Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Airplanes, 56589-56592 [2013-22203]
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Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations
3(m)(1) of the Act (12 U.S.C. 1813(m)(1))
and this part.
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■ 3. In § 330.3, revise paragraph (e) to
read as follows:
§ 330.3
General principles.
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(e) Deposits payable outside of the
United States and certain other
locations. (1) Any obligation of an
insured depository institution which is
payable solely at an office of that
institution located outside any State, as
the term ‘‘State’’ is defined in section
3(a)(3) of the Act (12 U.S.C. 1813(a)(3)),
is not a deposit for the purposes of this
part.
(2) Except as provided in paragraph
(e)(3) of this section, any obligation of
an insured depository institution which
is carried on the books and records of
an office of that institution located
outside any State, as referred to in
paragraph (e)(1) of this section, shall not
be an insured deposit for purposes of
this part, or any other provision of this
part, notwithstanding that the obligation
may also be payable at an office of that
institution located within any State.
(3) Rule of construction. For purposes
of this paragraph (e), Overseas Military
Banking Facilities operated under
Department of Defense regulations, 32
CFR Parts 230 and 231, are not
considered to be offices located outside
any State, as referred to in paragraph
(e)(1) of this section.
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BILLING CODE 6714–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0527; Directorate
Identifier 2013–CE–014–AD; Amendment
39–17577; AD 2013–18–04]
RIN 2120–AA64
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During scheduled maintenance, cracks
have been detected at the joint between the
hinge pin sub-assembly and the lock pin of
the main landing gear (MLG) lever hinge
fitting (LHF) of a Piaggio P.180 aeroplane.
The results of the subsequent investigation
revealed that the cracks were initiated by an
unforeseen friction in the MLG wheel lever
sub-assembly.
This condition, if not detected and
corrected, could lead to a structural failure of
the MLG, possibly resulting in loss of control
of the aeroplane during take-off or landing
runs.
To address this potential unsafe condition,
Piaggio Aero Industries (PAI) issued Service
Bulletin (SB) 80–0345 to provide instructions
for early identification of cracks in the MLG
LHF and, in case of identification of the
crack, replacement of the MLG.
For the reasons described above, this AD
required inspections of the MLG LHF and,
depending on findings, replacement of the
MLG.
This AD is considered to be an interim
action, and based on gathered experience,
further AD action may follow.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal and the FAA’s
response to each comment.
Airworthiness Directives; PIAGGIO
AERO INDUSTRIES S.p.A Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
Jkt 229001
Request To Change Compliance Time
From Hours Time-in-Service (TIS) to
Landings
Carlo Cardu of PIAGGIO AERO
INDUSTRIES S.p.A requested the
compliance time be changed from hours
TIS to landing, as recommended in the
related service bulletin, to take into
account actual landing gear usage.
We partially agreed with the
commenter to include landings as a
measure for the compliance of this AD
because the unsafe condition addressed
in this AD is a function of cycles on the
landing gear. We disagreed with only
using landings because this class of
airplane does not require landings to be
recorded. If an operator does document
landings, this is an acceptable measure.
However, if an operator does not record
landings, TIS is also an acceptable
measure for compliance.
We have changed the final rule AD
action based on this comment.
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. The
NPRM was published in the Federal
Register on June 19, 2013 (78 FR 36691).
The NPRM proposed to correct an
[FR Doc. 2013–22340 Filed 9–12–13; 8:45 am]
17:44 Sep 12, 2013
unsafe condition for the specified
products. The MCAI states:
Discussion
Dated at Washington, DC, this 10th day of
September, 2013.
By order of the Board of Directors.
Federal Deposit Insurance Corporation.
Robert E. Feldman,
Executive Secretary.
VerDate Mar<15>2010
We are adopting a new
airworthiness directive (AD) for all
PIAGGIO AERO INDUSTRIES S.p.A
Model P–180 airplanes. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as cracks at the joint between
the hinge pin sub-assembly and the lock
pin of the main landing gear lever hinge
fitting. We are issuing this AD to require
actions to address the unsafe condition
on these products.
DATES: This AD is effective October 18,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 18, 2013.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
Document 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 service information identified in
this AD, contact Piaggio Aero Industries
S.p.A—Airworthiness Office, Via Luigi
Cibrario, 4–16154 Genova-Italy; phone:
+39 010 6481353; fax: +39 010 6481881;
email: airworthiness@piaggioaero.it;
Internet: https://www.piaggioaero.com/#/
en/aftersales/service-support; and
Messier-Dowty Limited, Cheltenham
Road, Gloucester, GL2 9QH, England;
phone: +44(0)1452 712424; fax:
+44(0)1452 713821; email:
americatassc@safranmbd.com; Internet:
www.safranmbd.com. You may review
copies of the referenced service
information at the 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.
FOR FURTHER INFORMATION CONTACT:
Mike Kiesov, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4144; fax: (816)
329–4090; email: mike.kiesov@faa.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
56589
Request To Change the Requirement To
Replace the Main Landing Gear (MLG)
Lever Hinge Fitting (LHF)
Carlo Cardu of PIAGGIO AERO
INDUSTRIES S.p.A requested we
change the corrective action from
replacing the MLG LHF with a
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Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations
serviceable part to replacing the MLG
with a serviceable part based on the
description of a serviceable part in the
related service bulletin.
The commenter also requested we
change the language from MLG LHF to
MLG when referring to the inspections
required after replacement of the MLG.
We agreed with the commenter. Based
on the description of a serviceable part
in the service bulletin, the operator has
options to meet the intent of a
serviceable part that do not increase the
burden on the owners/operators of the
affected airplanes. We have changed the
final rule AD action based on this
comment.
Request To Clarify Inspection
Requirements for Newly Installed MLG
Carlo Cardu of PIAGGIO AERO
INDUSTRIES S.p.A requested changing
all repetitive inspection language for
newly installed MLG. The commenter
suggested changing this AD to specify
that a newly installed MLG is subject to
specific inspection reqirements.
We agreed with the commenter and
have changed the final rule AD action
based on this comment.
Request To Expand Criteria for
Determining a ‘‘Serviceable’’ MLG
Carlo Cardu of PIAGGIO AERO
INDUSTRIES S.p.A requested additional
language be added to clarify the
definition of a ‘‘serviceable’’ MLG.
We agreed with the commenter and
have changed the final rule AD action
based on this comment.
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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.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
36691, June 19, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 36691,
June 19, 2013).
We also determined that these changes
will not increase the economic burden
on any operator or increase the scope of
this AD.
Interim Action
We consider this AD interim action.
We are requiring inspection(s) of the left
and right MLG LHF with a report to the
manufacturer of the results if cracks are
found. We will work with the type
certificate holder to evaluate the report
VerDate Mar<15>2010
17:44 Sep 12, 2013
Jkt 229001
results to determine repetitive
inspection intervals and subsequent
terminating action. Based on this
evaluation, we may initiate further
rulemaking action to address the unsafe
condition identified in this AD.
Costs of Compliance
We estimate that this AD will affect
109 products of U.S. registry. We also
estimate that it will take about 11 total
work-hours, which is 2 work-hours for
the initial visual inspection; 2 workhours for the detailed visual inspection;
and 7 work-hours for the fluorescent
penetrant inspection, 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 $101,915, or $935 per product.
In addition, we estimate that any
necessary follow-on actions will take
about 7 work-hours and require parts
costing $21,540 to replace a left-hand
LHF, for a cost of $22,153, and $20,662
to replace a right-hand LHF, for a cost
of $21,257.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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
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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, 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; 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 the NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
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 AD:
■
2013–18–04 PIAGGIO AERO INDUSTRIES
S.p.A: Amendment 39–17577; Docket
No. FAA–2012–0962; Directorate
Identifier 2012–CE–033–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective October 18, 2013.
(b) Affected ADs
None.
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Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations
(c) Applicability
This AD applies to PIAGGIO AERO
INDUSTRIES S.p.A Model P–180 airplanes,
all serial numbers, certificated in any
category.
(d) Subject
Air Transport Association of America
(ATA) Code 32: Landing Gear.
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(e) Reason
This AD was prompted by results from
mandatory continuing airworthiness
information (MCAI) originated by an aviation
authority of another country to identify and
correct an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as cracks at the joint between the
hinge pin sub-assembly and the lock pin of
the main landing gear (MLG) lever hinge
fitting (LHF). We are issuing this AD to
prevent structural failure of the MLG LHF,
which could result in loss of control during
take-off or landing runs.
(f) Actions and Compliance
Unless already done, do the following
actions in paragraphs (f)(1) through (f)(8),
including all subparagraphs, of this AD:
(1) Within the next 200 landings after
October 18, 2013 (the effective date of this
AD), or within the next 3 months after
October 18, 2013 (the effective date of this
AD), whichever occurs first, and before
further flight after each MLG replacement,
visually inspect each MLG LHF for cracks
and verify freedom of rotation of the MLG
wheel lever subassemblies. Do the inspection
following Part 1 of the Accomplishment
Instructions in PIAGGIO AERO INDUSTRIES
S.p.A. Mandatory Service Bulletin No. 80–
0345, dated September 20, 2012; and
Paragraph A of the Accomplishment
Instructions in Appendix A of PIAGGIO
AERO INDUSTRIES S.p.A. Mandatory
Service Bulletin No. 80–0345, dated
September 20, 2012, which includes MessierDowty Service Bulletin No. P180–32–32,
dated September 10, 2012. The compliance
times for the entire AD are presented in
landings; however, it is not mandatory to
track landings for this class of airplane. If an
operator does not track landings, 1 hour timein-service (TIS) corresponds to 1 landing for
compliance with this AD.
(2) If, during the inspection required in
paragraph (f)(1) of this AD, freedom of
rotation of the MLG wheel lever subassembly
is not assured, before further flight, mark the
LHF on the affected MLG as ‘‘inspect as per
SB–80–0345’’ with an indelible pen, and
replace the MLG with a serviceable part as
defined in paragraph (f)(7) of this AD. Do the
replacement following Part 1 of the
Accomplishment Instructions in PIAGGIO
AERO INDUSTRIES S.p.A. Mandatory
Service Bulletin No. 80–0345, dated
September 20, 2012. The newly installed
MLG is subject to the inspection requirement
specified in paragraph (f)(1) of this AD and
all repetitive inspection requirements
specified in paragraphs (f)(3) and (f)(4) of this
AD.
(3) Within the compliance times specified
in paragraphs (f)(3)(i), (f)(3)(ii), and (f)(3)(iii)
of this AD, and repetitively thereafter at
VerDate Mar<15>2010
17:44 Sep 12, 2013
Jkt 229001
intervals not to exceed 200 landings, do a
detailed visual inspection of each MLG LHF
for cracks. Do the inspection following Part
2 of the Accomplishment Instructions in
PIAGGIO AERO INDUSTRIES S.p.A.
Mandatory Service Bulletin No. 80–0345,
dated September 20, 2012; and Paragraph B
of the Accomplishment Instructions in
Appendix A of PIAGGIO AERO INDUSTRIES
S.p.A. Mandatory Service Bulletin No. 80–
0345, dated September 20, 2012, which
includes Messier-Dowty Service Bulletin No.
P180–32–32, dated September 10, 2012.
(i) As of October 18, 2013 (the effective
date of this AD), if the MLG LHF has
accumulated 2,300 landings or less since
new, inspect before exceeding 2,500 landings
since new.
(ii) As of October 18, 2013 (the effective
date of this AD), if the MLG LHF has
accumulated more than 2,300 landings since
new, but less than 2,500 landings since new,
inspect within the next 200 landings after
October 18, 2013 (the effective date of this
AD).
(iii) As of October 18, 2013 (the effective
date of this AD), if the MLG LHF has
accumulated 2,500 landings or more since
new, inspect within the next 200 landings
after October 18, 2013 (the effective date of
this AD), or within the next 3 months after
October 18, 2013 (the effective date of this
AD), whichever occurs first.
(4) Within the compliance times specified
in paragraphs (f)(3)(i), (f)(3)(ii), and (f)(3)(iii)
of this AD and repetitively thereafter at
intervals not to exceed 750 landings, do a
fluorescent penetrant inspection on each
MLG LHF for cracks. Do the inspection
following Part 3 of the Accomplishment
Instructions in PIAGGIO AERO INDUSTRIES
S.p.A. Mandatory Service Bulletin No. 80–
0345, dated September 20, 2012; and
Paragraph C in Appendix A of PIAGGIO
AERO INDUSTRIES S.p.A. Mandatory
Service Bulletin No. 80–0345, dated
September 20, 2012, which includes MessierDowty Service Bulletin No. P180–32–32,
dated September 10, 2012.
(5) If, during any inspection required by
paragraphs (f)(1), (f)(3), (f)(4), (f)(7), and (f)(8)
of this AD, including all subparagraphs, any
crack is found, before further flight, replace
the MLG with a serviceable part as defined
in paragraph (f)(7) of this AD. Do the
replacement following the Accomplishment
Instructions in PIAGGIO AERO INDUSTRIES
S.p.A. Mandatory Service Bulletin No. 80–
0345, dated September 20, 2012. The newly
installed MLG is subject to the inspection
requirement specified in paragraph (f)(1) of
this AD and all repetitive inspection
requirements specified in paragraphs (f)(3)
and (f)(4) of this AD.
(6) Within 30 days after each MLG
replacement, submit an inspection result
report to PIAGGIO AERO INDUSTRIES S.p.A
at the address specified in paragraph (h) of
this AD using the Confirmation Slip attached
to PIAGGIO AERO INDUSTRIES S.p.A.
Mandatory Service Bulletin No. 80–0345,
dated September 20, 2012.
(7) For the purpose of this AD, a
‘‘serviceable’’ MLG is defined as an airworthy
MLG that has had the freedom of rotation
verified before installation and that has been
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56591
inspected following paragraphs (f)(3), (f)(4),
and (f)(8) (paragraph (f)(8) only applies if the
LHF on the MLG has been marked ‘‘inspect
as per SB–80–0345’’ as specified in
paragraph (f)(2) of this AD) of this AD,
including all subparagraphs, and is found
free of cracks. If status of detailed visual
inspections intervals, fluorescent penetrant
inspections intervals, or landings since new
cannot be determined from the Authorized
Release Certificate of the MLG to be installed,
before next flight after installation, inspect
the MLG LHF as specified in paragraphs
(f)(1), (f)(3), and (f)(4) of this AD. For the
purpose of this AD, a serviceable MLG
replacement is defined in paragraphs (f)(7)(i),
(f)(7)(ii), and (f)(7)(iii) of this AD. All newly
installed MLG LHF is subject to the
inspections required in paragraphs (f)(1),
(f)(3), and (f)(4) of this AD.
(i) Remove the unserviceable MLG and
replace it with a different serviceable MLG.
(ii) Rework the unserviceable MLG
following Part 2 and Part 3 of the
Accomplishment Instructions in PIAGGIO
AERO INDUSTRIES S.p.A. Mandatory
Service Bulletin No. 80–0345, dated
September 20, 2012, until it passes the check
for freedom of rotation and no cracks are
found.
(iii) Replace the cracked LHF in the
unserviceable MLG with a new LHF and,
after LHF replacement, check the MLG for
freedom of rotation.
(8) As of October 18, 2013 (the effective
date of this AD), any MLG with LHF marked
‘‘inspect as per SB 80–0345’’ that was
removed as specified in paragraph (f)(2) of
this AD may be reinstalled provided that
before installation, freedom of rotation has
been restored. Before further flight after
installation, the MLG LHF must be inspected
as specified in paragraphs (f)(1), (f)(3), and
(f)(4) of this AD. Continue thereafter with the
repetitive inspections at the intervals
specified in paragraphs (f)(3) and (f)(4) of this
AD.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Mike Kiesov, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4144; fax: (816) 329–
4090; email: mike.kiesov@faa.gov. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
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Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations
(h) Related Information
DEPARTMENT OF TRANSPORTATION
Refer to MCAI European Aviation Safety
Agency (EASA) AD No. 2013–0084, dated
April 5, 2013, which can be found in the AD
docket on the Internet at https://
www.regulations.gov; Messier-Dowty PCS–
2700 Paint Stripping document, dated
January 2011; Messier-Dowty PCS–2622 Cold
Degreasing (Solvent) document, Issue 2,
dated May 12, 2008; and Messier-Dowty Ltd
201034005 and 201034006 Component
Maintenance Manual, page 2, dated May 1,
2004, and page 1020, dated March 17, 2006,
which can be found on the Internet at:
https://www.safranmbd.com, for related
information.
(i) Material Incorporated by Reference
emcdonald on DSK67QTVN1PROD with RULES
(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) PIAGGIO AERO INDUSTRIES S.p.A.
Mandatory Service Bulletin No. 80–0345,
dated September 20, 2012.
(ii) PIAGGIO AERO INDUSTRIES S.p.A.
Mandatory Service Bulletin No. 80–0345,
Appendix A, dated September 20, 2012,
which includes Messier-Dowty Service
Bulletin No. P180–32–32, dated September
10, 2012.
(3) For PIAGGIO AERO INDUSTRIES
S.p.A. service information identified in this
AD, contact Piaggio Aero Industries S.p.A—
Airworthiness Office, Via Luigi Cibrario, 4–
16154 Genova-Italy; phone: +39 010 6481353;
fax: +39 010 6481881; email: airworthiness@
piaggioaero.it; Internet: https://
www.piaggioaero.com/#/en/aftersales/
service-support; and Messier-Dowty Limited,
Cheltenham Road, Gloucester, GL2 9QH,
England; phone: +44(0)1452 712424; fax:
+44(0)1452 713821; email: americatassc@
safranmbd.com; Internet:
www.safranmbd.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.
(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 August
29, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2013–22203 Filed 9–12–13; 8:45 am]
BILLING CODE 4910–13–P
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17:44 Sep 12, 2013
Jkt 229001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0379; Directorate
Identifier 2009–SW–26–AD; Amendment 39–
17580; AD 2013–18–07]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron, Inc. (Bell)
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding revised
Airworthiness Directive (AD) 76–12–07
for all Bell Model 204B and certain
serial-numbered Model 205A–1
helicopters with a certain tail rotor pitch
control chain (chain) installed. AD 76–
12–07 required visually inspecting the
chain to detect a crack in the link
segments and, for affected Model 205A–
1 helicopters, replacing the chain and
cable control system with a push-pull
control system. This new AD requires,
for Bell Model 204B, inspecting certain
chains at specified intervals, revising
the inspection procedures, installing a
tail rotor cable and chain damper kit
(damper kit), and revising the
maintenance manual or Instructions for
Continued Airworthiness (ICAs) to
include the inspection intervals. This
new AD also requires, for certain Bell
Model 205A–1 helicopters, replacing
the chain and cable control system with
an airworthy tail rotor push-pull control
system kit. This AD was prompted by
the rapid growth of a crack leading to
premature chain failure. The actions are
intended to prevent failure of the chain,
loss of tail rotor blade pitch control, and
subsequent loss of control of the
helicopter.
SUMMARY:
This AD is effective October 18,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 18, 2013.
ADDRESSES: For service information
identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482,
Fort Worth, TX 76101; telephone (817)
280–3391; fax (817) 280–6466; or at
https://www.bellcustomer.com/files/.
You may review a copy of the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas
76137.
DATES:
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the foreign
authority’s AD, any incorporated-byreference service information, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
Office (phone: 800–647–5527) is U.S.
Department of Transportation, Docket
Operations Office, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Michael Kohner, Aviation Safety
Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5170; email
7-AVS-ASW-170@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On June 3, 1976, we issued AD 76–
12–07, Amendment 39–2640 (41 FR
23939, June 14, 1976), Docket No. 76–
SW–19, which required repetitive
inspections at specified intervals for a
certain part-numbered chain installed
on Model 204B and 205A–1 helicopters.
AD 76–12–07 also required, before
further flight, replacing chains with
cracked or broken links or segments.
On September 12, 1979, we revised
AD 76–12–07 by issuing Amendment
39–3569 (44 FR 55555, September 27,
1979). The revised AD 76–12–07 limited
the applicability for the Model 205A–1
helicopter to certain serial numbers;
decreased the inspection interval of the
chain; and required replacing the
existing chain and cable control system
with a push-pull control system.
Both amendments were prompted by
several chain failures occurring in flight
and reports of cracked chain links on
Model 205A–1 helicopters. Those
actions were intended to detect cracks
in the chain link segments to prevent
failure of a chain and subsequent loss of
directional control of the helicopter.
On April 25, 2013, at 78 FR 24368, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 to
include an AD that would supersede
original and revised AD 76–12–07. The
NPRM proposed to expand the
applicability of AD 76–12–07 to a
newly-produced, similarly-designed
chain; reduce the inspection interval for
the Model 204B; and require installing
E:\FR\FM\13SER1.SGM
13SER1
]]>Agencies
[Federal Register Volume 78, Number 178 (Friday, September 13, 2013)]
[Rules and Regulations]
[Pages 56589-56592]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-22203]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0527; Directorate Identifier 2013-CE-014-AD;
Amendment 39-17577; AD 2013-18-04]
RIN 2120-AA64
Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
PIAGGIO AERO INDUSTRIES S.p.A Model P-180 airplanes. This AD results
from mandatory continuing airworthiness information (MCAI) issued by an
aviation authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as cracks at the joint between the hinge pin sub-assembly and
the lock pin of the main landing gear lever hinge fitting. We are
issuing this AD to require actions to address the unsafe condition on
these products.
DATES: This AD is effective October 18, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 18,
2013.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at Document 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 service information identified in this AD, contact Piaggio Aero
Industries S.p.A--Airworthiness Office, Via Luigi Cibrario, 4-16154
Genova-Italy; phone: +39 010 6481353; fax: +39 010 6481881; email:
airworthiness@piaggioaero.it; Internet: https://www.piaggioaero.com/#/en/aftersales/service-support; and Messier-Dowty Limited, Cheltenham
Road, Gloucester, GL2 9QH, England; phone: +44(0)1452 712424; fax:
+44(0)1452 713821; email: americatassc@safranmbd.com; Internet:
www.safranmbd.com. You may review copies of the referenced service
information at the 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.
FOR FURTHER INFORMATION CONTACT: Mike Kiesov, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4144; fax: (816) 329-4090; email:
mike.kiesov@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
The NPRM was published in the Federal Register on June 19, 2013 (78 FR
36691). The NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During scheduled maintenance, cracks have been detected at the
joint between the hinge pin sub-assembly and the lock pin of the
main landing gear (MLG) lever hinge fitting (LHF) of a Piaggio P.180
aeroplane.
The results of the subsequent investigation revealed that the
cracks were initiated by an unforeseen friction in the MLG wheel
lever sub-assembly.
This condition, if not detected and corrected, could lead to a
structural failure of the MLG, possibly resulting in loss of control
of the aeroplane during take-off or landing runs.
To address this potential unsafe condition, Piaggio Aero
Industries (PAI) issued Service Bulletin (SB) 80-0345 to provide
instructions for early identification of cracks in the MLG LHF and,
in case of identification of the crack, replacement of the MLG.
For the reasons described above, this AD required inspections of
the MLG LHF and, depending on findings, replacement of the MLG.
This AD is considered to be an interim action, and based on
gathered experience, further AD action may follow.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.
Request To Change Compliance Time From Hours Time-in-Service (TIS) to
Landings
Carlo Cardu of PIAGGIO AERO INDUSTRIES S.p.A requested the
compliance time be changed from hours TIS to landing, as recommended in
the related service bulletin, to take into account actual landing gear
usage.
We partially agreed with the commenter to include landings as a
measure for the compliance of this AD because the unsafe condition
addressed in this AD is a function of cycles on the landing gear. We
disagreed with only using landings because this class of airplane does
not require landings to be recorded. If an operator does document
landings, this is an acceptable measure. However, if an operator does
not record landings, TIS is also an acceptable measure for compliance.
We have changed the final rule AD action based on this comment.
Request To Change the Requirement To Replace the Main Landing Gear
(MLG) Lever Hinge Fitting (LHF)
Carlo Cardu of PIAGGIO AERO INDUSTRIES S.p.A requested we change
the corrective action from replacing the MLG LHF with a
[[Page 56590]]
serviceable part to replacing the MLG with a serviceable part based on
the description of a serviceable part in the related service bulletin.
The commenter also requested we change the language from MLG LHF to
MLG when referring to the inspections required after replacement of the
MLG.
We agreed with the commenter. Based on the description of a
serviceable part in the service bulletin, the operator has options to
meet the intent of a serviceable part that do not increase the burden
on the owners/operators of the affected airplanes. We have changed the
final rule AD action based on this comment.
Request To Clarify Inspection Requirements for Newly Installed MLG
Carlo Cardu of PIAGGIO AERO INDUSTRIES S.p.A requested changing all
repetitive inspection language for newly installed MLG. The commenter
suggested changing this AD to specify that a newly installed MLG is
subject to specific inspection reqirements.
We agreed with the commenter and have changed the final rule AD
action based on this comment.
Request To Expand Criteria for Determining a ``Serviceable'' MLG
Carlo Cardu of PIAGGIO AERO INDUSTRIES S.p.A requested additional
language be added to clarify the definition of a ``serviceable'' MLG.
We agreed with the commenter and have changed the final rule AD
action based on this comment.
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. We have determined that
these minor changes:
[Agr]re consistent with the intent that was proposed in
the NPRM (78 FR 36691, June 19, 2013) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 36691, June 19, 2013).
We also determined that these changes will not increase the economic
burden on any operator or increase the scope of this AD.
Interim Action
We consider this AD interim action. We are requiring inspection(s)
of the left and right MLG LHF with a report to the manufacturer of the
results if cracks are found. We will work with the type certificate
holder to evaluate the report results to determine repetitive
inspection intervals and subsequent terminating action. Based on this
evaluation, we may initiate further rulemaking action to address the
unsafe condition identified in this AD.
Costs of Compliance
We estimate that this AD will affect 109 products of U.S. registry.
We also estimate that it will take about 11 total work-hours, which is
2 work-hours for the initial visual inspection; 2 work-hours for the
detailed visual inspection; and 7 work-hours for the fluorescent
penetrant inspection, 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 $101,915, or $935 per product.
In addition, we estimate that any necessary follow-on actions will
take about 7 work-hours and require parts costing $21,540 to replace a
left-hand LHF, for a cost of $22,153, and $20,662 to replace a right-
hand LHF, for a cost of $21,257.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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 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; 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 the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
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 AD:
2013-18-04 PIAGGIO AERO INDUSTRIES S.p.A: Amendment 39-17577; Docket
No. FAA-2012-0962; Directorate Identifier 2012-CE-033-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective October 18,
2013.
(b) Affected ADs
None.
[[Page 56591]]
(c) Applicability
This AD applies to PIAGGIO AERO INDUSTRIES S.p.A Model P-180
airplanes, all serial numbers, certificated in any category.
(d) Subject
Air Transport Association of America (ATA) Code 32: Landing
Gear.
(e) Reason
This AD was prompted by results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority
of another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as cracks
at the joint between the hinge pin sub-assembly and the lock pin of
the main landing gear (MLG) lever hinge fitting (LHF). We are
issuing this AD to prevent structural failure of the MLG LHF, which
could result in loss of control during take-off or landing runs.
(f) Actions and Compliance
Unless already done, do the following actions in paragraphs
(f)(1) through (f)(8), including all subparagraphs, of this AD:
(1) Within the next 200 landings after October 18, 2013 (the
effective date of this AD), or within the next 3 months after
October 18, 2013 (the effective date of this AD), whichever occurs
first, and before further flight after each MLG replacement,
visually inspect each MLG LHF for cracks and verify freedom of
rotation of the MLG wheel lever subassemblies. Do the inspection
following Part 1 of the Accomplishment Instructions in PIAGGIO AERO
INDUSTRIES S.p.A. Mandatory Service Bulletin No. 80-0345, dated
September 20, 2012; and Paragraph A of the Accomplishment
Instructions in Appendix A of PIAGGIO AERO INDUSTRIES S.p.A.
Mandatory Service Bulletin No. 80-0345, dated September 20, 2012,
which includes Messier-Dowty Service Bulletin No. P180-32-32, dated
September 10, 2012. The compliance times for the entire AD are
presented in landings; however, it is not mandatory to track
landings for this class of airplane. If an operator does not track
landings, 1 hour time-in-service (TIS) corresponds to 1 landing for
compliance with this AD.
(2) If, during the inspection required in paragraph (f)(1) of
this AD, freedom of rotation of the MLG wheel lever subassembly is
not assured, before further flight, mark the LHF on the affected MLG
as ``inspect as per SB-80-0345'' with an indelible pen, and replace
the MLG with a serviceable part as defined in paragraph (f)(7) of
this AD. Do the replacement following Part 1 of the Accomplishment
Instructions in PIAGGIO AERO INDUSTRIES S.p.A. Mandatory Service
Bulletin No. 80-0345, dated September 20, 2012. The newly installed
MLG is subject to the inspection requirement specified in paragraph
(f)(1) of this AD and all repetitive inspection requirements
specified in paragraphs (f)(3) and (f)(4) of this AD.
(3) Within the compliance times specified in paragraphs
(f)(3)(i), (f)(3)(ii), and (f)(3)(iii) of this AD, and repetitively
thereafter at intervals not to exceed 200 landings, do a detailed
visual inspection of each MLG LHF for cracks. Do the inspection
following Part 2 of the Accomplishment Instructions in PIAGGIO AERO
INDUSTRIES S.p.A. Mandatory Service Bulletin No. 80-0345, dated
September 20, 2012; and Paragraph B of the Accomplishment
Instructions in Appendix A of PIAGGIO AERO INDUSTRIES S.p.A.
Mandatory Service Bulletin No. 80-0345, dated September 20, 2012,
which includes Messier-Dowty Service Bulletin No. P180-32-32, dated
September 10, 2012.
(i) As of October 18, 2013 (the effective date of this AD), if
the MLG LHF has accumulated 2,300 landings or less since new,
inspect before exceeding 2,500 landings since new.
(ii) As of October 18, 2013 (the effective date of this AD), if
the MLG LHF has accumulated more than 2,300 landings since new, but
less than 2,500 landings since new, inspect within the next 200
landings after October 18, 2013 (the effective date of this AD).
(iii) As of October 18, 2013 (the effective date of this AD), if
the MLG LHF has accumulated 2,500 landings or more since new,
inspect within the next 200 landings after October 18, 2013 (the
effective date of this AD), or within the next 3 months after
October 18, 2013 (the effective date of this AD), whichever occurs
first.
(4) Within the compliance times specified in paragraphs
(f)(3)(i), (f)(3)(ii), and (f)(3)(iii) of this AD and repetitively
thereafter at intervals not to exceed 750 landings, do a fluorescent
penetrant inspection on each MLG LHF for cracks. Do the inspection
following Part 3 of the Accomplishment Instructions in PIAGGIO AERO
INDUSTRIES S.p.A. Mandatory Service Bulletin No. 80-0345, dated
September 20, 2012; and Paragraph C in Appendix A of PIAGGIO AERO
INDUSTRIES S.p.A. Mandatory Service Bulletin No. 80-0345, dated
September 20, 2012, which includes Messier-Dowty Service Bulletin
No. P180-32-32, dated September 10, 2012.
(5) If, during any inspection required by paragraphs (f)(1),
(f)(3), (f)(4), (f)(7), and (f)(8) of this AD, including all
subparagraphs, any crack is found, before further flight, replace
the MLG with a serviceable part as defined in paragraph (f)(7) of
this AD. Do the replacement following the Accomplishment
Instructions in PIAGGIO AERO INDUSTRIES S.p.A. Mandatory Service
Bulletin No. 80-0345, dated September 20, 2012. The newly installed
MLG is subject to the inspection requirement specified in paragraph
(f)(1) of this AD and all repetitive inspection requirements
specified in paragraphs (f)(3) and (f)(4) of this AD.
(6) Within 30 days after each MLG replacement, submit an
inspection result report to PIAGGIO AERO INDUSTRIES S.p.A at the
address specified in paragraph (h) of this AD using the Confirmation
Slip attached to PIAGGIO AERO INDUSTRIES S.p.A. Mandatory Service
Bulletin No. 80-0345, dated September 20, 2012.
(7) For the purpose of this AD, a ``serviceable'' MLG is defined
as an airworthy MLG that has had the freedom of rotation verified
before installation and that has been inspected following paragraphs
(f)(3), (f)(4), and (f)(8) (paragraph (f)(8) only applies if the LHF
on the MLG has been marked ``inspect as per SB-80-0345'' as
specified in paragraph (f)(2) of this AD) of this AD, including all
subparagraphs, and is found free of cracks. If status of detailed
visual inspections intervals, fluorescent penetrant inspections
intervals, or landings since new cannot be determined from the
Authorized Release Certificate of the MLG to be installed, before
next flight after installation, inspect the MLG LHF as specified in
paragraphs (f)(1), (f)(3), and (f)(4) of this AD. For the purpose of
this AD, a serviceable MLG replacement is defined in paragraphs
(f)(7)(i), (f)(7)(ii), and (f)(7)(iii) of this AD. All newly
installed MLG LHF is subject to the inspections required in
paragraphs (f)(1), (f)(3), and (f)(4) of this AD.
(i) Remove the unserviceable MLG and replace it with a different
serviceable MLG.
(ii) Rework the unserviceable MLG following Part 2 and Part 3 of
the Accomplishment Instructions in PIAGGIO AERO INDUSTRIES S.p.A.
Mandatory Service Bulletin No. 80-0345, dated September 20, 2012,
until it passes the check for freedom of rotation and no cracks are
found.
(iii) Replace the cracked LHF in the unserviceable MLG with a
new LHF and, after LHF replacement, check the MLG for freedom of
rotation.
(8) As of October 18, 2013 (the effective date of this AD), any
MLG with LHF marked ``inspect as per SB 80-0345'' that was removed
as specified in paragraph (f)(2) of this AD may be reinstalled
provided that before installation, freedom of rotation has been
restored. Before further flight after installation, the MLG LHF must
be inspected as specified in paragraphs (f)(1), (f)(3), and (f)(4)
of this AD. Continue thereafter with the repetitive inspections at
the intervals specified in paragraphs (f)(3) and (f)(4) of this AD.
(g) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Mike Kiesov, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4144; fax: (816) 329-4090; email:
mike.kiesov@faa.gov. Before using any approved AMOC on any airplane
to which the AMOC applies, notify your appropriate principal
inspector (PI) in the FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
[[Page 56592]]
(h) Related Information
Refer to MCAI European Aviation Safety Agency (EASA) AD No.
2013-0084, dated April 5, 2013, which can be found in the AD docket
on the Internet at https://www.regulations.gov; Messier-Dowty PCS-
2700 Paint Stripping document, dated January 2011; Messier-Dowty
PCS-2622 Cold Degreasing (Solvent) document, Issue 2, dated May 12,
2008; and Messier-Dowty Ltd 201034005 and 201034006 Component
Maintenance Manual, page 2, dated May 1, 2004, and page 1020, dated
March 17, 2006, which can be found on the Internet at: https://www.safranmbd.com, for related information.
(i) 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) PIAGGIO AERO INDUSTRIES S.p.A. Mandatory Service Bulletin
No. 80-0345, dated September 20, 2012.
(ii) PIAGGIO AERO INDUSTRIES S.p.A. Mandatory Service Bulletin
No. 80-0345, Appendix A, dated September 20, 2012, which includes
Messier-Dowty Service Bulletin No. P180-32-32, dated September 10,
2012.
(3) For PIAGGIO AERO INDUSTRIES S.p.A. service information
identified in this AD, contact Piaggio Aero Industries S.p.A--
Airworthiness Office, Via Luigi Cibrario, 4-16154 Genova-Italy;
phone: +39 010 6481353; fax: +39 010 6481881; email:
airworthiness@piaggioaero.it; Internet: https://www.piaggioaero.com/#/en/aftersales/service-support; and Messier-Dowty Limited,
Cheltenham Road, Gloucester, GL2 9QH, England; phone: +44(0)1452
712424; fax: +44(0)1452 713821; email: americatassc@safranmbd.com;
Internet: www.safranmbd.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.
(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/ibr-locations.html.
Issued in Kansas City, Missouri, on August 29, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013-22203 Filed 9-12-13; 8:45 am]
BILLING CODE 4910-13-P
