49904 Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 

(b) Affected ADs 

This AD replaces AD 2017–12–13, 

Amendment 39–18928 (82 FR 27983, June 

20, 2017). 

(c) Applicability 

This AD applies to Airbus SAS airplanes 

specified in paragraphs (c)(1) through (3) of 

this AD, certificated in any category, as 

identified in European Union Aviation Safety 

Agency (EASA) AD 2020–0280, dated 

December 14, 2020 (EASA AD 2020–0280). 

(1) Model A318–111, –112, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

crack found during an inspection of the 

pocket radius of the fuselage frame, and a 

determination that similar cracks may 

develop in nearby areas of the fuselage frame 

and that additional airplanes are subject to 

the unsafe condition. The FAA is issuing this 

AD to address cracking of the pocket radius, 

which could lead to in-flight decompression 

of the airplane and possible injury to the 

passengers. 

(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 2020–0280. 

(h) Exceptions to EASA AD 2020–0280 

(1) Where EASA AD 2020–0280 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where paragraph (9) of EASA AD 2020– 

0280 specifies if any crack is found during 

any inspection to ‘‘contact Airbus for 

approved repair instructions and accomplish 

those instructions accordingly,’’ this AD 

requires if any cracking is found, the cracking 

must be repaired before further flight 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) Where paragraph (10) of EASA AD 

2020–0280 specifies credit for actions ‘‘in 

accordance with the instructions of an Airbus 

Repair Design Approval Sheet (RDAS), [and 

to] accomplish the next inspection of each 

repaired area in accordance with the 

instructions of, and within the compliance 

time as specified in, the applicable RDAS,’’ 

this AD requires using ‘‘in accordance with 

repair instructions approved, and within the 

compliance time specified in the repair 

approval, using a method approved by the 

Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature.’’ 

(4) Where paragraph (11) of EASA AD 

2020–0280 specifies terminating actions 

apply only if specified ‘‘in the Airbus RDAS 

instructions for a repaired aeroplane,’’ this 

AD requires using ‘‘in repair instructions 

approved using a method approved by the 

Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature.’’ 

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

2020–0280 does not apply to this AD. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2020–0280 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 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 Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3223; email Sanjay.Ralhan@

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. 

(3) The following service information was 

approved for IBR on October 5, 2021 (86 FR 

48485, August 31, 2021). 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0280, dated December 14, 

2020. 

(ii) [Reserved] 

(4) For EASA AD 2020–0280, 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. 

(5) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 216th 

St., Des Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

(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/ibrlocations.html. 

Issued on September 1, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–19245 Filed 9–1–21; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0137; Project 

Identifier MCAI–2020–00269–E; Amendment 

39–21688; AD 2021–17–05] 

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. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2014–04– 

06 for all Safran Helicopter Engines, 


lotter on DSK11XQN23PROD with RULES1
Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 49905 

S.A. (Safran Helicopter Engines) Arrius 

2B1, 2B1A, 2B2, and 2K1 model 

turboshaft engines. AD 2014–04–06 

required initial and repetitive 

inspections of the hydro-mechanical 

metering unit (HMU) high-pressure 

pump drive gear shaft splines, cleaning 

and inspections of the sleeve assembly 

splines, and replacement of the sleeve 

assembly on the affected high-pressure 

pump drive gear shaft or replacement of 

the HMU if the HMU fails inspection. 

This AD was prompted by in-flight 

shutdowns caused by interrupted fuel 

supply at the HMU. This AD requires 

revised inspections and continues to 

require cleaning of the sleeve assembly 

splines, and replacement of the sleeve 

assembly on the affected high-pressure 

pump drive gear shaft or replacement of 

the HMU if the HMU fails an inspection. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective October 12, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 12, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Safran Helicopter Engines, S.A., Avenue 

du 1er Mai, 40220 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– 

0137. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0137; 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 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: 

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 FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2014–04–06, 

Amendment 39–17764 (79 FR 9990, 

February 24, 2014), (AD 2014–04–06). 

AD 2014–04–06 applied to all 

Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, 

and 2K1 model turboshaft engines. The 

NPRM published in the Federal 

Register on March 12, 2021 (86 FR 

14017). The NPRM was prompted by inflight shutdowns caused by interrupted 

fuel supply at the HMU. Since the FAA 

issued AD 2014–04–06, the 

manufacturer has published new service 

information that revises the inspections 

for certain HMUs, reduces compliance 

times for initial inspections, and allows 

application of non-cumulative tolerance 

of 10% of operating hours to be applied 

to the timing of the repetitive inspection 

of HMUs installed on certain engines. In 

the NPRM, the FAA proposed to 

continue to require cleaning of the 

sleeve assembly splines and replacing 

the HMU or the sleeve assembly on the 

affected high-pressure pump drive gear 

shaft if the HMU fails inspection. In the 

NPRM, the FAA also proposed to 

require initial and repetitive inspections 

of the HMU high-pressure pump drive 

gear shaft splines. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

The European Union Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

AD 2020–0033, dated February 25, 2020 

(referred to after this as ‘‘the MCAI’’), to 

address the unsafe condition on these 

products. The MCAI states: 

A number of in-flight shut-down (IFSD) 

occurrences have been reported for ARRIUS 

2 engines. The results of the technical 

investigations concluded that these events 

were caused by deterioration of the splines 

on the high pressure (HP)/low pressure (LP) 

pump assembly drive shaft of the HMU, 

which eventually interrupted the fuel supply 

to the engine. 

This condition, if not detected and 

corrected, could lead to further cases of 

engine IFSD, possibly resulting in forced 

landing with consequent damage to the 

helicopter and injury to occupants. 

To address these occurrences, Turbome ́ca 

published MSB 319 73 2825 (up to version 

G) to provide instructions for inspection of 

the HMU and sleeve assembly. Consequently, 

EASA issued AD 2013–0082 to require 

repetitive inspections of the drive gear shaft 

splines of the HP pump, and, depending on 

findings, accomplishment of applicable 

corrective action(s). 

Since that [EASA] AD was issued, 

SAFRAN published the MSB to provide 

specific inspection instructions for HMU 

installed on a helicopter after 31 January 

2013, to reduce the compliance time for the 

initial inspection of Group 1 engines that 

were not previously inspected in accordance 

with version G or later of the MSB, and to 

provide some operational margin before the 

first inspection in all possible scenarios. 

For the reason described above, this 

[EASA] AD retains the requirements of AD 

2013–0082, which is superseded, and 

requires accomplishment of the actions in 

accordance with the instructions of the MSB, 

as defined in this [EASA] AD. 

You may obtain further information 

by examining the MCAI in the AD 

docket at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0137. 

FAA’s Determination 

This product has been approved by 

EASA and is approved for operation in 

the United States. Pursuant to the FAA’s 

bilateral agreement with the European 

Community, EASA has notified the 

agency of the unsafe condition 

described in the MCAI and service 

information. The FAA is issuing this 

final rule because the agency evaluated 

all the relevant information provided by 

EASA and determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety requires 

adoption of the AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. This AD is adopted as 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Safran Helicopter 

Engines Mandatory Service Bulletin 

(MSB) No. 319 73 2825, Version J, dated 

March 15, 2019. This MSB specifies 

procedures for inspecting the HMU 

high-pressure pump drive gear shaft 

splines and cleaning and inspecting the 

sleeve assembly splines. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in ADDRESSES. 

Per Safran Helicopter Engines 

standing practice at the time MSB 319 

73 2825, Version J, was issued, MSB 319 

73 2825, Version J, is undated. The issue 


lotter on DSK11XQN23PROD with RULES1
49906 Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 

date for MSB 319 73 2825, Version J, 

appears on the Safran Helicopter 

Engines Arrius 2 B1 Service Bulletin 

Index, No. X 319 L5 980 2, dated 

December 11, 2020. 

Costs of Compliance 

The FAA estimates that this AD 

affects 194 engines installed on 

helicopters of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Visual inspection of drive gear shaft splines; 

cleaning and inspection of sleeve assembly 

splines.

2 work-hours × $85 per hour = $170 ............. $900 $1,070 $207,580 

The FAA estimates the following 

costs to do any necessary replacements 

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 

replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace sleeve assembly on high-pressure pump 

drive gear shaft.

1 work-hour × $85 per hour = $85 ............................... $898 $983 

Replace HMU ............................................................... 1 work-hour × $85 per hour = $85 ............................... 45,000 45,085 

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 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 

2014–04–06, Amendment 39–17764 (79 

FR 9990, February 24, 2014); and 

■ b. Adding the following new 

airworthiness directive: 

2021–17–05 Safran Helicopter Engines, 

S.A. (Type Certificate previously held by 

Turbomeca S.A.): Amendment 39– 

21688; Docket No. FAA–2021–0137; 

Project Identifier MCAI–2020–00269–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 12, 2021. 

(b) Affected ADs 

This AD replaces AD 2014–04–06, 

Amendment 39–17764 (79 FR 9990, February 

24, 2014). 

(c) Applicability 

This AD applies to Safran Helicopter 

Engines, S.A. (Type Certificate previously 

held by Turbomeca S.A.) Arrius 2B1, 2B1A, 

2B2, and 2K1 model turboshaft engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7320—Fuel Controlling System. 

(e) Unsafe Condition 

This AD was prompted by in-flight 

shutdowns caused by interrupted fuel supply 

at the hydro-mechanical metering unit 

(HMU). The FAA is issuing this AD to 

prevent interrupted fuel supply at the HMU. 

The unsafe condition, if not addressed, could 

result in engine in-flight shutdown, forced 

landing of the helicopter, damage to the 

helicopter and injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within the compliance time specified 

in Table 1 to paragraph (g)(1) of this AD, as 

applicable, and before re-installation of the 

HMU after each removal from the engine, 

visually inspect the drive gear shaft splines 

of the high-pressure pump, and clean and 

inspect the sleeve assembly splines in 

accordance with paragraphs 2.4.2 and 2.4.3, 

or 4.4.2 and 4.4.3, as applicable, of Safran 


lotter on DSK11XQN23PROD with RULES1
Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 49907 

Helicopter Engines Mandatory Service Bulletin (MSB) 319 73 2825, Version J, dated 

March 15, 2019. 

(2) Repeat the inspection required by 

paragraph (g)(1) of this AD at intervals not to 

exceed 500 HMU operating hours since the 

previous inspection. 

Note 1 to paragraph (g)(2): A noncumulative tolerance of 10% of HMU 

operating hours (hrs) may be applied to the 

timing of each repetitive inspection, with a 

maximum allowable tolerance of +50 HMU 

operating hrs. For example, counting from 

the initial inspection, the repeat inspections 

would occur at the following times, with the 

tolerance noted in parentheses; 500 HMU 

operating hrs (+50 hrs), 1000 HMU operating 

hrs (+50 hrs), 1500 HMU operating hrs (+50 

hrs). 

(3) If a rejectable indication is found during 

any inspection required by paragraphs (g)(1) 

or (2) of this AD, replace the sleeve assembly 

on the affected high-pressure pump drive 

gear shaft or replace the affected HMU in 

accordance with paragraph 2.4.2 or 4.4.2 of 

the MSB. 

(h) Definitions 

(1) A Group 1 HMU is an HMU that was 

first installed on or before January 31, 2013, 

and that has not previously been inspected 

in accordance with Safran Helicopter Engines 

MSB 319 73 2825 Version G or later. 

(2) A Group 2 HMU is an HMU that was 

first installed after January 31, 2013, or a 

HMU that has previously been inspected in 

accordance with Safran Helicopter Engines 

MSB 319 73 2825 Version G or later. 

(i) No Reporting Requirement 

The reporting requirements specified in the 

Accomplishment Instructions, paragraph 

2.4.2, of the MSB are not required by this AD. 

(j) Credit for Previous Actions 

You may take credit for any initial 

inspection or replacement of an HMU or the 

sleeve assembly on the affected high-pressure 

pump drive gear shaft required by paragraph 

(g) of this AD if you performed the inspection 

or replacement in accordance with Safran 

Helicopter Engines MSB 319 73 2825, 

Version G, dated January 24, 2013; Version 

H, dated September 1, 2014; or Version I, 

dated April 26, 2016. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO 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 ECO Branch, send it to 

the attention of the person identified in 

Related Information. Information may be 

emailed to: ANE-AD-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. 

(l) Related Information 

For more information about this AD, 

contact Wego Wang, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: (781) 

238–7134; fax: fax: (781) 238–7199; email: 

wego.wang@faa.gov. 

(m) 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. 

(i) Safran Helicopter Engines Mandatory 

Service Bulletin (MSB) No. 319 73 2825, 

Version J, dated March 15, 2019. 

Note 2 to paragraph (m)(2)(i): Per Safran 

Helicopter Engines standing practice at the 

time MSB 319 73 2825, Version J, was issued, 

MSB 319 73 2825, Version J, is undated. The 

issue date for MSB 319 73 2825, Version J, 

appears on the Safran Helicopter Engines 

Arrius 2 B1 Service Bulletin Index, No. X 319 

L5 980 2, dated December 11, 2020. 

(ii) [Reserved] 

(3) For Safran Helicopter Engines service 

information identified in this AD, contact 

Safran Helicopter Engines, S.A., Avenue du 

1er Mai, 40220 Tarnos, France; phone: +33 

(0) 5 59 74 45 11. 

(4) You may view this service information 

at 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. 

(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 August 7, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–19226 Filed 9–3–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0498; Project 

Identifier 2019–SW–072–AD; Amendment 

39–21722; AD 2021–19–04] 

RIN 2120–AA64 

Airworthiness Directives; He ́licopte`res 

Guimbal Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 


lotter on DSK11XQN23PROD with RULES1ER07SE21.003</GPH>

Table 1 to Paragraph (g)(l) 

HMU Group/ Condition Compliance Time 

Group 1 / 150 HMU operating hours or Within 50 HMU operating hours after the 

more accumulated since new or since last effective date of this AD. 

overhaul. 

Group 1 / Less than 150 HMU operating Before exceeding 200 HMU operating 

hours accumulated since new or since last hours after the effective date of this AD. 

overhaul. 

Group 2 Within 500 HMU operating hours since 

the last inspection or since first 

installation of the HMU.