Airworthiness Directives; Airbus Airplanes, 1504-1508 [2015-33289]
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Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspect the Upper Skin Joints for
Adequate Sealant
Within the next 100 hours time-in-service
(TIS) after February 17, 2016 (the effective
date of this AD) or 12 months after February
17, 2016 (the effective date of this AD),
whichever occurs first, inspect the upper
skin joints for adequate sealant following Part
I of Piper Aircraft, Inc. Service Bulletin No.
1262B, dated April 23, 2015. No further
action per this AD is required if adequate
sealant is already applied.
(h) Inspect for Evidence of Water Intrusion/
Moisture
If you find missing or inadequate sealant
during the inspection required by paragraph
(g) of this AD, before further flight, inspect
for evidence of water intrusion/moisture
following Part II of Piper Aircraft, Inc.
Service Bulletin No. 1262B, dated April 23,
2015.
(1) If no evidence of water intrusion/
moisture is found during the inspection
required in paragraph (h) of this AD, before
further flight, rework the stringers and apply
sealant as required in paragraph (k) of this
AD.
(2) If evidence of water intrusion/moisture
is found during the inspection required in
paragraph (h) of this AD, before further flight,
do the actions required in paragraphs (i) and
(j) of this AD.
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(i) Inspect for Corrosion
If you find, as a result of the inspection
required by paragraph (h) of this AD,
evidence of water intrusion/moisture, before
further flight, inspect for corrosion following
Part II of Piper Aircraft, Inc. Service Bulletin
No. 1262B, dated April 23, 2015.
(1) If no evidence of corrosion is found
during the inspection required in paragraph
(i) of this AD, before further flight, rework the
stringers and apply sealant as required in
paragraph (k) of this AD.
(2) If evidence of corrosion is found during
the inspection required in paragraph (i) of
this AD, before further flight, obtain and
implement an FAA-approved corrective
action approved specifically for this AD. At
the operator’s discretion, assistance may be
provided by contacting Piper Aircraft, Inc. at
the address identified in paragraph (p)(3) of
this AD. After obtaining and implementing
an FAA-approved corrective action,
approved specifically for this AD, before
further flight, rework the stringers and apply
sealant as required in paragraph (k) of this
AD.
(j) Inspect for Deformation
If you find, as a result of the inspection
required by paragraph (h) of this AD,
evidence of water intrusion/moisture, before
further flight, do a visual inspection for skin
or stringer deformation.
(1) If no evidence of deformation is found
during the inspection required in paragraph
(j) of this AD, before further flight, rework the
stringers and apply sealant as required in
paragraph (k) of this AD.
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(2) If any visible deformation is found
during the inspection required in paragraph
(j) of this AD, before further flight, obtain and
implement an FAA-approved corrective
action, approved specifically for this AD. At
the operator’s discretion, assistance may be
provided by contacting Piper Aircraft, Inc. at
the address identified in paragraph (p)(3) of
this AD. After obtaining and implementing
an FAA-approved corrective action,
approved specifically for this AD, before
further flight, rework the stringers and apply
sealant as required in paragraph (k) of this
AD.
(k) Rework Stringers and Seal Skin Joints
If any inspection required by paragraphs
(g) through (j) of this AD reveals
discrepancies (no sealant/inadequate sealant,
evidence of water intrusion/moisture,
corrosion, or deformation), before further
flight, after completing any necessary
corrective actions, rework wing stringers and
seal skin joints following Part II of Piper
Aircraft, Inc. Service Bulletin No. 1262B,
dated April 23, 2015.
(l) Credit for Actions Done in Accordance
With Previous Service Information
Actions done before February 17, 2016 (the
effective date of this AD) following Part I and
Part II of Piper Aircraft, Inc. Service Bulletin
No. 1262, dated October 16, 2013, or Part I
and Part II of Piper Aircraft, Inc. Service
Bulletin No. 1262A, dated November 14,
2013, as applicable, are considered
acceptable for compliance with the
corresponding actions specified in
paragraphs (g), (h), (i), and (k) (including
subparagraphs) of this AD. Additional
inspections beyond Service Bulletin No. 1262
are required to fully comply with paragraph
(j) of this AD.
(m) Special Flight Permit
(1) In accordance with 14 CFR 39.23, a
single flight is allowed to a location to do the
actions in paragraph (g) of this AD.
(2) In accordance with 14 CFR 39.23, a
single flight is allowed to a location to do the
inspections, rework and installation of
sealant required in paragraphs (h) through (k)
of this AD. Prior to the flight to perform the
inspections, rework, and installation of
sealant, the following inspection must be
performed: If the inspection required by
paragraph (g) of this AD reveals no sealant,
inspect for evidence of wing damage (skin or
stringer deformation, e.g. buckling). Any
wing damage that is found must be repaired
before further flight and before any special
flight permit is authorized.
(n) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Atlanta Aircraft
Certification Office (ACO), 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 ACO, send it to the
attention of the person identified in
paragraph (l)(1) of this AD.
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(2) 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
(o) Related Information
For more information about this AD,
contact Gregory ‘‘Keith’’ Noles, Aerospace
Engineer, FAA, Atlanta ACO, 1701 Columbia
Avenue, College Park, Georgia 30337;
telephone: (404) 474–5551; fax: (404) 474–
5606; email: gregory.noles@faa.gov.
(p) 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) Piper Aircraft, Inc. Service Bulletin No.
1262B, dated April 23, 2015.
(ii) Reserved.
(3) For Piper Aircraft, Inc. service
information identified in this AD, contact
Piper Aircraft, Inc., Customer Service, 2926
Piper Drive, Vero Beach, Florida 32960;
telephone: (877) 879–0275; fax: None; email:
customer.service@piper.com; Internet:
www.piper.com.
(4) You may view this service information
at FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148. It
is also available on the Internet at https://
www.regulations.gov by searching for
locating Docket No. FAA–2015–4213.
(5) 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.
Issued in Kansas City, Missouri, on
December 24, 2015.
Pat Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–33170 Filed 1–12–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–1981; Directorate
Identifier 2014–NM–204–AD; Amendment
39–18362; AD 2016–01–03]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations
ACTION:
Final rule.
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–200 Freighter,
A330–200, A330–300, A340–200, and
A340–300 series airplanes. This AD was
prompted by reports that the inner bore
of some main landing gear (MLG) unit
bogie beams were insufficiently reprotected against corrosion after
inspection or maintenance actions were
accomplished. This AD requires for
certain MLG units, determining which
revision of the component maintenance
manual (CMM) was used to accomplish
the most recent MLG unit overhaul; a
detailed inspection for missing or
damaged paint, and if necessary, a
detailed inspection of the cadmium
plating for discrepancies, measurement
of the depth of the cadmium plating, a
general visual inspection of the base
metal for corrosion or damage, a
detailed inspection of repaired areas for
cracking or corrosion; and corrective
actions if necessary. We are issuing this
AD to detect and correct corrosion in
the bore of each MLG unit bogie beam,
which could result in collapse of a MLG
unit, and subsequent damage to the
airplane and injury to occupants.
DATES: This AD becomes effective
February 17, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 17, 2016.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-1981; or in
person at the 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.
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. For
Messier-Dowty service information
contact Messier-Dowty Limited,
Cheltenham Road, Gloucester, GL2
9QH, England; telephone +44(0) 1452
712424; fax+ 44(0) 1452 713821;
Internet https://www.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://
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SUMMARY:
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www.regulations.gov by searching for
and locating Docket No. FAA–2015–
1981.
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 certain Airbus Model A330–
200 Freighter, A330–200, A330–300,
A340–200, and A340–300 series
airplanes. The NPRM published in the
Federal Register on June 15, 2015 (80
FR 34098).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0222, dated October 6,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A330–200 Freighter, A330–200,
A330–300, A340–200, and A340–300
series airplanes. The MCAI states:
From in-service experience, it was found
that the inner bore of some bogie beams had
been insufficiently re-protected against
corrosion after inspection and/or possible
maintenance actions accomplished in this
area (absence of corrosion inhibitor and
damage to paint have been found in some
specific areas).
This condition, if not detected and
corrected, could lead to corrosion on the bore
of the bogie beam, potentially resulting in
Main Landing Gear (MLG) collapse,
ultimately resulting in damage to the
aeroplane and injury to the occupants.
To address this potential unsafe condition,
Airbus issued Alert Operators Transmission
(AOT) A32L004–14, providing inspection
instructions for some aeroplane
configurations.
For the reasons described above, this
[EASA] AD requires identification of the
MLG units that are possibly affected, [a
detailed] inspection [for missing or damaged
paint] of the MLG Bogie Beam bore and,
depending on findings, accomplishment of
the applicable corrective actions.
This [EASA] AD also prohibits the
installation of MLG units that have been
overhauled by using instructions from an
earlier Components Maintenance Manual
(CMM) revision.
Required actions also include a
detailed inspection of the cadmium
plating for discrepancies (gray in color),
measurement of the depth of the
cadmium plating if necessary, and a
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1505
general visual inspection of the base
metal for corrosion or damage, and a
detailed inspection of repaired areas for
cracking or corrosion. Corrective actions
include removing cadmium plating and
repairing any cracked, corroded, or
damaged areas; re-applying cadmium
plating and paint; and re-applying
temporary corrosion protection to the
bores of the MLG bogie beams.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2015-19810002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comments received.
The following presents the comments
received on the NPRM (80 FR 34098,
June 15, 2015) and the FAA’s response
to each comment.
Request for Clarification of Optional
Method of Compliance
Air France and American Airlines
(AA) requested that paragraph (j) of the
proposed AD (80 FR 34098, June 15,
2015) be revised to clarify that after
accomplishment of the actions in the
Accomplishment Instructions of
Messier-Dowty Service Bulletin A33/
34–32–272, dated November 16, 2007,
including Appendixes A, B, C, and D,
dated November 16, 2007; or Service
Bulletin A33/34–32–272, Revision 1,
dated September 22, 2008, including
Appendixes A, B, C, and D, dated
September 22, 2008; the actions
specified in the Messier-Dowty service
information identified in paragraphs
(j)(1) through (j)(5) of the proposed AD
must not be accomplished on that same
MLG unit.
We agree with the commenters’
request and have revised paragraph (j) of
this AD to clarify that after
accomplishment of the actions in the
Accomplishment Instructions of
Messier-Dowty Service Bulletin A33/
34–32–272, dated November 16, 2007,
including Appendixes A, B, C, and D,
dated November 16, 2007; or Service
Bulletin A33/34–32–272, Revision 1,
dated September 22, 2008, including
Appendixes A, B, C, and D, dated
September 22, 2008; the actions
specified in the Messier-Dowty service
information identified in paragraphs
(j)(1) through (j)(5) of this AD must not
be accomplished on that same MLG
unit. The actions in the
Accomplishment Instructions of
Messier-Dowty service information
identified in paragraphs (j)(1) through
(j)(5) do not provide sufficient corrosion
protection for the MLG units.
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Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations
Request To Correct Service Information
Reference
Air France requested that the
references to the Airbus component
maintenance manual in paragraph (g) of
the proposed AD be changed to MessierDowty component maintenance manual.
We agree with the commenter’s
request because the component
maintenance manuals were published
by Messier-Dowty, not Airbus. We have
revised paragraphs (g) and (k) of this AD
accordingly.
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Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (80 FR
34098, June 15, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (80 FR 34098,
June 15, 2015).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued Alert Operators
Transmission A32L004–14, dated July
28, 2014, including Appendixes 1, 2, 3,
and 4. This service information
describes procedures for inspections of
the bogie beam bore of the MLG.
Messier-Dowty has issued the
following service information, which
describes procedures for inspections of
the internal diameter of the bogie beam
for corrosion.
• Service Bulletin A33/34–32–272,
dated November 16, 2007, including
Appendixes A, B, C, and D, dated
November 16, 2007.
• Service Bulletin A33/34–32–272,
Revision 1, dated September 22, 2008,
including Appendixes A, B, C, and D,
dated September 22, 2008.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 89
airplanes of U.S. registry.
We also estimate that it will take
about 12 work-hours per product to
comply with the basic requirements of
this AD, and 1 work-hour to report the
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inspection findings. 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 $98,345,
or $1,105 per product.
We have received no definitive data
that would enable us to provide cost
estimates for any necessary follow-on
actions.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this 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,
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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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-1981; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section.
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2016–01–03 Airbus: Amendment 39–18362.
Docket No. FAA–2015–1981; Directorate
Identifier 2014–NM–204–AD.
(a) Effective Date
This AD becomes effective February 17,
2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD.
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Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations
(1) Model A330–201, A330–202, A330–
203, A330–223, A330–223F, A330–243,
A330–243F, A330–301, A330–302, A330–
303, A330–321, A330–322, A330–323, A330–
341, A330–342, and A330–343 airplanes; all
manufacturer serial numbers; except those on
which Airbus Modification 58896 has been
embodied in production or embodied
through Airbus Service Bulletin A330–32–
3237.
(2) Model A340–211, A340–212, A340–
213, A340–311, A340–312, and A340–313
airplanes; all manufacturer serial numbers;
except those on which Airbus Modification
58896 has been embodied in production or
embodied through Airbus Service Bulletin
A340–32–4279.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Reason
This AD was prompted by reports that the
inner bore of some main landing gear (MLG)
unit bogie beams were insufficiently reprotected against corrosion after inspection
or maintenance actions were accomplished.
We are issuing this AD to detect and correct
corrosion in the bore of each MLG unit bogie
beam, which could result in collapse of a
MLG unit, and subsequent damage to the
airplane and injury to occupants.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Identification of Affected MLG Units
Within 12 months after the effective date
of this AD: For MLG units having a 201252
series or 201490 series part number,
determine the revision of the Messier-Dowty
component maintenance manual (CMM) used
to do the most recent MLG unit overhaul. If
it is determined that the Messier-Dowty
CMM revision specified in paragraph (g)(1) or
(g)(2) of this AD was used to accomplish the
most recent MLG unit overhaul: Within 12
months after the effective date of this AD,
clean the area between the bogie pivot pin
and the bogie beam bore of each MLG unit
and do a detailed inspection for missing or
damaged paint, in accordance with Airbus
Alert Operators Transmission A32L004–14,
dated July 28, 2014, including Appendixes 1,
2, 3, and 4, which do not have a date.
(1) For MLG units having a part number in
the 201252 series: Messier-Dowty CMM 32–
11–74, Revision 25 or earlier.
(2) For MLG units having a part number in
the 201490 series: Messier-Dowty CMM 32–
12–05, Revision 20 or earlier.
(h) Inspection of Cadmium Plating
If, during the inspection required by
paragraph (g) of this AD, any missing or
damaged paint is found: Before further flight,
do a detailed inspection of the cadmium
plating for discrepancies, measure the depth
of the plating as applicable, and do a general
visual inspection of the base metal for
corrosion or damage, in accordance with
Airbus Alert Operators Transmission
A32L004–14, dated July 28, 2014, including
Appendixes 1, 2, 3, and 4, which do not have
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a date. If any discrepancy, damage, or
corrosion is found, before further flight, do
all applicable corrective actions, and do a
detailed inspection of repaired areas for
cracking or corrosion, in accordance with
Airbus Alert Operators Transmission
A32L004–14, dated July 28, 2014, including
Appendixes 1, 2, 3, and 4, which do not have
a date, except where Airbus Alert Operators
Transmission A32L004–14, dated July 28,
2014, including Appendixes 1, 2, 3, and 4,
specifies to contact Messier-Dowty if
cracking or corrosion is found in a repaired
area, before further flight, repair using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
(i) Reporting Requirement
At the applicable time specified in
paragraph (i)(1) or (i)(2) of this AD, report the
findings of the inspection required by
paragraph (g) of this AD to Airbus, Customer
Services Engineering—SEEL1, Attn: Philippe
Kerangueven, Product Leader A330/A340,
ATA–32, Landing Gear Systems, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; phone +33 (0) 5 67 19 18 42;
fax +33 0 5 67 19 12 05; email
philippe.kerangueven@airbus.com. The
report must include the information specified
in Appendix 2 of Airbus Alert Operators
Transmission A32L004–14, dated July 28,
2014.
(1) If the inspection was done on or after
the effective date of this AD: Within 90 days
after that inspection.
(2) If the inspection was done before the
effective date of this AD: Within 90 days after
the effective date of this AD.
(j) Optional Method of Compliance
Accomplishment of the boroscope
inspection of the internal diameter of the
bogie beam for corrosion or damage to the
protective treatments, measurement of the
depth of the protective treatments as
applicable, and accomplishment of all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Messier-Dowty Service Bulletin A33/34–32–
272, dated November 16, 2007, including
Appendixes A, B, C, and D, dated November
16, 2007; or Revision 1, dated September 22,
2008, including Appendixes A, B, C, and D,
dated September 22, 2008; are acceptable for
the corresponding actions required by
paragraphs (g) and (h) of this AD for that
MLG unit; however, after accomplishment of
the actions in the Accomplishment
Instructions of Messier-Dowty Service
Bulletin A33/34–32–272, dated November
16, 2007, including Appendixes A, B, C, and
D, dated November 16, 2007; or Service
Bulletin A33/34–32–272, Revision 1, dated
September 22, 2008, including Appendixes
A, B, C, and D, dated September 22, 2008; the
actions specified in the Messier-Dowty
service information identified in paragraphs
(j)(1) through (j)(5) of this AD must not be
accomplished on that same MLG unit. Where
Messier-Dowty Service Bulletin A33/34–32–
272, dated November 16, 2007, including
Appendixes A, B, C, and D, dated November
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
1507
16, 2007; or Revision 1, dated September 22,
2008, including Appendixes A, B, C, and D,
dated September 22, 2008; specify to contact
Messier-Dowty for repair information, the
repair must be accomplished using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA.
(1) Messier-Dowty Service Bulletin A33/34
32–285, dated July 9, 2010.
(2) Messier-Dowty Service Bulletin A33/34
32–285, Revision 1, dated October 4, 2011.
(3) Messier-Dowty Service Bulletin A33/34
32–285, Revision 2, dated October 4, 2012.
(4) Messier-Dowty Service Bulletin A33/34
32–285, Revision 3, dated September 11,
2013.
(5) Messier-Dowty Service Bulletin A33/34
32–285, Revision 4, dated January 23, 2014.
Note 1 to paragraph (j) of this AD:
Inspections done using the instructions in
Messier-Dowty Service Bulletin A33/34–32–
285, Revision 5, dated August 14, 2014, do
not affect the optional method of compliance
provided by this paragraph.
(k) Parts Installation Limitation
As of the effective date of this AD, any
overhauled MLG unit having a 201252 series
or 201490 series part number may be
installed on an airplane, provided the most
recent MLG overhaul was done using a
Messier-Dowty CMM that is not specified in
paragraph (g)(1) or (g)(2) of this AD, or, prior
to installation, the MLG unit passes the
inspection required by paragraph (g) of this
AD.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
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: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
E:\FR\FM\13JAR1.SGM
13JAR1
1508
Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES 200.
asabaliauskas on DSK5VPTVN1PROD with RULES
(m) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0222, dated
October 6, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2015-1981-0002.
(n) 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.
(i) Airbus Alert Operators Transmission
A32L004–14, dated July 28, 2014, including
Appendixes 1, 2, 3, and 4, which are not
dated.
(ii) Messier-Dowty Service Bulletin A33/
34–32–272, dated November 16, 2007,
including Appendixes A, B, C, and D, dated
November 16, 2007.
(iii) Messier-Dowty Service Bulletin A33/
34–32–272, Revision 1, dated September 22,
2008, including Appendixes A, B, C, and D,
dated September 22, 2008.
(3) 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.
(4) For Messier-Dowty service information
identified in this AD, contact Messier-Dowty
Limited, Cheltenham Road, Gloucester, GL2
9QH, England; telephone +44(0) 1452
712424; fax+ 44(0) 1452 713821; Internet
https://www.safranmbd.com.
(5) 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.
(6) 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
VerDate Sep<11>2014
15:56 Jan 12, 2016
Jkt 238001
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 29, 2015.
Philip Forde,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–33289 Filed 1–12–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–1049; Directorate
Identifier 2013–NM–110–AD; Amendment
39–18361; AD 2016–01–02]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. This AD was prompted by
reports that the horizontal stabilizer
trim actuator (HSTA) spur gear bolts
inside the gearbox were found loose,
broken, or backed out due to incorrect
bending of the anti-rotation tab washer
and the improper application of Loctite
glue during installation. This AD
requires replacing certain HSTAs with a
new HSTA. This AD also requires
revising the airplane flight manual
(AFM) and the maintenance or
inspection program, as applicable. We
are issuing this AD to prevent failure of
the HSTA and subsequent loss of
control of the airplane.
DATES: This AD becomes effective
February 17, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 17, 2016.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-1049; or in
person at the 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.
For service information identified in
this final rule, contact Bombardier, Inc.,
SUMMARY:
PO 00000
Frm 00028
Fmt 4700
Sfmt 4700
ˆ
400 Cote Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; telephone
514–855–5000; fax 514–855–7401; email
thd.crj@aero.bombardier.com; Internet
https://www.bombardier.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–2014–
1049.
FOR FURTHER INFORMATION CONTACT:
Luke Walker, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7363; fax
516–794–5531.
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 certain Bombardier, Inc. Model
CL–600–2B19 (Regional Jet Series 100 &
440) airplanes. The NPRM published in
the Federal Register on January 23,
2015 (80 FR 3522).
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2013–14,
dated June 4, 2013 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc. Model CL–
600–2B19 (Regional Jet Series 100 &
440) airplanes. The MCAI states:
There have been a number of reports where
the HSTA spur gear bolts inside the gearbox
were found loose, broken or backed out.
Investigation revealed that the root cause is
incorrect bending of the anti-rotation tab
washer and the improper application of
Loctite glue during installation.
The function of these bolts is to generate
sufficient preload between the two spur gears
such that the full torque is transferred by
friction between the two spur gears.
Loosening of the bolts would reduce the preload between two spur gears and decrease the
torque transfer. Partial or full torque would
be re-distributed to the secondary load path
(Tie-Rod) in torsion. The Tie-Rod is designed
to withstand axial load only in case of failure
of the primary load path (ACME screw), and
not torsional load. The secondary load path
(Tie-Rod) is therefore considered ineffective
and no longer provides protection as a
failsafe design of the system. Loose bolt(s) on
the HSTA spur gear combined with the
failure of the primary load path, could lead
to failure of the HSTA and subsequent loss
of the aeroplane.
E:\FR\FM\13JAR1.SGM
13JAR1
]]>Agencies
[Federal Register Volume 81, Number 8 (Wednesday, January 13, 2016)]
[Rules and Regulations]
[Pages 1504-1508]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-33289]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-1981; Directorate Identifier 2014-NM-204-AD;
Amendment 39-18362; AD 2016-01-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 1505]]
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, and
A340-300 series airplanes. This AD was prompted by reports that the
inner bore of some main landing gear (MLG) unit bogie beams were
insufficiently re-protected against corrosion after inspection or
maintenance actions were accomplished. This AD requires for certain MLG
units, determining which revision of the component maintenance manual
(CMM) was used to accomplish the most recent MLG unit overhaul; a
detailed inspection for missing or damaged paint, and if necessary, a
detailed inspection of the cadmium plating for discrepancies,
measurement of the depth of the cadmium plating, a general visual
inspection of the base metal for corrosion or damage, a detailed
inspection of repaired areas for cracking or corrosion; and corrective
actions if necessary. We are issuing this AD to detect and correct
corrosion in the bore of each MLG unit bogie beam, which could result
in collapse of a MLG unit, and subsequent damage to the airplane and
injury to occupants.
DATES: This AD becomes effective February 17, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 17,
2016.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-1981; or in person at the
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.
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. For Messier-Dowty service information contact Messier-
Dowty Limited, Cheltenham Road, Gloucester, GL2 9QH, England; telephone
+44(0) 1452 712424; fax+ 44(0) 1452 713821; Internet https://www.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-
1981.
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 certain Airbus Model A330-
200 Freighter, A330-200, A330-300, A340-200, and A340-300 series
airplanes. The NPRM published in the Federal Register on June 15, 2015
(80 FR 34098).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0222, dated October 6, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330-200 Freighter, A330-200, A330-300, A340-200, and A340-300 series
airplanes. The MCAI states:
From in-service experience, it was found that the inner bore of
some bogie beams had been insufficiently re-protected against
corrosion after inspection and/or possible maintenance actions
accomplished in this area (absence of corrosion inhibitor and damage
to paint have been found in some specific areas).
This condition, if not detected and corrected, could lead to
corrosion on the bore of the bogie beam, potentially resulting in
Main Landing Gear (MLG) collapse, ultimately resulting in damage to
the aeroplane and injury to the occupants.
To address this potential unsafe condition, Airbus issued Alert
Operators Transmission (AOT) A32L004-14, providing inspection
instructions for some aeroplane configurations.
For the reasons described above, this [EASA] AD requires
identification of the MLG units that are possibly affected, [a
detailed] inspection [for missing or damaged paint] of the MLG Bogie
Beam bore and, depending on findings, accomplishment of the
applicable corrective actions.
This [EASA] AD also prohibits the installation of MLG units that
have been overhauled by using instructions from an earlier
Components Maintenance Manual (CMM) revision.
Required actions also include a detailed inspection of the cadmium
plating for discrepancies (gray in color), measurement of the depth of
the cadmium plating if necessary, and a general visual inspection of
the base metal for corrosion or damage, and a detailed inspection of
repaired areas for cracking or corrosion. Corrective actions include
removing cadmium plating and repairing any cracked, corroded, or
damaged areas; re-applying cadmium plating and paint; and re-applying
temporary corrosion protection to the bores of the MLG bogie beams.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-1981-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comments received. The following
presents the comments received on the NPRM (80 FR 34098, June 15, 2015)
and the FAA's response to each comment.
Request for Clarification of Optional Method of Compliance
Air France and American Airlines (AA) requested that paragraph (j)
of the proposed AD (80 FR 34098, June 15, 2015) be revised to clarify
that after accomplishment of the actions in the Accomplishment
Instructions of Messier-Dowty Service Bulletin A33/34-32-272, dated
November 16, 2007, including Appendixes A, B, C, and D, dated November
16, 2007; or Service Bulletin A33/34-32-272, Revision 1, dated
September 22, 2008, including Appendixes A, B, C, and D, dated
September 22, 2008; the actions specified in the Messier-Dowty service
information identified in paragraphs (j)(1) through (j)(5) of the
proposed AD must not be accomplished on that same MLG unit.
We agree with the commenters' request and have revised paragraph
(j) of this AD to clarify that after accomplishment of the actions in
the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/
34-32-272, dated November 16, 2007, including Appendixes A, B, C, and
D, dated November 16, 2007; or Service Bulletin A33/34-32-272, Revision
1, dated September 22, 2008, including Appendixes A, B, C, and D, dated
September 22, 2008; the actions specified in the Messier-Dowty service
information identified in paragraphs (j)(1) through (j)(5) of this AD
must not be accomplished on that same MLG unit. The actions in the
Accomplishment Instructions of Messier-Dowty service information
identified in paragraphs (j)(1) through (j)(5) do not provide
sufficient corrosion protection for the MLG units.
[[Page 1506]]
Request To Correct Service Information Reference
Air France requested that the references to the Airbus component
maintenance manual in paragraph (g) of the proposed AD be changed to
Messier-Dowty component maintenance manual.
We agree with the commenter's request because the component
maintenance manuals were published by Messier-Dowty, not Airbus. We
have revised paragraphs (g) and (k) of this AD accordingly.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (80 FR 34098, June 15, 2015) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 34098, June 15, 2015).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued Alert Operators Transmission A32L004-14, dated
July 28, 2014, including Appendixes 1, 2, 3, and 4. This service
information describes procedures for inspections of the bogie beam bore
of the MLG.
Messier-Dowty has issued the following service information, which
describes procedures for inspections of the internal diameter of the
bogie beam for corrosion.
Service Bulletin A33/34-32-272, dated November 16, 2007,
including Appendixes A, B, C, and D, dated November 16, 2007.
Service Bulletin A33/34-32-272, Revision 1, dated
September 22, 2008, including Appendixes A, B, C, and D, dated
September 22, 2008.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 89 airplanes of U.S. registry.
We also estimate that it will take about 12 work-hours per product
to comply with the basic requirements of this AD, and 1 work-hour to
report the inspection findings. 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 $98,345, or $1,105 per product.
We have received no definitive data that would enable us to provide
cost estimates for any necessary follow-on actions.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-1981; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.
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 adding the following new airworthiness
directive (AD):
2016-01-03 Airbus: Amendment 39-18362. Docket No. FAA-2015-1981;
Directorate Identifier 2014-NM-204-AD.
(a) Effective Date
This AD becomes effective February 17, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
[[Page 1507]]
(1) Model A330-201, A330-202, A330-203, A330-223, A330-223F,
A330-243, A330-243F, A330-301, A330-302, A330-303, A330-321, A330-
322, A330-323, A330-341, A330-342, and A330-343 airplanes; all
manufacturer serial numbers; except those on which Airbus
Modification 58896 has been embodied in production or embodied
through Airbus Service Bulletin A330-32-3237.
(2) Model A340-211, A340-212, A340-213, A340-311, A340-312, and
A340-313 airplanes; all manufacturer serial numbers; except those on
which Airbus Modification 58896 has been embodied in production or
embodied through Airbus Service Bulletin A340-32-4279.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports that the inner bore of some main
landing gear (MLG) unit bogie beams were insufficiently re-protected
against corrosion after inspection or maintenance actions were
accomplished. We are issuing this AD to detect and correct corrosion
in the bore of each MLG unit bogie beam, which could result in
collapse of a MLG unit, and subsequent damage to the airplane and
injury to occupants.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Identification of Affected MLG Units
Within 12 months after the effective date of this AD: For MLG
units having a 201252 series or 201490 series part number, determine
the revision of the Messier-Dowty component maintenance manual (CMM)
used to do the most recent MLG unit overhaul. If it is determined
that the Messier-Dowty CMM revision specified in paragraph (g)(1) or
(g)(2) of this AD was used to accomplish the most recent MLG unit
overhaul: Within 12 months after the effective date of this AD,
clean the area between the bogie pivot pin and the bogie beam bore
of each MLG unit and do a detailed inspection for missing or damaged
paint, in accordance with Airbus Alert Operators Transmission
A32L004-14, dated July 28, 2014, including Appendixes 1, 2, 3, and
4, which do not have a date.
(1) For MLG units having a part number in the 201252 series:
Messier-Dowty CMM 32-11-74, Revision 25 or earlier.
(2) For MLG units having a part number in the 201490 series:
Messier-Dowty CMM 32-12-05, Revision 20 or earlier.
(h) Inspection of Cadmium Plating
If, during the inspection required by paragraph (g) of this AD,
any missing or damaged paint is found: Before further flight, do a
detailed inspection of the cadmium plating for discrepancies,
measure the depth of the plating as applicable, and do a general
visual inspection of the base metal for corrosion or damage, in
accordance with Airbus Alert Operators Transmission A32L004-14,
dated July 28, 2014, including Appendixes 1, 2, 3, and 4, which do
not have a date. If any discrepancy, damage, or corrosion is found,
before further flight, do all applicable corrective actions, and do
a detailed inspection of repaired areas for cracking or corrosion,
in accordance with Airbus Alert Operators Transmission A32L004-14,
dated July 28, 2014, including Appendixes 1, 2, 3, and 4, which do
not have a date, except where Airbus Alert Operators Transmission
A32L004-14, dated July 28, 2014, including Appendixes 1, 2, 3, and
4, specifies to contact Messier-Dowty if cracking or corrosion is
found in a repaired area, before further flight, repair using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(i) Reporting Requirement
At the applicable time specified in paragraph (i)(1) or (i)(2)
of this AD, report the findings of the inspection required by
paragraph (g) of this AD to Airbus, Customer Services Engineering--
SEEL1, Attn: Philippe Kerangueven, Product Leader A330/A340, ATA-32,
Landing Gear Systems, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; phone +33 (0) 5 67 19 18 42; fax +33 0 5 67 19 12 05;
email philippe.kerangueven@airbus.com. The report must include the
information specified in Appendix 2 of Airbus Alert Operators
Transmission A32L004-14, dated July 28, 2014.
(1) If the inspection was done on or after the effective date of
this AD: Within 90 days after that inspection.
(2) If the inspection was done before the effective date of this
AD: Within 90 days after the effective date of this AD.
(j) Optional Method of Compliance
Accomplishment of the boroscope inspection of the internal
diameter of the bogie beam for corrosion or damage to the protective
treatments, measurement of the depth of the protective treatments as
applicable, and accomplishment of all applicable corrective actions,
in accordance with the Accomplishment Instructions of Messier-Dowty
Service Bulletin A33/34-32-272, dated November 16, 2007, including
Appendixes A, B, C, and D, dated November 16, 2007; or Revision 1,
dated September 22, 2008, including Appendixes A, B, C, and D, dated
September 22, 2008; are acceptable for the corresponding actions
required by paragraphs (g) and (h) of this AD for that MLG unit;
however, after accomplishment of the actions in the Accomplishment
Instructions of Messier-Dowty Service Bulletin A33/34-32-272, dated
November 16, 2007, including Appendixes A, B, C, and D, dated
November 16, 2007; or Service Bulletin A33/34-32-272, Revision 1,
dated September 22, 2008, including Appendixes A, B, C, and D, dated
September 22, 2008; the actions specified in the Messier-Dowty
service information identified in paragraphs (j)(1) through (j)(5)
of this AD must not be accomplished on that same MLG unit. Where
Messier-Dowty Service Bulletin A33/34-32-272, dated November 16,
2007, including Appendixes A, B, C, and D, dated November 16, 2007;
or Revision 1, dated September 22, 2008, including Appendixes A, B,
C, and D, dated September 22, 2008; specify to contact Messier-Dowty
for repair information, the repair must be accomplished using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(1) Messier-Dowty Service Bulletin A33/34 32-285, dated July 9,
2010.
(2) Messier-Dowty Service Bulletin A33/34 32-285, Revision 1,
dated October 4, 2011.
(3) Messier-Dowty Service Bulletin A33/34 32-285, Revision 2,
dated October 4, 2012.
(4) Messier-Dowty Service Bulletin A33/34 32-285, Revision 3,
dated September 11, 2013.
(5) Messier-Dowty Service Bulletin A33/34 32-285, Revision 4,
dated January 23, 2014.
Note 1 to paragraph (j) of this AD: Inspections done using the
instructions in Messier-Dowty Service Bulletin A33/34-32-285,
Revision 5, dated August 14, 2014, do not affect the optional method
of compliance provided by this paragraph.
(k) Parts Installation Limitation
As of the effective date of this AD, any overhauled MLG unit
having a 201252 series or 201490 series part number may be installed
on an airplane, provided the most recent MLG overhaul was done using
a Messier-Dowty CMM that is not specified in paragraph (g)(1) or
(g)(2) of this AD, or, prior to installation, the MLG unit passes
the inspection required by paragraph (g) of this AD.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International 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: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a
[[Page 1508]]
person is not required to respond to, nor shall a person be subject
to a penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES 200.
(m) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2014-0222, dated October 6, 2014, for
related information. This MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-
1981-0002.
(n) 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.
(i) Airbus Alert Operators Transmission A32L004-14, dated July
28, 2014, including Appendixes 1, 2, 3, and 4, which are not dated.
(ii) Messier-Dowty Service Bulletin A33/34-32-272, dated
November 16, 2007, including Appendixes A, B, C, and D, dated
November 16, 2007.
(iii) Messier-Dowty Service Bulletin A33/34-32-272, Revision 1,
dated September 22, 2008, including Appendixes A, B, C, and D, dated
September 22, 2008.
(3) 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.
(4) For Messier-Dowty service information identified in this AD,
contact Messier-Dowty Limited, Cheltenham Road, Gloucester, GL2 9QH,
England; telephone +44(0) 1452 712424; fax+ 44(0) 1452 713821;
Internet https://www.safranmbd.com.
(5) 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.
(6) 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.
Issued in Renton, Washington, on December 29, 2015.
Philip Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-33289 Filed 1-12-16; 8:45 am]
BILLING CODE 4910-13-P
