Airworthiness Directives; Vulcanair S.p.A. Airplanes

[Federal Register Volume 88, Number 182 (Thursday, September 21, 2023)]
[Rules and Regulations]
[Pages 65122-65125]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-20481]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-1218; Project Identifier MCAI-2022-01025-A; 
Amendment 39-22536; AD 2023-17-10]
RIN 2120-AA64


Airworthiness Directives; Vulcanair S.p.A. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Vulcanair S.p.A. Model V1.0 airplanes. This 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 identifies the unsafe 
condition as corrosion on the lower fuselage truss. This AD requires a 
detailed visual inspection of the right-hand (RH) and left-hand (LH) 
lower rear attachments of the fuselage truss for

[[Page 65123]]

corrosion, a tactile inspection of the lower rear attachments for 
missing sealant, and a general visual inspection of the lower fuselage 
truss welded pipes for corrosion and the related rivets for missing 
stems and, depending on findings, additional inspections and actions 
(including a tap test) and applicable corrective actions. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective October 26, 2023.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 26, 
2023.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2023-1218; 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 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:
    <bullet> For service information identified in this final rule, 
contact Vulcanair S.p.A., via G. Pascoli, 7, 80026 Casoria (NA), Italy; 
phone: +39 081 5918111; email: [email protected]; website: 
support.vulcanair.com.
    <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. It is also available at 
regulations.gov under Docket No. FAA-2023-1218.

FOR FURTHER INFORMATION CONTACT: John DeLuca, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (516) 
228-7369; email: [email protected].

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 Vulcanair 
S.p.A. Model V1.0 airplanes. The NPRM published in the Federal Register 
on June 27, 2023 (88 FR 41510). The NPRM was prompted by AD 2022-0155, 
dated August 1, 2022 (referred to after this 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 there have been reports of corrosion on the lower fuselage 
truss on two Vulcanair Model V1.0 airplanes. Missing sealant or missing 
rivet stems were determined to be the root cause of corrosion by 
allowing water ingress into the lower fuselage truss. In both reported 
cases, corrosion was externally visible, having penetrated the 
thickness of the pipes. However, corrosion could be present inside the 
pipes and remain undetected without proper inspection. This condition, 
if not detected and corrected, could result in loss of control of the 
airplane.
    In the NPRM, the FAA proposed to require a detailed visual 
inspection of the RH and LH lower rear attachments of the fuselage 
truss for corrosion, a tactile inspection of the lower rear attachments 
for missing sealant, and a general visual inspection of the lower 
fuselage truss welded pipes for corrosion and the related rivets for 
missing stems and, depending on findings, additional inspections and 
actions (including a tap test) and applicable corrective actions. The 
FAA is issuing this AD to address the unsafe condition on these 
products. The unsafe condition, if not addressed, could result in loss 
of control of the airplane.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2023-1218.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

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 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 Vulcanair S.p.A. Service Bulletin No. VA-22, 
Revision 0, dated June 15, 2022 (Vulcanair SB VA-22). This service 
information specifies procedures for inspections of the lower fuselage 
truss for corrosion, missing sealant, and missing rivet stems; and, in 
case of findings, additional inspections and actions to detect 
corrosion, including a tap test and raising the airplane nose. This 
service information specifies to contact Vulcanair for corrective 
actions.
    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

    Although Vulcanair SB VA-22, which is referenced in the MCAI, 
specifies that ``in case of doubts, raise the aircraft nose and audibly 
detect the presence of corrosion residues inside the fuselage truss,'' 
this AD does not require that action.
    Paragraph (1) of the MCAI states to ``accomplish a general visual 
and tactile inspection of the right-hand (RH) and left-hand (LH) lower 
rear attachments of the fuselage truss'' in accordance with the 
instructions of Part A of Vulcanair SB VA-22. However, step 14, Part A, 
of Vulcanair SB VA-22 specifies to do a detailed visual inspection. In 
email communication between EASA and the FAA, EASA clarified that this 
should be a detailed visual inspection performed in accordance with the 
procedures specified in Vulcanair SB VA-22; therefore, this AD requires 
a detailed visual inspection of the RH and LH lower rear attachments of 
the fuselage truss for corrosion.
    The MCAI requires contacting the manufacturer for approved 
corrective action instructions if any corrosion is found on the lower 
fuselage truss. This AD requires contacting either the Manager, 
International Validation Branch, FAA; or EASA; or Vulcanair's EASA 
Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.

Costs of Compliance

    The FAA estimates that this AD affects 17 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

[[Page 65124]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Detailed visual inspection and        8 work-hours x $85 per               $0             $680          $11,560
 tactile inspection of the RH and LH   hour = $680.
 lower rear attachments, and a
 general visual inspection of the
 pipes.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary actions 
that would be required based on the results of the required 
inspections.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Remove sealant and detailed inspection of       4 work-hours x $85 per hour =                 $0            $340
 inner face of longitudinal tubes connected to   $340.
 lower rear attachments.
Detailed visual inspection and tap test of the  4 work-hours x $85 per hour =                  0             340
 lower fuselage truss pipes.                     $340.
Installation of plug P/N 5034-011 on RH and LH  0.50 work-hour x $85 per hour =              130          172.50
 lower rear attachments.                         $42.50.
----------------------------------------------------------------------------------------------------------------

    The corrective action instructions that may be needed as a result 
of these inspections could vary significantly from airplane to 
airplane. The FAA has no data to determine the costs to accomplish 
those corrective actions or the number of airplanes that might need 
these corrective actions.

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

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:

2023-17-10 Vulcanair S.p.A.: Amendment 39-22536; Docket No. FAA-
2023-1218; Project Identifier MCAI-2022-01025-A.

(a) Effective Date

    This airworthiness directive (AD) is effective October 26, 2023.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Vulcanair S.p.A. Model V1.0 airplanes, serial 
numbers (S/Ns) 1001 through 1034 inclusive, except S/Ns 1008 and 
1019, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 5311, Fuselage Main, 
Frame.

(e) Unsafe Condition

    This AD was prompted by 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 identifies the unsafe condition as corrosion on 
the lower fuselage truss. The FAA is issuing this AD to address the 
unsafe condition. The unsafe condition, if not addressed, could 
result in loss of control of the airplane.

(f) Compliance

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

(g) Required Actions

    Within 100 hours time-in-service or 12 months after the 
effective date of this AD, whichever occurs first, do a detailed 
visual inspection of the right-hand (RH) and left-hand (LH) lower 
rear attachments of the fuselage truss for corrosion, a tactile 
inspection of the RH and LH lower rear attachments of the fuselage 
truss for missing sealant, a general visual inspection of the pipes 
on the lower fuselage truss for corrosion, and a general visual 
inspection of the pipes on the lower fuselage truss for rivets with 
missing stems, in accordance with steps 13 and 14 of Part A, in Part 
2, Work Procedure, of Vulcanair S.p.A. Service Bulletin No. VA-22, 
Revision 0, dated June 15, 2022 (Vulcanair SB VA-22).
    (1) If, during the inspections required by the introductory text 
of paragraph (g) of this AD, no missing sealant and no corrosion of

[[Page 65125]]

the LH and RH lower rear attachments are detected, and no corrosion 
and no missing rivet stems of the lower fuselage truss pipes are 
detected, before further flight, install part number (P/N) 5034-011 
plugs on both the RH and LH rear attachments, in accordance with 
step 16 of Part A, in Part 2, Work Procedure, of Vulcanair SB VA-22. 
After installation of the plugs, no further action is required by 
this AD.
    (2) If, during the inspections required by the introductory text 
of paragraph (g) of this AD, corrosion, missing sealant, or missing 
rivet stems are detected, before further flight, do the following as 
applicable:
    (i) If corrosion or missing sealant is detected during the 
detailed visual inspection or tactile inspection of the RH and LH 
lower rear attachments, remove any sealant, and do a detailed visual 
inspection for corrosion in accordance with step 26 of Part B, in 
Part 2, Work Procedure, of Vulcanair SB VA-22.
    (ii) If corrosion or missing rivet stems are detected during the 
general visual inspection of the lower fuselage truss pipes, do a 
detailed visual inspection and tap test for corrosion in accordance 
with steps 27 and 28 of Part B, in Part 2, Work Procedure, of 
Vulcanair SB VA-22.
    (3) If, during any inspection required by paragraph (g)(2) of 
this AD, any corrosion is detected on the lower fuselage truss, 
before further flight, contact the Manager, International Validation 
Branch, FAA; or European Union Aviation Safety Agency (EASA); or 
Vulcanair's EASA Design Organization Approval (DOA) for corrective 
action instructions and do the corrective actions. If approved by 
the DOA, the approval must include the DOA-authorized signature.
    (4) If, during the inspections required by paragraph (g)(2) of 
this AD, no corrosion is detected, before further flight, apply 
sealant on rivets with absent stems, restore as necessary the 
sealant inside the RH and LH lower rear attachments, and install 
plugs P/N 5034-011 on both the RH and LH rear attachments, in 
accordance with the instructions in steps 31 and 32 of Part B, in 
Part 2, Work Procedure, of Vulcanair SB VA-22.

(h) Special Flight Permits

    Special flight permits are prohibited.

(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: [email protected]. 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 2022-0155, dated August 1, 2022, for 
related information. This EASA AD may be found in the AD docket at 
regulations.gov under Docket No. FAA-2023-1218.
    (2) For more information about this AD, contact John DeLuca, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (516) 228-7369; email: 
[email protected].

(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) Vulcanair S.p.A. Service Bulletin No. VA-22, Revision 0, 
dated June 15, 2022.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Vulcanair S.p.A., via G. Pascoli, 7, 80026 Casoria (NA), Italy; 
phone: +39 081 5918111; email: [email protected]; website: 
support.vulcanair.com.
    (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: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on September 18, 2023.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2023-20481 Filed 9-20-23; 8:45 am]
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