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Federal Register / Vol. 86, No. 178 / Friday, September 17, 2021 / Proposed Rules Authority for This Rulemaking Title 49 of the United States Code specifies the FAAs 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 Agencys 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 The FAA has determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation:
1 Is not a significant regulatory action under Executive Order 12866, 2 Would not affect intrastate aviation in Alaska, and 3 Would 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 Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by:

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a. Removing Airworthiness Directive 20120616, Amendment 3916997 77
FR 19061, March 30, 2012; and b. Adding the following new airworthiness directive:

Pilatus Aircraft Ltd.: Docket No. FAA2021
0786; Project Identifier MCAI2021
00429A.
a Comments Due Date The FAA must receive comments on this airworthiness directive AD by November 1, 2021.
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.
Models 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.
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

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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 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 Related Information or email: 9AVS-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
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