Federal Register / Vol. 87, No. 99 / Monday, May 23, 2022 / Rules and Regulations 31125 

and intervals are allowed unless they are 

approved as specified in the provisions of the 

‘‘Ref. Publications’’ section of EASA AD 

2020–0211 or EASA AD 2021–0026. 

(j) New Maintenance or Inspection Program 

Revision 

Except as specified in paragraph (k) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, EASA AD 2021–0208, 

dated September 15, 2021. Accomplishing 

the revision of the existing maintenance or 

inspection program required by this 

paragraph terminates the requirements of 

paragraph (g) of this AD. 

(k) Exceptions to EASA AD 2021–0208 

(1) Where EASA AD 2021–0208 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) The requirements specified in 

paragraphs (1) and (2) of EASA AD 2021– 

0208 do not apply to this AD. 

(3) Paragraph (3) of EASA AD 2021–0208 

specifies to revise ‘‘the AMP’’ within 12 

months after its effective date, but this AD 

requires revising the existing maintenance or 

inspection program, as applicable, within 90 

days after the effective date of this AD. 

(4) The initial compliance time for doing 

the tasks specified in paragraph (3) of EASA 

AD 2021–0208 is at the applicable 

‘‘limitations’’ as incorporated by the 

requirements of paragraph (3) of EASA AD 

2021–0208, or within 90 days after the 

effective date of this AD, whichever occurs 

later. 

(5) The provisions specified in paragraphs 

(4) and (5) of EASA AD 2021–0208 do not 

apply to this AD. 

(6) The ‘‘Remarks’’ section of EASA AD 

2021–0208 does not apply to this AD. 

(7) Where EASA AD 2021–0208 refers to 

Airbus A350 Airworthiness Limitations 

Section (ALS) Part 4, Revision 6 and 

Variation 6.1, replace the text ‘‘Airbus A350 

Airworthiness Limitations Section (ALS) Part 

4, Revision 6 and Variation 6.1,’’ with 

‘‘Airbus A350 Airworthiness Limitations 

Section (ALS) Part 4, Revision 6 and 

Variation 6.1; for any airworthiness 

limitations (tasks and life limits) that are in 

both documents, the airworthiness 

limitations (tasks and life limits) specified in 

Variation 6.1 prevail.’’ 

(l) New Provisions for Alternative Actions 

and Intervals 

After the existing maintenance or 

inspection program has been revised as 

required by paragraph (j) of this AD, no 

alternative actions (e.g., inspections) and 

intervals are allowed unless they are 

approved as specified in the provisions of the 

‘‘Ref. Publications’’ section of EASA AD 

2021–0208. 

(m) Terminating Action for Certain 

Requirements of AD 2019–20–01 

Accomplishing the actions required by 

paragraph (g) or (j) of this AD terminates the 

repetitive greasing task for batch 02 group of 

affected thrust reverser actuators required by 

paragraph (g) of AD 2019–20–01. 

(n) Additional AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, International Validation 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 responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (o) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(o) Related Information 

For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

Large Aircraft Section, FAA, International 

Validation Branch, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 206– 

231–3225; email dan.rodina@faa.gov. 

(p) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on June 21, 2022. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2021–0208, dated September 15, 

2021. 

(ii) [Reserved] 

(4) The following service information was 

approved for IBR on September 3, 2021 (86 

FR 40934, July 30, 2021). 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0211, dated October 5, 

2020. 

(ii) European Union Aviation Safety 

Agency (EASA) AD 2021–0026, dated 

January 20, 2021. 

(5) For the EASA ADs identified in this 

AD, contact EASA, Konrad-Adenauer-Ufer 3, 

50668 Cologne, Germany; telephone +49 221 

8999 000; email ADs@easa.europa.eu; 

internet www.easa.europa.eu. You may find 

this EASA AD on the EASA website at 

https://ad.easa.europa.eu. 

(6) You may view this material 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. 

(7) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, email 

fr.inspection@nara.gov, or go to: https://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on April 15, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. R1–2022–10460 Filed 5–20–22; 8:45 am] 

BILLING CODE 0099–10–D 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0146; Project 

Identifier AD–2021–00449–R; Amendment 

39–22054; AD 2022–11–04] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2020–26– 

13, which applied to certain Sikorsky 

Aircraft Corporation (Sikorsky) Model 

S–92A helicopters. AD 2020–26–13 

required 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 required repetitively inspecting 

certain parts, and depending on the 

inspection results, removing parts from 

service. Finally AD 2020–26–13 

prohibited 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 

AD retains certain requirements and the 

prohibition for installing certain 

stabilizer assemblies on any helicopter 

from AD 2020–26–13, corrects certain 

part numbers, and requires additional 

repetitive inspections. The actions of 

this AD are intended to address an 

unsafe condition on these products. 

DATES: This AD is effective June 27, 

2022. 


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The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 1, 2021 (85 FR 84201, 

December 28, 2020). 

ADDRESSES: For service information 

identified in this final rule, 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. It is also available 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0146. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov in 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 

AD, any service information that is 

incorporated by reference, 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: 

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: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2020–26–13, 

Amendment 39–21368 (85 FR 84201, 

December 28, 2020) (AD 2020–26–13). 

AD 2020–26–13 applied to 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. The NPRM published in the 

Federal Register on February 23, 2022 

(87 FR 10115). The NPRM was 

prompted by the discovery that 

incorrect P/Ns were identified in the 

Applicability and the Required Actions 

paragraphs of AD 2020–26–13. 

Additionally, after the FAA issued AD 

2020–26–13, Sikorsky notified the FAA 

that an additional repetitive inspection 

of certain parts of the stabilizer strut 

assembly is required to prevent the 

unsafe condition. Finally, after the FAA 

issued AD 2020–26–13, 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. 

In the NPRM, the FAA proposed to 

expand the applicability of AD 2020– 

26–13 by adding an additional partnumbered stabilizer assembly. The 

NPRM also proposed to correct 

paragraph (g)(4) of the Required Actions 

so that the installation of the titanium 

stabilizer strut fitting is terminating 

action for the 50-hour time-in-service 

(TIS) inspections of the aluminum 

stabilizer strut fitting. The NPRM also 

proposed to require an additional 

repetitive inspection of certain parts of 

the stabilizer strut assembly. Finally, the 

NPRM proposed to incorporate the FAA 

approved global AMOC. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comments from 

Sikorsky stating that in the section titled 

‘‘Actions Since AD 2020–26–13 Was 

Issued’’ of the NPRM, the part number 

specified (92070–20117–04) is incorrect 

and should be 92070–20117–041. The 

FAA acknowledges this comment; 

however, the part number is not used in 

the ‘‘Background’’ section of this final 

rule. In light of this, the commenter’s 

request no longer applies. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety requires 

adopting the AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for minor editorial 

changes, and any other changes 

described previously, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Related Service Information Under 1 

CFR Part 51 

This AD continues 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 the ADDRESSES section. 

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. 

Differences Between This AD and the 

Service Information 

The service information requires 

returning affected parts to a Sikorsky 

specialist; this AD does not. 

Costs of Compliance 

The FAA estimates that this AD 

affects 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 AD. 

Visually inspecting the stabilizer 

assembly and attached hardware takes 

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 takes about 1 work-hour and 

parts cost about $10,000 for an 

estimated cost of $10,085 per 

replacement. 


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Federal Register / Vol. 87, No. 99 / Monday, May 23, 2022 / Rules and Regulations 31127 

If required, replacing the upper and 

lower support strut rod ends, including 

lug and conical fitting, takes about 1 

work-hour and parts cost about $10,000 

for an estimated cost of $10,085 per 

replacement. 

If required, replacing Mylar washers 

takes about 0.5 work-hour and parts cost 

about $76 for an estimated cost of $119 

per replacement. 

If required, performing a fluorescent 

penetrant inspection takes about 3 

work-hours for an estimated cost of 

$255 per inspection. 

If required, replacing a stabilizer 

assembly takes about 6 work-hours and 

parts cost about $312,000 for an 

estimated cost of $312,510 per 

replacement. 

If required, replacing a forward root 

fitting takes about 10 work-hours and 

parts cost about $25,000 for an 

estimated cost of $25,850 per 

replacement. 

If required, replacing a stabilizer strut 

fitting takes about 10 work-hours and 

parts 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 takes 

about 20 work-hours and parts cost 

about $50,000 for an estimated cost of 

$51,700 per replacement. 

If required, removing wear or 

corrosion and applying corrosion 

preventative compound takes about 0.5 

work-hour and parts cost a nominal 

amount for an estimated cost of $43 per 

action. 

If required, replacing a stabilizer 

attachment bolt and barrel nut set takes 

about 1 work-hour and parts cost about 

$500 for an estimated cost of $585 per 

replacement. 

If required, replacing a fastener takes 

about 0.1 work-hour and parts 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 takes about 5 work-hours 

for an estimated cost of $425 per 

inspection. 

If required, applying alodine or 

equivalent and applying abrasionresistant Teflon coating takes 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 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 has determined that 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: 

■ 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: 

2022–11–04 Sikorsky Aircraft Corporation: 

Amendment 39–22054; Docket No. 

FAA–2022–0146; Project Identifier AD– 

2021–00449–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 27, 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, 

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, 


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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 penetrant 

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 paragraph (i) of this 

AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(i) Related Information 

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. 

(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 February 1, 2021 (85 FR 

84201, December 28, 2020). 


lotter on DSK11XQN23PROD with RULES1
Federal Register / Vol. 87, No. 99 / Monday, May 23, 2022 / Rules and Regulations 31129 

(i) S–92 Maintenance Manual, SA S92A– 

AMM–000, Temporary Revision (TR) 55–33, 

dated March 24, 2020. 

(ii) [Reserved] 

(4) For Sikorsky Aircraft Corporation 

service information identified in this AD, 

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. 

(5) You may view this service information 

at 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: fr.inspection@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on May 16, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–10952 Filed 5–20–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0518; Project 

Identifier MCAI–2021–00822–T; Amendment 

39–22046; AD 2022–10–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus SAS Model A320–214, –251N, 

and –271N airplanes. This AD was 

prompted by reports that damaged seat 

rail covers were detected in the forward 

and aft seat fixation area of some 

airplanes during initial delivery. This 

AD requires a one-time detailed 

inspection of the affected passenger 

seats and corrective actions if necessary, 

as specified in a European Union 

Aviation Safety Agency (EASA). The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD becomes effective June 

7, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 7, 2022. 

The FAA must receive comments on 

this AD by July 7, 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 material incorporated by reference 

(IBR) in this AD, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +49 221 8999 000; 

email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

IBR material on the EASA website at 

https://ad.easa.europa.eu. You may 

view this material 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. 

It is also available in the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0518. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0518; 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 

AD, the mandatory continuing 

airworthiness information (MCAI), any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

Large Aircraft Section, FAA, 

International Validation Branch, 2200 

South 216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3229; email 

vladimir.ulyanov@faa.gov. 

SUPPLEMENTARY INFORMATION: 

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–2022–0518; 

Project Identifier MCAI–2021–00822–T’’ 

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 Vladimir Ulyanov, 

Aerospace Engineer, Large Aircraft 

Section, FAA, International Validation 

Branch, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 

206–231–3229; email vladimir.ulyanov@

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. 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0166, 

dated July 13, 2021 (EASA AD 2021– 

0166) (also referred to as the MCAI), to 

correct an unsafe condition for certain 

Airbus SAS Model A320–214, –251N, 

and –271N airplanes. 

This AD was prompted by reports that 

damaged seat rail covers were detected 

in the forward and aft seat fixation area 

of some airplanes during initial 

delivery. The FAA is issuing this AD to 


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