Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 30763 

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: 

2021–11–12 Pilatus Aircraft Ltd.: 

Amendment 39–21574; Docket No. 

FAA–2020–1074; Project Identifier 

MCAI–2020–01257–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 15, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pilatus Aircraft Ltd. 

Model PC–24 airplanes, serial numbers (S/ 

Ns) 101 through 162, S/N 164, S/N 165, S/ 

N 167, and S/N 168, certificated in any 

category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7120, Engine Mount Section. 

(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 

identifies the unsafe condition as engine 

attachment hardware not conforming to the 

approved design. The FAA is issuing this AD 

to detect and address incorrectly installed 

attachment hardware in the engine and 

nacelle area. The unsafe condition, if not 

addressed, could result in damage to the 

engine attachment hardware, which may 

affect the structural integrity of the airplane. 

(f) Actions and Compliance 

Unless already done, do the actions in 

paragraphs (f)(1) and (2) of this AD at the 

next annual inspection after the effective date 

of this AD or within 11 months after the 

effective date of this AD, whichever occurs 

later. 

(1) Inspect the left hand (LH) and right 

hand (RH) middle inner nacelles for loose 

nuts and correctly install any loose nut 

before further flight by following section 

3.B(1) of the Accomplishment Instructions in 

Pilatus PC–24 Service Bulletin No. 71–001, 

dated June 30, 2020 (Pilatus SB 71–001). 

(2) Inspect the LH and RH front and rear 

engine beams for missing washers by 

following section 3.B(2)(a) through (b) of the 

Accomplishment Instructions in Pilatus SB 

71–001. If there are any missing washers, 

before further flight, do an eddy current 

inspection of the bolt holes for damage by 

following section 3.C of the Accomplishment 

Instructions in Pilatus SB 71–001. Where 

Pilatus SB 71–001 specifies obtaining repair 

instructions from Pilatus, the instructions 

must be accomplished using a method 

approved by the Manager, International 

Validation Branch, FAA; or the European 

Union Aviation Safety Agency (EASA); or 

Pilatus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(g) 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. If sending 

information directly to the manager of the 

International Validation Branch, send it to 

the attention of the person identified in 

Related Information. 

(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. 

(h) 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) 329–4059; fax: (816) 329–4090; 

email: doug.rudolph@faa.gov. 

(2) Refer to EASA AD 2020–0194, dated 

September 8, 2020, for more information. 

You may examine the EASA AD at https:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–1074. 

(i) 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. 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) Pilatus PC–24 Service Bulletin No. 71– 

001, dated June 30, 2020. 

(ii) [Reserved] 

(3) For Pilatus Aircraft Ltd. service 

information identified in this AD, contact 

CH–6371, Stans, Switzerland; phone: +41 

848 24 7 365; email: techsupport.ch@pilatusaircraft.com; website: https://www.pilatusaircraft.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) 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 May 17, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–12044 Filed 6–9–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0812; Project 

Identifier MCAI–2020–01317–A; Amendment 

39–21561; AD 2021–10–28] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Pilatus Aircraft Ltd. (Pilatus) Model PC– 

24 airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority of another country to 

identify and correct an unsafe condition 


khammond on DSKJM1Z7X2PROD with RULES
30764 Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 

on an aviation product. The MCAI 

identifies the unsafe condition as the 

need to revise certain airworthiness 

limitations and certification 

maintenance instructions. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective July 15, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 15, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Pilatus Aircraft Ltd., Customer Support 

General Aviation, CH–6371 Stans, 

Switzerland; phone: +41 848 24 7 365; 

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) 329–4148. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0812; 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, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE, Washington, DC 

20590. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aviation Safety 

Engineer, FAA, General Aviation & 

Rotorcraft Section, International 

Validation Branch, 901 Locust, Room 

301, Kansas City, MO 64106; phone: 

(816) 329–4059; fax: (816) 329–4090; 

email: doug.rudolph@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 all Pilatus Model PC–24 

airplanes. The NPRM published in the 

Federal Register on March 11, 2021 (86 

FR 13838). The NPRM was based on 

MCAI from the European Union 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union. EASA 

issued AD 2020–0202, dated September 

22, 2020 (referred to after this as ‘‘the 

MCAI’’) to correct an unsafe condition 

for Pilatus Model PC–24 airplanes. The 

MCAI states: 

The airworthiness limitations and 

certification maintenance instructions for 

Pilatus PC–24 aeroplanes, which are 

approved by EASA, are currently defined and 

published in Pilatus PC–24 AMM [Aircraft 

Maintenance Manual] Chapter 04–00–00. 

These instructions have been identified as 

mandatory for continued airworthiness. 

Failure to accomplish these instructions 

could result in an unsafe condition. 

Previously, EASA issued AD 2020–0074, 

[dated March 27, 2020,] requiring the actions 

described in the Pilatus PC–24 AMM Chapter 

04–00–00, Document Number 02378 Issue 

005 at Revision 14. 

Since that AD was issued, Pilatus 

published the ALS [Airworthiness 

Limitations section, at Issue 005 Revision 

19], which contains the following new and/ 

or more restrictive tasks as specified in 

Mandatory Structural Inspection Items data 

module PC24–AA04–20–0000–00A–000A–A 

Issue 005 Revision 00: 

—AL–27–00–025 and AL–27–00–026: 

Control column sprocket gear assembly, 

and 

—AL–27–00–027: Control wheel column 

assembly. 

In addition, Airworthiness Limitations 

Description data module PC24–A–A04–00– 

0000–00A–040A–A Issue 008 Revision 00 

includes: 

—The new limit of validity following the 

completion of the Full Scale Fatigue Test, 

and 

—Usage assumptions/conditions for 

operations on unpaved and grass 

runaways. 

EASA AD 2020–0074, dated March 

27, 2020, required revising the 

Airworthiness Limitations section (ALS) 

to correct an error in the horizontal 

stabilizer primary trim system 

secondary power source operational 

test. The MCAI retains the requirements 

of EASA AD 2020–0074, dated March 

27, 2020, which the MCAI supersedes, 

and requires the additional revisions 

discussed previously. You may examine 

the MCAI in the AD docket at https:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0812. 

In the NPRM, the FAA proposed to 

require replacing the revised sections of 

the ALS described previously into the 

existing AMM or instructions for 

continued airworthiness. 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 

This product has been approved by 

the aviation authority of another 

country and is approved for operation in 

the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI and service information 

referenced above. 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 Chapter 04, 

Airworthiness Limitations, Pilatus PC– 

24 Aircraft Maintenance Manual (PC–24 

AMM) Report 02378, Issue 005, 

Revision 19, dated May 26, 2020. This 

service information contains the parent 

data module and the new limit of 

validity and updates the usage 

assumptions and conditions for 

operations on unpaved and grass 

runways. This document also contains 

the revised subsections with revised 

maintenance actions. 

The FAA also reviewed Horizontal 

stabilizer primary trim system 

secondary power source—Operation 

test, data module PC24–A–E27–40– 

0000–01A–320A–A, dated September 

25, 2019, from PC–24 AMM Report 

02378, Issue 005, Revision 19, dated 

May 26, 2020. This service information 

contains revised procedures for task 

number AL–27–40–022 in the 

certification maintenance requirements. 

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 the ADDRESSES. 

Costs of Compliance 

The FAA estimates that this AD will 

affect 42 products of U.S. registry. The 

FAA also estimates that it will take 

about 1 work-hour per product to 

comply with the requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. 

Based on these figures, the FAA 

estimates the cost of this AD on U.S. 

operators will be $3,570 or $85 per 

product. 

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 


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Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 30765 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) 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. 

(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: 

2021–10–28 Pilatus Aircraft Ltd.: 

Amendment 39–21561; Docket No. 

FAA–2020–0812; Project Identifier 

MCAI–2020–01317–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 15, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pilatus Aircraft Ltd. 

Model PC–24 airplanes, all serial numbers, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2740: Stabilizer Control System. 

(e) Reason 

This AD was prompted by the need to 

revise the Airworthiness Limitations section 

(ALS) of the existing aircraft maintenance 

manual (AMM) to add new and more 

restrictive tasks for the control column 

sprocket gear assembly and control wheel 

column assembly, to address the new limit of 

validity and update the usage assumptions 

and conditions for operations on unpaved 

and grass runways, and to correct an error in 

the horizontal stabilizer primary trim system 

secondary power source operational test. The 

FAA is issuing this AD to prevent reduction 

in the structural integrity of the airframe and 

components, as well as an unrecognized 

failure of the manual pitch trim. These 

conditions, if not addressed, could result in 

loss of airplane control. 

(f) Actions and Compliance 

(1) Before further flight, unless already 

done, revise the ALS of the existing AMM or 

instructions for continued airworthiness 

(ICA) for your airplane by incorporating the 

following documents. 

(i) Airworthiness Limitations, AMM data 

module PC24–A–A04–00–0000–00A–040A– 

A, Issue 008, Revision 00, dated May 26, 

2020, from Chapter 04, Airworthiness 

Limitations, Pilatus PC–24 Aircraft 

Maintenance Manual (PC–24 AMM) Report 

02378, Issue 005, Revision 19, dated May 26, 

2020. 

(ii) Mandatory structural inspection items, 

AMM data module PC24–A–A04–20–0000– 

00A–000A–A, Issue 005, Revision 00, dated 

May 26, 2020, from Chapter 04, 

Airworthiness Limitations, Pilatus PC–24 

Aircraft Maintenance Manual (PC–24 AMM) 

Report 02378, Issue 005, Revision 19, dated 

May 26, 2020. 

(iii) Certification maintenance 

requirements, AMM data module PC24–A– 

A04–30–0000–00A–000A–A, Issue 007, 

Revision 00, dated October 14, 2019, from 

Chapter 04, Airworthiness Limitations, 

Pilatus PC–24 Aircraft Maintenance Manual 

(PC–24 AMM) Report 02378, Issue 005, 

Revision 19, dated May 26, 2020. 

(iv) Horizontal stabilizer primary trim 

system secondary power source—Operation 

test, AMM data module PC24–A–E27–40– 

0000–01A–320A–A, dated September 25, 

2019, from PC–24 AMM Report 02378, Issue 

005, Revision 19, dated May 26, 2020. Your 

ALS must require this procedure for task 

number AL–27–40–022 in the certification 

maintenance requirements. 

Note 1 to paragraph (f)(1) of this AD: 

Pilatus PC–24 Aircraft Maintenance Manual, 

Airworthiness Limitations, AMM data 

module PC24–A–A04–00–0000–00A–040A– 

A, Issue 008, Revision 00, dated May 26, 

2020, is the parent data module for Chapter 

04 of the PC–24 AMM and consists of four 

subsections (sub-data modules). The parent 

data module and four sub-data modules 

comprise the complete ALS of Chapter 04, 

Airworthiness Limitations, Pilatus PC–24 

Aircraft Maintenance Manual (PC–24 AMM) 

Report 02378, Issue 005, Revision 19, dated 

May 26, 2020. Incorporating Pilatus PC–24 

Aircraft Maintenance Manual, Airworthiness 

Limitations, AMM data module PC24–A– 

A04–00–0000–00A–040A–A, Issue 008 

Revision 00, dated May 26, 2020, and all four 

subsections listed in Section 1 General, is 

acceptable, but not required, for compliance 

with this AD. 

(2) As of the effective date of this AD, 

except as provided in paragraph (g) of this 

AD, no alternative replacement times, 

inspection intervals, or tasks may be 

approved for the affected parts. 

(3) The actions required by paragraph (f)(1) 

of this AD may be performed by the owner/ 

operator (pilot) holding at least a private pilot 

certificate and must be entered into the 

aircraft records showing compliance with 

this AD in accordance with 14 CFR 43.9(a)(1) 

through (4), and 14 CFR 91.417(a)(2)(v). The 

record must be maintained as required by 14 

CFR 91.417, 121.380, or 135.439. 

(g) Alternative Methods of Compliance 

(AMOCs) 

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. Send 

information to Doug Rudolph, Aviation 

Safety Engineer, FAA, General Aviation & 

Rotorcraft Section, International Validation 

Branch, 901 Locust, Room 301, Kansas City, 

MO 64106; phone: (816) 329–4059; fax: (816) 

329–4090; email: doug.rudolph@faa.gov. 

Before using any approved AMOC on any 

airplane to which the AMOC applies, notify 

your appropriate principal inspector (PI) in 

the FAA Flight Standards District Office 

(FSDO), or lacking a PI, your local FSDO. 

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. 

(h) Related Information 

Refer to European Union Aviation Safety 

Agency (EASA) AD 2020–0202, dated 

September 22, 2020, for more information. 

You may examine the EASA AD at https:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–0812. 

(i) 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. 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) Chapter 04, Airworthiness Limitations, 

Pilatus PC–24 Aircraft Maintenance Manual 


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30766 Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 

(PC–24 AMM) Report 02378, Issue 005, 

Revision 19, dated May 26, 2020. 

(ii) Horizontal stabilizer primary trim 

system secondary power source—Operation 

test, AMM data module PC24–A–E27–40– 

0000–01A–320A–A, dated September 25, 

2019, from PC–24 AMM Report 02378, Issue 

005, Revision 19, dated May 26, 2020. 

(3) For Pilatus Aircraft Ltd. service 

information identified in this AD, contact 

Pilatus Aircraft Ltd., Customer Support 

General Aviation, CH–6371 Stans, 

Switzerland; phone: +41 848 24 7 365; 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) 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 May 7, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–12045 Filed 6–9–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1175; Product 

Identifier 2018–SW–071–AD; Amendment 

39–21563; AD 2021–11–01] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Canada Limited Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2013–20– 

13 for certain Bell Helicopter Textron 

Canada Limited (now Bell Textron 

Canada Limited) (Bell) Model 206B and 

206L helicopters. AD 2013–20–13 

required installing a placard beneath the 

engine power dual tachometer and 

revising the Operating Limitations 

section of the existing Rotorcraft Flight 

Manual (RFM) for your helicopter. This 

AD was prompted by the engine 

manufacturer expanding the RPM (N2) 

steady-state operation avoidance range 

limits. This AD retains certain 

requirements of AD 2013–20–13, and 

requires revising certain sections of the 

existing RFM for your helicopter and 

installing or replacing a placard. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective July 15, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 15, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact Bell 

Textron Canada Limited, 12,800 Rue de 

l’Avenir, Mirabel, Quebec J7J1R4; 

telephone (450) 437–2862 or (800) 363– 

8023; fax (450) 433–0272; or at https:// 

www.bellcustomer.com. You may view 

this service information at the FAA, 

Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. For information on the 

availability of this material at the FAA, 

call (817) 222–5110. Service information 

that is incorporated by reference is also 

available on the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

1175. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–1175; 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 Transport Canada AD, any 

comments received, and other 

information. The street 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: 

Michael Hughlett, Aviation Safety 

Engineer, General Aviation & Rotorcraft 

Section, International Validation 

Branch, FAA, 10101 Hillwood Pkwy., 

Fort Worth, TX 76177; telephone (817) 

222–5889; email Michael.Hughlett@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–20–13, 

Amendment 39–17619 (78 FR 66252, 

November 5, 2013), (AD 2013–20–13). 

AD 2013–20–13 applied to Bell Model 

206B helicopters, serial number (S/N) 

004 through 4675, including helicopters 

converted from Model 206A; and Bell 

Model 206L helicopters, S/N 45001 

through 45153, and 46601 through 

46617. The NPRM published in the 

Federal Register on March 11, 2021 (86 

FR 13828). The NPRM proposed to 

require, within 25 hours time-in-service 

(TIS), revising the Operating Limitations 

and the Normal Procedures sections of 

the existing RFM for your helicopter 

and installing or replacing a placard. 

The NPRM was prompted by a 

determination from the manufacturers 

that the steady-state operation 

avoidance range limits needed to be 

expanded, amendments to the RFM 

needed to be incorporated, and a new 

placard (decal) needed to be installed. 

Transport Canada AD CF–2018–23, 

dated August 22, 2018 (AD CF–2018– 

23), issued by Transport Canada, which 

is the aviation authority for Canada, 

corrects an unsafe condition for Bell 

Model 206B series helicopters including 

those converted from Model 206A, S/Ns 

up to 4690, and model 206L series 

helicopters, S/Ns 45001 through 45153 

and 46601 through 46617. Transport 

Canada advises that Rolls Royce has 

expanded the RPM (N2) steady-state 

operation avoidance range limits due to 

several failures of the third stage turbine 

wheel. According to Transport Canada, 

Rolls Royce determined that detrimental 

vibrations could occur within a 

particular range of turbine speeds, 

which may be a contributing factor to 

these failures. Bell has also amended the 

RFMs and the engine starting 

procedures for RPM (N2) and provided 

a new decal (placard) to inform pilots to 

avoid steady-state operations at those 

engine turbine speeds. This condition, if 

not addressed, could result in turbine 

failure, engine power loss, and 

subsequent loss of control of the 

helicopter. 

Accordingly, Transport Canada AD 

CF–2018–23 requires incorporating the 

amended RFM power plant operating 

limitations and engine starting 

procedures for RPM (N2) steady-state 

operation and installing a new decal. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to the FAA’s bilateral 

agreement with Canada, Transport 

Canada, its technical representative, has 

notified the FAA of the unsafe condition 

described in its AD. The FAA reviewed 


khammond on DSKJM1Z7X2PROD with RULES