382 Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0873; Project 

Identifier MCAI–2021–00336–R; Amendment 

39–21873; AD 2021–26–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2018–11– 

01, which applied to certain Airbus 

Helicopters Model AS332L2 and 

EC225LP helicopters. AD 2018–11–01 

required installing a cut-out for the lefthand (LH) and right-hand (RH) rail 

support junction profiles and 

repetitively inspecting splices, frame 

5295, and related equipment for a crack. 

Since the FAA issued AD 2018–11–01, 

the manufacturer has developed a 

modification for in-service helicopters 

for replacing aluminum splices with 

steel splices on frame 5295. This AD 

retains the requirements of AD 2018– 

11–01 and requires a modification for 

replacing aluminum splices with steel 

splices on frame 5295 if cracking is 

found. This AD also provides 

terminating action for the repetitive 

inspections. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective February 9, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 9, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 North 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. You may view 

this service information at the FAA, 

Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. For information on the 

availability of this material at the FAA, 

call (817) 222–5110. Service information 

that is incorporated by reference is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0873. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0873; 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 Union Aviation 

Safety Agency (EASA) AD, 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: 

Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance 

& Airworthiness Division, FAA, 1600 

Stewart Ave., Suite 410, Westbury, NY 

11590; telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2018–11–01, 

Amendment 39–19289 (83 FR 23778, 

May 23, 2018), (AD 2018–11–01). AD 

2018–11–01 applied to Airbus 

Helicopters Model AS332L2 and 

EC225LP helicopters with an extended 

aluminum splice installed on frame 

5295, except helicopters with steel 

splice kit part number 332A08–2649– 

3072 installed. AD 2018–11–01 required 

installing a cut-out for the LH and RH 

rail support junction profiles and 

repetitively inspecting splices, frame 

5295, and related equipment for a crack. 

AD 2018–11–01 was prompted by 

reports of cracks on frame 5295 and on 

splices installed to prevent those cracks. 

The FAA issued AD 2018–11–01 to 

address a crack in frame 5295, which if 

not detected and corrected, could lead 

to loss of structural integrity of the 

helicopter frame and subsequent loss of 

control of the helicopter. 

The NPRM published in the Federal 

Register on October 22, 2021 (86 FR 

58600). In the NPRM, the FAA proposed 

to retain the requirements of AD 2018– 

11–01 and require a modification for 

replacing aluminum splices with steel 

splices on frame 5295 if cracking is 

found. The NPRM was prompted by 

EASA AD 2021–0075, dated March 16, 

2021 (EASA AD 2021–0075), which 

supersedes EASA Emergency AD 2014– 

0098–E, dated April 25, 2014 (EASA 

Emergency AD 2014–0098–E), issued by 

EASA, which is the Technical Agent for 

the Member States of the European 

Union. 

EASA advises that since EASA 

Emergency AD 2014–0098–E was 

issued, Airbus Helicopters developed 

MOD 0728463, available for helicopters 

in service through the applicable 

modification service bulletin, providing 

instructions to replace aluminum 

splices with steel splices on frame 5295. 

Airbus Helicopters also issued the 

applicable inspection alert service 

bulletins, as defined in EASA AD 2021– 

0075. Accordingly, EASA AD 2021– 

0075 retains the requirements of EASA 

Emergency AD 2014–0098–E, which is 

superseded, and requires a 

modification, replacing aluminum 

splices with steel splices on helicopters 

on which any cracked aluminum splice 

has been detected. EASA AD 2021–0075 

also advises that the modification is 

terminating action for the repetitive 

inspections. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

These helicopters have been approved 

by 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 reviewed 

the relevant data and determined that 

air safety requires adopting this AD as 

proposed. Accordingly, the FAA is 

issuing this AD to address the unsafe 

condition on these helicopters. Except 

for minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed the following 

Airbus Helicopters service information. 

• Alert Service Bulletins Nos. AS332– 

05.00.97, Revision 1; and EC225– 

05A038, Revision 1; both dated 

February 9, 2021; which specify 

procedures for, among other actions, 

installing a cut-out for the LH and RH 

rail support junction profiles and 

inspecting splices, frame 5295, and 

related equipment for a crack. These 

documents are distinct since they apply 

to different helicopter models. 

• Service Bulletins Nos. AS332– 

53.01.97, Revision 0; and EC225–53– 

061, Revision 0; both dated February 9, 

2021; which specify procedures for 

modifying the helicopter by replacing 

the aluminum LH and RH splices with 


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Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations 383 

steel splices under the plates and the 

brackets of the main gear box (MGB) 

bars. The modification includes taking 

reference readings of the brackets of the 

MGB bars, removing the MGB brackets 

and plates, removing the aluminum 

splices and inspecting the joggling areas 

for scratches or other damage, 

inspecting frame 5295 for cracking 

(including a dye penetrant inspection if 

the inspection results are not 

conclusive), identifying the current 

measurements (values) of the rivet and 

attachment plate holes for installation of 

the steel splice (including determining 

the values of the rivet holes and 

attachment plate holes on frame 5295 

with a calibrated pad and determining 

the elongations of the holes and the 

lengths of the straps), modifying the 

door hinge rail brackets on the LH and 

RH sides, and installing the steel 

splices. These documents are distinct 

since they apply to different helicopter 

models. 

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 Eurocopter 

Helicopters (now Airbus Helicopters) 

Service Bulletin No. 53–003, Revision 4, 

for Model EC225LP helicopters and 

Service Bulletin No. 53.01.52, Revision 

5, for Model AS332L2 helicopters, both 

dated July 23, 2010. The service 

bulletins specify procedures to reinforce 

frame 5295 by installing a new titanium 

plate underneath the fitting and a new 

widened aluminum splice below the 

upper corner of the door. 

The FAA also reviewed Airbus 

Helicopters Service Bulletin No. 05– 

019, Revision 4, dated September 22, 

2014, for Model EC225 LP helicopters. 

This service information specifies 

procedures for cutting out the junction 

profiles. 

The FAA also reviewed Airbus 

Helicopters Alert Service Bulletins Nos. 

AS332–05.00.97, Revision 0; and 

EC225–05A038, Revision 0; both dated 

April 15, 2014; which specify 

procedures for, among other actions, 

installing a cut-out for the LH and RH 

rail support junction profiles and 

inspecting splices, frame 5295, and 

related equipment for a crack. 

Redesignation of AD 2018–11–01 

Paragraph Identifier 

Since AD 2018–11–01 was issued, the 

AD format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have been redesignated in 

this AD, as listed in the following table: 

REVISED PARAGRAPH IDENTIFIER

Requirement in AD 

2018–11–01 

Corresponding 

requirement in this 

AD 

paragraph (e) ............ paragraph (g) 

paragraph (f) ............. paragraph (j)(1) 

Differences Between This AD and the 

EASA AD 2021–0075 

EASA AD 2021–0075 requires 

contacting Airbus Helicopters for 

approved repair instructions if any 

crack is found during an inspection. 

This AD would not require that action. 

Costs of Compliance 

The FAA estimates that this AD 

would affect 38 helicopters of U.S. 

registry. The FAA estimates the 

following costs to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Retained installation of cut-outs on frame 

5295 from AD 2018–11–01.

40 work-hours × $85 per hour = $3,400 ........ $5,000 $8,400 $319,200 

Retained inspection of frame 5295 from AD 

2018–11–01.

2 work-hours × $85 per hour = $170, per inspection cycle.0 170, per 

inspection 

cycle 

6,460, per 

inspection 

cycle. 

The FAA estimates the following 

costs to do any necessary repairs that 

would be required based on the results 

of the inspection. The agency has no 

way of determining the number of 

aircraft that might need these repairs: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Action Labor cost Parts cost Cost per 

product 

Repair ........................................................................... 40 work-hours × $85 per hour = $3,400 ...................... $5,000 $8,400 

New modification (replacement of aluminum splices 

with steel splices).

830 work-hours × $85 per hour = $70,550 .................. 35,000 105,550 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 


TKELLEY on DSK125TN23PROD with RULES1
384 Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations 

(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 

2018–11–01, Amendment 39–19289 (83 

FR 23778, May 23, 2018); and 

■ b. Adding the following new 

airworthiness directive: 

2021–26–14 Airbus Helicopters: 

Amendment 39–21873; Docket No. 

FAA–2021–0873; Project Identifier 

MCAI–2021–00336–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective February 9, 2022. 

(b) Affected ADs 

This AD replaces AD 2018–11–01, 

Amendment 39–19289 (83 FR 23778, May 23, 

2018) (AD 2018–11–01). 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model AS332L2 and Model EC225LP 

helicopters, certificated in any category, as 

specified in paragraphs (c)(1) and (2) of this 

AD. 

(1) Model AS332L2 helicopters equipped 

with extended aluminum splices on frame 

5295 installed in accordance with Airbus 

Helicopters (AH) Modification (MOD) 

0726517, Eurocopter (EC) AS332 Service 

Bulletin (SB) 53.01.52, or AH repair design 

332–53–507–06, 332–53–21–07, or 332–53– 

82–06; except helicopters embodying AH 

MOD 0728463, AH SB AS 332–53.01.97, or 

repair design 332–53–409–12, 332–53–1284– 

13, 332–53–1079–16, or 332–53–1358–16. 

Note 1 to paragraph (c)(1): As referenced 

in paragraphs (c)(1) and (2) of this AD, 

helicopters with AH MOD 0728463 installed 

have replaced the aluminum splices with 

steel splices. 

(2) Model EC225LP helicopters equipped 

with extended aluminum splices on frame 

5295 installed in accordance with AH MOD 

0726517, or EC EC225 SB 53–003 (pre AH 

MOD 0726493 and post AH MOD 0726517), 

except helicopters embodying AH MOD 

0728463, or SB EC225–53–061. 

Note 2 to paragraph (c)(2): Helicopters with 

AH MOD 0726493 have installed steel splice 

kit part number 332A08–2649–3072. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5300, Fuselage Structure. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

on frame 5295 and on aluminum splices 

installed to prevent those cracks. The FAA is 

issuing this AD to address cracking on frame 

5295 and on the inner skins. The unsafe 

condition, if not addressed, could result in 

loss of structural integrity of the helicopter 

frame and subsequent loss of control of the 

helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Installation and Inspections 

With New Service Information and 

Corrective Actions (Modification) 

This paragraph retains the requirements of 

paragraph (e) of AD 2018–11–01, with new 

service information and corrective actions 

(modification). 

(1) Before a splice reaches 1,700 hours 

time-in-service (TIS), within 50 hours TIS, or 

before the helicopter reaches 11,950 hours 

TIS, whichever occurs latest, do the 

following. 

(i) Install the rail support cut-out and 

identify the left-hand (LH) and right-hand 

(RH) junction profile, in accordance with the 

Accomplishment Instructions, paragraph 

3.B.2., of Airbus Helicopters Alert Service 

Bulletin (ASB) No. EC225–05A038, Revision 

1, dated February 9, 2021 (Airbus Helicopters 

ASB No. EC225–05A038, Revision 1); or 

Airbus Helicopters ASB No. AS332–05.00.97, 

Revision 1, dated February 9, 2021 (Airbus 

Helicopters ASB No. AS332–05.00.97, 

Revision 1); whichever is applicable to your 

helicopter. 

(ii) Inspect each splice for a crack in the 

area depicted as Area Y in Figure 3 of Airbus 

Helicopters ASB No. EC225–05A038, 

Revision 1; or Airbus Helicopters ASB No. 

AS332–05.00.97, Revision 1; whichever is 

applicable to your helicopter. If a crack 

exists, do the applicable action required by 

paragraph (g)(1)(ii)(A) or (B) of this AD. 

(A) For any cracking found before the 

effective date of this AD: Repair or replace 

the splice before further flight. 

(B) For any cracking found on or after the 

effective date of this AD: Before further flight, 

modify the helicopter in accordance with 

paragraph 3.B.2. of the Accomplishment 

Instructions of Airbus Helicopters Service 

Bulletin (SB) No. AS332–53.01.97, Revision 

0, dated February 9, 2021 (Airbus Helicopters 

SB No. AS332–53.01.97, Revision 0); or 

Service Bulletin No. EC225–53–061, Revision 

0, dated February 9, 2021 (Airbus Helicopters 

SB No. EC225–53–061, Revision 0); as 

applicable to your helicopter; except as 

specified in paragraph (h) of this AD. 

(2) Thereafter at intervals not to exceed 110 

hours TIS, inspect each splice for a crack in 

the area depicted as Area Y in Figure 3 of 

Airbus Helicopters ASB No. EC225–05A038, 

Revision 1; or Airbus Helicopters ASB No. 

AS332–05.00.97, Revision 1; whichever is 

applicable to your helicopter. If a crack 

exists, do the applicable actions required by 

paragraph (g)(2)(i) or (ii) of this AD. 

Accomplishing the modification specified in 

paragraph (g)(1)(ii)(B) and (g)(2)(ii) of this AD 

terminates the inspections required by this 

paragraph. 

(i) For any cracking found before the 

effective date of this AD: Repair or replace 

the splice before further flight. 

(ii) For any cracking found on or after the 

effective date of this AD: Before further flight, 

modify the helicopter in accordance with 

paragraph 3.B.2. of the Accomplishment 

Instructions of Airbus Helicopters SB No. 

AS332–53.01.97, Revision 0; or Airbus 

Helicopters SB No. EC 225–53–061, Revision 

0; as applicable to your helicopter; except as 

specified in paragraph (h) of this AD. 

(h) Service Information Exceptions 

(1) Where Airbus Helicopters ASB No. 

EC225–05A038, Revision 1; Airbus 

Helicopters ASB No. AS332–05.00.97, 

Revision 1; Airbus Helicopters SB No. 

AS332–53.01.97, Revision 0; and Airbus 

Helicopters SB No. EC 225–53–061, Revision 

0; specify to perform dye-penetrant 

inspections ‘‘if in doubt’’ or ‘‘if any doubt,’’ 

this AD requires performing a dye-penetrant 

inspection during inspections done on or 

after the effective date of this AD. 

(2) Where Airbus Helicopters SB No. 

AS332–53.01.97, Revision 0; and Airbus 

Helicopters SB No. EC 225–53–061, Revision 

0; specify discarding parts, this AD requires 

removing those parts from service. 

(3) Where Airbus Helicopters SB No. 

AS332–53.01.97, Revision 0; and Airbus 

Helicopters SB No. EC 225–53–061, Revision 

0, specify contacting Airbus Helicopter for 

corrective action or further procedures, this 

AD requires repair done in accordance with 

a method approved by the Manager, General 

Aviation & Rotorcraft Section, International 

Validation Branch, FAA; or EASA; or Airbus 

Helicopters’ EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(4) Airbus Helicopters SB No. AS332– 

53.01.97, Revision 0; and Airbus Helicopters 

SB No. EC 225–53–061, Revision 0, specify 

a visual check and dye penetrant inspection 

for cracks on the inside and outside of frame 

5295. For this AD, if any cracking is found 

during any visual check or dye penetrant 

inspection on the inside and outside of frame 

5295, before further flight, repair in 

accordance with a method approved by the 

Manager, General Aviation & Rotorcraft 

Section, International Validation Branch, 

FAA; or EASA; or Airbus Helicopters’ EASA 

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(i) Reporting Not Required 

Although Airbus Helicopters SB No. 

AS332–53.01.97, Revision 0; and Airbus 


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Federal Register / Vol. 87, No. 3 / Wednesday, January 5, 2022 / Rules and Regulations 385 

Helicopters SB No. EC 225–53–061, Revision 

0; specify to submit certain information to 

the manufacturer, this AD does not include 

that requirement. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for the 

installation of the rail support cut-out 

required by paragraph (g)(1)(i) of this AD, if 

that action was performed before June 27, 

2018 (the effective date of AD 2018–11–01) 

using Airbus Helicopters MOD 0728090 or 

Airbus Helicopters SB No. 05–019, Revision 

4, dated September 22, 2014. 

(2) This paragraph provides credit for the 

actions required by paragraphs (g)(1) and (2) 

of this AD, if the actions were performed 

before the effective date of this AD using 

Airbus Helicopters ASB No. EC225–05A038, 

Revision 0, dated April 15, 2014; or Airbus 

Helicopters ASB No. AS332–05.00.97, 

Revision 0, dated April 15, 2014. 

(k) Special Flight Permits 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the helicopter to a location where 

the actions can be performed, provided no 

passengers are onboard. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

Branch, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 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 International Validation 

Branch, send it to the attention of the person 

identified in paragraph (m)(1) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@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. 

(m) Related Information 

(1) For more information about this AD, 

contact Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave., Suite 410, Westbury, NY 11590; 

telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(3) and (4) of this AD. 

(3) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2021–0075, dated March 16, 

2021. You may view the EASA AD at https:// 

www.regulations.gov in Docket No. FAA– 

2021–0873. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Airbus Helicopters Alert Service 

Bulletin No. AS332–05.00.97, Revision 1, 

dated February 9, 2021. 

(ii) Airbus Helicopters Alert Service 

Bulletin No. EC225–05A038, Revision 1, 

dated February 9, 2021. 

(iii) Airbus Helicopters Service Bulletin 

No. AS332–53.01.97, Revision 0, dated 

February 9, 2021. 

(iv) Airbus Helicopters Service Bulletin 

No. EC225–53–061, Revision 0, dated 

February 9, 2021. 

(3) For service information identified in 

this AD, contact Airbus Helicopters, 2701 

North 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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

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

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

ibr-locations.html. 

Issued on December 10, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–28469 Filed 1–4–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0839; Project 

Identifier MCAI–2020–01697–R; Amendment 

39–21877; AD 2021–26–18] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2020–21– 

01 for certain Airbus Helicopters Model 

AS–365N2, AS 365N3, EC 155B, 

EC155B1, and SA–365N1 helicopters. 

AD 2020–21–01 required modifying the 

main gearbox (MGB) tail rotor (T/R) 

drive flange installation. This AD was 

prompted by several reported 

occurrences of loss of tightening torque 

of the Shur-Lok nut, which serves as a 

retainer of the MGB T/R drive flange. 

This AD continues to require modifying 

the MGB T/R drive flange installation, 

and includes additional helicopters in 

the applicability for the required 

actions. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective February 9, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 9, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 12, 2020 (85 FR 

63440, October 8, 2020). 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 North Forum 

Drive, Grand Prairie, TX 75052; phone: 

(972) 641–0000 or (800) 232–0323; fax: 

(972) 641–3775; or at https://

www.airbus.com/helicopters/services/ 

support.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–2021–0839. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0839; 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 Union Aviation 

Safety Agency (EASA) AD, 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: 

Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance 

& Airworthiness Division, FAA, 1600 

Stewart Ave., Suite 410, Westbury, NY 

11590; phone: (516) 228–7330; email: 

andrea.jimenez@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2020–21–01, 


TKELLEY on DSK125TN23PROD with RULES1