Federal Register / Vol. 86, No. 28 / Friday, February 12, 2021 / Rules and Regulations 9269 

matters requiring board attention, documents 

of resolution, and supervisory 

recommendations) a supervised financial 

institution for, and the Bureau will not issue 

an enforcement action on the basis of, a 

‘‘violation’’ of or ‘‘non-compliance’’ with 

supervisory guidance. In some situations, 

examiners may reference (including in 

writing) supervisory guidance to provide 

examples of appropriate consumer protection 

and risk management practices and other 

actions for addressing compliance with laws 

or regulations. 

• Supervisory criticisms should continue 

to be specific as to practices, operations or 

other matters that could cause consumer 

harm or could cause violations of laws, 

regulations, final agency orders, or other 

legally enforceable conditions. 

• The Bureau may decide to seek public 

comment on supervisory guidance. Seeking 

public comment on supervisory guidance 

does not mean that the guidance is intended 

to be a regulation or have the force and effect 

of law. The comment process helps the 

Bureau to improve its understanding of an 

issue, to gather information on institutions’ 

risk management practices, or to seek ways 

to achieve a supervisory objective most 

effectively and with the least burden on 

institutions. 

• The Bureau will aim to reduce the 

issuance of multiple supervisory guidance 

documents on the same topic and will 

generally limit such multiple issuances going 

forward. 

• The Bureau will continue efforts to make 

the role of supervisory guidance clear in 

communications to examiners and to 

supervised financial institutions and 

encourages supervised institutions with 

questions about this statement or any 

applicable supervisory guidance to discuss 

the questions with their appropriate agency 

contact. 

Dated: January 19, 2021. 

Grace Feola, 

Federal Register Liaison, Bureau of Consumer 

Financial Protection. 

[FR Doc. 2021–01524 Filed 2–11–21; 8:45 am] 

BILLING CODE 4810–AM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0027; Project 

Identifier MCAI–2021–00048–R; Amendment 

39–21425; AD 2021–04–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2020–19– 

02, which applied to certain Airbus 

Helicopters (previously Eurocopter 

France) Model SA330J helicopters. AD 

2020–19–02 required repetitively 

inspecting affected tail rotor (T/R) 

blades and depending on the inspection 

results, repairing or replacing the T/R 

blade. AD 2020–19–02 also prohibited 

installing an affected T/R blade unless 

it passed the inspections. This AD 

retains the requirements of AD 2020– 

19–02 and also clarifies the 

applicability, clarifies the affected T/R 

blades in the required actions, reduces 

a compliance time, and corrects the 

prohibition requirement. This AD was 

prompted by the determination that 

these corrections are necessary. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD becomes effective 

March 1, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of October 7, 2020 (85 FR 59416, 

September 22, 2020). 

The FAA must receive comments on 

this AD by March 29, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this final rule, contact Airbus 

Helicopters, 2701 N Forum Drive, Grand 

Prairie, TX 75052; telephone 972–641– 

0000 or 800–232–0323; fax 972–641– 

3775; or at https://www.airbus.com/ 

helicopters/services/technicalsupport.html. 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. It is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0027. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0027; 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 European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, AD Program Manager, General 

Aviation & Rotorcraft Unit, 

Airworthiness Products Section, 

Operational Safety Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

matthew.fuller@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued AD 2020–19–02, 

Amendment 39–21243 (85 FR 59416, 

September 22, 2020) (AD 2020–19–02), 

for certain Airbus Helicopters 

(previously Eurocopter France) Model 

SA330J helicopters. AD 2020–19–02 

required, for each T/R blade part 

number (P/N) 330A12–0005–(all dash 

numbers) and 330A12–0006–(all dash 

numbers), repetitively accomplishing a 

visual and in-depth inspection for 

debonding and eddy current inspecting 

for a crack. If there was debonding 

within allowable limits, AD 2020–19–02 

required repairing or replacing the T/R 

blade. If there was debonding that 

exceeded allowable limits or a crack, 

AD 2020–19–02 required replacing the 

T/R blade. AD 2020–19–02 also 

prohibited installing an affected T/R 

blade unless it passed the inspections. 

AD 2020–19–02 was prompted by EASA 

AD No. 2016–0059–E, dated March 22, 

2016 (EASA AD 2016–0059–E), issued 

by the EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Airbus Helicopters 

(formerly Eurocopter, Eurocopter 

France, Aerospatiale) Model SA 330 J 

helicopters. EASA AD 2016–0059–E 

retains the requirements of Direction 

Ge ́ne ́rale de l’Aviation Civile (DGAC) 

France AD 87–032–052(B)R3, dated 

January 23, 1991, which it supersedes, 

and also mandates improved service 

instructions. EASA advises of two 

reports of cracked metal T/R blade skin, 

which subsequently led to rotor blade 

vibrations and forced landing of the 

helicopter. According to EASA, this 

condition, if not addressed, could result 

in additional occurrences of T/R blade 

structural damage, possibly resulting in 

significant vibrations and reduced 

control of the helicopter. 

9270 Federal Register / Vol. 86, No. 28 / Friday, February 12, 2021 / Rules and Regulations 

Actions Since AD 2020–19–02 Was 

Issued 

Since the FAA issued AD 2020–19– 

02, it was identified that the compliance 

time for the initial visual inspection of 

T/R blade P/N 330A12–0006–(all dash 

numbers) (with a de-icing system) was 

inadvertently stated as within 30 hours 

time-in-service (TIS). This final rule 

corrects this compliance time to within 

15 hours TIS. 

Since the FAA issued AD 2020–19– 

02, it was also identified that the parts 

prohibition requirement could cause 

confusion about when the inspections 

must be accomplished prior to 

installation. This final rule clarifies this. 

Additionally, this final rule clarifies 

the applicability by identifying that T/ 

R blade P/N 330A12–0005–(all dash 

numbers) is without a de-icing system 

installed and that T/R blade P/N 

330A12–0006–(all dash numbers) is 

with a de-icing system installed. This 

final rule also clarifies the required 

actions by adding the P/Ns. 

FAA’s Determination 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA about the unsafe condition 

described in its AD. The FAA is 

proposing this AD after evaluating all 

known relevant information and 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other helicopters of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Airbus Helicopters 

Emergency Alert Service Bulletin No. 

05.101, Revision 0, dated March 21, 

2016, for Model SA330J helicopters 

with certain T/R blades with and 

without a de-icing system installed. 

This service information specifies 

procedures for a visual and in-depth 

inspection of the T/R blades for skin 

debonding and an eddy current 

inspection of the T/R blades for a crack 

using various crack detectors. 

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 section. 

AD Requirements 

This AD requires, for T/R blade P/N 

330A12–0006–(all dash numbers) (with 

a de-icing system), within 15 hours TIS 

after the effective date of this AD or 

within 15 hours TIS after last inspecting 

the T/R blade as required by paragraph 

(f)(1) of AD 2020–19–02, whichever 

occurs first, and thereafter at intervals 

not to exceed 15 hours TIS; and for T/ 

R blade P/N 330A12–0005–(all dash 

numbers) (without a de-icing system), 

within 30 hours TIS after the effective 

date of this AD, or within 30 hours TIS 

after last inspecting the T/R blade as 

required by paragraph (f)(1) of AD 2020– 

19–02, whichever occurs first, and 

thereafter at intervals not to exceed 30 

hours TIS: 

• Accomplishing a visual and indepth inspection of each T/R blade for 

debonding. If there is debonding within 

allowable limits, this AD requires 

repairing or replacing the T/R blade. If 

there is debonding that exceeds 

allowable limits, this AD requires 

replacing the T/R blade. 

• Eddy current inspecting each T/R 

blade for a crack. If there is a crack, this 

AD requires replacing the T/R blade. 

This AD also prohibits installing an 

affected T/R blade on any helicopter 

unless it passes the inspections required 

by this AD. 

Differences Between This AD and the 

EASA AD 

The EASA AD requires returning a T/ 

R blade with a discrepancy to Airbus 

Helicopters; whereas this AD requires 

repairing or replacing the T/R blade if 

there is debonding within allowable 

limits and replacing the T/R blade if 

there is debonding that exceeds 

allowable limits or a crack instead. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (APA) (5 

U.S.C. 551 et seq.) authorizes agencies 

to dispense with notice and comment 

procedures for rules when the agency, 

for ‘‘good cause,’’ finds that those 

procedures are ‘‘impracticable, 

unnecessary, or contrary to the public 

interest.’’ Under this section, an agency, 

upon finding good cause, may issue a 

final rule without providing notice and 

seeking comment prior to issuance. 

Further, section 553(d) of the APA 

authorizes agencies to make rules 

effective in less than thirty days, upon 

a finding of good cause. 

An unsafe condition exists that 

requires the immediate adoption of this 

AD without providing an opportunity 

for public comments prior to adoption. 

The FAA has found that the risk to the 

flying public justifies foregoing notice 

and comment prior to adoption of this 

rule because the initial instance of the 

repetitive inspections must be 

completed within 15 or 30 hours TIS, a 

time period of up to approximately two 

months based on the average flight-hour 

utilization rates of these helicopters. 

Accordingly, notice and opportunity for 

prior public comment are impracticable 

and contrary to the public interest 

pursuant to 5 U.S.C. 553(b)(3)(B). 

In addition, the FAA finds that good 

cause exists pursuant to 5 U.S.C. 553(d) 

for making this amendment effective in 

less than 30 days, for the same reasons 

the FAA found good cause to forego 

notice and comment. 

Comments Invited 

The FAA invites you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2021–0027; 

Project Identifier MCAI–2021–00048–R’’ 

at the beginning of your comments. The 

most helpful comments reference a 

specific portion of the final rule, explain 

the reason for any recommended 

change, and include supporting data. 

The FAA will consider all comments 

received by the closing date and may 

amend this final rule because of those 

comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this final rule. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this AD contain 

commercial or financial information 

that is customarily treated as private, 

that you actually treat as private, and 

that is relevant or responsive to this AD, 

it is important that you clearly designate 

the submitted comments as CBI. Please 

mark each page of your submission 

containing CBI as ‘‘PROPIN.’’ The FAA 

will treat such marked submissions as 

confidential under the FOIA, and they 

will not be placed in the public docket 

of this AD. Submissions containing CBI 

should be sent to Matt Fuller, AD 

Program Manager, General Aviation & 

Rotorcraft Unit, Airworthiness Products 

Section, Operational Safety Branch, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222– 

5110; email matthew.fuller@faa.gov. 

Any commentary that the FAA receives 

which is not specifically designated as 

Federal Register / Vol. 86, No. 28 / Friday, February 12, 2021 / Rules and Regulations 9271 

CBI will be placed in the public docket 

for this rulemaking. 

Regulatory Flexibility Act 

The requirements of the Regulatory 

Flexibility Act (RFA) do not apply when 

an agency finds good cause pursuant to 

5 U.S.C. 553 to adopt a rule without 

prior notice and comment. Because the 

FAA has determined that it has good 

cause to adopt this rule without prior 

notice and comment, RFA analysis is 

not required. 

Costs of Compliance 

The FAA estimates that this AD 

affects 17 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates the following costs to 

comply with this AD. 

Inspecting the T/R blades for 

debonding takes about 0.75 work-hour 

for an estimated cost of $64 per 

helicopter and $1,088 for the U.S. fleet, 

per inspection cycle. Eddy current 

inspecting the T/R blades for a crack 

takes about 1.75 work-hours for an 

estimated cost of $149 per helicopter 

and $2,533 for the U.S. fleet, per 

inspection cycle. 

If required, replacing a T/R blade 

takes about 4 work-hours and parts cost 

about $19,000, for an estimated cost of 

$19,340. 

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, I certify 

that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of 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: 

■ a. Removing Airworthiness Directive 

2020–19–02, Amendment 39–21243 (85 

FR 59416, September 22, 2020); and 

■ b. Adding the following new 

airworthiness directive: 

2021–04–04 Airbus Helicopters: 

Amendment 39–21425; Docket No. 

FAA–2021–0027; Project Identifier 

MCAI–2021–00048–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 1, 2021. 

(b) Affected ADs 

This AD replaces AD 2020–19–02, 

Amendment 39–21243 (85 FR 59416, 

September 22, 2020) (AD 2020–19–02). 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model SA330J helicopters, certificated in any 

category, with a tail rotor (T/R) blade part 

number (P/N) 330A12–0005–(all dash 

numbers) (without a de-icing system) or 

330A12–0006–(all dash numbers) (with a deicing system), installed. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, Tail Rotor Blades. 

(e) Unsafe Condition 

This AD was prompted by two reports of 

cracked metal T/R blade skin. The FAA is 

issuing this AD to address fatigue cracking of 

a T/R blade. The unsafe condition, if not 

addressed, could result in failure of a T/R 

blade and subsequent loss of control of the 

helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For T/R blade P/N 330A12–0006–(all 

dash numbers) (with a de-icing system), 

within 15 hours time-in-service (TIS) after 

the effective date of this AD or within 15 

hours TIS after last inspecting the T/R blade 

as required by paragraph (f)(1) of AD 2020– 

19–02, whichever occurs first, and thereafter 

at intervals not to exceed 15 hours TIS; and 

for T/R blade P/N 330A12–0005–(all dash 

numbers) (without a de-icing system), within 

30 hours TIS after the effective date of this 

AD, or within 30 hours TIS after last 

inspecting the T/R blade as required by 

paragraph (f)(1) of AD 2020–19–02, 

whichever occurs first, and thereafter at 

intervals not to exceed 30 hours TIS: 

(i) Inspect each T/R blade for debonding by 

following the visual and in-depth inspection 

procedures in the Accomplishment 

Instructions, paragraph 3.B.2., of Airbus 

Helicopters Emergency Alert Service Bulletin 

No. 05.101, Revision 0, dated March 21, 2016 

(EASB 05.101). If there is debonding within 

allowable limits, before further flight, repair 

or replace the T/R blade. If there is 

debonding that exceeds allowable limits, 

before further flight, replace the T/R blade. 

(ii) Eddy current inspect each T/R blade for 

a crack by following the Accomplishment 

Instructions, paragraph 3.B.3.a. of EASB 

05.101, then either paragraph 3.B.3.b.1. or 

3.B.3.b.2. of EASB 05.101 depending on your 

crack detector, and paragraph 3.B.3.c. of 

EASB 05.101 except the ‘‘if there are no 

cracks’’ and ‘‘if there are one or several 

cracks’’ steps. Instead of the ‘‘if there are no 

cracks’’ and ‘‘if there are one or several 

cracks’’ steps, if there is a crack, before 

further flight, replace the T/R blade. 

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

not install a T/R blade identified in 

paragraph (c) of this AD on any helicopter 

unless the actions of paragraphs (g)(1)(i) and 

(ii) of this AD have been accomplished. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Strategic Policy 

Rotorcraft Section, 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 (i)(1) of this AD. 

Information may be emailed to: 9-ASW-FTWAMOC-Requests@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. 

(i) Related Information 

(1) For more information about this AD, 

contact Matt Fuller, AD Program Manager, 

General Aviation & Rotorcraft Unit, 

9272 Federal Register / Vol. 86, No. 28 / Friday, February 12, 2021 / Rules and Regulations 

Airworthiness Products Section, Operational 

Safety Branch, FAA, 10101 Hillwood Pkwy., 

Fort Worth, TX 76177; telephone (817) 222– 

5110; email matthew.fuller@faa.gov. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (now 

European Union Aviation Safety Agency) 

(EASA) AD No. 2016–0059–E, dated March 

22, 2016. You may view the EASA AD on the 

internet at https://www.regulations.gov in 

Docket No. FAA–2021–0027. 

(j) 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. 

(3) The following service information was 

approved for IBR on October 7, 2020 (85 FR 

59416, September 22, 2020). 

(i) Airbus Helicopters Emergency Alert 

Service Bulletin No. 05.101, Revision 0, 

dated March 21, 2016. 

(ii) [Reserved] 

(4) For Airbus Helicopters service 

information identified in this AD, contact 

Airbus Helicopters, 2701 N Forum Drive, 

Grand Prairie, TX 75052; telephone 972–641– 

0000 or 800–232–0323; fax 972–641–3775; or 

at https://www.airbus.com/helicopters/ 

services/technical-support.html. 

(5) 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. 

(6) 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 3, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–03056 Filed 2–10–21; 2:00 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0049; Project 

Identifier MCAI–2021–00033–A; Amendment 

39–21427; AD 2021–04–06] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Pilatus Aircraft Ltd. (Pilatus) Model PC– 

7 airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by the 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as a 

missing release bar retaining screw on a 

Harley-type buckle assembly installed 

on a harness shoulder strap. This 

condition, if not corrected, could lead to 

loss of pilot restraint and consequently 

loss of airplane control or injuries to the 

crew. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective February 12, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 12, 2021. 

The FAA must receive comments on 

this AD by March 29, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For IrvinGQ Limited service 

information identified in this final rule, 

contact Pilatus Aircraft Ltd., 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, Missouri 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–2021– 

0049. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0049; 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 street address for 

the Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aviation Safety 

Engineer, General Aviation & Rotorcraft 

Section, International Validation 

Branch, FAA, 901 Locust, Room 301, 

Kansas City, Missouri 64106; phone: 

(816) 329–4059; fax: (816) 329–4090; 

email: doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The Federal Office of Civil Aviation 

(FOCA), which is the aviation authority 

for Switzerland, has issued FOCA AD 

HB–2021–001–E, dated January 8, 2021 

(referred to after this as ‘‘the MCAI’’), to 

address the unsafe condition on Pilatus 

Model PC–7 airplanes. The MCAI states: 

An occurrence was reported where in an in 

service event a missing release bar retaining 

screw on a Harley-type buckle assembly 

installed on a harness shoulder strap on an 

ejection seat was detected. 

This condition, if not corrected, could lead 

to loss of pilot restraint and consequently 

loss of aeroplane control or injuries to the 

crew. 

To address this potential unsafe condition, 

Pilatus and IrvinGQ issued the [service 

bulletins] SBs to provide inspection 

instructions. 

For the reason described above, this 

[FOCA] AD requires the inspection of the 

Harley-type buckle assemblies on the seat 

harnesses of the front and rear seats, as 

defined in this AD, and prohibits (re-) 

installation of affected parts. 

FOCA advises that the release bar 

retaining screws on the affected Harleytype buckle assemblies were incorrectly 

peened during manufacture. This 

inadequate peening of the retaining 

screws has led to loose screws that can 

potentially be removed by hand or the 

actual screw falling out of the 

assemblies. You may examine the MCAI 

in the AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0049. 

FAA’s Determination 

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 the State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI and service information 

referenced above. The FAA is issuing 

this AD because the agency has