Federal Register / Vol. 86, No. 131 / Tuesday, July 13, 2021 / Rules and Regulations 36635 

9 months’’, this AD requires a compliance 

time of within 108 hours time-in-service. 

(5) Where paragraph (5) of EASA AD 2015– 

0017 specifies a compliance time of ‘‘within 

3 months’’, this AD requires a compliance 

time of within 36 hours time-in-service. 

(6) Where paragraph (3) of EASA AD 2015– 

0017 specifies replacing a part with a 

serviceable part, this AD requires removing 

the part from service. 

(7) Where the service information 

referenced in EASA AD 2015–0017 specifies 

to use tooling, equivalent tooling may be 

used. 

(8) Where the service information 

referenced in paragraph (2) of EASA AD 

2015–0017 specifies a visual check of the 

control grip coiled cable, this AD requires, 

before next flight after the effective date of 

this AD involving a hoist operation, visually 

checking the control grip with coiled cable 

for mechanical damage including deformed 

or damaged switches, damaged housing, 

abrasion, cracks, and cuts. These visual 

checks may be performed by the owner/ 

operator (pilot) holding at least a private pilot 

certificate and must be entered into the 

aircraft records showing compliance with 

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

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

record must be maintained as required by 14 

CFR 91.417, 121.380, or 135.439. 

(9) Where EASA AD 2015–0017 refers to 

November 10, 2014, the effective date of 

EASA AD 2014–0235, this AD requires using 

the effective date of this AD. 

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

2015–0017 does not apply to this AD. 

(i) 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 (j) 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. 

(j) Related Information 

For more information about this AD, 

contact Blaine Williams, Aerospace Engineer, 

Cabin Safety & Environmental Systems 

Section, Los Angeles ACO Branch, 

Compliance & Airworthiness Division, 3960 

Paramount Blvd., Lakewood, CA 90712; 

telephone (562) 627–5371; email 

blaine.williams@faa.gov. 

(k) 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. 

(i) European Aviation Safety Agency 

(EASA) AD 2015–0017, dated February 4, 

2015. 

(ii) [Reserved] 

(3) For EASA AD 2015–0017, contact the 

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. 

(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. 

This material may be found in the AD docket 

on the internet at https://

www.regulations.gov by searching for and 

locating Docket No. FAA–2021–0308. 

(5) 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 fedreg.legal@

nara.gov, or go to https://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued on June 16, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–14778 Filed 7–12–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1033; Project 

Identifier MCAI–2020–01393–R; Amendment 

39–21622; AD 2021–13–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2017–17– 

01, which applied to certain Airbus 

Helicopters Model AS332L2 and 

EC225LP helicopters. AD 2017–17–01 

required repetitive inspections of the 

main rotor blade (MRB) attachment 

pins. This AD continues to require the 

repetitive inspections of the MRB 

attachment pins, and also requires 

repetitive measurement of the 

attachment pin chamfer at certain 

intervals after corrosion removal, as 

specified in a European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD, which is 

incorporated by reference. This AD was 

prompted by the FAA’s determination 

that it is necessary to measure the 

attachment pin chamfer after corrosion 

removal, that replacement of an 

attachment pin after four corrosion 

removals is no longer necessary, and 

that all Airbus Helicopters Model 

AS332L2 and EC225LP helicopters are 

affected by the unsafe condition. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective August 17, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 17, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

the EASA, Konrad-Adenauer-Ufer 3, 

50668 Cologne, Germany; phone: +49 

221 8999 000; email: ADs@

easa.europa.eu; internet: 

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

material on the EASA website at https:// 

ad.easa.europa.eu. You may view this 

material 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 in the AD docket on the 

internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2020–1033. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

1033; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

any comments received, and other 

information. The 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: 

Katherine Venegas, Aviation Safety 

Engineer, Cabin Safety, Mechanical and 

Environmental Systems Section, Los 

Angeles ACO Branch, FAA, 3960 

Paramount Boulevard, Lakewood, CA 

90712–4137; phone: 562–627–5353; 

email: katherine.venegas@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The EASA, which is the Technical 

Agent for the Member States of the 


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36636 Federal Register / Vol. 86, No. 131 / Tuesday, July 13, 2021 / Rules and Regulations 

European Union, has issued EASA AD 

2018–0172, dated August 7, 2018 (EASA 

AD 2018–0172) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for all Airbus 

Helicopters Model AS332L2 and 

EC225LP helicopters. EASA AD 2018– 

0172 superseded EASA AD 2015–0016, 

dated January 30, 2015 (which 

prompted FAA AD 2017–17–01, 

Amendment 39–18991 (82 FR 39506, 

August 21, 2017) (AD 2017–17–01)). 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2017–17–01. 

AD 2017–17–01 applied to certain 

Airbus Helicopters Model AS332L2 and 

EC225LP helicopters. The NPRM 

published in the Federal Register on 

November 24, 2020 (85 FR 74931). The 

NPRM was prompted by the FAA’s 

determination that it is necessary to 

measure the attachment pin chamfer 

after corrosion removal, that 

replacement of an attachment pin after 

four corrosion removals is no longer 

necessary, and that all Airbus 

Helicopters Model AS332L2 and 

EC225LP helicopters are affected by the 

unsafe condition. The NPRM proposed 

to continue to require the repetitive 

inspections of the MRB attachment pins, 

as specified in an EASA AD. The NPRM 

also proposed to require repetitive 

measurement of the attachment pin 

chamfer at certain intervals after 

corrosion removal, as specified in an 

EASA AD. 

The FAA is issuing this AD to address 

cracked MRB attachment pins which 

could result in loss of an MRB and 

subsequent loss of control of the 

helicopter. See the MCAI for additional 

background information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The following presents 

the comments received on the NPRM 

and the FAA’s response to each 

comment. 

Request To Allow Rework of Corrosion 

Pits 

Air Center Helicopters, Inc. (ACH) 

and Airbus Helicopters (AH) requested 

that the FAA allow rework of corrosion 

pits. ACH disagreed with the FAA’s 

determination to disallow blade pin 

rework, and stated that scrapping blade 

pins due to disallowing rework is 

fiscally irresponsible, due to substantial 

replacement costs (each main rotor hub 

has 10 blade pins). ACH pointed out 

that since the FAA issued AD 2017–17– 

01, ACH has removed and reworked 

numerous corrosion pitted EC225 blade 

pins from service in accordance with 

Airbus Helicopters Alert Service 

Bulletin EC225–05A040. ACH discussed 

that in many cases the corrosion pitting 

was nearly undetectable using 10X 

magnification, and that additional 

inspections were done using a 0.005 

inch ball gauge. ACH also mentioned 

that visible corrosion pitting was often 

undetectable using the ball gauge, and 

pointed out that to ACH, the 

undetectable corrosion pitting indicated 

that the blade pin was salvageable with 

a minimum of rework. 

ACH agreed with not allowing blade 

pin rework in FAA AD 2017–17–01 

because Revision 0 of Airbus 

Helicopters Alert Service Bulletin 

EC225–05A040 did not specify a 

method to determine dimensional 

airworthiness after rework. ACH stated 

that Revision 1 of Airbus Helicopters 

Alert Service Bulletin EC225–05A040, 

included post rework inspection 

procedures and dimensional criteria for 

post rework blade pin airworthiness, 

and that Revision 2 of Airbus 

Helicopters Alert Service Bulletin 

EC225–05A040 introduced a maximum 

radius to the caliper points of 0.6 mm 

(0.0236 inch) to ensure the point seats 

properly within the external blade pin 

blend radius ensuring accurate wall 

thickness measurements. ACH specified 

that Airbus Helicopters Alert Service 

Bulletin EC225–05A040 provides a 

definitive procedure for inspection and 

verification of blade pin airworthiness 

after corrosion pitting rework, and that 

the procedure was approved by EASA. 

ACH and AH argued that the term 

‘‘corrosion’’ in Airbus Helicopters Alert 

Service Bulletin EC225–05A040, is 

intended to include corrosion pitting. 

AH pointed out that the service 

information is currently at Revision 2, 

that the revision was based on research 

and feedback from customer reports, 

and implemented detailed inspection 

procedures and measurements to 

determine airworthiness of the blade 

pins. AH then stated that the FAA did 

not reflect the intentions of the latest 

service information. 

The FAA disagrees with the request. 

Although the MCAI and service 

information specify rework in case 

corrosion is found, neither clearly 

address action in the case of corrosion 

pitting. Corrosion pitting is different 

than uniform corrosion and can be more 

dangerous. Additionally, the FAA does 

not agree with the inference that the 

intention of the service information is to 

allow rework of corrosion pits. The FAA 

has not revised this AD in this regard. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. The FAA has 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2018–0172 specifies 

procedures for repetitive inspections for 

corrosion and cracking of the 

attachment pins and corrective actions 

if necessary, and repetitive conditional 

measurement of the thickness of the 

chamfer of the attachment pins at 

certain intervals after corrosion removal. 

Corrective actions include corrosion 

removal and replacement of the 

attachment pins. This material 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. 

Differences Between This Proposed AD 

and the MCAI 

EASA AD 2018–0172 requires an 

inspection of the affected part in 

accordance with the applicable service 

information. The service information for 

Model AS332L2 helicopters and the 

service information for Model EC225LP 

helicopters both describe procedures for 

an inspection for corrosion and cracking 

of the attachment pins. However, the 

service information for Model AS332L2 

helicopters also describes an inspection 

of the protective coating of each 

attachment pin for scratches and 

missing protective coating and sanding 

if necessary; the service information for 

Model EC225LP helicopters does not 

describe those actions. 

Although EASA AD 2018–0172 

requires corrective actions if there is 

corrosion or cracking of the attachment 

pins, EASA AD 2018–0172 does not 

require any corrective actions if there is 

any scratch or any missing protective 

coating. 

This AD requires inspecting the 

protective coating of each attachment 

pin for scratches and missing protective 

coating, and sanding if there is any 

scratch or any missing protective 

coating, for all affected helicopters. 

EASA AD 2018–0172 requires 

removing corrosion but does not 


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Federal Register / Vol. 86, No. 131 / Tuesday, July 13, 2021 / Rules and Regulations 36637 

provide a corrective action if there are 

corrosion pits. This AD requires 

replacing an attachment pin that has 

any corrosion pitting. 

The service information referenced in 

EASA AD 2018–0172 specifies to do a 

non-destructive inspection if in doubt 

about whether there is a crack; that 

action is not required by this AD. 

The service information referenced in 

EASA AD 2018–0172 specifies 

contacting Airbus Helicopters if any 

attachment pin with a crack is found 

and returning that part to Airbus 

Helicopters; those actions are not 

required by this AD. 

Costs of Compliance 

The FAA estimates that this AD 

affects 28 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 actions from AD 

2017-17-01.

1 work-hour × $85 per hour = $85 per 

inspection cycle.

$0 $85 per inspection cycle ... $2,380 per inspection 

cycle. 

The FAA estimates the following 

costs to do any necessary on-condition 

measurements (new action), corrosion 

removal, and replacements that would 

be required based on the results of any 

required actions. The FAA has no way 

of determining the number of 

helicopters that might need these oncondition measurements, corrosion 

removal, and replacements: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per product 

Up to 11 work-hours × $85 per hour = Up to $935 ...................................................... Up to $5,720 ...................... Up to $6,655. 

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: 

(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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing Airworthiness Directive 

2017–17–01, Amendment 39–18991 (82 

FR 39506, August 21, 2017); and 

■ b. Adding the following new 

airworthiness directive: 

2021–13–17 Airbus Helicopters: 

Amendment 39–21622; Docket No. 

FAA–2020–1033; Project Identifier 

MCAI–2020–01393–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 17, 2021. 

(b) Affected ADs 

This AD removes AD 2017–17–01, 

Amendment 39–18991 (82 FR 39506, August 

21, 2017) (AD 2017–17–01). 

(c) Applicability 

This AD applies to all Airbus Helicopters 

Model AS332L2 and EC225LP helicopters, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Codes 6200, Main Rotor System. 

(e) Reason 

This AD was prompted by a report of three 

cracked main rotor blade (MRB) attachment 

pins. The FAA is issuing this AD to address 

cracked MRB attachment pins which could 

result in loss of an MRB and subsequent loss 

of control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD 2018–0172, dated 

August 7, 2018 (EASA AD 2018–0172). 

(h) Exceptions to EASA AD 2018–0172 

(1) Where EASA AD 2018–0172 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where EASA AD 2018–0172 refers to 

February 13, 2015 (the effective date of EASA 

AD 2015–0016, dated January 30, 2015), this 

AD requires using September 25, 2017 (the 

effective date of AD 2017–17–01). 


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

2018–0172 does not apply to this AD. 

(4) Where paragraph (1) of EASA AD 2018– 

0172 specifies to inspect each affected part, 

for this AD, prior to the inspection for 

corrosion, inspect the protective coating on 

the inside of the attachment pin for scratches 

and missing protective coating. If there is any 

scratch or any missing protective coating, 

prior to the inspection for corrosion, sand the 

attachment pin to remove the varnish in the 

area depicted as ‘‘Area A’’ in Figure 1 of the 

‘‘applicable ASB’’ as defined in EASA AD 

2018–0172. 

(5) Where paragraph (3) of EASA AD 2018– 

0172 requires removing corrosion, for this 

AD, if there is any corrosion pitting, before 

further flight, replace the affected attachment 

pin. Do not sand the attachment pin to 

remove a corrosion pit. 

(6) Although the service information 

referenced in EASA AD 2018–0172 specifies 

to do a non-destructive inspection if in doubt 

about whether there is a crack, that action is 

not required by this AD. 

(7) Although the service information 

referenced in EASA AD 2018–0172 specifies 

contacting Airbus Helicopters if any 

attachment pin with a crack is found and 

returning that part to Airbus Helicopters, 

those actions are not required by this AD. 

(8) Although the service information 

referenced in EASA AD 2018–0172 specifies 

discarding certain parts, that action is not 

required by this AD. 

(9) Where EASA AD 2018–0172 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(i) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, are not allowed. 

(j) 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 (k) 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. 

(k) Related Information 

For more information about this AD, 

contact Katherine Venegas, Aviation Safety 

Engineer, Cabin Safety, Mechanical and 

Environmental Systems Section, Los Angeles 

ACO Branch, FAA, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5353; email: 

katherine.venegas@faa.gov. 

(l) 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. 

(i) European Aviation Safety Agency 

(EASA) AD 2018–0172, dated August 7, 

2018. 

(ii) [Reserved] 

(3) For EASA AD 2018–0172, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +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. 

(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. This 

material may be found in the AD docket on 

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

by searching for and locating Docket No. 

FAA–2020–1033. 

(5) 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 fedreg.legal@

nara.gov, or go to: https://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued on June 17, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–14775 Filed 7–12–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0195; Project 

Identifier MCAI–2020–00262–R; Amendment 

39–21624; AD 2021–13–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2014–11– 

02 for Airbus Helicopters Model SA– 

365N, SA–365N1, AS–365N2, and AS 

365 N3 helicopters. AD 2014–11–02 

required repetitively inspecting frame 

number (No.) 9 for a crack. This AD was 

prompted by Airbus Helicopters 

developing a modification that provides 

an optional terminating action for the 

repetitive inspections required by AD 

2014–11–02. This AD retains the 

requirements of AD 2014–11–02, 

provides an optional terminating action 

for the repetitive inspections, and 

reduces the applicability by excluding 

certain post-modified helicopters. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective August 17, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 17, 2021. 

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–2021–0195. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.govby 

searching for and locating Docket No. 

FAA–2021–0195; 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: Matt 

Fuller, AD Program Manager, General 

Aviation & Rotorcraft Unit, 

Airworthiness Products Section, 

Operational Safety Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

matthew.fuller@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2014–11–02, 

Amendment 39–17852 (79 FR 33050, 

June 10, 2014) (AD 2014–11–02). AD 

2014–11–02 applied to Airbus 

Helicopters (previously Eurocopter 


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