Airworthiness Directives; Costruzioni Aeronautiche Tecnam S.P.A Airplanes

[Federal Register Volume 90, Number 30 (Friday, February 14, 2025)]
[Rules and Regulations]
[Pages 9599-9601]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-02638]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-0202; Project Identifier MCAI-2024-00739-A; 
Amendment 39-22957; AD 2025-03-09]
RIN 2120-AA64


Airworthiness Directives; Costruzioni Aeronautiche Tecnam S.P.A 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Costruzioni Aeronautiche Tecnam S.P.A. (Tecnam) Model P2010 and 
P2010 TDI airplanes. This AD was prompted by the disconnection of a 
rudder pedals torque tube from one of its hinges. This AD requires 
modifying the airplane by installing larger diameter retainer washers 
on both the left-hand (LH) and right-hand (RH) rudder pedals torque 
tube hinges, installing new self-locking nuts, doing a functional or 
operating test of the system to ensure the retaining washers are 
installed properly, and applying a torque stripe on the LH and RH nuts 
and bolts threads. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective March 3, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 3, 
2025.
    The FAA must receive comments on this AD by March 31, 2025.

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 regulations.gov. 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 regulations.gov under 
Docket No. FAA-2025-0202; 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 
street address for Docket Operations is listed above.
    Material Incorporated by Reference:
    <bullet> For Tecnam material identified in this AD, contact TECNAM 
Costruzioni Aeronautiche S.p.A., Via Maiorise, 81043 Capua CE, Italy; 
phone: +39 0823 997538; email: tecnam.com">technical.support@tecnam.com; website: 
tecnam.com.
    <bullet> You may view this material 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-2025-0202.

FOR FURTHER INFORMATION CONTACT: Emma Copeland, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: (678) 227-4257; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2025-0202; Project Identifier MCAI-
2024-00739-A'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the final rule, 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 final rule 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 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this final rule.

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 AD contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and

[[Page 9600]]

that is relevant or responsive to this AD, 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 AD. Submissions containing 
CBI should be sent to Emma Copeland, 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 
AD 2024-0239, dated December 10, 2024 (EASA AD 2024-0239) (also 
referred to as the MCAI), to correct an unsafe condition on certain 
serial-numbered Tecnam Model P2010 and P2010 TDI airplanes, except 
those on which Tecnam Modification MOD2010/359 has been embodied. The 
MCAI states that an occurrence was reported of the disconnection of a 
rudder pedals torque tube from one of its hinges. The unsafe condition, 
if not addressed, could result in the rudder pedals assembly slipping 
out of its housing, resulting in the inability of the flightcrew to 
maintain the safe flight and landing of the airplane and loss of 
control of the airplane. To address the unsafe condition, Tecnam 
designed Modification MOD2010/359, which introduces larger diameter 
retainer washers on the LH and RH rudder pedals torque tube hinges, and 
issued a modification service bulletin for in-service airplanes. EASA 
issued the MCAI to require modification of in-service airplanes.
    The FAA is issuing this AD to address the unsafe condition on these 
products. You may examine the MCAI in the AD docket at regulations.gov 
under Docket No. FAA-2025-0202.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed TECNAM Service Bulletin No. 817-CS-Ed. 1, Rev. 1, 
dated December 11, 2024 (TECNAM SB 817-CS-Ed. 1, Rev. 1). This material 
specifies procedures for modifying the LH and RH rudder pedals torque 
tube hinges by installing larger diameter retainer washers on the LH 
and RH rudder pedals torque tube hinges.
    This material is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

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 material referenced above. The FAA is issuing this AD 
after determining that the unsafe condition described previously is 
likely to exist or develop on other products of the same type design.

AD Requirements

    This AD requires accomplishing the actions specified in TECNAM SB 
817-CS-Ed. 1, Rev. 1, described previously.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b) of the Administrative Procedure Act (APA) (5 U.S.C. 
551 et seq.) authorizes agencies to dispense with notice and comment 
procedures for rules when the agency, for ``good cause,'' finds that 
those procedures are ``impracticable, unnecessary, or contrary to the 
public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies foregoing notice and comment prior to adoption of this rule 
because a rudder pedal torque tube disconnecting from one of its hinges 
could cause the rudder pedals assembly to slip out of its housing 
resulting in the inability of the flightcrew to maintain the safe 
flight and landing of the airplane. Since this condition can result 
rapidly and without warning, the FAA has determined that the rudder 
pedal torque tube hinges must be modified within 25 hours time-in-
service or 30 days, whichever occurs first after the effective date of 
this AD. These compliance times are shorter than the time necessary for 
the public to comment and for publication of the final rule. 
Accordingly, notice and opportunity for prior public comment are 
impracticable and contrary to the public interest pursuant to 5 U.S.C. 
553(b).
    In addition, the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days, 
for the same reasons the FAA found good cause to forgo notice and 
comment.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 100 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modify the airplane (including          1 work-hour x $85 per                $30            $115         $11,500
 installing larger diameter retainer     hour = $85.
 washers, installing new self-locking
 nuts, doing a functional or operating
 test of the system, and applying a
 torque stripe on the LH and RH nuts
 and bolts threads).
----------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected operators.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue

[[Page 9601]]

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, and
    (2) Will not affect intrastate aviation in Alaska.

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

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:

2025-03-09 Costruzioni Aeronautiche Tecnam S.P.A.: Amendment 39-
22957; Docket No. FAA-2025-0202; Project Identifier MCAI-2024-00739-
A.

(a) Effective Date

    This airworthiness directive (AD) is effective March 3, 2025.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Costruzioni Aeronautiche Tecnam S.P.A. 
(Tecnam) Model P2010 and P2010 TDI airplanes, all serial numbers (S/
Ns) up to and including S/N 317, certificated in any category, 
except those on which the Tecnam modification MOD2010/359 has been 
installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 2720, Rudder Control 
System.

(e) Unsafe Condition

    This AD was prompted by the disconnection of a rudder pedals 
torque tube from one of its hinges. The FAA is issuing this AD to 
address the unsafe condition. The unsafe condition, if not 
addressed, could result in the rudder pedals assembly slipping out 
of its housing, resulting in the inability of the flightcrew to 
maintain the safe flight and landing of the airplane and loss of 
control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    Within 25 hours time-in-service or 30 days, whichever occurs 
first after the effective date of this AD, modify your airplane by 
installing larger diameter retainer washers on the left-hand (LH) 
and right-hand (RH) rudder pedals torque tube hinges, installing new 
self-locking nuts, doing a functional or operating test of the 
system to ensure the retaining washers are installed properly and do 
not interfere with the lugs, and applying a torque stripe on the LH 
and RH nuts and bolts threads, in accordance with steps N 3, 4, 5, 
6, and 7 of Appendix B, Accomplishment Instructions, in TECNAM 
Service Bulletin No. 817-CS-Ed. 1, Rev. 1, dated December 11, 2024.

(h) Special Flight Permits

    A one-time special flight permit may be issued in accordance 
with 14 CFR 21.197 and 21.199 in order to fly to a maintenance base 
to perform the required action in this AD provided it is a non-
revenue flight and limited to only essential flight crew.

(i) Credit for Previous Actions

    You may take credit for the actions required by paragraph (g) of 
this AD if you performed those actions before the effective date of 
this AD using TECNAM Service Bulletin No. 817-CS-Ed. 1, Rev. 0, 
dated December 6, 2024.

(j) 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, send 
it to the attention of the person identified in paragraph (k)(1) of 
this AD and email to: [email protected]. 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.

(k) Additional Information

    (1) For more information about this AD, contact Emma Copeland, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (678) 227-4257; email: 
[email protected].
    (2) Material identified in this AD that is not incorporated by 
reference is available at the address specified in paragraph (l)(3) 
of this AD.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the material listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless the AD specifies otherwise.
    (i) TECNAM Service Bulletin No. 817-CS-Ed. 1, Rev. 1, dated 
December 11, 2024.
    (ii) [Reserved]
    (3) For Tecnam material identified in this AD, contact TECNAM 
Costruzioni Aeronautiche S.p.A., Via Maiorise, 81043 Capua CE, 
Italy; phone: +39 0823 997538; email: tecnam.com">technical.support@tecnam.com; 
website: tecnam.com.
    (4) You may view this material 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 material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on February 7, 2025.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2025-02638 Filed 2-13-25; 8:45 am]
BILLING CODE 4910-13-P

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