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. AD 2011-17-09 required revisions to certain operator
maintenance documents to include new inspections. AD 2012-25-12
required replacing certain main landing gear (MLG) bogie beams before
reaching new reduced life limits. This new AD requires revising the
maintenance or inspection program, as applicable, to incorporate new,
more restrictive, or revised instructions and/or airworthiness
limitation requirements. This AD was prompted by revisions to certain
airworthiness limitation item (ALI) documents, which specify more
restrictive instructions and/or airworthiness limitations. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective June 29, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 29,
2017.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
January 30, 2013 (77 FR 75825, December 26, 2012).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
September 30, 2011 (76 FR 53305, August 26, 2011).
ADDRESSES: For 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
final rule, 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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8428.
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 AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
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:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) 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 applied to all Airbus Model A330-200, -200
Freighter, and -300 series airplanes. AD 2012-25-12 applied to all
Airbus Model A330-200 and -300 series airplanes. The SNPRM published in
the Federal Register on December 16, 2016 (81 FR 91062). We preceded
the SNPRM with a notice of proposed rulemaking (NPRM) that published in
the Federal Register on January 13, 2016 (81 FR 1570). The NPRM was
prompted by a determination that more restrictive instructions and/or
airworthiness limitations should be incorporated into the maintenance
or inspection program, as applicable. The NPRM proposed to require
revising the maintenance or inspection program, as applicable, to
incorporate new or revised airworthiness limitation requirements. The
SNPRM proposed 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 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.
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, or
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.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the SNPRM or on the determination
of the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
[[Page 24037]]
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 Appendixes A through F, dated July
20, 2012. This service information describes 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.
Costs of Compliance
We estimate that this AD affects 82 airplanes of U.S. registry.
The actions that are required by AD 2011-17-09, and retained in
this AD, 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 AD, take about 16 work-hours, at an average labor rate of $85 per
work-hour, with required parts cost of 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 AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD 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, 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. For the
reasons discussed above, I certify that this AD:
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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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:
2017-10-24 Airbus: Amendment 39-18898; Docket No. FAA-2015-8428;
Directorate Identifier 2014-NM-032-AD.
(a) Effective Date
This AD is effective June 29, 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
limitation item 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 Airworthiness
Limitations Section (ALS) Part 1, Safe Life Airworthiness Limitation
Items (SL-ALI), Revision 05, dated July 29, 2010. Comply with all
ALIs in 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
Additional Exception
This paragraph restates the requirements of paragraph (i) of AD
2011-17-09, with additional exception. Except as provided by
paragraphs (k) and (m)(1) 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
[[Page 24038]]
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 Appendixes A through F, dated July 31, 2009;
or Messier-Bugatti-Dowty Service Letter A33-34 A20, Revision 7,
including Appendixes 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 Airbus's EASA
Design Organization Approval (DOA). 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 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 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 it 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 alternative
method of compliance (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 manager of the International Branch, send it to the
attention of the person identified in paragraph (n)(2) of this AD.
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.
(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 EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0009, dated January 8,
2014, 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-2015-8428.
(2) For more information about this AD, 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.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
June 29, 2017.
(i) Airbus A330 Airworthiness Limitations Section Part 1, Safe
Life Airworthiness Limitation Items, Revision 08, dated April 11,
2016.
(ii) Messier-Bugatti-Dowty Service Letter A33-34 A20, Revision
7, including Appendixes A through F, dated July 20, 2012.
(4) The following service information was approved for IBR on
January 30, 2013 (77 FR 75825, December 26, 2012).
(i) Messier-Dowty Service Letter A33-34 A20, Revision 5,
including Appendixes A through F, dated July 31, 2009.
(ii) Reserved.
(5) The following service information was approved for IBR on
September 30, 2011 (76 FR 53305, August 26, 2011).
(i) Airbus A330 Airworthiness Limitations Section, Part 1, Safe
Life Airworthiness Limitation Items, Revision 05, dated July 29,
2010. The revision level of this document is indicated only on the
title page and in the Record of Revisions; the revision date of this
document is not indicated on the title page of this document.
(ii) Reserved.
(6) 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.
(7) 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.
(8) 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.
(9) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
[[Page 24039]]
Issued in Renton, Washington, on May 10, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10266 Filed 5-24-17; 8:45 am]
BILLING CODE 4910-13-P
