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2023-25-03 PIAGGIO AVIATION S.P.A.: Amendment 39-22630; Docket No. FAA-2023-1819; Project Identifier MCAI-2023-00052-A.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective February 2, 2024.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This  AD applies  to Piaggio  Aviation S.p.A.  Model P-180  airplanes,
    serial numbers 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 al-
    ready done.

(g) REQUIRED ACTIONS

(1) Within the applicable compliance time  specified  in  Table 1 to para-
    graph (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   
    ______________________________________________________________________
         P-180 SERIAL NUMBER             COMPLIANCE TIME (HOURS TIME-IN-
                                         SERVICE (TIS) OR CALENDAR TIME,
                                         WHICHEVER OCCURS FIRST AFTER THE
                                         EFFECTIVE DATE OF THIS AD)
    ______________________________________________________________________
    1002; and 1034 through 3016          Within 220 hours TIS or 13 months
    inclusive

    1004 through 1033 inclusive          Within 320 hours TIS or 13 months
    ______________________________________________________________________

(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.

(3) If level 1 corrosion is found  during the inspection required by para-
    graph (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 para-
    graph (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 assem-
    bly in accordance with instructions from either the Manager,  Interna-
    tional 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 para-
    graph (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 in
     -spection 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:  9-AVS-AIR-730-AMOC@faa.gov.
    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 infor-
    mation.  This EASA AD may be found in the AD docket at regulations.gov
    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: sungmo.d.cho@faa.gov.

(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: technicalsupport@
    piaggioaerospace.it.

(4) You may view this service information at the FAA,  Airworthiness Prod-
    ucts 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 material at the National Archives and Records Admin-
    istration (NARA). For information on the availability of this material
    at NARA,  visit www.archives.gov/federal-register/cfr/ibr-locations or
    email fr.inspection@nara.gov.

Issued on December 8, 2023. Victor Wicklund, Deputy Director, Compliance &
Airworthiness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer, FAA
1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (781) 238-7241;
email: sungmo.d.cho@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-1819; Project Identifier MCAI-2023-00052-A;
Amendment 39-22630; AD 2023-25-03]
RIN 2120-AA64

Airworthiness Directives; Piaggio Aviation S.p.A. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Piaggio Aviation S.p.A. (Piaggio) Model P-180 airplanes. This
AD is 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 AD requires 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 is
terminating action for the repetitive inspections. The FAA is issuing
this AD to address the unsafe condition on these products.

DATES: This AD is effective February 2, 2024.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of February 2,
2024.

ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov
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 final rule, the mandatory
continuing airworthiness information (MCAI), any comments received, and
other information. The address for Docket Operations is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
Material Incorporated by Reference:
For service information identified in this final rule,
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: technicalsupport@piaggioaerospace.it.
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. It is also available at
regulations.gov under Docket No. FAA-2023-1819.

FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (781)
238-7241; email: sungmo.d.cho@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain serial-numbered
Piaggio Model P-180 airplanes. The NPRM published in the Federal
Register on September 7, 2023 (88 FR 61482). The NPRM was prompted by
AD 2023-0007, dated January 13, 2023 (also referred to as the MCAI),
issued by the European Union Aviation Safety Agency (EASA), which is
the Technical Agent for the Member States of the European Union. 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.
In the NPRM, the FAA proposed to 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 is terminating action for the repetitive
inspections.
The FAA is issuing this AD to address corrosion on the various
aluminum alloy reinforcements in the HS central box. The unsafe
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 regulations.gov under
Docket No. FAA-2023-1819.

Discussion of Final Airworthiness Directive

Comments

The FAA received a comment from one individual commenter. The
commenter supported the NPRM and requested a change. The following
presents the comment received on the NPRM and the FAA's response to the
comment.

Request To Revise Costs of Compliance Section of the NPRM

An individual commenter requested that the FAA contact Piaggio for
the exact price per unit of replacement
parts. The commenter explained that this would provide operators with a
more accurate estimate of the NPRM's economic effect and allow
operators to be financially prepared.
The FAA disagrees with the commenter's request because the
estimated cost for a replacement HS assembly provided in this final
rule is based on a cost estimate from Piaggio. Accordingly, the FAA
considers the cost estimates provided in this final rule to be
sufficient and the FAA has not changed this AD regarding this issue.

Conclusion

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 referenced above. The FAA reviewed the relevant data,
considered the comment received, and determined that air safety
requires adopting this AD as proposed. Accordingly, the FAA is issuing
this AD to address the unsafe condition on these products. This AD is
adopted as proposed in the NPRM.

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.

Differences Between This 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 AD requires 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 AD does not require that
action.

Costs of Compliance

The FAA estimates that this AD affects 102 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:

Estimated Costs

Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Initial inspection of HS central box for corrosion 6 work-hours x $85 per hour = $510
$0
$510
$52,020

On-Condition Costs

Action
Labor cost
Parts cost
Cost per product
Repetitive inspections of HS central box for corrosion 6 work-hours x $85 per hour = $510, per inspection cycle $0 $510, per inspection cycle
Repetitive inspections for surface cracks, distortion, and damage 6 work-hours x $85 per hour = $510 0 $510, per inspection cycle
Replace HS assembly 10 work-hours x $85 per hour = $850 150,000 $150,850

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

This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) 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 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.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive: