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Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations 3 If all 48 fasteners were replaced before the effective date of this AD by following the instructions in paragraph g2 of this AD, then the initial and recurring inspections detailed in paragraph g1 of this AD are not required provided you report the information required by paragraph h of this AD.

208B5344, 208B5346 through 208B5350, 208B5353, 208B5354, 208B5356 through 208B5359, 208B5362 through 208B5366, 208B5401, 208B5403, 208B5404, and 208B5408; certificated in any category.
d Subject Joint Aircraft System Component JASC
Code: 5520, Elevator Structure.
e Unsafe Condition This AD was prompted by reports of loose elevator torque tube attach fasteners. The FAA is issuing this AD to detect and correct loosening and eventual failure of the elevator torque tube attach fasteners. The unsafe condition, if not addressed, could result in loss of elevator control, resulting 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 Inspection and Fastener Replacement 1 At the following compliance times, inspect each inboard and outboard elevator torque tube attach fastener for looseness and fretting by following sections 2.C. and 2.D. of Task 273000290, Left and Right Elevator Torque Tube Attach Points Borescope Special Detailed Inspection, dated October 1, 2018, of the Cessna Model 208 Maintenance Manual. You must also inspect for incorrectly installed fasteners.
i For airplanes that have accumulated less than 800 hours time-in-service TIS as of the effective date of this AD, complete the initial inspection before the airplane accumulates 800 hours TIS or within 200 hours TIS after the effective date of the AD, whichever occurs later. Thereafter, repeat the visual inspection at intervals not to exceed 200
hours TIS until the airplane has accumulated 4,000 hours TIS or until all 48 elevator torque tube attach fasteners are replaced, whichever occurs first.
ii For airplanes that have accumulated 800 or more hours TIS but less than 4,000
hours TIS as of the effective date of this AD, complete the initial inspection within 200
hours TIS after the effective date of the AD.
Thereafter, repeat the visual inspection at intervals not to exceed 200 hours TIS until the airplane has accumulated 4,000 hours TIS or until all 48 elevator torque tube attach fasteners are replaced, whichever occurs first.
iii For airplanes that have accumulated 4,000 or more hours TIS as of the effective date of this AD, complete a one-time visual inspection within 200 hours TIS after the effective date of the AD. No repetitive inspections are required after completion of the one-time visual inspection.
2 If there are any loose, fretting, or incorrectly installed fasteners, remove the elevator and replace all 48 elevator torque tube attach fasteners 24 per side, with 12
each on the inboard and outboard elevator torque tube attach point before further flight.
Maintain proper alignment by marking each part prior to removal and by replacing one fastener at a time. Replacing all 48 fasteners is terminating action for the repetitive inspections required by paragraphs g1i and ii of this AD.

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h Reporting Requirement Within 30 days after doing the initial inspection regardless if loose, fretting, or incorrectly installed fasteners were found or within 30 days after the effective date of this AD, whichever occurs later, and then within 30 days after each inspection where loose, fretting, or incorrectly installed fasteners were found, report the following information to the FAA at Wichita-COS@faa.gov:
1 Name and address of owner.
2 Date of the inspection.
3 Name, address, phone number, and email address of person submitting the report.
4 Airplane serial number, registration number, and total hours TIS on the airplane at the time of the inspection.
5 If an earlier inspection identified loose, fretting, or incorrectly installed fasteners, identify the hours TIS on the airplane and which fasteners were replaced, if known, or if all fasteners were replaced.
6 If loose, fretting, or incorrectly installed fasteners were found, detailed information including a sketch or picture showing the location of the loose, fretting, or incorrectly installed fasteners and identification of any installed supplemental type certificates STCs, alterations, repairs, or field approvals affecting the area of concern.
i Alternative Methods of Compliance AMOCs 1 The Manager, Wichita 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 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 the Related Information section of this AD.
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 Bobbie Kroetch, Aviation Safety Engineer, Wichita ACO Branch, FAA, 1801
Airport Road, Wichita, KS 67209; phone:
3169464155; fax: 3169464107; email:
bobbie.kroetch@faa.gov or Wichita-COS@
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. 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.

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i Task 273000290, Left and Right Elevator Torque Tube Attach Points Borescope Special Detailed Inspection, dated October 1, 2018, of the Cessna Model 208 Maintenance Manual.
ii Reserved 3 For Textron Aviation, Inc. service information identified in this AD, contact Textron Aviation Inc., One Cessna Boulevard, Wichita, KS 67215; phone: 316
5175800; email: teamturbopropsupport@
txtav.com; website: https
support.cessna.com.
4 You may view this service information at FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust St., Kansas City, MO 64106. For information on the availability of this material at the FAA, call 8163294148.
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: fedreg.legal@nara.gov, or go to:
https www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on February 8, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202103478 Filed 3521; 8:45 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20210095; Project Identifier MCAI202001658R; Amendment 3921439; AD 20210417
RIN 2120AA64

Airworthiness Directives; Airbus Helicopters Federal Aviation Administration FAA, DOT.
ACTION: Final rule; request for comments.
AGENCY:

The FAA is adopting a new airworthiness directive AD for certain Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350D, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. This AD was prompted by two reports of debonding of the tail rotor T/R blade leading edge protection shields. This AD requires repetitively inspecting certain T/R blades and depending on the inspection results, replacing the T/
R blade, as specified in a European Union Aviation Safety Agency EASA
AD, which is incorporated by reference IBR. This AD also prohibits installing certain T/R blades. The FAA is issuing
SUMMARY:

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