Airworthiness Directives; Vulcanair S.p.A. Airplanes, 1340-1343 [2022-00056]

Download as PDF 1340 Federal Register / Vol. 87, No. 7 / Tuesday, January 11, 2022 / Rules and Regulations features installed: After modification or reidentification, as applicable, of the airplane as required by paragraph (g) of this AD. (2) For airplanes that have PSUs or life vest panels with the secondary retention features installed: As of the effective date of this AD. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive (AD) 2019–03–26, Amendment 39– 19578 (84 FR 7266, March 4, 2019); and ■ b. Adding the following new AD: ■ ■ 2021–26–17 The Boeing Company: Amendment 39–21876; Docket No. FAA–2021–0504; Project Identifier AD– 2020–01380–T. (a) Effective Date This airworthiness directive (AD) is effective February 15, 2022. (b) Affected ADs This AD replaces AD 2019–03–26, Amendment 39–19578 (84 FR 7266, March 4, 2019) (AD 2019–03–26). (c) Applicability This AD applies to The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes, certificated in any category, without a Boeing Sky Interior (BSI). (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/furnishings. (e) Unsafe Condition This AD was prompted by reports of passenger service units (PSUs) becoming detached from the supporting airplane structure in several Model 737 series airplanes during survivable accidents. The FAA is issuing this AD to address PSUs and life vest panels detaching from the supporting airplane structure, which could lead to passenger injuries and impede passenger and crew egress during evacuation. (f) Compliance Comply with this AD within the compliance times specified, unless already done. khammond on DSKJM1Z7X2PROD with RULES (g) Required Actions Within 60 months after April 8, 2019 (the effective date of AD 2019–03–26), do all applicable actions identified as ‘‘RC’’ (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–25–1707, Revision 2, dated July 27, 2020. (h) Parts Installation Limitation As of the applicable time specified in paragraph (h)(1) or (2) of this AD, no person may install on any airplane a PSU or life vest panel, unless the lanyard assembly has been modified (secondary retention features added) or re-identified, as applicable, as required by paragraph (g) of this AD. (1) For airplanes that have PSUs or life vest panels without the secondary retention VerDate Sep<11>2014 17:25 Jan 10, 2022 Jkt 256001 (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by The Boeing Company Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2019–03–26 are approved as AMOCs for the corresponding provisions of Boeing Special Attention Service Bulletin 737–25–1707, Revision 2, dated July 27, 2020, that are required by paragraph (g) of this AD. (j) Related Information For more information about this AD, contact Tony Koung, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3985; email: tony.koung@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) 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) Boeing Special Attention Service Bulletin 737–25–1707, Revision 2, dated July 27, 2020. (ii) [Reserved] (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https:// www.myboeingfleet.com. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 availability of this material at the FAA, call 206–231–3195. (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 fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on December 13, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–00031 Filed 1–10–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0871; Project Identifier MCAI–2020–01581–A; Amendment 39–21874; AD 2021–26–15] RIN 2120–AA64 Airworthiness Directives; Vulcanair S.p.A. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain km, Vulcanair S.p.A. Model P.68C, P.68C–TC, P.68 ‘‘OBSERVER,’’ P.68 OBSERVER 2, P.68R, and P.68TC OBSERVER airplanes. 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 a damaged stabilator trim control cable. This AD requires inspecting the stabilator trim control cables and replacing if necessary. This AD also requires reporting the results of each inspection to Vulcanair S.p.A. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 15, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 15, 2022. ADDRESSES: For service information identified in this final rule, contact Vulcanair S.p.A., Fulvio Oloferni, via Giovanni Pascoli, 7, Naples, 80026, Italy; phone: +39 081 5918 135; email: airworthiness@vulcanair.com; website: www.vulcanair.com. You may view this service information at the FAA, SUMMARY: E:\FR\FM\11JAR1.SGM 11JAR1 Federal Register / Vol. 87, No. 7 / Tuesday, January 11, 2022 / Rules and Regulations 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 https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0871. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0871; 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. FOR FURTHER INFORMATION CONTACT: Gregory Johnson, Aviation Safety Engineer, International Validation Section, FAA, 901 Locust, Room 301, Kansas City, MO 64106; phone: (720) 626–5462; email: gregory.johnson@ 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 Vulcanair S.p.A. Model P.68C, P.68C– TC, P.68 ‘‘OBSERVER,’’ P.68 OBSERVER 2, P.68R, and P.68TC OBSERVER airplanes. The NPRM published in the Federal Register on October 8, 2021 (86 FR 56229). The NPRM was prompted by MCAI originated by the European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. EASA issued EASA AD 2020–0262, dated November 30, 2020 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition on certain serial-numbered Vulcanair S.p.A. Model P.68R, P.68C, P.68C–TC, P.68 ‘‘OBSERVER,’’ P.68 ‘‘OBSERVER 2,’’ and P.68TC ‘‘OBSERVER’’ airplanes. The MCAI states: Two occurrences have been reported of finding a damaged stabilator trim control cable connected to the stabilator trim actuator assembly, mounted on fuselage frame No.16. The related technical investigation concluded that the cause of the damage is a design issue. This condition, if not detected and corrected, could lead to failure of an affect [sic] part, preventing trim surface control (remaining in the last position), possibly resulting in reduced control of the aeroplane. To address this potential unsafe condition, and pending a design improvement, Vulcanair published the [service bulletin] SB, to provide inspection instructions for detecting damage. For the reasons described above, this [EASA] AD requires repetitive inspections of the affected parts, and, depending on findings, replacement. This [EASA] AD is considered to be an interim action and further [EASA] AD action may follow. You may examine the MCAI in the AD docket at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0871. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the costs. 1341 country and is 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 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. P.68 Variants Service Bulletin No. 263, dated October 20, 2020. The service information contains procedures for repetitively inspecting each stabilator trim control cable part number 5.6067– 1, 5.6161–1, 5.6171–1, 5.6231–2, or 5.6231–4 for broken wires and replacing the cable if necessary. 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 the ADDRESSES section. Interim Action The FAA considers this AD an interim action. The inspection reports required by this AD will enable the manufacturer to obtain better insight into the nature, cause, and extent of the damage, and eventually to develop final action to address the unsafe condition. Once final action has been identified, the FAA might consider further rulemaking. Costs of Compliance Conclusion The FAA estimates that this AD affects 127 airplanes of U.S. registry. This product has been approved by the aviation authority of another The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspection ......... 0.50 work-hour × $85 per hour = $42.50 per inspection cycle. 1 work-hour × $85 per hour = $85 per reporting cycle. khammond on DSKJM1Z7X2PROD with RULES Report ............... Parts cost The FAA estimates the following costs to do any replacements that would VerDate Sep<11>2014 17:25 Jan 10, 2022 Jkt 256001 $0 $42.50 per inspection cycle .......... $5,397.50 per inspection cycle. $0 $85 per inspection cycle ............... $10,795 per inspection cycle. be required based on the results of the inspection. The FAA has no way of PO 00000 Frm 00025 Cost on U.S. operators Cost per airplane Fmt 4700 Sfmt 4700 determining the number of airplanes that might need this replacement: E:\FR\FM\11JAR1.SGM 11JAR1 1342 Federal Register / Vol. 87, No. 7 / Tuesday, January 11, 2022 / Rules and Regulations ON-CONDITION COSTS Action Labor cost Replacement .... 2 work-hours × $85 per hour = $170 ....................................................................................... khammond on DSKJM1Z7X2PROD with RULES Paperwork Reduction Act 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 currently 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 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177–1524. 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 VerDate Sep<11>2014 17:25 Jan 10, 2022 Jkt 256001 Parts cost Cost per airplane $340 $510 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. (e) Unsafe Condition This AD was prompted by a damaged stabilator trim control cable connected to the stabilator trim actuator assembly, mounted on fuselage frame No. 16. The FAA is issuing this AD to detect and address failure of a stabilator trim control cable, which could prevent trim surface control thereby leaving the cable remaining in the last position. The unsafe condition, if not addressed, could result in reduced control of the airplane. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (g) Required Actions Before a stabilator trim control cable part number 5.6067–1, 5.6161–1, 5.6171–1, 5.6231–2, or 5.6231–4 accumulates more than 400 hours time-in-service (TIS) since first installation on an airplane or within 50 hours TIS after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 50 hours TIS, visually inspect the stabilator trim control cable for broken wires and replace the stabilator trim control cable before further flight if there is broken wire in a strand in accordance with steps 1 through 22 of Part 2 Work Procedure in Vulcanair S.p.A. P.68 Variants Service Bulletin No. 263, dated October 20, 2020. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2021–26–15 Vulcanair S.p.A.: Amendment 39–21874; Docket No. FAA–2021–0871; Project Identifier MCAI–2020–01581–A. (a) Effective Date This airworthiness directive (AD) is effective February 15, 2022. (b) Affected ADs None. (c) Applicability This AD applies to Vulcanair S.p.A. (Vulcanair) Model P.68C, P.68C–TC, P.68 ‘‘OBSERVER,’’ P.68 OBSERVER 2, P.68R, and P.68TC OBSERVER airplanes, serial numbers 333, 337 to 339 inclusive, 378, 379, and 383 and larger (except serial numbers 387 and 398), certificated in any category, with a stabilator trim control cable part number 5.6067–1, 5.6161–1, 5.6171–1, 5.6231–2, or 5.6231–4 installed. (d) Subject Joint Aircraft System Component (JASC) Code 2740, Stabilizer Control System. PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (h) Reporting Within 14 days after the initial inspection required by paragraph (g) of this AD or within 14 days after the effective date of this AD, whichever occurs later, report the results of the initial inspection to Vulcanair at continued.airworthiness@vulcanaair.com or at the address in paragraph (l)(3) of this AD. Thereafter, report the inspection results within 14 days after each inspection. Each report must include the following information: (1) Owner/operator name, mailing address, phone number, and email address; (2) Airplane model, serial number, and registration number; (3) Airplane hours TIS at the time of the inspection; (4) Stabilator trim control cable hours TIS at the time of the inspection; (5) Date of the inspection; (6) Inspection result (positive or negative); and (7) A description of any non-conformity (damage). (i) Special Flight Permit Special flight permits are prohibited. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the E:\FR\FM\11JAR1.SGM 11JAR1 Federal Register / Vol. 87, No. 7 / Tuesday, January 11, 2022 / Rules and Regulations 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 certification office, send it to the attention of the person identified in paragraph (k)(1) of this AD and email to: 9-AVS-AIR-730-AMOC@faa.gov. (2) 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) Related Information (1) For more information about this AD, contact Gregory Johnson, Aviation Safety Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Section, 901 Locust, Room 301, Kansas City, MO 64106; phone: (720) 626–5462; email: gregory.johnson@faa.gov. (2) Refer to European Union Aviation Safety Agency (EASA) AD 2020–0262, dated November 30, 2020, for more information. You may examine the EASA AD in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA– 2021–0871. khammond on DSKJM1Z7X2PROD with RULES (l) 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. P.68 Variants Service Bulletin No. 263, dated October 20, 2020. (ii) [Reserved] (3) For service information identified in this AD, contact Vulcanair S.p.A., Fulvio Oloferni, via Giovanni Pascoli, 7, Naples, 80026, Italy; phone: +39 081 5918 135; email: airworthiness@vulcanair.com; website: www.vulcanair.com. (4) You may view this service information at 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: fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on December 10, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–00056 Filed 1–10–22; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 17:25 Jan 10, 2022 Jkt 256001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0567; Project Identifier AD–2021–00663–E; Amendment 39–21865; AD 2021–26–06] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90 model turbofan engines. This AD was prompted by two separate in-flight shutdowns (IFSDs) resulting from failure of the transfer gearbox (TGB) radial bevel gear (TGB radial gearshaft). This AD requires visual inspection of the TGB radial gearshaft and, depending on the results of the inspection, replacement of the TGB radial gearshaft. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 15, 2022. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 15, 2022. ADDRESSES: For service information identified in this final rule, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: (513) 552–3272; email: aviation.fleetsupport@ge.com; website: https://www.ge.com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (817) 222– 5110. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0567. SUMMARY: Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0567; 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, 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 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 1343 W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Stephen Elwin, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7236; fax: (781) 238– 7199; email: Stephen.L.Elwin@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 all GE GE90–76B, GE90–85B, GE90–90B, GE90–94B, GE90–110B1, and GE90–115B model turbofan engines with a certain TGB radial gearshaft installed. The NPRM published in the Federal Register on August 12, 2021 (86 FR 44321). The NPRM was prompted by notification of two separate IFSDs resulting from the failure of the TGB radial gearshaft. After further investigation, the manufacturer determined that rework on the TGB radial gearshaft teeth chamfers during manufacturing may have caused local burrs and micro-cracks which led to high-cycle fatigue failure. GE subsequently issued service information to provide instructions for a one-time visual inspection of the affected radial gearshafts for the presence of burrs or rework on TGB radial gearshaft teeth chamfers. In the NPRM, the FAA proposed to require visual inspection of the TGB radial gearshaft and, depending on the results of the inspection, replacement of the TGB radial gearshaft. The FAA is issuing this AD to address the unsafe condition on these products. Discussion of Final Airworthiness Directive Comments The FAA received comments from 5 commenters. The commenters were Air Line Pilots Association, International, The Boeing Company, FedEx Express, Japan Airlines (JAL), and United Airlines. The following presents the comments received on the NPRM and the FAA’s response to each comment. Question on the Difference Between This AD and the Service Information JAL asked why there is a difference between the affected serial numbers (S/ Ns) in this AD and the related service bulletins (SBs). The FAA notes that the applicable SBs include several populations of TGB radial gearshafts. The FAA determined that TGB radial gearshafts with S/Ns starting with prefix FIAAXXXX, FIA05XXX to FIA09XXX, or FIA0AXXX to FIA0NXXX are not subject to the E:\FR\FM\11JAR1.SGM 11JAR1

Agencies

[Federal Register Volume 87, Number 7 (Tuesday, January 11, 2022)]
[Rules and Regulations]
[Pages 1340-1343]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-00056]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0871; Project Identifier MCAI-2020-01581-A; 
Amendment 39-21874; AD 2021-26-15]
RIN 2120-AA64


Airworthiness Directives; Vulcanair 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 km, Vulcanair S.p.A. Model P.68C, P.68C-TC, P.68 ``OBSERVER,'' 
P.68 OBSERVER 2, P.68R, and P.68TC OBSERVER airplanes. 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 a damaged stabilator trim control cable. This 
AD requires inspecting the stabilator trim control cables and replacing 
if necessary. This AD also requires reporting the results of each 
inspection to Vulcanair S.p.A. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective February 15, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 15, 
2022.

ADDRESSES: For service information identified in this final rule, 
contact Vulcanair S.p.A., Fulvio Oloferni, via Giovanni Pascoli, 7, 
Naples, 80026, Italy; phone: +39 081 5918 135; email: 
[email protected]; website: www.vulcanair.com. You may view 
this service information at the FAA,

[[Page 1341]]

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 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2021-0871.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0871; 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.

FOR FURTHER INFORMATION CONTACT: Gregory Johnson, Aviation Safety 
Engineer, International Validation Section, FAA, 901 Locust, Room 301, 
Kansas City, MO 64106; phone: (720) 626-5462; 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 serial-numbered 
Vulcanair S.p.A. Model P.68C, P.68C-TC, P.68 ``OBSERVER,'' P.68 
OBSERVER 2, P.68R, and P.68TC OBSERVER airplanes. The NPRM published in 
the Federal Register on October 8, 2021 (86 FR 56229). The NPRM was 
prompted by MCAI originated by the European Union Aviation Safety 
Agency (EASA), which is the Technical Agent for the Member States of 
the European Union. EASA issued EASA AD 2020-0262, dated November 30, 
2020 (referred to after this as ``the MCAI''), to correct an unsafe 
condition on certain serial-numbered Vulcanair S.p.A. Model P.68R, 
P.68C, P.68C-TC, P.68 ``OBSERVER,'' P.68 ``OBSERVER 2,'' and P.68TC 
``OBSERVER'' airplanes. The MCAI states:

    Two occurrences have been reported of finding a damaged 
stabilator trim control cable connected to the stabilator trim 
actuator assembly, mounted on fuselage frame No.16. The related 
technical investigation concluded that the cause of the damage is a 
design issue.
    This condition, if not detected and corrected, could lead to 
failure of an affect [sic] part, preventing trim surface control 
(remaining in the last position), possibly resulting in reduced 
control of the aeroplane.
    To address this potential unsafe condition, and pending a design 
improvement, Vulcanair published the [service bulletin] SB, to 
provide inspection instructions for detecting damage.
    For the reasons described above, this [EASA] AD requires 
repetitive inspections of the affected parts, and, depending on 
findings, replacement.
    This [EASA] AD is considered to be an interim action and further 
[EASA] AD action may follow.

    You may examine the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0871.

Discussion of Final Airworthiness Directive

Comments

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

Conclusion

    This product has been approved by the aviation authority of another 
country and is 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 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. P.68 Variants Service Bulletin 
No. 263, dated October 20, 2020. The service information contains 
procedures for repetitively inspecting each stabilator trim control 
cable part number 5.6067-1, 5.6161-1, 5.6171-1, 5.6231-2, or 5.6231-4 
for broken wires and replacing the cable if necessary. 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 the ADDRESSES section.

Interim Action

    The FAA considers this AD an interim action. The inspection reports 
required by this AD will enable the manufacturer to obtain better 
insight into the nature, cause, and extent of the damage, and 
eventually to develop final action to address the unsafe condition. 
Once final action has been identified, the FAA might consider further 
rulemaking.

Costs of Compliance

    The FAA estimates that this AD affects 127 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
           Action                  Labor cost         Parts cost      Cost per airplane          operators
----------------------------------------------------------------------------------------------------------------
Inspection.................  0.50 work-hour x $85               $0  $42.50 per inspection  $5,397.50 per
                              per hour = $42.50                      cycle.                 inspection cycle.
                              per inspection cycle.
Report.....................  1 work-hour x $85 per              $0  $85 per inspection     $10,795 per
                              hour = $85 per                         cycle.                 inspection cycle.
                              reporting cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any replacements that 
would be required based on the results of the inspection. The FAA has 
no way of determining the number of airplanes that might need this 
replacement:

[[Page 1342]]



                           On-Condition Costs
------------------------------------------------------------------------
                                                             Cost per
        Action             Labor cost       Parts cost       airplane
------------------------------------------------------------------------
Replacement...........  2 work-hours x              $340            $510
                         $85 per hour =
                         $170.
------------------------------------------------------------------------

Paperwork Reduction Act

    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 currently 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 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, completing and reviewing the collection of 
information. All responses to this collection of information are 
mandatory. Send comments regarding this burden estimate or any other 
aspect of this collection of information, including suggestions for 
reducing this burden to: Information Collection Clearance Officer, 
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 
76177-1524.

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:

2021-26-15 Vulcanair S.p.A.: Amendment 39-21874; Docket No. FAA-
2021-0871; Project Identifier MCAI-2020-01581-A.

(a) Effective Date

    This airworthiness directive (AD) is effective February 15, 
2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Vulcanair S.p.A. (Vulcanair) Model P.68C, 
P.68C-TC, P.68 ``OBSERVER,'' P.68 OBSERVER 2, P.68R, and P.68TC 
OBSERVER airplanes, serial numbers 333, 337 to 339 inclusive, 378, 
379, and 383 and larger (except serial numbers 387 and 398), 
certificated in any category, with a stabilator trim control cable 
part number 5.6067-1, 5.6161-1, 5.6171-1, 5.6231-2, or 5.6231-4 
installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 2740, Stabilizer 
Control System.

(e) Unsafe Condition

    This AD was prompted by a damaged stabilator trim control cable 
connected to the stabilator trim actuator assembly, mounted on 
fuselage frame No. 16. The FAA is issuing this AD to detect and 
address failure of a stabilator trim control cable, which could 
prevent trim surface control thereby leaving the cable remaining in 
the last position. The unsafe condition, if not addressed, could 
result in reduced control of the airplane.

(f) Compliance

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

(g) Required Actions

    Before a stabilator trim control cable part number 5.6067-1, 
5.6161-1, 5.6171-1, 5.6231-2, or 5.6231-4 accumulates more than 400 
hours time-in-service (TIS) since first installation on an airplane 
or within 50 hours TIS after the effective date of this AD, 
whichever occurs later, and thereafter at intervals not to exceed 50 
hours TIS, visually inspect the stabilator trim control cable for 
broken wires and replace the stabilator trim control cable before 
further flight if there is broken wire in a strand in accordance 
with steps 1 through 22 of Part 2 Work Procedure in Vulcanair S.p.A. 
P.68 Variants Service Bulletin No. 263, dated October 20, 2020.

(h) Reporting

    Within 14 days after the initial inspection required by 
paragraph (g) of this AD or within 14 days after the effective date 
of this AD, whichever occurs later, report the results of the 
initial inspection to Vulcanair at 
[email protected] or at the address in 
paragraph (l)(3) of this AD. Thereafter, report the inspection 
results within 14 days after each inspection. Each report must 
include the following information:
    (1) Owner/operator name, mailing address, phone number, and 
email address;
    (2) Airplane model, serial number, and registration number;
    (3) Airplane hours TIS at the time of the inspection;
    (4) Stabilator trim control cable hours TIS at the time of the 
inspection;
    (5) Date of the inspection;
    (6) Inspection result (positive or negative); and
    (7) A description of any non-conformity (damage).

(i) Special Flight Permit

    Special flight permits are prohibited.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the

[[Page 1343]]

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

    (1) For more information about this AD, contact Gregory Johnson, 
Aviation Safety Engineer, FAA, General Aviation & Rotorcraft 
Section, International Validation Section, 901 Locust, Room 301, 
Kansas City, MO 64106; phone: (720) 626-5462; email: 
[email protected].
    (2) Refer to European Union Aviation Safety Agency (EASA) AD 
2020-0262, dated November 30, 2020, for more information. You may 
examine the EASA AD in the AD docket at https://www.regulations.gov 
by searching for and locating Docket No. FAA-2021-0871.

(l) 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. P.68 Variants Service Bulletin No. 263, 
dated October 20, 2020.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Vulcanair S.p.A., Fulvio Oloferni, via Giovanni Pascoli, 7, Naples, 
80026, Italy; phone: +39 081 5918 135; email: 
[email protected]; website: www.vulcanair.com.
    (4) You may view this service information at 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on December 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2022-00056 Filed 1-10-22; 8:45 am]
BILLING CODE 4910-13-P
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