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. 


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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. 
49908 Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

He ́licopte`res Guimbal Model Cabri G2 

helicopters with any metal bushing 

installed on the main rotor (M/R) 

swashplate guide bellcrank. This AD 

was prompted by a report of cracks 

discovered on the M/R scissor link 

during scheduled maintenance on 

several helicopters. This AD requires 

removing all metal bushings from 

service, visually inspecting the lug bore 

area and depending on the inspection 

results, removing certain parts from 

service and installing certain partnumbered plastic bushings. This AD 

also prohibits installing any metal 

bushing on any helicopter. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 12, 

2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

He ́licopte`res Guimbal, Basile Ginel, 

1070, rue du Lieutenant Parayre, 

Ae ́rodrome d’Aix-en-Provence, 13290 

Les Milles, France; telephone 33–04– 

42–39–10–88; email basile.ginel@

guimbal.com; web https://

www.guimbal.com. You may view the 

referenced 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0498; 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 street 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 by adding an AD that would 

apply to He ́licopte`res Guimbal (HG) 

Model Cabri G2 helicopters, certificated 

in any category, with any metal 

bushings installed on the main rotor 

(M/R) swashplate guide bellcrank and 

without plastic bushing part number 

HG22–1001 or HG modification 16–009. 

The NPRM published in the Federal 

Register on July 9, 2021 (86 FR 36241). 

In the NPRM, the FAA proposed to 

require within 50 hours time-in-service 

or 2 months, whichever occurs first after 

the effective date of this AD, 

disconnecting the bellcrank from the 

swashplate guide, removing each bolt 

and using a certain tool, removing 

certain parts from service. The NPRM 

also proposed to require visually 

inspecting the lug bore area for 

corrosion and cracks and depending on 

the inspection results, removing certain 

parts from service, or repairing the area 

using an FAA-approved method, 

installing certain part-numbered plastic 

bushings, coating the area with a 

compound, reinstalling certain parts, 

applying a specified torque, and 

installing cotter pins. The NPRM was 

prompted by EASA AD 2019–0185, 

dated July 30, 2019 (EASA AD 2019– 

0185), issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union, to correct an 

unsafe condition for He ́licopte`res 

Guimbal Model Cabri G2 helicopters. 

EASA advises that during scheduled 

maintenance on several helicopters, 

cracks were found on the M/R scissor 

link due to corrosion. EASA states this 

corrosion was caused by stress induced 

by the mounting of the metal bushing 

inside the lug hole. EASA further states 

metal bushings are also installed on the 

M/R swashplate guide bellcrank, where 

similar cracking may occur. This 

condition, if not addressed, could result 

in failure of the M/R swashplate guide 

bellcrank and reduced control of the 

helicopter. 

Accordingly, EASA AD 2019–0185 

requires replacing any part-numbered 

metal bushing with plastic bushing part 

number (P/N) HG22–1001. EASA AD 

2019–0185 also prohibits installing any 

part-numbered metal bushing on the M/ 

R swashplate guide bellcrank other than 

P/N HG22–1001 on any helicopter. 

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 products. 

Related Service Information 

The FAA reviewed Guimbal Service 

Bulletin SB 17–003, Revision D, dated 

August 27, 2019 (SB 17–003 Rev D). 

This service information specifies 

disconnecting the bellcrank installed on 

the swashplate guide by removing the 

bolts that connect the bellcrank to the 

swashplate guide, removing any existing 

bushings, and visually inspecting the 

lug bore area for corrosion or cracks. 

This service information also specifies if 

there is any corrosion or cracks, 

reporting the information to HG 

support, installing the new plastic 

bushings, reinstalling the bellcrank, 

applying a specified torque, and 

installing cotter pins. 

Other Related Service Information 

The FAA also reviewed Guimbal 

Service Bulletin SB 17–003, Revision C, 

dated July 12, 2019 (SB 17–003 Rev C). 

SB 17–003 Rev C specifies the same 

procedures as SB 17–003 Rev D, except 

SB 17–003 Rev D updates the reference 

to EASA AD 2019–0185. 

Differences Between This AD and EASA 

AD 2019–0185 

EASA AD 2019–0185 applies to all 

Model Cabri G2 helicopters, whereas 

this AD only applies to Model Cabri G2 

helicopters with any metal bushings 

installed and without HG modification 

16–009. The service information 

required by the EASA AD requires 

contacting He ́licopte`res Guimbal for 

corrective actions when corrosion or 

cracks are found in the lug bore area 

whereas this AD requires removing the 

swashplate guide from service or 

repairing it using an FAA-approved 

method. 

Costs of Compliance 

The FAA estimates that this AD 

affects 32 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates the following costs to 

comply with this AD. 

Disconnecting the bellcrank, 

removing each metal bushing and 

visually inspecting for corrosion and 


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Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 49909 

cracks would take about 0.5 work-hours 

for an estimated cost of $43 per 

inspection cycle. 

Installing each plastic bushing, 

coating with compound, re-installing 

the bellcrank, and applying torque 

would take about 0.5 work-hours and 

parts would cost about $10 for an 

estimated cost of $53 per helicopter. 

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 helicopters 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. 

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: 

2021–19–04 He ́licopte`res Guimbal: 

Amendment 39–21722; Docket No. 

FAA–2021–0498; Project Identifier 

2019–SW–072–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 12, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to He ́licopte`res Guimbal 

(HG) Model Cabri G2 helicopters, certificated 

in any category, with any metal bushings 

installed on the main rotor (M/R) swashplate 

guide bellcrank and without plastic bushing 

part number HG22–1001 or HG modification 

16–009. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700, Rotorcraft Flight Control. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracks on the M/R scissor link. The FAA is 

issuing this AD to replace the metal bushings 

installed on the M/R swashplate guide 

bellcrank with plastic bushings. The unsafe 

condition, if not addressed, could result in 

failure of the M/R swashplate guide bellcrank 

and reduced control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 50 hours time-in-service (TIS) or 

2 months, whichever occurs first after the 

effective date of this AD: 

(i) Disconnect the bellcrank from the 

swashplate guide by removing each bolt and, 

ensuring that the bellcrank remains attached 

to the flight control rod, remove each metal 

bushing from service using a bushing 

disassembly tool. 

(ii) Visually inspect the lug bore area for 

any corrosion and any cracks. If there is any 

corrosion or any cracks, before further flight, 

remove the swashplate guide from service or 

repair it using an FAA-approved method. If 

there is no corrosion and no cracks, install 

plastic bushing part number HG22–1001, 

coat plastic bushing with isolation 

compound, re-install the bellcrank, torque 

each bolt to 7.5 Nm–9 Nm (5.5 ft-lbs–6.6 ftlbs), and install cotter pins. 

(2) As of the effective date of this AD, do 

not install any metal bushing on any 

helicopter. 

(h) 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 (i)(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. 

(i) 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) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2019–0185, dated July 30, 2019. 

You may view the EASA AD on the internet 

at https://www.regulations.gov in Docket No. 

FAA–2021–0498. 

(j) Material Incorporated by Reference 

None. 

Issued on August 30, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–19037 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–2021–0497; Project 

Identifier 2019–SW–043–AD; Amendment 

39–21711; AD 2021–18–10] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Canada Limited Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bell Textron Canada Limited Model 429 

helicopters. This AD was prompted by 

three reports of unexpected forces or 

uncommanded inputs to the directional 

(yaw) control system. This AD requires 

revising the existing Rotorcraft Flight 


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