Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations 13157 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0811; Product 

Identifier 2019–CE–055–AD; Amendment 

39–21431; AD 2021–04–10] 

RIN 2120–AA64 

Airworthiness Directives; Textron 

Aviation, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Textron Aviation Inc. (Textron) (type 

certificate previously held by Cessna 

Aircraft Company) Models 208 and 

208B airplanes. This AD was prompted 

by reports of loose elevator torque tube 

attach fasteners. This AD requires 

repetitively inspecting the inboard and 

outboard elevator torque tube 

attachments for loose or incorrectly 

installed fasteners, replacing all 

fasteners if loose or incorrectly installed 

fasteners are found, and reporting the 

inspection results to the FAA. This AD 

also includes optional actions to 

terminate the repetitive inspections. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective April 12, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 12, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Textron Aviation Inc., One Cessna 

Boulevard, Wichita, KS 67215; phone: 

316–517–5800; email: 

teamturbopropsupport@txtav.com; 

website: https://support.cessna.com. 

You may view this service information 

at the 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 816–329–4148. 

It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0811. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0811; 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, 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: 

Bobbie Kroetch, Aviation Safety 

Engineer, Wichita ACO Branch, FAA, 

1801 Airport Road, Wichita, KS 67209; 

phone: 316–946–4155; fax: 316–946– 

4107; email: bobbie.kroetch@faa.gov or 

Wichita-COS@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Textron (type certificate 

previously held by Cessna Aircraft 

Company) Models 208 and 208B 

airplanes. The NPRM published in the 

Federal Register on September 22, 2020 

(85 FR 59457). The NPRM was 

prompted by reports of loose elevator 

torque tube attach fasteners on low 

flight time Textron Model 208B 

airplanes. Textron identified a quality 

escape affecting certain serial-numbered 

Model 208 and 208B airplanes. Fastener 

holes in the inboard and outboard 

elevator torque tube connections may 

have been oversized and fasteners at the 

inboard and outboard torque tube 

connections may have been installed 

incorrectly. 

In the NPRM, the FAA proposed to 

require repetitively inspecting the 

inboard and outboard elevator torque 

tube attachments for loose or incorrectly 

installed fasteners, replacing all 

fasteners if loose or incorrectly installed 

fasteners are found, and reporting the 

inspection results to the FAA. The 

NPRM also proposed optional actions to 

terminate the repetitive inspections. 

This condition, if not addressed, could 

result in failure of the elevator torque 

tube fasteners, leading to loss of elevator 

control and loss of controlled flight. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

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 Task 27–30–00– 

290, Left and Right Elevator Torque 

Tube Attach Points (Borescope) Special 

Detailed Inspection, dated October 1, 

2018, of the Cessna Model 208 

Maintenance Manual (Task 27–30–00– 

290). This service information contains 

procedures for performing a detailed 

borescope inspection of the left and 

right elevator torque tube attach points. 

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 ADDRESSES. 

Other Related Service Information 

The FAA also reviewed Textron 

Aviation Mandatory Caravan Service 

Bulletin CAB–27–06, dated October 14, 

2019 (CAB–27–06). This service 

information contains instructions for 

visually inspecting the left and right 

elevator torque tube attach points for the 

presence of loose rivets and replacing 

loose or incorrectly installed rivets. 

Differences Between This AD and the 

Service Information 

Task 27–30–00–290 only specifies 

replacing loose fasteners. This AD 

requires replacement of all 48 fasteners 

if any single inboard or outboard 

elevator torque tube attach fastener is 

found loose or incorrectly installed. The 

FAA determined based on field 

evidence that identification of one loose 

fastener often indicates other fasteners 

may be affected. 

CAB–27–06, which is not 

incorporated by reference in this AD, 

specifies performing an initial 

inspection within 800 flight hours or 12 

months from date of receipt, whichever 

occurs first. This AD requires an initial 

inspection before the airplane 

accumulates 800 hours time-in-service 

(TIS) or within 200 hours TIS after the 

AD effectivity date, whichever occurs 

later. 

CAB–27–06 also specifies, without 

sufficient data, that an inspection is not 

required for airplanes that have reached 

4,000 hours. The FAA determined an 

inspection of high-time airplanes is 

necessary to verify whether these 

airplanes are affected. This AD requires 

a one-time visual inspection for 

airplanes that have already accumulated 

4,000 hours TIS. 

Costs of Compliance 

The FAA estimates that this AD 

affects 232 airplanes of U.S. registry. 


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13158 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations 

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 

Inspection ........................... 1 work-hour × $85 per hour = $85 .......... Not applicable ... $85 per inspection 

cycle.

$19,720 per inspection cycle. 

Reporting Requirement ...... 1 work-hour × $85 per hour = $85 .......... Not applicable .. $85 per report.$19,720 per report. 

The FAA estimates the following 

costs to do any necessary replacements 

that would be required based on the 

results of the inspection. The FAA has 

no way of determining the number of 

airplanes that might need these 

replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Fastener Replacement: All 48 Fasteners ..................... 16 work-hours × $85 per hour = $1,360 ...................... $10 $1,370 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this AD may be covered under 

warranty, thereby reducing the cost 

impact on affected operators. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to a penalty for failure to comply with 

a collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a currently valid 

OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public 

reporting for this collection of 

information is estimated to take 

approximately 1 hour per response, 

including the time for reviewing 

instructions, searching existing data 

sources, gathering and maintaining the 

data needed, and completing and 

reviewing the collection of information. 

All responses to this collection of 

information are mandatory. Send 

comments regarding this burden 

estimate or any other aspect of this 

collection of information, including 

suggestions for reducing this burden to: 

Information Collection Clearance 

Officer, Federal Aviation 

Administration, 10101 Hillwood 

Parkway, Fort Worth, TX 76177–1524. 

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 

■ 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 adding 

the following new airworthiness 

directive: 

2021–04–10 Textron Aviation, Inc. (Type 

Certificate Previously Held by Cessna 

Aircraft Company): Amendment 39– 

21431; Docket No. FAA–2020–0811; 

Product Identifier 2019–CE–055–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 12, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Textron Aviation Inc. 

(Textron) (type certificate previously held by 

Cessna Aircraft Company) Model 208 

airplanes, serial numbers 20800564 through 

20800594 and 20800603 through 20800605; 

and Model 208B airplanes, serial numbers 

208B5141 through 208B5285, 208B5287 

through 208B5305, 208B5307 through 

208B5312, 208B5314, 208B5316 through 


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Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations 13159 

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. 

(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 27–30–00–290, 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 (g)(1)(i) 

and (ii) of this AD. 

(3) If all 48 fasteners were replaced before 

the effective date of this AD by following the 

instructions in paragraph (g)(2) of this AD, 

then the initial and recurring inspections 

detailed in paragraph (g)(1) of this AD are not 

required provided you report the information 

required by paragraph (h) of this AD. 

(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: 

316–946–4155; fax: 316–946–4107; 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. 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) Task 27–30–00–290, 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– 

517–5800; 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 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: 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. 2021–03478 Filed 3–5–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0095; Project 

Identifier MCAI–2020–01658–R; Amendment 

39–21439; AD 2021–04–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: 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 


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