12804 Federal Register / Vol. 86, No. 42 / Friday, March 5, 2021 / Rules and Regulations 

(i) of this AD, after the maintenance or 

inspection program has been revised as 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (l)(1) of this AD. 

(i) New Maintenance or Inspection Program 

Revision 

Except as specified in paragraph (j) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, European Union Aviation 

Safety Agency (EASA) AD 2020–0215, dated 

October 6, 2020 (EASA AD 2020–0215). 

Accomplishing the maintenance or 

inspection program revision required by this 

paragraph terminates the requirements of 

paragraph (g) of this AD. 

(j) Exceptions to EASA AD 2020–0215 

(1) The requirements specified in 

paragraphs (1) and (2) of EASA AD 2020– 

0215 do not apply to this AD. 

(2) Paragraph (3) of EASA AD 2020–0215 

specifies revising ‘‘the approved AMP’’ 

within 12 months after its effective date, but 

this AD requires revising the existing 

maintenance or inspection program, as 

applicable, to incorporate the ‘‘limitations, 

tasks and associated thresholds and 

intervals’’ specified in paragraph (3) of EASA 

AD 2020–0215 within 90 days after the 

effective date of this AD. 

(3) The initial compliance time for doing 

the tasks specified in paragraph (3) of EASA 

AD 2020–0215 is at the applicable 

‘‘associated thresholds’’ specified in 

paragraph (3) of EASA AD 2020–0215, or 

within 90 days after the effective date of this 

AD, whichever occurs later. 

(4) The provisions specified in paragraphs 

(4) and (5) of EASA AD 2020–0215 do not 

apply to this AD. 

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

2020–0215 does not apply to this AD. 

(k) New Provisions for Alternative Actions 

and Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (i) of this AD, no alternative 

actions (e.g., inspections) or intervals are 

allowed unless they are approved as 

specified in the provisions of the ‘‘Ref. 

Publications’’ section of EASA AD 2020– 

0215. 

(l) Other FAA 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 (m) 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 Dassault Aviation’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(m) Related Information 

For more information about this AD, 

contact Tom Rodriguez, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3226; email tom.rodriguez@

faa.gov. 

(n) 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 April 9, 2021. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0215, dated October 6, 

2020. 

(ii) [Reserved] 

(4) The following service information was 

approved for IBR on January 4, 2019 (83 FR 

61523, November 30, 2018). 

(i) Section 5–40–00, Airworthiness 

Limitations, Revision 13, dated July 2017, of 

the Dassault Falcon 10 Maintenance Manual. 

(ii) [Reserved] 

(5) For EASA AD 2020–0215, 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. 

(6) For Dassault Aviation service 

information identified in this AD, contact 

Dassault Falcon Jet Corporation, Teterboro 

Airport, P.O. Box 2000, South Hackensack, 

NJ 07606; telephone 201–440–6700; internet 

https://www.dassaultfalcon.com. 

(7) 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. 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–2020–1111. 

(8) 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 February 11, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–04340 Filed 3–4–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1106; Project 

Identifier MCAI–2020–01065–T; Amendment 

39–21435; AD 2021–04–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus SAS Model A350–941 and 

A350–1041 airplanes. This AD was 

prompted by reports that suitable 

corrosion protection treatment had not 

been applied to certain areas of the seat 

track. This AD requires a one-time 

detailed inspection of the seat tracks 

between certain frames for suitable 

corrosion protection or presence of 

corrosion, and on-condition actions if 

necessary, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is incorporated by reference. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective April 9, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 9, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, 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 

IBR material on the EASA website at 

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

view this IBR 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 on 

the internet at https://

www.regulations.gov by searching for 


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Federal Register / Vol. 86, No. 42 / Friday, March 5, 2021 / Rules and Regulations 12805 

and locating Docket No. FAA–2020– 

1106. 

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– 

1106; 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: 

Kathleen Arrigotti, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3218; email 

kathleen.arrigotti@faa.gov. 

Background 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2020–0166, dated July 27, 2020 (EASA 

AD 2020–0166) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for certain Airbus SAS 

Model A350–941 and A350–1041 

airplanes. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus SAS Model 

A350–941 and A350–1041 airplanes. 

The NPRM published in the Federal 

Register on December 4, 2020 (85 FR 

78279). The NPRM was prompted by 

reports that suitable corrosion 

protection treatment had not been 

applied to certain areas of the seat track. 

The NPRM proposed to require a onetime detailed inspection of the seat 

tracks between certain frames for 

suitable corrosion protection or 

presence of corrosion, and on-condition 

actions if necessary, as specified in 

EASA AD 2020–0166. 

The FAA is issuing this AD to address 

a potential structural deficiency at 

certain seat track locations, providing 

insufficient resistance to environmental 

damage. This condition, if not 

addressed, could lead to seat or 

monument detachment during an 

emergency landing, possibly resulting in 

injury to occupants and preventing safe 

evacuation from the airplane. See the 

MCAI for additional background 

information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Clarification of Terminology 

The FAA has added paragraph (h)(3) 

to this AD to clarify the definition of 

‘‘deficiencies,’’ which is used in EASA 

AD 2020–0166 but is not referred to in 

the service information referenced in 

EASA AD 2020–0166. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety and the 

public interest require adopting this 

final rule with the change described 

previously and 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. 

The FAA also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2020–0166 describes 

procedures for a one-time detailed 

inspection of the seat tracks between 

certain frames for suitable corrosion 

protection or presence of corrosion, and 

on-condition actions if necessary. Oncondition actions include applying 

protection, removing corrosion, 

measuring the dimensions of the seat 

rails, and performing a splice repair. 

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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 5 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

14 work-hours × $85 per hour = $1,190 ..................................................................................... $0 $1,190 $5,950 

The FAA estimates the following 

costs to do any necessary on-condition 

actions that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of aircraft that might need these 

on-condition actions: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

6 work-hours × $85 per hour = $510 ...................................................................................................................... $0 $510 

According to the manufacturer, some 

or all of the costs of this AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

operators. The FAA does not control 

warranty coverage for affected operators. 

As a result, the FAA has included all 

known costs in the 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 


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12806 Federal Register / Vol. 86, No. 42 / Friday, March 5, 2021 / Rules and Regulations 

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 adding 

the following new airworthiness 

directive: 

2021–04–14 Airbus SAS: Amendment 39– 

21435; Docket No. FAA–2020–1106; 

Project Identifier MCAI–2020–01065–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 9, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus SAS Model 

A350–941 and A350–1041 airplanes, 

certificated in any category, as identified in 

European Union Aviation Safety Agency 

(EASA) AD 2020–0166, dated July 27, 2020 

(EASA AD 2020–0166). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports that 

suitable corrosion protection treatment had 

not been applied to certain areas of the seat 

track. The FAA is issuing this AD to address 

a potential structural deficiency at certain 

seat track locations, providing insufficient 

resistance to environmental damage. This 

condition, if not addressed, could lead to seat 

or monument detachment during an 

emergency landing, possibly resulting in 

injury to occupants and preventing safe 

evacuation from the airplane. 

(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, EASA AD 2020–0166. 

(h) Exceptions to EASA AD 2020–0166 

(1) Where EASA AD 2020–0166 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

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

2020–0166 does not apply to this AD. 

(3) Where paragraph (2) of EASA AD 2020– 

0166 refers to ‘‘deficiencies,’’ for this AD 

deficiencies include unsuitable corrosion 

protection or presence of corrosion. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2020–0166 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Other FAA 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 (k) 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. 

(3) Required for Compliance (RC): Except 

as required by paragraph (j)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Related Information 

For more information about this AD, 

contact Kathleen Arrigotti, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

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

telephone and fax 206–231–3218; email 

kathleen.arrigotti@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 Union Aviation Safety Agency 

(EASA) AD 2020–0166, dated July 27, 2020 

(EASA AD 2020–0166). 

(ii) [Reserved] 

(3) For EASA AD 2020–0166, 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 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. 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–2020–1106. 

(5) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 


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Federal Register / Vol. 86, No. 42 / Friday, March 5, 2021 / Rules and Regulations 12807 

(NARA). For information on the availability 

of this material at NARA, email fedreg.legal@

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

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

Issued on February 9, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–04350 Filed 3–4–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0132; Project 

Identifier MCAI–2020–00947–E; Amendment 

39–21466; AD 2021–05–22] 

RIN 2120–AA64 

Airworthiness Directives; Safran 

Helicopter Engines, S.A. (Type 

Certificate Previously Held by 

Turbomeca, S.A.), Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Safran Helicopter Engines, S.A. (Safran 

Helicopter Engines) Arriel 1B, Arriel 1C, 

Arriel 1C2, Arriel 1D1, Astazou XIV B, 

and Astazou XIV H model turboshaft 

engines. This AD was prompted by the 

detection of positive segregation 

(freckles) on Stage 2 high-pressure 

turbine (HPT) disks and Stage 3 turbine 

wheels. This AD requires removal from 

service of certain Stage 2 HPT disks for 

Safran Helicopter Engines Arriel 1B, 1C, 

1C2, and 1D1 model turbofan engines 

and affected Stage 3 turbine wheels for 

Safran Helicopter Engines Astazou XIV 

B and XIV H model turbofan engines. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective March 22, 

2021. 

The FAA must receive comments on 

this AD by April 19, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this final rule, contact Safran Helicopter 

Engines, S.A., Avenue du 1er Mai, 

Tarnos, France; phone: +33 (0) 5 59 74 

45 11. You may view this service 

information at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 1200 District Avenue, 

Burlington, MA 01803. For information 

on the availability of this material at the 

FAA, call (781) 238–7759. It is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0132. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0132; 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 mandatory continuing 

airworthiness information (MCAI), any 

comments received, and other 

information. The street address for the 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Wego Wang, Aviation Safety Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

(781) 238–7134; fax: (781) 238–7199; 

email: wego.wang@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The European Union Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

AD 2020–0151–E, dated July 9, 2020, for 

Safran Helicopter Engines Arriel 1B, 

Arriel 1C, Arriel 1C2, and Arriel 1D1 

model turboshaft engines, and AD 

2020–0161–E, dated July 17, 2020, for 

Safran Helicopter Engines Astazou XIV 

B and Astazou XIV H model turboshaft 

engines to address an unsafe condition 

for the specified products. EASA AD 

2020–0151–E states: 

Positive segregation (freckles) was detected 

on Stage 2 HP turbine discs manufactured 

from a certain block of material. Other parts 

manufactured from that same block of 

material may also be affected by this nonconformity. 

This condition, if not corrected, could lead 

to HP turbine disc failure and result in highenergy debris release, with consequent 

damage to, and reduced control of, the 

helicopter. 

To address this unsafe condition, SAFRAN 

issued the MSB, as defined in this [EASA] 

AD, to identify affected HP turbine discs and 

provide instructions for replacement. 

For the reason described above, this 

[EASA] AD requires replacement of affected 

parts with serviceable parts, and prohibits reinstallation of affected parts. 

EASA AD 2020–0161–E states: 

Positive segregation (freckles) was detected 

on Stage 3 turbine wheels manufactured from 

a certain block of material. Other parts 

manufactured from that same block of 

material may also be affected by this nonconformity. 

This condition, if not corrected, could lead 

to turbine wheel failure and result in highenergy debris release, with consequent 

damage to, and reduced control of, the 

helicopter. 

To address this unsafe condition, SAFRAN 

issued the MSB, as defined in this [EASA] 

AD, to identify affected turbine wheels and 

provide instructions for replacement. 

For the reason described above, this 

[EASA] AD requires replacement of affected 

parts with serviceable parts, and prohibits reinstallation of affected parts. 

You may obtain further information 

by examining the MCAIs in the AD 

docket at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0132. 

FAA’s Determination 

This product has been approved by 

EASA and is approved for operation in 

the United States. Pursuant to our 

bilateral agreement with the European 

Community, EASA has notified us of 

the unsafe condition described in the 

MCAI. The FAA is issuing this AD 

because the agency evaluated all the 

relevant information provided by EASA 

and has determined that the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. 

Related Service Information 

The FAA reviewed Safran Mandatory 

Service Bulletin (MSB) 292 72 0860, 

Version A, dated July 9, 2020 (MSB 292 

72 0860). MSB 292 72 0860 identifies 

affected Stage 2 HPT disks and 

describes procedures for removing and 

replacing affected Stage 2 HPT disks on 

Safran Helicopter Engines Arriel 1B, 

Arriel 1C, Arriel 1C2, and Arriel 1D1 

model turbofan engines. The FAA also 

reviewed Safran MSB 283 72 0814, 

Version A, dated July 16, 2020 (MSB 

283 72 0814). MSB 283 72 0814 

describes procedures for replacing the 

Stage 3 turbine wheel on Safran 

Helicopter Engines Astazou XIV B and 

Astazou XIV H model turbofan engines. 

AD Requirements 

This AD requires the removal from 

service and replacement of affected 

Stage 2 HPT disks for Safran Helicopter 

Engines Arriel 1B, Arriel 1C, Arriel 1C2, 

and Arriel 1D1 model turbofan engines. 


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