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Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations 20212422 Pilatus Aircraft Ltd.:
Amendment 3921843; Docket No.
FAA20210786; Project Identifier MCAI202100429A.
a Effective Date This AD is effective January 25, 2022.
b Affected ADs This AD replaces AD 20120616, Amendment 3916997 77 FR 19061, March 30, 2012.
c Applicability This AD applies to Pilatus Aircraft Ltd.
Model PC6, PC6H1, PC6H2, PC6/350, PC6/350H1, PC6/350H2, PC6/A, PC6/
AH1, PC6/AH2, PC6/BH2, PC6/B1
H2, PC6/B2H2, PC6/B2H4, PC6/CH2, and PC6/C1H2 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.

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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 PC6 Service Bulletin SB No. 55003, dated November 29, 2013 Pilatus SB 55003;
Pilatus PC6 SB No. 55003, Revision 1, dated December 9, 2014 Pilatus SB 55
003R1; Pilatus PC6 SB No. 55003, Revision 2, dated January 19, 2017 Pilatus 55003R2; Pilatus PC6 SB No. 55003, Revision 3, dated November 6, 2017 Pilatus 55003R3; or Pilatus PC6 SB No. 55005, dated February 25, 2021 Pilatus SB 55005.
2 Group 2 airplanes: Airplanes that have been modified in accordance with Pilatus SB
55003, SB 55003R1, SB 55003R2, Pilatus SB 55003R3; or Pilatus SB 55005.
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
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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 55005.
2 For Group 1 airplanes: Within 100
hours time-in-service TIS after the inspection required by paragraph h1 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 55005.
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 55005. Modifying the elevator, rudder, and RH aileron hinge bolt installations terminates the repetitive inspections required by paragraph h2 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 l1 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 3294059; fax: 816 3294090;
email: doug.rudolph@faa.gov.
2 Refer to European Union Aviation Safety Agency EASA AD 20210098, dated April 9, 2021, for more information. You may
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examine the EASA AD in the AD docket at https www.regulations.gov by searching for and locating it in Docket No. FAA2021
0786.
3 You may obtain information related to Pilatus SB 55003, SB 55003R1, SB 55
003R2, Pilatus SB 55003R3; or Pilatus SB
55005, which are not incorporated by reference, using the contact information found in paragraph m3 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 552a 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 PC6 Service Bulletin SB No.
55005, dated February 25, 2021.
ii Reserved 3 Pilatus Aircraft Ltd., Customer Support General Aviation, CH6371 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 3294148.
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. 202127507 Filed 122021; 8:45 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20201077; Project Identifier MCAI202000819A; Amendment 3921842; AD 20212421
RIN 2120AA64

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 EMB500 and EMB505 airplanes. This AD was prompted by a report that the
SUMMARY:

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