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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 h2: Guidance for repairing the HPT rotor stage 1 disk can be found in GE Repair Document RD 150
1811P1, 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
2387132; fax: 781 2387199; 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 491013C

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20210786; Project Identifier MCAI202100429A; Amendment 3921843; AD 20212422
RIN 2120AA64

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, CH6371 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 3294148.

ADDRESSES:

You may examine the AD docket at https www.regulations.gov by searching for and locating Docket No.
FAA20210786; 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, M30, West Building Ground Floor, Room W12140, 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 201206
16, which applied to all Pilatus Aircraft Ltd. Pilatus Model PC6, PC6H1, PC6H2, PC6/350, PC6/350H1, 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. 202127480 Filed 122021; 8:45 am
VerDate Sep<11>2014

6/350H2, PC6/A, PC6/AH1, PC6/
AH2, PC6/BH2, PC6/B1H2, PC6/
B2H2, PC6/B2H4, PC6/CH2, and PC6/C1H2 airplanes. AD 20120616
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 20120616, 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 20120616 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 3294059; fax: 816 3294090;
email: doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:

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Background The FAA issued a notice of proposed rulemaking NPRM to amend 14 CFR
part 39 to supersede AD 20120616, Amendment 3916997 77 FR 19061, March 30, 2012 AD 20120616. AD
20120616 applied to all Pilatus Model PC6, PC6H1, PC6H2, PC6/350, PC6/350H1, PC6/350H2, PC6/A, PC6/AH1, PC6/AH2, PC6/BH2, PC6/B1H2, PC6/B2H2, PC6/B2
H4, PC6/CH2, and PC6/C1H2
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
20210098, 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 PC6 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 55001 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 55003
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 55003 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 20110230
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 actions. 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 reinstallation of affected parts.

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