47038 Federal Register / Vol. 86, No. 160 / Monday, August 23, 2021 / Proposed Rules 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical power. 

(e) Unsafe Condition 

This AD was prompted by reports of erratic 

electrical system status on the push button 

annunciators (PBAs) and the engine 

instrument and crew alerting system (EICAS), 

while on-ground and during flight. The FAA 

is issuing this AD to address erroneous 

indications that could mislead pilots, causing 

them to turn off active electrical power 

sources, leading to partial or complete loss of 

electrical power. Loss of electrical power 

could result in the loss of flight displays and 

reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of the Airplane Flight Manual 

(AFM) 

Within 60 days after the effective date of 

this AD: Revise the Emergency Procedures 

and Non-Normal Procedures sections of the 

existing AFM and applicable corresponding 

operational procedures to include the 

information in Section 03–19, Electrical, of 

Chapter 03, Emergency Procedures, and 

Section 05–19, Electrical, of Chapter 05, NonNormal Procedures, of the Bombardier 

Challenger 300 (Imperial Version) Airplane 

Flight Manual, Publication No. CSP 100–1, 

Revision 63, dated April 1, 2021 (for 

airplanes having serial numbers 20003 

through 20500 inclusive); or Bombardier 

Challenger 350 Airplane Flight Manual, 

Publication No. CH 350 AFM, Revision 29, 

dated April 1, 2021 (for airplanes having 

serial numbers 20501 through 20999 

inclusive); as applicable. 

Note 1 to paragraph (g): For obtaining the 

sections for Bombardier Challenger 300 

(Imperial Version) Airplane Flight Manual, 

Publication No. CSP 100–1, use Document 

Identification No. CH 300 AFM–I. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Section 03–19, 

Electrical, of Chapter 03, Emergency 

Procedures, and Section 05–19, Electrical, of 

Chapter 05, Non-Normal Procedures, of the 

Bombardier Challenger 300 (Imperial 

Version) Airplane Flight Manual, Publication 

No. CSP 100–1, Revision 62, dated December 

22, 2020; or Bombardier Challenger 350 

Airplane Flight Manual, Publication No. CH 

350 AFM, Revision 28, dated December 22, 

2020; as applicable. 

Note 2 to paragraph (h): For obtaining the 

sections for Bombardier Challenger 300 

(Imperial Version) Airplane Flight Manual, 

Publication No. CSP 100–1, use Document 

Identification No. CH 300 AFM–I. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO 

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 manager of the certification office, 

send it to ATTN: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO Branch, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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, New York ACO Branch, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) TCCA AD 

CF–2020–46, dated November 17, 2020, for 

related information. This MCAI may be 

found in the AD docket on the internet at 

https://www.regulations.gov by searching for 

and locating Docket No. FAA–2021–0691. 

(2) For more information about this AD, 

contact Steven Dzierzynski, Aerospace 

Engineer, Avionics and Electrical Systems 

Section, FAA, New York ACO Branch, 1600 

Stewart Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7367; fax 516– 

794–5531; email 9-avs-nyaco-cos@faa.gov. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 200 CoˆteVertu Road West, Dorval, Que ́bec H4S 2A3, 

Canada; North America toll-free telephone 1– 

866–538–1247 or direct-dial telephone 1– 

514–855–2999; email ac.yul@

aero.bombardier.com; internet https://

www.bombardier.com. 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. 

Issued on August 17, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–17943 Filed 8–20–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0688; Project 

Identifier 2019–SW–025–AD] 

RIN 2120–AA64 

Airworthiness Directives; He ́licopte`res 

Guimbal Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

He ́licopte`res Guimbal (HG) Model Cabri 

G2 helicopters. This proposed AD was 

prompted by the determination that 

certain parts need life limits and 

certification maintenance requirement 

(CMR) tasks. This proposed AD would 

require establishing life limits and CMR 

tasks for various parts and removing any 

parts from service that have reached or 

exceeded their life limits. Depending on 

the results of the CMR tasks, this 

proposed AD would require corrective 

action. The FAA is proposing this AD to 

address the unsafe condition on these 

products. 

DATES: The FAA must receive comments 

on this proposed AD by October 7, 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 between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. 

For service information identified in 

this NPRM, contact He ́licopte`res 

Guimbal, Basile Ginel, 1070, rue du 

Lieutenant Parayre, Ae ́rodrome d’Aixen-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 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. 


jbell on DSKJLSW7X2PROD with PROPOSALS
Federal Register / Vol. 86, No. 160 / Monday, August 23, 2021 / Proposed Rules 47039 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0688; 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 

NPRM, the European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency (EASA) AD, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

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: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2021–0688; Project Identifier 

2019–SW–025–AD’’ at the beginning of 

your comments. The most helpful 

comments reference a specific portion of 

the proposal, explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend this proposal 

because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this NPRM. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this NPRM 

contain commercial or financial 

information that is customarily treated 

as private, that you actually treat as 

private, and that is relevant or 

responsive to this NPRM, it is important 

that you clearly designate the submitted 

comments as CBI. Please mark each 

page of your submission containing CBI 

as ‘‘PROPIN.’’ The FAA will treat such 

marked submissions as confidential 

under the FOIA, and they will not be 

placed in the public docket of this 

NPRM. Submissions containing CBI 

should be sent to 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. Any 

commentary that the FAA receives 

which is not specifically designated as 

CBI will be placed in the public docket 

for this rulemaking. 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, issued EASA AD 2016–0032, 

dated February 24, 2016 (EASA AD 

2016–0032), to correct an unsafe 

condition for HG Model Cabri G2 

helicopters. EASA AD 2016–0032 states 

HG has revised the airworthiness 

limitations and maintenance tasks 

specified in the existing maintenance 

manual. EASA further advised the 

revisions include new and more 

restrictive applicable life limits and 

compliance times for applicable tasks. 

Accordingly, EASA 2016–0032 required 

replacing each affected part before 

exceeding its life limit, accomplishing 

all applicable maintenance tasks within 

the defined intervals as described in 

revised maintenance manual and if 

discrepancies were found 

accomplishing the corrective actions in 

accordance with the applicable 

maintenance instructions or contacting 

HG. EASA AD 2016–0032 also required 

revising the existing Aircraft 

Maintenance Program (AMP) for your 

helicopter by incorporating the actions 

specified in the revised maintenance. 

After EASA issued EASA AD 2016– 

0032, HG again revised the 

airworthiness limitations and 

maintenance tasks. 

Accordingly, EASA superseded EASA 

AD 2016–0032 with EASA AD 2019– 

0025, dated February 4, 2019 (EASA AD 

2019–0025). EASA advises new and 

more restrictive life limits have been 

established for cooling fan part number 

(P/N) G52–00–001, and P/N G52–00– 

002, which have been identified as 

mandatory for continued airworthiness 

in He ́licopte`res Guimbal Cabri G2 

Maintenance Manual (MM) and 

Instructions for Continued 

Airworthiness J70–002 Issue 06, Section 

C, Airworthiness Limitations, dated 

December 6, 2018 (MM J70–002 Issue 

06). In addition to the new life limits, 

EASA further advises of new and more 

restrictive inspection intervals 

identified in MM J70–002–Issue 06 for 

cooling fan P/N G52–00–001 with a 

certain mounted cooling fan front flange 

P/N G52–02–200, or P/N G52–02–201. 

EASA further advises MM J70–002 Issue 

06, revised the tail structure paint to 

include certain part-numbered tail 

booms and an additional figure. This 

condition, if not addressed, could result 

in parts remaining in service beyond 

their fatigue life and failure of a part, 

which could result in loss of control of 

the helicopter. 

Accordingly, EASA AD 2019–0025 

retains the requirements of EASA AD 

2016–0032 and requires replacing each 

affected part before exceeding its life 

limit, accomplishing all applicable 

maintenance tasks within the defined 

intervals as described in MM J70–002 

Issue 6, and if discrepancies are found 

accomplishing the corrective actions in 

accordance with the applicable 

maintenance instructions or contacting 

HG. EASA AD 2019–0025 also requires 

revising the tail structure paint scheme 

to include certain part-numbered tail 

booms and an additional figure. EASA 

AD 2019–0025 requires revising the 

existing AMP for your helicopter by 

incorporating the actions specified in 

MM J70–002 Issue 6. 

FAA’s Determination 

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 is 

proposing this AD after evaluating all 

known relevant information and 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other helicopters of the same 

type designs. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed He ́licopte`res 

Guimbal Cabri G2 MM J70–002 Issue 06. 

This service information specifies 

airworthiness life limits, inspection 

intervals, and CMR requirements for 

parts installed on Cabri G2 helicopters. 

Issue 06 establishes life limits for 

certain part-numbered cooling fan front 

flanges, and engine pulley ball bearings 

and CMR requirements for certain 

cooling fan front flanges. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 


jbell on DSKJLSW7X2PROD with PROPOSALS
47040 Federal Register / Vol. 86, No. 160 / Monday, August 23, 2021 / Proposed Rules 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require, 

before further flight after the effective 

date of this AD, removing from service 

certain part-numbered cooling fan front 

flanges and engine pulley ball bearings 

that have accumulated or exceeded their 

life limit. This proposed AD would also 

require establishing recurring CMR tasks 

for certain part-numbered cooling fan 

front flanges. Depending on the results 

of the CMR tasks, this proposed AD 

would also require corrective action. 

Additionally, this proposed AD would 

require painting certain part-numbered 

tail booms with glossy white paint. 

Differences Between This Proposed AD 

and EASA AD 2019–0025 

EASA AD 2019–0025 requires 

contacting He ́licopte`res Guimbal for 

corrective actions when a discrepancy is 

found, whereas this proposed AD would 

require removing the part from service. 

EASA AD 2019–0025 requires 

accomplishing the actions specified in 

MM J70–002 Issue 06, whereas this 

proposed AD would require establishing 

a life limit for certain part-numbered 

cooling fan front flanges and certain 

part-numbered engine pulley ball 

bearings and removing any part from 

service accordingly instead. EASA AD 

2019–0025 requires revising the AMP 

with the actions specified in MM J70– 

002 Issue 06, whereas the proposed AD 

would not. 

Costs of Compliance 

The FAA estimates that this proposed 

AD would affect 32 helicopters of U.S. 

Registry. The FAA estimates that 

operators may incur the following costs 

in order to comply with this proposed 

AD. Labor costs are estimated at $85 per 

work-hour. 

Replacing a cooling fan front flange 

would take about 16 work-hours and 

parts would cost about $4,500 for an 

estimated cost of $5,860 per helicopter 

and $187,520 for the U.S. fleet, per 

replacement cycle. 

Replacing an engine pulley ball 

bearing would take about 12 work-hours 

and parts would cost about $250 for an 

estimated cost of $1,270 per helicopter 

and $40,640 for the U.S. fleet, per 

replacement cycle. 

The FAA has no way of determining 

the estimated costs to do allowable 

repairs based on the results of the CMR 

tasks. If required, replacing a cracked 

cooling fan front flange would take 

about 16 work-hours and parts would 

cost about $4,500 for an estimated cost 

of $5,860. 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

operators. 

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 determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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, I certify 

this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would 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 Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

He ́licopte`res Guimbal: Docket No. FAA– 

2021–0688; Project Identifier 2019–SW– 

025–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by October 7, 

2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to He ́licopte`res Guimbal 

(HG) Model Cabri G2 helicopters, certificated 

in any category. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7100, Powerplant System. 

(e) Unsafe Condition 

This AD was prompted by a notification of 

certain parts remaining in service beyond 

their fatigue life or beyond maintenance 

intervals required by the certification 

maintenance requirements (CMRs) of the 

Instructions for Continued Airworthiness. 

The FAA is issuing this AD to prevent failure 

of a part, which could result in loss of control 

of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Before further flight after the effective 

date of this AD, remove from service any part 

that has reached or exceeded its life limit, as 

specified in paragraphs (g)(1)(i) through (iii) 

of this AD, and thereafter remove from 

service any part on or before each part 

reaches its life limit: 

(i) The life limit for cooling fan front flange 

part number (P/N) G52–02–200 mounted on 

pulley (12 screws) P/N G52–10–100 or G52– 

10–101; and cooling fan front flange P/N 

G52–02–201 mounted or having been 

mounted on pulley (12 screws) P/N G52–10– 

100 or G52–10–101, installed on cooling fan 

P/N G52–00–001 or G52–00–002; is 2,200 

total hours time-in-service (TIS). 

(ii) The life limit for cooling fan front 

flange P/N G52–02–201 mounted on pulley 

(24 screws) P/N G52–10–102 and having 

never been mounted on pulley (12 screws) P/ 

N G52–10–100 or G52–10–101, installed on 

cooling fan P/N G52–00–001 or G52–00–002, 

is 4,400 total hours TIS. 

(iii) The life limit for engine pulley ball 

bearing P/N HG61–0790 and HG61–1944, 

installed on engine pulley assembly P/N 

G51–14–1XX, is 2,200 total hours TIS. 

(2) Perform the following CMR tasks as 

follows: 

(i) Cooling fan front flange P/N G52–02– 

200 mounted on pulley (12 screws) P/N G52– 

10–100 or G52–10–101; and cooling fan front 


jbell on DSKJLSW7X2PROD with PROPOSALS
Federal Register / Vol. 86, No. 160 / Monday, August 23, 2021 / Proposed Rules 47041 

flange P/N G52–02–201 mounted or having 

been mounted on pulley (12 screws) P/N 

G52–10–100 or G52–10–101, installed on 

cooling fan P/N G52–00–001, and with 500 

or more total hours TIS since new as of the 

effective date of this AD: Within 5 hours TIS 

after the effective date of this AD and 

thereafter at intervals not to exceed 50 hours 

TIS, or 70 engine start-stop cycles, whichever 

occurs first, inspect the cooling fan front 

flange for a crack in accordance with 

He ́licopte`res Guimbal Cabri G2 Maintenance 

Manual (MM) and Instructions for Continued 

Airworthiness J70–002 Issue 06, Section C, 

Airworthiness Limitations, dated December 

6, 2018 (MM J70–002 Issue 06), sub section 

52–A–10 Cooling Fan Inspection, paragraphs 

(c) through (d). If any crack is found, before 

further flight, remove the cooling fan front 

flange from service. 

(ii) Cooling fan front flange P/N G52–02– 

200 mounted on pulley (12 screws) P/N G52– 

10–100 or G52–10–101; and cooling fan front 

flange P/N G52–02–201 mounted or having 

been mounted on pulley (12 screws) P/N 

G52–10–100 or G52–10–101, installed on 

cooling fan P/N G52–00–001, and with less 

than 500 total hours TIS since new as of the 

effective date of this AD: Before 

accumulating 500 total hours TIS since new 

and thereafter at intervals not to exceed 50 

hours TIS, or 70 engine start-stop cycles, 

whichever occurs first, inspect the cooling 

fan front flange for a crack in accordance 

with MM J70–002 Issue 06, sub section 52– 

A–10 Cooling Fan Inspection, paragraphs (c) 

through (d). If any crack is found, before 

further flight, remove the cooling fan front 

flange from service. 

(iii) Cooling fan front flange P/N G52–02– 

201 mounted on pulley (24 screws) P/N G52– 

10–102 and having never been mounted on 

pulley (12 screws) P/N G52–10–100 or G52– 

10–101, installed on cooling fan P/N G52– 

00–002: Before accumulating 500 total hours 

TIS since new and thereafter at intervals not 

to exceed 100 hours TIS, inspect the cooling 

fan front flange for a crack in accordance 

with MM J70–002, Issue 06, sub section 52– 

A–10 Cooling Fan Inspection, paragraphs (c) 

through (d). If any crack is found, before 

further flight, remove the cooling fan front 

flange from service. 

(iv) For helicopters with tail boom P/N 

G65–00–101, G65–00–102 or G65–00–103 

and subsequent installed: Before further 

flight after the effective date of this AD, paint 

or verify the tail boom upper surface in 

accordance with MM J70–002, Issue 06, sub 

section C–23 Tail Structure Paint, as 

applicable to your helicopter. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (g)(2)(i), (ii) 

and (iii) of this AD, if those actions were 

performed before the effective date of this AD 

using He ́licopte`res Guimbal Cabri G2 MM 

and Instructions for Continued Airworthiness 

J70–002 Issue 05.1, Section C, Airworthiness 

Limitations, dated October 30, 2015, sub 

section 52–A–10 Cooling Fan Inspection, 

paragraphs (c) through (d). 

(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)(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. 

(j) 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) For service information identified in 

this AD, 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 

this 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. 

(3) The subject of this AD is addressed in 

European Aviation Safety Agency (now 

European Union Aviation Safety Agency 

(EASA) AD 2019–0025, dated February 4, 

2019. You may view the EASA AD on the 

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

Docket No. FAA–2021–0688. 

Issued on August 16, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–17944 Filed 8–20–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0689; Project 

Identifier AD–2020–01589–R] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Sikorsky Aircraft Corporation 

(Sikorsky) Model S–92A helicopters. 

This proposed AD was prompted by a 

cracked main rotor stationary 

swashplate assembly (swashplate 

assembly). This proposed AD would 

require visually inspecting the 

swashplate assembly at specified 

intervals and depending on the results, 

removing the swashplate assembly from 

service. The FAA is proposing this AD 

to address the unsafe condition on these 

products. 

DATES: The FAA must receive comments 

on this proposed AD by October 7, 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 NPRM, contact your local Sikorsky 

Field Representative or Sikorsky’s 

Service Engineering Group at Sikorsky 

Aircraft Corporation, 124 Quarry Road, 

Trumbull, CT 06611; telephone 1–800– 

946–4337 (1–800–Winged–S); email 

wcs_cust_service_eng.gr-sik@lmco.com. 

Operators may also log on to the 

Sikorsky 360 website at https://

www.sikorsky360.com. 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0689; 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 

NPRM, any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Jared Hyman, Aerospace Engineer, 


jbell on DSKJLSW7X2PROD with PROPOSALS