[Federal Register Volume 78, Number 118 (Wednesday, June 19, 2013)]
[Proposed Rules]
[Pages 36691-36693]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-14569]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 78, No. 118 / Wednesday, June 19, 2013 /
Proposed Rules
[[Page 36691]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0527; Directorate Identifier 2013-CE-014-AD]
RIN 2120-AA64
Airworthiness Directives; Piaggio Aero Industries S.p.A Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Piaggio Aero Industries S.p.A Model P-180 airplanes. This proposed AD
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 lever hinge fitting.
We are issuing this proposed AD to require actions to address the
unsafe condition on these products.
DATES: We must receive comments on this proposed AD by August 5, 2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed 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: [email protected]; Internet: http://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:
[email protected]; 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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: 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:
[email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0527;
Directorate Identifier 2013-CE-014-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No. 2013-0084, dated April 5, 2013 (referred to after this as ``the
MCAI''), 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.
Relevant Service Information
Piaggio Aero Industries S.p.A. has issued Mandatory Service
Bulletin No. 80-0345, and Appendix A, both dated September 20, 2012,
which includes Messier-Dowty Service Bulletin No. P180-32-32, dated
September 10, 2012. The actions described in this service information
are intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of the Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation
[[Page 36692]]
in the United States. Pursuant to our bilateral agreement with this
State of Design Authority, they have notified us of the unsafe
condition described in the MCAI and service information referenced
above. We are proposing this AD because we evaluated all information
and determined the unsafe condition exists and is likely to exist or
develop on other products of the same type design.
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 proposed AD will affect 109 products of U.S.
registry. We also estimate that it would 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 proposed AD. The average labor rate is $85 per
work-hour.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $101,915, or $935 per product.
In addition, we estimate that any necessary follow-on actions would
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 proposed
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
Piaggio Aero Industries S.p.A: Docket No. FAA-2013-0527; Directorate
Identifier 2013-CE-014-AD.
(a) Comments Due Date
We must receive comments by August 5, 2013.
(b) Affected ADs
None.
(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 hours time-in-service (TIS) after the
effective date of this AD or within the next 3 months after the
effective date of this AD, whichever occurs first, and repetitively
thereafter before further flight after each MLG (subassembly)
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 Piaggio Aero Industries S.p.A.
Appendix A, dated September 20, 2012, which includes Messier-Dowty
Service Bulletin No. P180-32-32, dated September 10, 2012.
(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 LHF with a serviceable part. 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 LHF is subject to the repetitive
inspection requirement specified in paragraph (f)(1) of this AD and
all 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 hours TIS, do a detailed
visual inspection of each MLG LHF for cracks. Do the inspection
following Part
[[Page 36693]]
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 Piaggio
Aero Industries S.p.A. Appendix A, dated September 20, 2012, that
includes Messier-Dowty Service Bulletin No. P180-32-32, dated
September 10, 2012.
(i) As of the effective date of this AD, if the MLG LHF has
accumulated 2,300 hours TIS or less since new, inspect before
exceeding 2,500 hours TIS since new.
(ii) As of the effective date of this AD, if the MLG LHF has
accumulated more than 2,300 hours TIS since new, but less than 2,500
hours TIS since new, inspect within the next 200 hours TIS after the
effective date of this AD.
(iii) As of the effective date of this AD, if the MLG LHF has
accumulated 2,500 hours TIS or more since new, inspect within the
next 200 hours TIS after the effective date of this AD or within the
next 3 months after 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 hours TIS, 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 of the
Accomplishment Instructions in PIAGGIO AERO INDUSTRIES S.p.A.
Appendix A, dated September 20, 2012, that 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. Do the replacement following the
Accomplishment Instructions in Piaggio Aero Industries S.p.A.
Mandatory Service Bulletin No. 80-0345, dated September 20, 2012.
After installing a serviceable MLG, continue with the repetitive
inspection requirements of paragraphs (f)(1), (f)(3), and (f)(4)
this AD.
(6) Within 30 days after each MLG LHF 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 an
airworthy MLG verified before installation for freedom of rotation
and has been inspected following paragraphs (f)(3) and (f)(4) of
this AD, including all subparagraphs, and is found free of cracks.
If status of detailed visual inspections intervals, fluorescent
penetrant inspections intervals, or hours TIS 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)(3) and (f)(4) of this AD. Any
newly install MLG LHF is subject to the repetitive inspections
required in paragraphs (f)(1), (f)(3), and (f)(4) of this AD.
(8) As of 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)(3) and (f)(4) of this AD. Continue
thereafter with the repetitive inspections at the intervals
specified paragraphs (f)(1), (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:
[email protected]. 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.
(3) Reporting Requirements: For any reporting requirement in
this AD, a federal agency may not conduct or sponsor, and a 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.
(h) Related Information
(1) Refer to MCAI European Aviation Safety Agency (EASA) AD No.
2013-0084, dated April 5, 2013; 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, for related information.
(2) For service information identified in and related to 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: [email protected]; Internet:
http://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:
[email protected]; 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.
Issued in Kansas City, Missouri, on June 13, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013-14569 Filed 6-18-13; 8:45 am]
BILLING CODE 4910-13-P