Proposed Rule2023-19092
Airworthiness Directives; Piaggio Aviation S.p.A. Airplanes
Primary source
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Published
September 7, 2023
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for certain Piaggio Aviation S.p.A. (Piaggio) Model P-180 airplanes. This proposed AD was prompted by a report of corrosion on the various aluminum alloy reinforcements in the horizontal stabilizer (HS) central box caused by a humid environment inside the box from water ingress and/or condensation. This proposed AD would require a one-time detailed inspection of the HS central box for corrosion; an assessment of the corrosion level; and depending on the determination, repetitive detailed inspections of the HS central box for corrosion and the internal composite structure for surface cracks, distortion, and damage; and repair or replacement of the HS assembly. Repair or replacement of the HS assembly would be terminating action for the repetitive inspections. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 88 Issue 172 (Thursday, September 7, 2023)</title>
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[Federal Register Volume 88, Number 172 (Thursday, September 7, 2023)]
[Proposed Rules]
[Pages 61482-61485]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2023-19092]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-1819; Project Identifier MCAI-2023-00052-A]
RIN 2120-AA64
Airworthiness Directives; Piaggio Aviation S.p.A. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Piaggio Aviation S.p.A. (Piaggio) Model P-180 airplanes.
This proposed AD was prompted by a report of corrosion on the various
aluminum alloy reinforcements in the horizontal stabilizer (HS) central
box caused by a humid environment inside the box from water ingress
and/or condensation. This proposed AD would require a one-time detailed
inspection of the HS central box for corrosion; an assessment of the
corrosion level; and depending on the determination, repetitive
detailed inspections of the HS central box for corrosion and the
internal composite structure for surface cracks, distortion, and
damage; and repair or replacement of the HS assembly. Repair or
replacement of the HS assembly would be terminating action for the
repetitive inspections. The FAA is proposing this AD to address the
unsafe condition on these products.
DATES: The FAA must receive comments on this NPRM by October 23, 2023.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> 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.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2023-1819; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this NPRM, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
<bullet> For service information identified in this NPRM, contact
Piaggio Aviation S.p.A., P180 Customer Support, via Pionieri e Aviatori
d'Italia, snc--16154 Genoa, Italy; phone: +39 331 679 74 93; email:
<a href="/cdn-cgi/l/email-protection#8efaebede6e0e7edefe2fdfbfefee1fcfacefee7efe9e9e7e1efebfce1fdfeefedeba0e7fa"><span class="__cf_email__" data-cfemail="85f1e0e6edebece6e4e9f6f0f5f5eaf7f1c5f5ece4e2e2eceae4e0f7eaf6f5e4e6e0abecf1">[email protected]</span></a>.
<bullet> You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 901 Locust,
Kansas City, MO 64106. For information on the availability of this
material at the FAA, call (817) 222-5110.
FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (781)
238-7241; email: <a href="/cdn-cgi/l/email-protection#85f6f0ebe2e8eaabe1abe6edeac5e3e4e4abe2eaf3"><span class="__cf_email__" data-cfemail="bbc8ced5dcd6d495df95d8d3d4fbdddada95dcd4cd">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2023-1819; Project Identifier
MCAI-2023-00052-A'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
[[Page 61483]]
<a href="http://regulations.gov">regulations.gov</a>, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Sungmo Cho, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590. Any commentary that the FAA receives which is
not specifically designated as CBI will be placed in the public docket
for this rulemaking.
Background
The European Union Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Union, has issued
EASA AD 2023-0007, dated January 13, 2023 (referred to after this as
``the MCAI''), to correct an unsafe condition on certain serial-
numbered Piaggio Model P-180 airplanes.
The MCAI states that an occurrence of corrosion was found inside
the HS central box of a Piaggio Model P-180 airplane during scheduled
maintenance. A subsequent investigation and inspection of 16 other
Piaggio Model P-180 airplanes of various configurations and ages
revealed that corrosion of differing levels of severity was found on
various aluminum alloy reinforcements in the HS central box of all the
inspected airplanes. The MCAI also states that this corrosion was
caused by the formation of a humid environment inside the HS central
box, from water ingress and/or condensation. Further investigation
revealed that airplanes left in prolonged inactivity or parked outside
are more prone to develop corrosion damage.
To address the unsafe condition, the MCAI requires a one-time
detailed inspection of the HS central box for corrosion, contacting
Piaggio for a determination of the corrosion level, and depending on
that determination, repetitive detailed inspections of the HS central
box for corrosion and the internal composite structure for surface
cracks, distortion, and damage; and depending on the results, repair or
replacement of the HS assembly. The MCAI states that repair or
replacement of the HS assembly is terminating action for the repetitive
inspections.
This condition, if not addressed, could result in reduced
structural integrity of the HS, and loss of control of the airplane.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2023-1819.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Piaggio Aerospace Service Bulletin 80-0489,
Revision 2, dated November 30, 2022 (Piaggio SB 80-0489, Revision 2).
This service information specifies procedures for a one-time detailed
inspection of the HS central box for corrosion, a report of the
inspection results to Piaggio for a determination of the corrosion
level, repetitive inspections of the HS central box as needed, and
applicable corrective actions. The corrective actions include
installation of a serviceable HS assembly, which is terminating action
for the repetitive inspections.
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 ADDRESSES.
FAA's Determination
These products have been approved by the aviation authority of
another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with this State of Design
Authority, it has notified the FAA of the unsafe condition described in
the MCAI and service information described above. The FAA is issuing
this NPRM after determining that the unsafe condition described
previously is likely to exist or develop on other products of the same
type design.
Proposed AD Requirements in This NPRM
This proposed AD would require accomplishing the actions specified
in the MCAI, except as discussed under ``Differences Between this
Proposed AD and the MCAI.''
Differences Between This Proposed AD and the MCAI
The MCAI requires contacting the manufacturer for a determination
of the corrosion level if any corrosion is found during the initial
inspection of the HS central box, and if it is determined that level 2
or 3 corrosion is present, having the manufacturer provide the
threshold and intervals for doing repetitive inspections of the HS
central box. This proposed AD would require contacting either the FAA,
EASA, or Piaggio's EASA Design Organization Approval (DOA). If approved
by the DOA, the approval must include the DOA-authorized signature.
Although Piaggio SB 80-0489, Revision 2, specifies to record the
image of the location of corroded areas, this proposed AD would not
require that action.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 102 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Initial inspection of HS central box 6 work-hours x $85 per $0 $510 $52,020
for corrosion. hour = $510.
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[[Page 61484]]
On-Condition Costs
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Action Labor cost Parts cost Cost per product
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Repetitive inspections of HS central 6 work-hours x $85 per $0 $510, per inspection cycle.
box for corrosion. hour = $510, per
inspection cycle.
Repetitive inspections for surface 6 work-hours x $85 per 0 $510, per inspection cycle.
cracks, distortion, and damage. hour = $510.
Replace HS assembly.................. 10 work-hours x $85 per 150,000 $150,850.
hour = $850.
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The repair of the HS assembly that may be required as a result of
any inspection could vary significantly from airplane to airplane. The
FAA has no data to determine the costs to accomplish the repair or the
number of airplanes that may require the repair.
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.
The FAA is 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
The FAA 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) Would not affect intrastate aviation in Alaska, and
(3) Would 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 airworthiness
directive:
Piaggio Aviation S.p.A: Docket No. FAA-2023-1819; Project Identifier
MCAI-2023-00052-A.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by October 23, 2023.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Piaggio Aviation S.p.A. Model P-180
airplanes, serial numbers (S/Ns) 1002, 1004 through 1234 inclusive,
3001 through 3012 inclusive, and 3016, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code 5510, Horizontal
Stabilizer Structure.
(e) Unsafe Condition
This AD was prompted by a report of corrosion on the various
aluminum alloy reinforcements in the horizontal stabilizer (HS)
central box caused by a humid environment inside the box from water
ingress and/or condensation. The FAA is issuing this AD to address
this condition. The unsafe condition, if not addressed, could result
in reduced structural integrity of the HS and loss of control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within the applicable compliance time specified in Table 1
to paragraph (g)(1) of this AD, do a detailed inspection of the HS
central box for corrosion, in accordance with step (8), of Part A,
of the Accomplishment Instructions in Piaggio Aerospace Service
Bulletin 80-0489, Revision 2, dated November 30, 2022 (Piaggio SB
80-0489, Revision 2), except you are not required to record any
images.
Table 1 to Paragraph (g)(1)--HS Central Box One Time Inspection
------------------------------------------------------------------------
Compliance time (hours time-in-
service (TIS) or calendar time,
P-180 serial No. whichever occurs first after
the effective date of this AD)
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1002; and 1034 through 3016 inclusive.. Within 220 hours TIS or 13
months.
1004 through 1033 inclusive............ Within 320 hours TIS or 13
months.
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(2) If, during the inspection required by paragraph (g)(1) of
this AD, any corrosion is detected, before next flight, contact
either the Manager, International Validation Branch, FAA; European
Union Aviation Safety Agency (EASA); or Piaggio's EASA Design
Organization Approval (DOA), for an assessment of the corrosion
level (level 1, 2, or 3).
Note 1 to paragraph (g)(2): Appendix 1, Inspection Results Form,
in Piaggio SB 80-0489, Revision 2, may be used when contacting the
FAA, EASA, or Piaggio's EASA DOA.
[[Page 61485]]
(3) If level 1 corrosion is found during the inspection required
by paragraph (g)(1) of this AD, no further action is required by
this AD.
(4) If level 2 corrosion is found during the inspection required
by paragraph (g)(1) of this AD, do the action in either paragraph
(g)(4)(i) or (ii) of this AD.
(i) Before further flight replace the HS assembly or repair the
HS assembly in accordance with instructions from either the Manager,
International Validation Branch, FAA; EASA; or Piaggio's EASA DOA.
If approved by the DOA, the approval must include the DOA-authorized
signature.
(ii) Within 400 hours TIS or 12 months, whichever occurs first
after the inspection required by paragraph (g)(1) of this AD, and
thereafter at intervals not to exceed 400 hours TIS or 12 months,
whichever occurs first after the most recent inspection, repeat the
inspection required by paragraph (g)(1) of this AD. In addition,
inspect the internal composite structure of the HS central box for
surface cracks, distortion, and damage. After each repetitive
inspection, before further flight, assess the inspection findings as
required by paragraph (g)(2) of this AD. If it is determined that
the level 2 corrosion has worsened since the last inspection; or if
any surface cracks, distortion, or damage is found during any
inspection; before further flight, replace the HS assembly or repair
the HS assembly in accordance with instructions from either the
Manager, International Validation Branch, FAA; EASA; or Piaggio's
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature. These inspections must be repeated at
intervals not to exceed 400 hours TIS or 12 months, whichever occurs
first after the most recent inspection, until a maximum of 660 hours
TIS or 13 months, whichever occurs first after the inspection
required by paragraph (g)(1) of this AD has been reached, at which
time the HS assembly must be repaired or replaced.
(5) If level 3 corrosion is found during the inspection required
by paragraph (g)(1) of this AD, do the actions required by paragraph
(g)(5)(i) or (ii) of this AD.
(i) Before further flight after the inspection required by
paragraph (g)(1) of this AD, replace the HS assembly or repair the
HS assembly in accordance with instructions from either the Manager,
International Validation Branch, FAA; EASA; or Piaggio's EASA DOA.
If approved by the DOA, the approval must include the DOA-authorized
signature.
(ii) Within 200 hours TIS or 6 months, whichever occurs first
after the inspection required by paragraph (g)(1) of this AD, and
thereafter at intervals not to exceed 200 hours TIS or 6 months,
whichever occurs first after the most recent inspection, repeat the
inspection required by paragraph (g)(1) of this AD. In addition,
inspect the internal composite structure of the HS central box for
surface cracks, distortion, and damage. After each repetitive
inspection, before further flight, assess the inspection findings as
required by paragraph (g)(2) of this AD. If it is determined that
the level 3 corrosion has worsened since the last inspection; or if
any surface cracks, distortion, or damage is found; before further
flight, replace the HS assembly or repair the HS assembly in
accordance with instructions from either the Manager, International
Validation Branch, FAA; EASA; or Piaggio's EASA DOA. If approved by
the DOA, the approval must include the DOA-authorized signature.
These inspections must be repeated at intervals not to exceed 200
hours TIS or 6 months, whichever occurs first after the most recent
inspection, until a maximum of 660 hours TIS or 13 months, whichever
occurs first after the inspection required by paragraph (g)(1) of
this AD, at which time the HS assembly must be repaired or replaced.
(6) Repair or replacement of the HS assembly is terminating
action for the repetitive inspections required by paragraphs
(g)(4)(ii) and (g)(5)(ii) of this AD.
(h) Credit for Previous Actions
You may take credit for the actions required by paragraphs
(g)(1) through (5) of this AD if you performed those actions before
the effective date of this AD using Piaggio Aerospace Service
Bulletin 80-0489, Revision 1, dated May 13, 2022.
(i) Alternative Methods of Compliance (AMOCs)
The Manager, International Validation Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the International Validation Branch, mail
it to the address identified in paragraph (j)(2) of this AD or email
to: <a href="/cdn-cgi/l/email-protection#b48d99f5e2e799f5fde69983878499f5f9fbf7f4d2d5d59ad3dbc2"><span class="__cf_email__" data-cfemail="e3dacea2b5b0cea2aab1ced4d0d3cea2aeaca0a3858282cd848c95">[email protected]</span></a>. If mailing information, also submit
information by email. 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.
(j) Additional Information
(1) Refer to EASA AD 2023-0007, dated January 13, 2023, for
related information. This EASA AD may be found in the AD docket at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2023-1819.
(2) For more information about this AD, contact Sungmo Cho,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (781) 238-7241; email:
<a href="/cdn-cgi/l/email-protection#d4a7a1bab3b9bbfab0fab7bcbb94b2b5b5fab3bba2"><span class="__cf_email__" data-cfemail="b6c5c3d8d1dbd998d298d5ded9f6d0d7d798d1d9c0">[email protected]</span></a>.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (k)(3) and (4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference 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 Aerospace Service Bulletin 80-0489, Revision 2,
dated November 30, 2022.
(ii) [Reserved]
(3) For service information identified in this AD, contact
Piaggio Aviation S.p.A., P180 Customer Support, via Pionieri e
Aviatori d'Italia, snc--16154 Genoa, Italy; phone: +39 331 679 74
93; email: <a href="/cdn-cgi/l/email-protection#7d09181e1513141e1c110e080d0d120f093d0d141c1a1a14121c180f120e0d1c1e18531409"><span class="__cf_email__" data-cfemail="d5a1b0b6bdbbbcb6b4b9a6a0a5a5baa7a195a5bcb4b2b2bcbab4b0a7baa6a5b4b6b0fbbca1">[email protected]</span></a>.
(4) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 901
Locust, Kansas City, MO 64106. For information on the availability
of this material at the FAA, call (817) 222-5110.
(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, email: <a href="/cdn-cgi/l/email-protection#3254401c5b5c41425751465b5d5c725c5340531c555d44"><span class="__cf_email__" data-cfemail="4127336f282f3231242235282e2f012f2033206f262e37">[email protected]</span></a>, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on August 30, 2023.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2023-19092 Filed 9-6-23; 8:45 am]
BILLING CODE 4910-13-P
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