Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes, 72181-72183 [2021-27507]

Download as PDF Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (2) A ‘‘part eligible for installation’’ is an HPT rotor stage 1 disk that is not listed in Figure 1 or Figure 2 to paragraph (c) of this AD or an HPT rotor stage 1 disk that has been repaired using an FAA-approved repair. Note 1 to paragraph (h)(2): Guidance for repairing the HPT rotor stage 1 disk can be found in GE Repair Document RD #150– 1811–P1, dated March 17, 2020. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO 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 certification office, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: ANE-ADAMOC@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. (j) Related Information For more information about this AD, contact Scott Stevenson, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7132; fax: (781) 238–7199; email: Scott.M.Stevenson@faa.gov. (k) Material Incorporated by Reference None. Issued on December 15, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. BILLING CODE 4910–13–C DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0786; Project Identifier MCAI–2021–00429–A; Amendment 39–21843; AD 2021–24–22] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes jspears on DSK121TN23PROD with RULES1 For service information identified in this final rule, contact Pilatus Aircraft Ltd., Customer Support General Aviation, CH–6371 Stans, Switzerland; phone: +41 848 247 365; email: techsupport.ch@pilatusaircraft.com; website: https:// www.pilatus-aircraft.com. 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 (816) 329–4148. ADDRESSES: You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0786; 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: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2012–06– 16, which applied to all Pilatus Aircraft Ltd. (Pilatus) Model PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC– SUMMARY: 17:14 Dec 20, 2021 This AD is effective January 25, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 25, 2022. DATES: Examining the AD Docket [FR Doc. 2021–27480 Filed 12–20–21; 8:45 am] VerDate Sep<11>2014 6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ B2–H2, PC–6/B2–H4, PC–6/C–H2, and PC–6/C1–H2 airplanes. AD 2012–06–16 required installing a new rudder and elevator locking screw and modifying the installation of the rudder and elevator hinge bolt. Since the FAA issued AD 2012–06–16, the European Union Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on these products. This AD does not retain any actions required by AD 2012–06–16 and requires inspecting and modifying the rudder, elevator, and right-hand (RH) aileron hinge bolt installations. The FAA is issuing this AD to address the unsafe condition on these products. Jkt 256001 Doug Rudolph, Aviation Safety Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Branch, 901 Locust, Room 301, Kansas City, MO 64106; phone: (816) 329–4059; fax: (816) 329–4090; email: doug.rudolph@faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 72181 Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2012–06–16, Amendment 39–16997 (77 FR 19061, March 30, 2012) (AD 2012–06–16). AD 2012–06–16 applied to all Pilatus Model PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC–6/350–H2, PC–6/A, PC–6/A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/B2–H2, PC–6/B2– H4, PC–6/C–H2, and PC–6/C1–H2 airplanes and required installing a new elevator and rudder locking screw and modifying the installation of the elevator and rudder hinge bolt. The NPRM published in the Federal Register on September 17, 2021 (86 FR 51835). The NPRM was prompted by AD 2021–0098, dated April 9, 2021 (referred to after this as ‘‘the MCAI’’), issued by EASA, which is the Technical Agent for the Member States of the European Union. The MCAI states: Occurrences were reported where, on certain PC–6 aeroplanes, the elevator or the rudders was lost or partially detached during flight. All the occurrences happened on PC– 6 aeroplanes in CONFIG 1. This condition, if not corrected, could lead to in-flight failure of the elevator or rudder attachment, possibly resulting in reduced control of the aeroplane. To address this potential unsafe condition, Pilatus issued SB 55–001 (original issue and Revision 1) to provide rework instructions for the elevator and rudder hinge bolt locking. Consequently, EASA published AD 2011– 0230 to require this rework. Subsequently, Pilatus issued recommended SB 55–003 (later revised) to provide instructions to modify the hinge bolt installation of the elevator and rudder. This [service bulletin] SB, being recommended only, had no impact on the existing EASA AD. Since that [EASA] AD and the recommended Pilatus SB 55–003 were published, the latest risk assessment determined that the modification of the hinge bolt installation of the elevator, rudder and right-hand (RH) aileron installation must be required to reach an acceptable level of safety for the affected aeroplanes. Consequently, Pilatus issued the SB, as defined in this [EASA] AD, to provide instructions to modify the affected aeroplanes into CONFIG 2 standard. For the reasons described above, this [EASA] AD supersedes EASA AD 2011–0230 and requires, for certain aeroplanes, a onetime inspection of the elevator and rudder installation, followed by repetitive inspections of the elevator and rudder, and, depending on findings, accomplishment of applicable corrective action(s). This [EASA] AD also requires modification of the elevator, rudder and RH aileron hinge bolt installations into CONFIG 2, which is the terminating action for the repetitive inspections required by this [EASA] AD. Finally, this [EASA] AD prohibits (re)installation of affected parts. E:\FR\FM\21DER1.SGM 21DER1 72182 Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations You may examine the MCAI in the AD docket at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0786. 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. Discussion of Final Airworthiness Directive Related Service Information Under 1 CFR Part 51 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 and service information referenced above. The FAA reviewed The FAA reviewed Pilatus PC–6 Service Bulletin (SB) No. 55–005, dated February 25, 2021 (Pilatus SB 55–005). The service information specifies procedures for repetitively inspecting the hinge bolt installations and taking any necessary corrective actions until the hinge bolt is modified. Modifying the hinge bolt installation in accordance with Pilatus SB 55–005 makes the airplane a CONFIG 2 design. 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. Other Related Service Information Pilatus also issued Pilatus PC–6 SB No. 55–003, dated November 29, 2013; Pilatus PC–6 SB No. 55–003, Revision 1, dated December 9, 2014; Pilatus PC–6 SB No. 55–003, Revision 2, dated January 19, 2017; and Pilatus PC–6 SB No. 55–003, Revision 3, dated November 6, 2017. This service information specifies procedures for modifying the hinge bolt installations, which makes the airplane a CONFIG 2 design. This service information was superseded by Pilatus SB 55–005. Costs of Compliance The FAA estimates that this AD affects 50 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 Inspecting CONFIG 1 airplanes ........................ 4.5 work-hours × $85 per hour = $382.50 ...... Not applicable ... Modifying from CONFIG 1 to CONFIG 2 .......... 14 work-hours × $85 per hour = $1,190 ......... $1,200 ............... $382.50 per inspection cycle. $2,390 ......................... $19,125 per inspection cycle. $119,500. The FAA estimates the following costs to do any necessary corrective actions that would be required based on the results of the mandated inspection. The FAA has no way of determining the number of airplanes that might need these actions: jspears on DSK121TN23PROD with RULES1 ON-CONDITION COSTS Action Labor cost Accomplishing corrective actions ................................. .5 work-hour × $85 per hour = $42.50 ......................... Authority for This Rulemaking Regulatory Findings 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. 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. VerDate Sep<11>2014 17:14 Dec 20, 2021 Jkt 256001 PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 Parts cost $200 Cost per product $242.50 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive AD 2012–06–16, Amendment 39–16997 (77 FR 19061, March 30, 2012); and ■ b. Adding the following new airworthiness directive: ■ ■ E:\FR\FM\21DER1.SGM 21DER1 Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations 2021–24–22 Pilatus Aircraft Ltd.: Amendment 39–21843; Docket No. FAA–2021–0786; Project Identifier MCAI–2021–00429–A. (a) Effective Date This AD is effective January 25, 2022. (b) Affected ADs This AD replaces AD 2012–06–16, Amendment 39–16997 (77 FR 19061, March 30, 2012). (c) Applicability This AD applies to Pilatus Aircraft Ltd. Model PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC–6/350–H2, PC–6/A, PC–6/ A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1– H2, PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2, and PC–6/C1–H2 airplanes, all serial numbers, certificated in any category. Note 1 to paragraph (c): These airplanes may also be identified as Fairchild Republic Company airplanes, Fairchild Industries airplanes, Fairchild Heli Porter airplanes, or Fairchild-Hiller Corporation airplanes. (d) Subject Joint Aircraft System Component (JASC) Codes 2700, Flight Control System; 2710, Aileron Control System; 2720, Rudder Control System; and 2730, Elevator Control System. (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 describes the unsafe condition as detachment or partial detachment of the elevator or rudder in flight. The FAA is issuing this AD to prevent failure of the elevator or rudder attachment. The unsafe condition, if not addressed, could result in loss of control of the airplane. jspears on DSK121TN23PROD with RULES1 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions The following definitions apply for purposes of this AD. (1) Group 1 airplanes: Airplanes that have not been modified in accordance with Pilatus PC–6 Service Bulletin (SB) No. 55–003, dated November 29, 2013 (Pilatus SB 55–003); Pilatus PC–6 SB No. 55–003, Revision 1, dated December 9, 2014 (Pilatus SB 55– 003R1); Pilatus PC–6 SB No. 55–003, Revision 2, dated January 19, 2017 (Pilatus 55–003R2); Pilatus PC–6 SB No. 55–003, Revision 3, dated November 6, 2017 (Pilatus 55–003R3); or Pilatus PC–6 SB No. 55–005, dated February 25, 2021 (Pilatus SB 55–005). (2) Group 2 airplanes: Airplanes that have been modified in accordance with Pilatus SB 55–003, SB 55–003R1, SB 55–003R2, Pilatus SB 55–003R3; or Pilatus SB 55–005. (h) Inspect Elevator, Rudder, and RH Aileron Hinge Bolt Installations (1) For Group 1 airplanes: Within 14 days after the effective date of this AD, inspect the VerDate Sep<11>2014 17:14 Dec 20, 2021 Jkt 256001 elevator, rudder, and RH aileron hinge bolt installations and take any corrective actions before further flight by following the Accomplishment Instructions-Part 1-On Aircraft-Inspection in Pilatus SB 55–005. (2) For Group 1 airplanes: Within 100 hours time-in-service (TIS) after the inspection required by paragraph (h)(1) of this AD and thereafter at intervals not to exceed 100 hours TIS until the modification required by paragraph (i) of this AD is done, inspect the elevator, rudder, and RH aileron hinge bolt installations and take any corrective actions before further flight by following the Accomplishment InstructionsPart 2-On Aircraft-CONFIG 1-Repeat Inspections in Pilatus SB 55–005. (i) Modify Group 1 Airplanes Within 11 months after the effective date of this AD, modify the hinge bolt installations on the elevator, rudder, and RH aileron assemblies by following the Accomplishment Instructions-Part 3-On Aircraft-Modification from CONFIG 1 to CONFIG 2 in Pilatus SB 55–005. Modifying the elevator, rudder, and RH aileron hinge bolt installations terminates the repetitive inspections required by paragraph (h)(2) of this AD. (j) Installation Prohibition As of the following applicable compliance time, do not install on any airplane an elevator assembly part number (P/N) 113.50.06.011, 113.50.06.012, 6305.0010.00, 6305.0010.52, 6305.0010.53, 6305.0010.54, or 6305.0010.55, or a rudder assembly P/N 113.40.06.018, 6302.0010.51, or 6302.0010.52. (1) For Group 1 airplanes: As of the modification required by paragraph (i) of this AD. (2) For Group 2 airplanes: As of the effective date of this AD. (k) 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 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 (l)(1) of this AD and email: 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. (l) Related Information (1) For more information about this AD, contact Doug Rudolph, Aviation Safety Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Branch, 901 Locust, Room 301, Kansas City, MO 64106; phone: (816) 329–4059; fax: (816) 329–4090; email: doug.rudolph@faa.gov. (2) Refer to European Union Aviation Safety Agency (EASA) AD 2021–0098, dated April 9, 2021, for more information. You may PO 00000 Frm 00039 Fmt 4700 Sfmt 4700 72183 examine the EASA AD in the AD docket at https://www.regulations.gov by searching for and locating it in Docket No. FAA–2021– 0786. (3) You may obtain information related to Pilatus SB 55–003, SB 55–003R1, SB 55– 003R2, Pilatus SB 55–003R3; or Pilatus SB 55–005, which are not incorporated by reference, using the contact information found in paragraph (m)(3) of this AD. (m) 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) Pilatus PC–6 Service Bulletin (SB) No. 55–005, dated February 25, 2021. (ii) [Reserved] (3) Pilatus Aircraft Ltd., Customer Support General Aviation, CH–6371 Stans, Switzerland; phone: +41 848 247 365; email: techsupport.ch@pilatus-aircraft.com; website: https://www.pilatus-aircraft.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 (816) 329–4148. (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 November 19, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–27507 Filed 12–20–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–1077; Project Identifier MCAI–2020–00819–A; Amendment 39–21842; AD 2021–24–21] RIN 2120–AA64 Airworthiness Directives; Embraer S.A. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model EMB–500 and EMB–505 airplanes. This AD was prompted by a report that the SUMMARY: E:\FR\FM\21DER1.SGM 21DER1

Agencies

[Federal Register Volume 86, Number 242 (Tuesday, December 21, 2021)]
[Rules and Regulations]
[Pages 72181-72183]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-27507]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0786; Project Identifier MCAI-2021-00429-A; 
Amendment 39-21843; AD 2021-24-22]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2012-06-
16, which applied to all Pilatus Aircraft Ltd. (Pilatus) Model PC-6, 
PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-
H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-
H2, and PC-6/C1-H2 airplanes. AD 2012-06-16 required installing a new 
rudder and elevator locking screw and modifying the installation of the 
rudder and elevator hinge bolt. Since the FAA issued AD 2012-06-16, the 
European Union Aviation Safety Agency (EASA) superseded its mandatory 
continuing airworthiness information (MCAI) to correct an unsafe 
condition on these products. This AD does not retain any actions 
required by AD 2012-06-16 and requires inspecting and modifying the 
rudder, elevator, and right-hand (RH) aileron hinge bolt installations. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective January 25, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 25, 
2022.

ADDRESSES: For service information identified in this final rule, 
contact Pilatus Aircraft Ltd., Customer Support General Aviation, CH-
6371 Stans, Switzerland; phone: +41 848 247 365; email: 
aircraft.com">[email protected]aircraft.com; website: https://www.pilatus-
aircraft.com. 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 (816) 329-4148.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0786; 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: Doug Rudolph, Aviation Safety 
Engineer, FAA, General Aviation & Rotorcraft Section, International 
Validation Branch, 901 Locust, Room 301, Kansas City, MO 64106; phone: 
(816) 329-4059; fax: (816) 329-4090; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2012-06-16, Amendment 39-16997 (77 FR 
19061, March 30, 2012) (AD 2012-06-16). AD 2012-06-16 applied to all 
Pilatus Model PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-
H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, 
PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes and required installing 
a new elevator and rudder locking screw and modifying the installation 
of the elevator and rudder hinge bolt. The NPRM published in the 
Federal Register on September 17, 2021 (86 FR 51835).
    The NPRM was prompted by AD 2021-0098, dated April 9, 2021 
(referred to after this as ``the MCAI''), issued by EASA, which is the 
Technical Agent for the Member States of the European Union. The MCAI 
states:

    Occurrences were reported where, on certain PC-6 aeroplanes, the 
elevator or the rudders was lost or partially detached during 
flight. All the occurrences happened on PC-6 aeroplanes in CONFIG 1.
    This condition, if not corrected, could lead to in-flight 
failure of the elevator or rudder attachment, possibly resulting in 
reduced control of the aeroplane.
    To address this potential unsafe condition, Pilatus issued SB 
55-001 (original issue and Revision 1) to provide rework 
instructions for the elevator and rudder hinge bolt locking. 
Consequently, EASA published AD 2011-0230 to require this rework. 
Subsequently, Pilatus issued recommended SB 55-003 (later revised) 
to provide instructions to modify the hinge bolt installation of the 
elevator and rudder. This [service bulletin] SB, being recommended 
only, had no impact on the existing EASA AD.
    Since that [EASA] AD and the recommended Pilatus SB 55-003 were 
published, the latest risk assessment determined that the 
modification of the hinge bolt installation of the elevator, rudder 
and right-hand (RH) aileron installation must be required to reach 
an acceptable level of safety for the affected aeroplanes. 
Consequently, Pilatus issued the SB, as defined in this [EASA] AD, 
to provide instructions to modify the affected aeroplanes into 
CONFIG 2 standard.
    For the reasons described above, this [EASA] AD supersedes EASA 
AD 2011-0230 and requires, for certain aeroplanes, a one-time 
inspection of the elevator and rudder installation, followed by 
repetitive inspections of the elevator and rudder, and, depending on 
findings, accomplishment of applicable corrective action(s). This 
[EASA] AD also requires modification of the elevator, rudder and RH 
aileron hinge bolt installations into CONFIG 2, which is the 
terminating action for the repetitive inspections required by this 
[EASA] AD. Finally, this [EASA] AD prohibits (re)installation of 
affected parts.


[[Page 72182]]


    You may examine the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0786.

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 and 
service information 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 Pilatus PC-6 Service Bulletin (SB) No. 55-005, 
dated February 25, 2021 (Pilatus SB 55-005). The service information 
specifies procedures for repetitively inspecting the hinge bolt 
installations and taking any necessary corrective actions until the 
hinge bolt is modified. Modifying the hinge bolt installation in 
accordance with Pilatus SB 55-005 makes the airplane a CONFIG 2 design. 
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.

Other Related Service Information

    Pilatus also issued Pilatus PC-6 SB No. 55-003, dated November 29, 
2013; Pilatus PC-6 SB No. 55-003, Revision 1, dated December 9, 2014; 
Pilatus PC-6 SB No. 55-003, Revision 2, dated January 19, 2017; and 
Pilatus PC-6 SB No. 55-003, Revision 3, dated November 6, 2017. This 
service information specifies procedures for modifying the hinge bolt 
installations, which makes the airplane a CONFIG 2 design. This service 
information was superseded by Pilatus SB 55-005.

Costs of Compliance

    The FAA estimates that this AD affects 50 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 product      operators
----------------------------------------------------------------------------------------------------------------
Inspecting CONFIG 1 airplanes.  4.5 work-hours x $85    Not applicable......  $382.50 per       $19,125 per
                                 per hour = $382.50.                           inspection        inspection
                                                                               cycle.            cycle.
Modifying from CONFIG 1 to      14 work-hours x $85     $1,200..............  $2,390..........  $119,500.
 CONFIG 2.                       per hour = $1,190.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
corrective actions that would be required based on the results of the 
mandated inspection. The FAA has no way of determining the number of 
airplanes that might need these actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Accomplishing corrective actions..............  .5 work-hour x $85 per hour =               $200         $242.50
                                                 $42.50.
----------------------------------------------------------------------------------------------------------------

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:
0
a. Removing Airworthiness Directive AD 2012-06-16, Amendment 39-16997 
(77 FR 19061, March 30, 2012); and
0
b. Adding the following new airworthiness directive:


[[Page 72183]]


2021-24-22 Pilatus Aircraft Ltd.: Amendment 39-21843; Docket No. 
FAA-2021-0786; Project Identifier MCAI-2021-00429-A.

(a) Effective Date

    This AD is effective January 25, 2022.

(b) Affected ADs

    This AD replaces AD 2012-06-16, Amendment 39-16997 (77 FR 19061, 
March 30, 2012).

(c) Applicability

    This AD applies to Pilatus Aircraft Ltd. Model PC-6, PC-6-H1, 
PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-
6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, 
and PC-6/C1-H2 airplanes, all serial numbers, certificated in any 
category.
    Note 1 to paragraph (c): These airplanes may also be identified 
as Fairchild Republic Company airplanes, Fairchild Industries 
airplanes, Fairchild Heli Porter airplanes, or Fairchild-Hiller 
Corporation airplanes.

(d) Subject

    Joint Aircraft System Component (JASC) Codes 2700, Flight 
Control System; 2710, Aileron Control System; 2720, Rudder Control 
System; and 2730, Elevator Control System.

(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 describes the unsafe condition as detachment or 
partial detachment of the elevator or rudder in flight. The FAA is 
issuing this AD to prevent failure of the elevator or rudder 
attachment. 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) Definitions

    The following definitions apply for purposes of this AD.
    (1) Group 1 airplanes: Airplanes that have not been modified in 
accordance with Pilatus PC-6 Service Bulletin (SB) No. 55-003, dated 
November 29, 2013 (Pilatus SB 55-003); Pilatus PC-6 SB No. 55-003, 
Revision 1, dated December 9, 2014 (Pilatus SB 55-003R1); Pilatus 
PC-6 SB No. 55-003, Revision 2, dated January 19, 2017 (Pilatus 55-
003R2); Pilatus PC-6 SB No. 55-003, Revision 3, dated November 6, 
2017 (Pilatus 55-003R3); or Pilatus PC-6 SB No. 55-005, dated 
February 25, 2021 (Pilatus SB 55-005).
    (2) Group 2 airplanes: Airplanes that have been modified in 
accordance with Pilatus SB 55-003, SB 55-003R1, SB 55-003R2, Pilatus 
SB 55-003R3; or Pilatus SB 55-005.

(h) Inspect Elevator, Rudder, and RH Aileron Hinge Bolt Installations

    (1) For Group 1 airplanes: Within 14 days after the effective 
date of this AD, inspect the elevator, rudder, and RH aileron hinge 
bolt installations and take any corrective actions before further 
flight by following the Accomplishment Instructions-Part 1-On 
Aircraft-Inspection in Pilatus SB 55-005.
    (2) For Group 1 airplanes: Within 100 hours time-in-service 
(TIS) after the inspection required by paragraph (h)(1) of this AD 
and thereafter at intervals not to exceed 100 hours TIS until the 
modification required by paragraph (i) of this AD is done, inspect 
the elevator, rudder, and RH aileron hinge bolt installations and 
take any corrective actions before further flight by following the 
Accomplishment Instructions-Part 2-On Aircraft-CONFIG 1-Repeat 
Inspections in Pilatus SB 55-005.

(i) Modify Group 1 Airplanes

    Within 11 months after the effective date of this AD, modify the 
hinge bolt installations on the elevator, rudder, and RH aileron 
assemblies by following the Accomplishment Instructions-Part 3-On 
Aircraft-Modification from CONFIG 1 to CONFIG 2 in Pilatus SB 55-
005. Modifying the elevator, rudder, and RH aileron hinge bolt 
installations terminates the repetitive inspections required by 
paragraph (h)(2) of this AD.

(j) Installation Prohibition

    As of the following applicable compliance time, do not install 
on any airplane an elevator assembly part number (P/N) 
113.50.06.011, 113.50.06.012, 6305.0010.00, 6305.0010.52, 
6305.0010.53, 6305.0010.54, or 6305.0010.55, or a rudder assembly P/
N 113.40.06.018, 6302.0010.51, or 6302.0010.52.
    (1) For Group 1 airplanes: As of the modification required by 
paragraph (i) of this AD.
    (2) For Group 2 airplanes: As of the effective date of this AD.

(k) 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 
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 (l)(1) of this AD 
and email: [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.

(l) Related Information

    (1) For more information about this AD, contact Doug Rudolph, 
Aviation Safety Engineer, FAA, General Aviation & Rotorcraft 
Section, International Validation Branch, 901 Locust, Room 301, 
Kansas City, MO 64106; phone: (816) 329-4059; fax: (816) 329-4090; 
email: [email protected].
    (2) Refer to European Union Aviation Safety Agency (EASA) AD 
2021-0098, dated April 9, 2021, for more information. You may 
examine the EASA AD in the AD docket at https://www.regulations.gov 
by searching for and locating it in Docket No. FAA-2021-0786.
    (3) You may obtain information related to Pilatus SB 55-003, SB 
55-003R1, SB 55-003R2, Pilatus SB 55-003R3; or Pilatus SB 55-005, 
which are not incorporated by reference, using the contact 
information found in paragraph (m)(3) of this AD.

(m) 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) Pilatus PC-6 Service Bulletin (SB) No. 55-005, dated 
February 25, 2021.
    (ii) [Reserved]
    (3) Pilatus Aircraft Ltd., Customer Support General Aviation, 
CH-6371 Stans, Switzerland; phone: +41 848 247 365; email: 
aircraft.com">[email protected]aircraft.com; website: https://www.pilatus-
aircraft.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 (816) 329-4148.
    (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 November 19, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-27507 Filed 12-20-21; 8:45 am]
BILLING CODE 4910-13-P

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