Federal Register / Vol. 87, No. 36 / Wednesday, February 23, 2022 / Proposed Rules 10115 

(TCCA); or De Havilland Aircraft of Canada 

Limited’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) TCCA AD 

CF–2009–29R4, dated October 1, 2021, for 

related information. This MCAI may be 

found in the AD docket on the internet at 

https://www.regulations.gov by searching for 

and locating Docket No. FAA–2022–0143. 

(2) For more information about this AD, 

contact Antariksh Shetty, Aerospace 

Engineer, Airframe and Propulsion Section, 

FAA, New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531; 

email 9-avs-nyaco-cos@faa.gov. 

(3) For service information identified in 

this AD, contact De Havilland Aircraft of 

Canada Limited, Q-Series Technical Help 

Desk, 123 Garratt Boulevard, Toronto, 

Ontario M3K 1Y5, Canada; telephone 416– 

375–4000; fax 416–375–4539; email thd@

dehavilland.com; internet https://

dehavilland.com. You may view this service 

information at the FAA, Airworthiness 

Products Section, Operational Safety Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

Issued on February 15, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–03718 Filed 2–22–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0146; Project 

Identifier AD–2021–00449–R] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2020–26–13, which applies to certain 

Sikorsky Aircraft Corporation (Sikorsky) 

Model S–92A helicopters. AD 2020–26– 

13 requires establishing the life limit for 

certain part-numbered horizontal 

stabilizer root fittings FWD (forward 

root fittings) and certain part-numbered 

stabilizer strut fittings. AD 2020–26–13 

also requires repetitively inspecting 

certain parts, and depending on the 

inspection results, removing parts from 

service. Finally AD 2020–26–13 

prohibits installing certain stabilizer 

assemblies on any helicopter. Since the 

FAA issued AD 2020–26–13, the 

manufacturer notified the FAA that due 

to an error in the service information, 

certain part numbers in AD 2020–26–13 

are incorrect. Also, the FAA determined 

that additional inspections are required 

to address the unsafe condition. This 

proposed AD would retain certain 

requirements and the prohibition for 

installing certain stabilizer assemblies 

on any helicopter from AD 2020–26–13 

and would correct certain part numbers 

and require additional repetitive 

inspections. The FAA is proposing this 

AD to address the unsafe condition on 

these products. 

DATES: The FAA must receive comments 

on this proposed AD by April 11, 2022. 

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 NPRM, contact Sikorsky’s 

Engineering Group at Sikorsky Aircraft 

Corporation, 124 Quarry Road, 

Trumbell, CT 06611, United States; 

phone: (800) 946–4337; email: wcs_

cust_service_eng.gr-sik@lmco.com; 

website: www.sikorsky360.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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0146; 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 

NPRM, any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Dorie Resnik, Aerospace Engineer, 

Aviation Safety Section, Boston ACO 

Branch, Compliance & Airworthiness 

Division, 1200 District Avenue, 

Burlington, MA 01803; telephone (781) 

238–7693; email 9-AVS-AIR-BACOCOS@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2022–0146; Project Identifier AD– 

2021–00449–R’’ at the beginning of your 

comments. The most helpful comments 

reference a specific portion of the 

proposal, 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 the proposal 

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 proposed 

AD. 

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 NPRM 

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 NPRM, 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 

NPRM. Submissions containing CBI 

should be sent to Dorie Resnik, 

Aerospace Engineer, Aviation Safety 

Section, Boston ACO Branch, 

Compliance & Airworthiness Division, 

1200 District Avenue, Burlington, MA 

01803; telephone (781) 238–7693; email 

9-AVS-AIR-BACO-COS@faa.gov. Any 

commentary that the FAA receives 

which is not specifically designated as 

CBI will be placed in the public docket 

for this rulemaking. 


khammond on DSKJM1Z7X2PROD with PROPOSALS
10116 Federal Register / Vol. 87, No. 36 / Wednesday, February 23, 2022 / Proposed Rules 

Background 

The FAA issued AD 2020–26–13, 

Amendment 39–21368 (85 FR 84201, 

December 28, 2020) (AD 2020–26–13) 

for Sikorsky Model S–92A helicopters 

with forward root fitting part number 

(P/N) 92209–07111–101 or 92070– 

20125–101; or stabilizer strut fitting P/ 

N 92209–07404–041, 92209–07403–041, 

or 92070–20117–041 installed on 

horizontal stabilizer assembly (stabilizer 

assembly) P/N 92070–20117–045, 

92070–20117–046, 92070–20125–041, 

92070–20125–042, 92070–20125–043, 

92070–20125–044, 92205–07400–043, 

or 92205–07400–045. AD 2020–26–13 

was prompted by seven incidents of 

fatigue cracks in forward root fittings. 

Fatigue cracking in a forward root fitting 

degrades the load path and increases the 

load on other assembly parts, 

particularly at the aft horizontal 

stabilizer attachment points; therefore 

AD 2020–26–13 requires determining 

the total hours time-in-service (TIS) of 

the forward root fitting and the 

stabilizer strut fitting, establishing a life 

limit of 7,900 total hours TIS for certain 

part-numbered forward root fittings, and 

establishing a life limit of 19,100 total 

hours TIS for certain stabilizer strut 

fittings. For certain part-numbered 

stabilizer strut fittings, AD 2020–26–13 

also requires repetitive inspections of 

certain parts of an affected stabilizer 

strut assembly. The FAA issued AD 

2020–26–13 to prevent a forward root 

fitting from remaining in service beyond 

its life limit and to detect fatigue 

cracking in a forward root fitting and 

prevent increased load and stress 

cracking in the stabilizer root fitting aft. 

Actions Since AD 2020–26–13 Was 

Issued 

Since the FAA issued AD 2020–26– 

13, Sikorsky notified the FAA that 

incorrect P/Ns are identified in the 

Applicability and the Required Actions 

paragraphs of AD 2020–26–13. This 

NPRM would expand the applicability 

of AD 2020–26–13 by adding an 

additional part-numbered stabilizer 

assembly. This NPRM would correct 

paragraph (g)(4) of the Required Actions 

so that the installation of the titanium 

stabilizer strut fitting P/N 92209–07404– 

041 is terminating action for the 50-hour 

TIS inspections of the aluminum 

stabilizer strut fitting P/N 92070–20117– 

04 or 92209–07403–041. 

Sikorsky also notified the FAA that an 

additional repetitive inspection of 

certain parts of the stabilizer strut 

assembly is required to prevent the 

unsafe condition; this NPRM includes 

this repetitive inspection. Additionally, 

since AD 2020–26–13 was issued, 

Sikorsky requested and the FAA 

approved a global Alternative Method of 

Compliance (AMOC) to allow only 

removing parts from service that are 

cracked, corroded, or have fretting, 

deformation, or wear rather than require 

removing the upper and lower support 

strut rod ends, including lug and 

conical fitting and both upper and lower 

attachment fittings on the stabilizer 

from service. This NPRM incorporates 

that global AMOC into the proposed 

requirements. 

FAA’s Determination 

The FAA is issuing this NPRM after 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

This proposed AD would continue to 

require S–92 Maintenance Manual, SA 

S92A–AMM–000, Temporary Revision 

(TR) 55–33, dated March 24, 2020 (TR 

55–33), which the Director of the 

Federal Register approved for 

incorporation by reference as of 

February 1, 2021 (85 FR 84201, 

December 28, 2020). 

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 reviewed S–92 Maintenance 

Manual SA S92A–AWL–000, TR No. 4– 

58, dated October 2, 2017 (TR 4–58), 

and S–92 Maintenance Manual SA 

S92A–AWL–000, TR No. 4–66 dated 

November 20, 2019 (TR 4–66). This 

service information revises Task 4–00– 

00–200–000, Table 1 Replacement 

Schedule, dated November 30, 2015. 

Both TR 4–58 and 4–66 revise the 

Airworthiness Limitations Schedule by 

removing certain part-numbered 

components, introducing new partnumbered components, and establishing 

replacement intervals and recurring 

inspections for the forward root fitting 

and the horizontal stabilizer strut fitting. 

TR 4–58 also specifies inspecting the 

horizontal stabilizer and attaching 

hardware at a recurring interval of 250 

hours TIS. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

determining the total hours TIS of the 

forward root fitting and the stabilizer 

strut fitting. This proposed AD would 

also require establishing a life limit of 

7,900 total hours TIS for certain partnumbered forward root fittings and 

establishing a life limit of 19,100 total 

hours TIS for stabilizer strut fitting P/N 

92070–20117–041. Finally, this 

proposed AD would require for certain 

part-numbered stabilizer strut fittings 

installed, repetitively visually 

inspecting the following at intervals not 

to exceed 50 hours TIS: 

• The hat bushing and both upper 

and lower fittings for a crack, corrosion, 

fretting, deformation, and wear. 

• Both upper and lower support strut 

rod ends, including each lug and 

conical fitting, and both upper and 

lower attachment fittings on the 

stabilizer and pylon, including the 

bushings, for a crack, corrosion, fretting, 

deformation, and wear. 

• The surface of each Mylar washer 

P/N 92070–20117–104 on certain 

stabilizer assemblies. 

This proposed AD would also require 

repetitively inspecting the following at 

intervals not to exceed 250 hours TIS or 

one year, whichever occurs first: 

• Each stabilizer attachment bolt and 

barrel nut set for corrosion, a crack, and 

damage to the threads indicated by 

uneven threads, missing threads, or 

cross-threading. 

• Each forward root fitting and aft 

attachment fitting, including inspecting 

the bolt holes and fastener holes for a 

crack, wear, and corrosion; or as an 

alternative to detect any crack, 

fluorescent penetrant inspecting (FPI) 

the area. 

• Each forward and aft attachment 

fitting mating surface for wear of the 

abrasion-resistant Teflon coating and 

degradation. For the purposes of this 

inspection, degradation may be 

indicated by fretting. If there is any wear 

of the coating or fretting, this proposed 

AD would require stripping the coating 

and performing a FPI or eddy current 

inspection to inspect for a crack. If there 

is no crack, this proposed AD would 

require recoating the surfaces. 

Depending on the inspection results, 

this proposed AD would require 

removing parts from service before 

further flight. 

Finally, this proposed AD would 

prohibit installing stabilizer assembly P/ 

N 92205–07400–043, 92205–07400–045, 

and 92205–07400–047 on any 

helicopter. 

Differences Between This Proposed AD 

and the Service Information 

The service information specifies that 

returning affected parts to a Sikorsky 

specialist is required; whereas this 

proposed AD would not include this 

requirement. 


khammond on DSKJM1Z7X2PROD with PROPOSALS
Federal Register / Vol. 87, No. 36 / Wednesday, February 23, 2022 / Proposed Rules 10117 

Costs of Compliance 

The FAA estimates that this proposed 

AD would affect 82 helicopters of U.S. 

registry. Labor costs are estimated at $85 

per work-hour. Based on these numbers, 

the FAA estimates the following costs to 

comply with this proposed AD. 

Visually inspecting the stabilizer 

assembly and attached hardware would 

take about 3 work-hours for an 

estimated cost of $255 per helicopter 

and $20,910 for the U.S. fleet per 

inspection cycle. 

If required, replacing a hat bushing 

and both upper fittings and lower 

fittings would take about 1 work-hour 

and parts would cost about $10,000 for 

an estimated cost of $10,085 per 

replacement. 

If required, replacing the upper and 

lower support strut rod ends, including 

lug and conical fitting, would take about 

1 work-hour and parts would cost about 

$10,000 for an estimated cost of $10,085 

per replacement. 

If required, replacing Mylar washers 

would take about 0.5 work-hour and 

parts would cost about $76 for an 

estimated cost of $119 per replacement. 

If required, performing a fluorescent 

penetrant inspection would take about 3 

work-hours for an estimated cost of 

$255 per inspection. 

If required, replacing a stabilizer 

assembly would take about 6 workhours and parts would cost about 

$312,000 for an estimated cost of 

$312,510 per replacement. 

If required, replacing a forward root 

fitting would take about 10 work-hours 

and parts would cost about $25,000 for 

an estimated cost of $25,850 per 

replacement. 

If required, replacing a stabilizer strut 

fitting would take about 10 work-hours 

and parts would cost about $10,000 for 

an estimated cost of $10,850 per 

replacement. 

If required, replacing a forward root 

fitting and an aft attachment fitting 

would take about 20 work-hours and 

parts would cost about $50,000 for an 

estimated cost of $51,700 per 

replacement. 

If required, removing wear or 

corrosion and applying corrosion 

preventative compound would take 

about 0.5 work-hour and parts would 

cost a nominal amount for an estimated 

cost of $43 per action. 

If required, replacing a stabilizer 

attachment bolt and barrel nut set 

would take about 1 work-hour and parts 

would cost about $500 for an estimated 

cost of $585 per replacement. 

If required, replacing a fastener would 

take about 0.1 work-hour and parts 

would cost a nominal amount for an 

estimated cost of $9 per fastener. 

If required, removing the abrasionresistant Teflon coating to inspect each 

forward and aft attachment fitting 

mating surface would take about 5 

work-hours for an estimated cost of 

$425 per inspection. 

If required, applying alodine or 

equivalent and applying abrasionresistant Teflon coating would take 

about 5 work hours with minimal parts 

cost for an estimated cost of $425 per 

application. 

According to Sikorsky, some of the 

costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. The FAA does not control 

warranty coverage for affected 

individuals. As a result, the FAA has 

included all costs in this cost estimate. 

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 

The FAA 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 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 

AD 2020–26–13, Amendment 39–21368 

(85 FR 84201, December 28, 2020); and 

■ b. Adding the following new 

airworthiness directive: 

Sikorsky Aircraft Corporation: Docket No. 

FAA–2022–0146; Project Identifier AD– 

2021–00449–R. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) action by April 

11, 2022. 

(b) Affected ADs 

This AD replaces AD 2020–26–13, 

Amendment 39–21368 (85 FR 84201, 

December 28, 2020) (AD 2020–26–13). 

(c) Applicability 

This AD applies to Sikorsky Aircraft 

Corporation Model S–92A helicopters, 

certificated in any category, with the 

following installed: Horizontal stabilizer root 

fitting FWD (forward root fitting) part 

number (P/N) 92209–07111–101 or 92070– 

20125–101; or stabilizer strut fitting P/N 

92209–07403–041 or 92070–20117–041 

installed on horizontal stabilizer assembly 

(stabilizer assembly) P/N 92070–20117–045, 

92070–20117–046, 92070–20125–041, 

92070–20125–042, 92070–20125–043, 

92070–20125–044, 92205–07400–043, 

92205–07400–045, or 92205–07400–047. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 5510, Horizontal Stabilizer Structure. 

(e) Unsafe Condition 

This AD was prompted by incidents of 

fatigue cracks in a forward root fitting and 

life limit recalculations for forward root 

fitting P/N 92209–07111–101 and 92070– 

20125–101. The FAA is issuing this AD to 

prevent a forward root fitting from remaining 

in service beyond its life limit, detect fatigue 

cracking in a forward root fitting, and prevent 

increased load and stress cracking in the 

stabilizer root fitting aft. The unsafe 

condition, if not addressed, could result in 

failure of a stabilizer root fitting, separation 

of the stabilizer assembly from the helicopter, 


khammond on DSKJM1Z7X2PROD with PROPOSALS
10118 Federal Register / Vol. 87, No. 36 / Wednesday, February 23, 2022 / Proposed Rules 

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) Within 50 hours time-in-service (TIS) 

after the effective date of this AD: 

(i) Determine the total hours TIS of the 

forward root fitting P/N 92209–07111–101 or 

92070–20125–101. If the total hours TIS of 

the forward root fitting is unknown, use the 

total hours TIS of the stabilizer assembly 

instead. 

(A) If the forward root fitting has 

accumulated 7,900 or more total hours TIS, 

before further flight, remove the forward root 

fitting from service. 

(B) If the forward root fitting has 

accumulated less than 7,900 total hours TIS, 

before exceeding 7,900 total hours TIS, 

remove the forward root fitting from service. 

(ii) Thereafter following paragraph (g)(1)(i) 

of this AD, remove the forward root fitting 

from service before accumulating 7,900 total 

hours TIS. 

(iii) For stabilizer assemblies with 

stabilizer strut fitting P/N 92070–20117–041 

installed, perform the following actions: 

(A) Determine the total hours TIS of 

stabilizer strut fitting P/N 92070–20117–041. 

(B) If the stabilizer strut fitting has 

accumulated 19,100 or more total hours TIS, 

before further flight, remove the stabilizer 

strut fitting from service. 

(C) If the stabilizer strut fitting has 

accumulated less than 19,100 total hours TIS, 

before exceeding 19,100 total hours TIS, 

remove the stabilizer strut fitting from 

service. 

(iv) Thereafter following paragraph 

(g)(1)(iii) of this AD, remove the stabilizer 

strut fitting from service before accumulating 

19,100 total hours TIS. 

(2) For helicopters with stabilizer strut 

fitting P/N 92070–20117–041 or 92209– 

07403–041 installed, within 50 hours TIS 

after the effective date of this AD and 

thereafter at intervals not to exceed 50 hours 

TIS: 

(i) Remove the support strut and using a 

cheese cloth (or similar cloth) and isopropyl 

alcohol, clean the upper and lower support 

strut rod ends, horizontal stabilizer 

attachment fitting, and the tail rotor pylon 

attachment fitting. 

(ii) If installed, visually inspect the surface 

of each Mylar washer P/N 92070–20117–104 

(Mylar washer). The surface should be 

smooth and continuous. If there is any visible 

damage such as any tear or scrape, remove 

the Mylar washer from the peelable-ply 

washer P/N 92070–20117–105 (peelable-ply 

washer) and remove the Mylar washer from 

service as follows: 

(A) Dampen a low-lint cloth with 3M 6041 

adhesive remover and place on the top of the 

Mylar washer. 

(B) Allow the adhesive remover to soften 

the Mylar washer and peel the Mylar washer 

back. 

(C) Repeat with more solvent until the 

Mylar washer and adhesive are removed. 

(D) Clean the peelable-ply washer with 

cheese cloth moistened with isopropyl 

alcohol and adhere a new Mylar washer to 

the peelable-ply washer. 

Note 1 to paragraph (g)(2)(ii): Stabilizer 

assembly P/Ns 92070–20125–041, 92070– 

20125–042, 92070–20125–043, and 92070– 

20125–044 do not utilize the Mylar washer. 

The inspection of the Mylar washer is not 

required on helicopters with stabilizer 

assembly P/N 92070–20125–041, 92070– 

20125–042, 92070–20125–043, or 92070– 

20125–044 installed. 

(iii) Using a 10X or higher power 

magnifying glass, a flashlight, and a mirror, 

visually inspect the hat bushing and both 

upper fittings and lower fittings for a crack, 

corrosion, fretting, deformation, and wear. If 

there is a crack, corrosion, fretting, 

deformation, or wear on any part, before 

further flight, remove the part from service. 

(iv) Using a 10X or higher power 

magnifying glass, a flashlight, and a mirror, 

visually inspect both upper and lower 

support strut rod ends, including each lug 

and conical fitting, and both upper and lower 

attachment fittings on the stabilizer and 

pylon including the bushings for a crack, 

corrosion, fretting, deformation, and wear. If 

there is a crack, corrosion, fretting, 

deformation, or wear on any part, before 

further flight, remove the part from service. 

(3) Within 250 hours TIS or one year, 

whichever occurs first after the effective date 

of this AD, and thereafter at intervals not to 

exceed 250 hours TIS or one year, whichever 

occurs first: 

(i) Remove the stabilizer assembly and 

visually inspect each stabilizer attachment 

bolt and barrel nut set for corrosion, a crack, 

and damage to the threads. For the purposes 

of this inspection, damage may be indicated 

by uneven threads, missing threads, or crossthreading. 

(A) If there is corrosion within allowable 

limits, before further flight, treat for corrosion 

in accordance with FAA-approved 

procedures. 

(B) If there is corrosion that exceeds 

allowable limits, or a crack, or damage to the 

threads, before further flight, remove the bolt 

and barrel nut set from service. 

(ii) Inspect the forward root fitting and the 

aft attachment fitting by: 

(A) Gaining access to the inside of the 

horizontal stabilizer. 

(B) Using Brulin Cleaner SD 1291 (or 

equivalent) and a low-lint cloth, remove all 

traces of sealing compound, oil, and dirt from 

the stabilizer mounting surfaces. 

(C) Using a 10X or higher magnifying glass, 

inspect for any crack, wear, and corrosion. 

(1) If there is a crack, before further flight, 

remove the affected forward root fitting and 

the affected aft attachment fitting from 

service. 

(2) If there is wear or corrosion that 

exceeds allowable limits, before further 

flight, remove the affected forward root 

fitting and the affected aft attachment fitting 

from service. 

(3) If there is wear or corrosion within 

allowable limits, before further flight, treat 

for corrosion in accordance with FAAapproved procedures. 

(D) Visually inspect each attachment fitting 

bolt hole and fastener hole for a crack, wear, 

and corrosion. 

(1) If there is a crack, before further flight, 

remove the affected forward root fitting and 

the affected aft attachment fitting from 

service. 

(2) If there is wear or corrosion that 

exceeds allowable limits, before further 

flight, remove the affected forward root 

fitting and the affected aft attachment fitting 

from service. 

(3) If there is wear or corrosion within 

allowable limits, before further flight, treat 

for corrosion in accordance with FAA 

approved procedures. 

(E) Inspect for loose or working fasteners. 

If there is a loose or working fastener, before 

further flight, remove the fastener from 

service. 

(iii) As an alternative means to inspect for 

cracks in paragraphs (g)(3)(i) and (ii) of this 

AD, perform a florescent penetrate inspection 

(FPI). 

(iv) Visually inspect each forward and aft 

attachment fitting mating surface for wear of 

the abrasion-resistant Teflon coating and 

degradation. For the purposes of this 

inspection, degradation may be indicated by 

fretting. Refer to Figure 204, of S–92 

Maintenance Manual, SA S92A–AMM–000, 

Temporary Revision 55–33, Task 55–11–01– 

210–004, dated March 24, 2020 (TR 55–33), 

for a depiction of the area to be inspected. 

For the purposes of this inspection, wear may 

be indicated by less than 100% coverage of 

the abrasion-resistant Teflon coating. If there 

is wear to the abrasion-resistant Teflon 

coating or degradation, before further flight: 

(A) Chemically strip the abrasion-resistant 

Teflon coating from the entire mounting pad 

in accordance with paragraph 7.A.(7)(a) of TR 

55–33. 

(B) FPI or eddy current inspect for a crack. 

If there is a crack, before further flight, 

remove the stabilizer assembly from service. 

(C) If there is no crack, treat the affected 

area by applying alodine or equivalent. 

Apply abrasion-resistant Teflon coating in 

accordance with paragraphs 7.A.(7)(d) 

through (e) of TR 55–33. 

(4) Installing stabilizer strut fitting P/N 

92209–07404–041 is a terminating action for 

the requirements in paragraph (g)(2) of this 

AD. 

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

not install stabilizer assembly P/N 92205– 

07400–043, 92205–07400–045, or 92205– 

07400–047 on any helicopter. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Boston 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 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. 


khammond on DSKJM1Z7X2PROD with PROPOSALS
Federal Register / Vol. 87, No. 36 / Wednesday, February 23, 2022 / Proposed Rules 10119 

(i) Related Information 

(1) For more information about this AD, 

contact Dorie Resnik, Aerospace Engineer, 

Boston ACO Branch, 1200 District Avenue, 

Burlington, Massachusetts 01803; telephone 

781–238–7693; email 9-AVS-AIR-BACOCOS@faa.gov. 

(2) For service information identified in 

this AD, contact Sikorsky’s Engineering 

Group Sikorsky Aircraft Corporation, 124 

Quarry Road, Trumbell, CT, 06611, United 

States; phone: (800) 946–4337; email: wcs_

cust_service_eng.gr-sik@lmco.com; website: 

www.sikorsky360.com. You may view this 

referenced 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. 

Issued on February 16, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–03769 Filed 2–22–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Parts 4 and 820 

[Docket No. FDA–2021–N–0507] 

RIN 0910–AH99 

Medical Devices; Quality System 

Regulation Amendments 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Proposed rule. 

SUMMARY: The Food and Drug 

Administration (FDA, the Agency, or 

we) is proposing to amend the device 

current good manufacturing practice 

(CGMP) requirements of the Quality 

System (QS) Regulation to align more 

closely with the international consensus 

standard for devices by converging with 

the quality management system (QMS) 

requirements used by other regulatory 

authorities from other jurisdictions (i.e., 

other countries). We propose to do so 

through incorporating by reference an 

international standard specific for 

device quality management systems set 

by the International Organization for 

Standardization (ISO), the 2016 edition 

of ISO 13485 (ISO 13485). Through this 

rulemaking we also propose additional 

requirements to align with existing 

requirements in the Federal Food, Drug, 

and Cosmetic Act (FD&C Act) and its 

implementing regulations, and make 

conforming edits to the Code of Federal 

Regulations (CFR) to clarify the device 

CGMP requirements for combination 

products. This action, if finalized, will 

continue our efforts to align our 

regulatory framework with that used by 

other regulatory authorities to promote 

consistency in the regulation of devices 

and provide timelier introduction of 

safe, effective, high-quality devices for 

patients. 

DATES: Submit either electronic or 

written comments on the proposed rule 

by May 24, 2022. Submit written 

comments (including recommendations) 

on the collection of information under 

the Paperwork Reduction Act of 1995 

(PRA) by March 25, 2022. 

ADDRESSES: You may submit comments 

as follows. Please note that late, 

untimely filed comments will not be 

considered. Electronic comments must 

be submitted on or before May 24, 2022. 

The https://www.regulations.gov 

electronic filing system will accept 

comments until 11:59 p.m. Eastern Time 

at the end of May 24, 2022. Comments 

received by mail/hand delivery/courier 

(for written/paper submissions) will be 

considered timely if they are 

postmarked or the delivery service 

acceptance receipt is on or before that 

date. 

Electronic Submissions 

Submit electronic comments in the 

following way: 

• Federal eRulemaking Portal: 

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

instructions for submitting comments. 

Comments submitted electronically, 

including attachments, to https://

www.regulations.gov will be posted to 

the docket unchanged. Because your 

comment will be made public, you are 

solely responsible for ensuring that your 

comment does not include any 

confidential information that you or a 

third party may not wish to be posted, 

such as medical information, your or 

anyone else’s Social Security number, or 

confidential business information, such 

as a manufacturing process. Please note 

that if you include your name, contact 

information, or other information that 

identifies you in the body of your 

comments, that information will be 

posted on https://www.regulations.gov. 

• If you want to submit a comment 

with confidential information that you 

do not wish to be made available to the 

public, submit the comment as a 

written/paper submission and in the 

manner detailed (see ‘‘Written/Paper 

Submissions’’ and ‘‘Instructions’’). 

Written/Paper Submissions 

Submit written/paper submissions as 

follows: 

• Mail/Hand Delivery/Courier (for 

written/paper submissions): Dockets 

Management Staff (HFA–305), Food and 

Drug Administration, 5630 Fishers 

Lane, Rm. 1061, Rockville, MD 20852. 

• For written/paper comments 

submitted to the Dockets Management 

Staff, FDA will post your comment, as 

well as any attachments, except for 

information submitted, marked and 

identified, as confidential, if submitted 

as detailed in ‘‘Instructions.’’ 

Instructions: All submissions received 

must include the Docket No. FDA– 

2021–N–0507 for ‘‘Medical Devices; 

Quality System Regulation 

Amendments.’’ Received comments, 

those filed in a timely manner (see 

ADDRESSES), will be placed in the docket 

and, except for those submitted as 

‘‘Confidential Submissions,’’ publicly 

viewable at https://www.regulations.gov 

or at the Dockets Management Staff 

between 9 a.m. and 4 p.m., Monday 

through Friday, 240–402–7500. 

• Confidential Submissions—To 

submit a comment with confidential 

information that you do not wish to be 

made publicly available, submit your 

comments only as a written/paper 

submission. You should submit two 

copies total. One copy will include the 

information you claim to be confidential 

with a heading or cover note that states 

‘‘THIS DOCUMENT CONTAINS 

CONFIDENTIAL INFORMATION.’’ The 

Agency will review this copy, including 

the claimed confidential information, in 

its consideration of comments. The 

second copy, which will have the 

claimed confidential information 

redacted/blacked out, will be available 

for public viewing and posted on 

https://www.regulations.gov. Submit 

both copies to the Dockets Management 

Staff. If you do not wish your name and 

contact information to be made publicly 

available, you can provide this 

information on the cover sheet and not 

in the body of your comments and you 

must identify this information as 

‘‘confidential.’’ Any information marked 

as ‘‘confidential’’ will not be disclosed 

except in accordance with 21 CFR 10.20 

and other applicable disclosure law. For 

more information about FDA’s posting 

of comments to public dockets, see 80 

FR 56469, September 18, 2015, or access 

the information at: https://

www.govinfo.gov/content/pkg/FR-2015- 

09-18/pdf/2015-23389.pdf. 

Docket: For access to the docket to 

read background documents or the 

electronic and written/paper comments 

received, go to https://

www.regulations.gov and insert the 

docket number, found in brackets in the 

heading of this document, into the 

‘‘Search’’ box and follow the prompts 


khammond on DSKJM1Z7X2PROD with PROPOSALS