19614 Federal Register / Vol. 87, No. 65 / Tuesday, April 5, 2022 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0020; Project 

Identifier MCAI–2021–00784–R; Amendment 

39–22000; AD 2022–07–12] 

RIN 2120–AA64 

Airworthiness Directives; He ́licopte`res 

Guimbal Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2021–02– 

20, which applied to certain 

He ́licopte`res Guimbal (HG) Model Cabri 

G2 helicopters. AD 2021–02–20 

required initial and repetitive 

inspections of certain rotating and nonrotating scissor fittings, and depending 

on the results, replacing the affected 

assembly. AD 2021–02–20 also 

prohibited installing certain main rotor 

hubs (MRHs) and swashplate guides 

unless the initial inspection was 

accomplished. This AD was prompted 

by a report of a crack in a rotating 

scissor fitting. This AD retains certain 

requirements of AD 2021–02–20, and 

requires installation of newly designed 

parts, provides a terminating action for 

the initial and repetitive inspections, 

and revises the applicability. This AD 

also extends the repetitive inspection 

interval and prohibits installing certain 

MRHs and swashplate guides. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective May 10, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 10, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of February 22, 2021 (86 FR 

8299, February 5, 2021). 

ADDRESSES: For service information 

identified in this final rule, contact 

He ́licopte`res Guimbal, 1070, rue du 

Lieutenant Parayre, Ae ́rodrome d’Aixen-Provence, 13290 Les Milles, France; 

telephone 33–04–42–39–10–88; email 

support@guimbal.com; or at 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. Service information that is 

incorporated by reference is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2022–0020. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0020; or in person at Docket 

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

Monday through Friday, except Federal 

holidays. The AD docket contains this 

final rule, the European Union Aviation 

Safety Agency (EASA) AD, any 

comments received, and other 

information. The address for Docket 

Operations is U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Darren Gassetto, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance 

& Airworthiness Division, FAA, 1600 

Stewart Ave., Suite 410, Westbury, NY 

11590; telephone (516) 228–7323; email 

Darren.Gassetto@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2021–02–20, 

Amendment 39–21403 (86 FR 8299, 

February 5, 2021) (AD 2021–02–20). AD 

2021–02–20 applied to HG Model Cabri 

G2 helicopters, with rotating or nonrotating scissor fitting part number (P/N) 

G12–00–200, installed on the MRH or 

swashplate guide, respectively. The 

NPRM published in the Federal 

Register on January 31, 2022 (87 FR 

4822). In the NPRM, the FAA proposed 

to retain certain inspection and 

corrective action requirements of AD 

2021–02–20. The NPRM also proposed 

to require within 60 hours time-inservice (TIS) or 6 months, whichever 

occurs first after the effective date of the 

proposed AD, and thereafter at intervals 

not to exceed 60 hours TIS or 6 months, 

whichever occurs first, leaving each 

scissor fitting assembled and visually 

inspecting each scissor fitting for a 

crack. If there is a crack during the 

initial inspection or the recurring 

inspection, the NPRM proposed to 

require before further flight, replacing 

certain parts or as an alternative, 

installing HG modification (mod) 20– 

040. 

The NPRM proposed to require, 

within 60 months or during the next 

main gearbox overhaul, whichever 

occurs first after the effective date of the 

proposed AD, removing from service 

MRH P/N G12–00–100, or G12–00–101, 

or G12–00–102 and swashplate guide 

P/N G21–01–101 or G21–01–102 and 

installing HG mod 20–040. The 

proposed NPRM also allowed installing 

HG mod 20–040 to be a terminating 

action for the initial and recurring 

visual inspections required by the 

proposed AD. 

Additionally, for any pre-HG mod 20– 

040 helicopter, as of February 22, 2021 

(the effective date of AD 2021–02–20), 

the NPRM proposed to prohibit 

installing an MRH or swashplate guide, 

with a certain part-numbered rotating or 

non-rotating scissor fitting installed, 

unless certain actions have been 

accomplished. For any post-HG mod 

20–040 helicopter, as of the effective 

date of the proposed AD, the NPRM 

proposed to prohibit installing an MRH 

or swashplate guide, with a certain partnumbered rotating or non-rotating 

scissor fitting installed, on any 

helicopter. 

The NPRM was prompted by EASA 

AD 2021–0155, dated July 2, 2021 

(EASA AD 2021–0155), issued by 

EASA, which is the Technical Agent for 

the Member States of the European 

Union, to correct an unsafe condition 

for HG Cabri G2 helicopters, all 

manufacturer serial numbers. EASA 

advises that a design change was 

developed for the MRH and swashplate 

guide including installation instructions 

for the modification. EASA AD 2021– 

0155 advises the design change requires 

installing new scissor fitting P/N G12– 

00–202, which is not affected by stress 

corrosion cracking. EASA AD 2021– 

0155 further advises once a helicopter 

installs a certain part-numbered MRH 

and a certain part-numbered swashplate 

guide containing the newly designed 

scissor fitting, HG mod 20–040 is 

accomplished. This condition, if not 

addressed, could result in failure of a 

rotating or non-rotating scissor fitting 

and subsequent loss of control of the 

helicopter. 

Accordingly, EASA AD 2021–0155 

retains the requirements of EASA AD 

2020–0199, dated September 21, 2020, 

and corrected September 24, 2020 

(EASA AD 2020–0199), which 

prompted AD 2021–02–20, and requires 

replacement of the MRH and swashplate 

guide assemblies with assemblies 

equipped with the newly designed 

scissor fitting. EASA AD 2021–0155 also 

increases the interval for the repetitive 

inspection and prohibits any affected 

part to be installed on any helicopter 

that has HG mod 20–040 installed. 

EASA AD 2021–0155 allows a 

terminating action for the initial and 


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repetitive inspections if the helicopter 

has been modified and includes the 

updated modification information. 

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 helicopters. This AD 

is adopted as proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Guimbal Service 

Bulletin SB 20–012, Revision C; SB 20– 

011, Revision D; and SB 21–007 

Revision C, each dated July 22, 2021 (SB 

20–012 Rev C, SB 20–011 Rev D, and SB 

21–007 Rev C). SB 20–012 Rev C 

specifies removing the bolts connecting 

the two scissor fittings P/N G12–00–200 

and accomplishing a one-time detailed 

inspection for a crack in certain areas. 

SB 20–012 Rev C also specifies 

reassembling the two scissor fittings 

using correct bolt torque limits, 

installing new cotter pins, and reporting 

any findings to HG customer support. 

SB 20–011 Rev D specifies procedures 

for a recurring inspection after 

accomplishment of SB 20–012 Rev C of 

the same areas of the scissor fittings for 

a crack as SB 20–012 Rev C, except 

without removing the bolts which 

connect the two scissor fittings. SB 20– 

011 Rev D also specifies reporting any 

findings to HG customer support. SB 

21–007 Rev C specifies instructions for 

installing the newly designed scissor 

fitting. 

This AD also requires Guimbal 

Service Bulletin SB 20–012, Revision B, 

dated October 5, 2020 (SB 20–012 Rev 

B), which the Director of the Federal 

Register approved for incorporation by 

reference as of February 22, 2021 (86 FR 

8299, February 5, 2021). 

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. 

Other Related Service Information 

The FAA also reviewed Guimbal 

Service Bulletin SB 20–011, Revision C, 

dated October 5, 2020 (SB 20–011 Rev 

C). SB 20–011 Rev C specifies the same 

procedures as SB–20–011 Rev D, except 

SB 20–011 Rev D updates the 

applicability and references SB 21–007 

Rev C. 

The FAA reviewed Guimbal Service 

Bulletin SB 20–011, Revision B, and SB 

20–012, Revision A, each dated 

September 1, 2020 (SB 20–011 Rev B 

and SB 20–012 Rev A). SB 20–012 Rev 

A specifies the same procedures as SB 

20–012 Rev B, except SB 20–012 Rev B 

revises the compliance time, adds the 

EASA AD identification information, 

and updates the Situation section 

description. SB 20–011 Rev B specifies 

the same procedures as SB 20–011 Rev 

C, except SB 20–011 Rev C adds the 

EASA AD identification information 

and updates the Situation section 

description. 

The FAA also reviewed Guimbal 

Service Bulletin SB 21–007, Revision B, 

dated April 4, 2021 which states the 

same procedures as SB 21–007 Rev C, 

except SB 21–007 Rev C revises the 

compliance time to coincide with the 

effective date of EASA AD 2021–0155. 

Differences Between This AD and EASA 

AD 2021–0155 

EASA AD 2021–0155 requires 

detailed inspections, whereas this AD 

requires cleaning each scissor fitting 

and visually inspecting each scissor 

fitting using a flashlight. EASA AD 

2021–0155 also requires reporting 

certain information, whereas this AD 

does not. EASA AD 2021–0155 requires 

replacing certain parts if a crack is 

detected with serviceable parts, whereas 

this AD requires replacing certain parts 

with airworthy parts. 

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. 

Removing and installing the bolt and 

cotter pins in the initial inspection takes 

a minimal amount of time with a 

minimal parts cost. 

Inspecting each scissor fitting takes 

about 0.5 work-hour for an estimated 

cost of $43 per fitting, per inspection 

cycle. There are 2 scissor fittings 

installed on a helicopter, for an 

estimated cost of $85 per helicopter and 

$2,720 for the U.S. fleet, per inspection 

cycle. 

Removing an MRH and swashplate 

guide and installing the improved MRH 

and swashplate guide takes about 6 

work-hours and parts cost about $1,608 

through the parts exchange program for 

an estimated cost of $2,118 per 

helicopter and $67,776 for the U.S. fleet. 

The FAA expects the majority of 

operators to use the parts exchange 

program. If not accomplished through 

the parts exchange program, an 

improved MRH and swashplate guide 

costs about $8,695 for an estimated cost 

of $9,205 per helicopter and $294,560 

for the U.S. fleet. 

The FAA estimates the following 

costs to do any necessary on-condition 

replacements that are required based on 

the results of the inspection. The agency 

has no way of determining the number 

of aircraft that might need these oncondition replacements: 

Replacement of an MRH due to a 

crack in the scissor fitting with an 

airworthy MRH takes about 5 workhours and parts cost about $7,360 for an 

estimated cost of $7,785 per helicopter; 

and replacement of a swashplate guide 

due to a crack in the scissor fitting with 

an airworthy swashplate guide takes 

about 6 work-hours and parts cost about 

$1,312 for an estimated cost of $1,822 

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 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: 


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(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 

2021–02–20, Amendment 39–21403 (86 

FR 8299, February 5, 2021); and 

■ b. Adding the following new 

airworthiness directive: 

2022–07–12 He ́licopte`res Guimbal: 

Amendment 39–22000; Docket No. 

FAA–2022–0020; Project Identifier 

MCAI–2021–00784–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 10, 2022. 

(b) Affected ADs 

This AD replaces AD 2021–02–20, 

Amendment 39–21403 (86 FR 8299, February 

5, 2021) (AD 2021–02–20). 

(c) Applicability 

This AD applies to He ́licopte`res Guimbal 

(HG) Model Cabri G2 helicopters, all serial 

numbers, certificated in any category. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700, Rotorcraft Flight Control; 6710, 

Main Rotor Control. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

crack in a rotating scissor fitting. The FAA 

is issuing this AD to detect a crack and 

prevent failure of a scissor fitting. The unsafe 

condition, if not addressed, could result in 

failure of a rotating or non-rotating scissor 

fitting and subsequent loss of control of the 

helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

For helicopters with rotating or nonrotating scissor fitting part number (P/N) 

G12–00–200, installed on the main rotor hub 

(MRH) or swashplate guide, respectively: 

(1) Within 30 hours time-in-service (TIS) or 

30 calendar days, whichever occurs first after 

February 22, 2021 (the effective date of AD 

2021–02–20): 

(i) Remove the cotter pins and bolts 

connecting the rotating and non-rotating 

scissor fitting by following the Required 

Actions, IPC 4.1–2 a), of Guimbal Service 

Bulletin SB 20–012, Revision B, dated 

October 5, 2020 (SB 20–012 Rev B). Remove 

the cotter pins from service. Clean each 

scissor fitting. Using a flashlight, visually 

inspect each scissor fitting by following the 

Required Actions, IPC 4.1–2 b), of SB 20–012 

Rev B. As an alternative to using SB 20–012 

Rev B, you may remove the cotter pins and 

bolts in accordance with the Required 

Actions, IPC 4.1–2 a), of Guimbal Service 

Bulletin SB 20–012, Revision C, dated July 

22, 2021 (SB 20–012 Rev C), and visually 

inspect each scissor fitting in accordance 

with the Required Actions, IPC 4.1–2 b), of 

SB 20–012 Rev C. 

(ii) If there is a crack, before further flight, 

replace the MRH or swashplate guide with an 

airworthy part as applicable; or, as an 

alternative, you may accomplish the 

modification specified in paragraph (g)(3) of 

this AD. 

(iii) If there is not a crack, reassemble the 

scissor fittings by following the Required 

Actions, IPC 4.1–2 c), of SB 20–012 Rev B. 

As an alternative to using SB 20–012 Rev B, 

you may reassemble the scissor fittings in 

accordance with the Required Actions, IPC 

4.1–2 c), of SB 20–012 Rev C. 

(2) Thereafter, within 60 hours TIS or 6 

months, whichever occurs first after the 

effective date of this AD, and thereafter at 

intervals not to exceed 60 hours TIS or 6 

months, whichever occurs first: 

(i) Leaving each rotating and non-rotating 

scissor fitting assembled, clean each scissor 

fitting. Using a flashlight, visually inspect 

each scissor fitting by following the Required 

Actions, IPC 4.1–2 a), of Guimbal Service 

Bulletin SB 20–011, Revision D, dated July 

22, 2021. 

(ii) If there is a crack, before further flight, 

replace the MRH or swashplate guide, with 

an airworthy part as applicable; or, as an 

alternative, you may accomplish the 

modification specified in paragraph (g)(3) of 

this AD. 

(3) Within 60 months, or during the next 

main gearbox overhaul, whichever occurs 

first after the effective date of this AD, 

remove MRH P/N G12–00–100, or G12–00– 

101, or G12–00–102 and swashplate guide P/ 

N G21–01–101 or G21–01–102 from service 

and modify your helicopter by installing 

MRH P/N G12–00–103 and swashplate guide 

P/N G21–01–103 containing scissor fitting P/ 

N G12–00–202 (HG modification (mod) 20– 

040) by following the Required Actions, IPC 

2.1–0 a) through k) and m) through aa) of 

Guimbal Service Bulletin SB 21–007, 

Revision C, dated July 22, 2021. 

Note 1 to paragraph (g)(3): HG mod 20– 

040, as referenced in paragraphs (g)(3), and 

(h)(1) and (2) of this AD, is accomplished 

after installation of MRH P/N G12–00–103 

and swashplate guide P/N G21–01–103 

containing scissor fitting P/N G12–00–202. 

(4) Completing the actions required by 

paragraph (g)(3) of this AD constitutes a 

terminating action for the requirements in 

paragraphs (g)(1) and (2) of this AD. 

(h) Parts Installation 

(1) For any pre-HG mod 20–040 helicopter: 

As of February 22, 2021 (the effective date of 

AD 2021–02–20), do not install an MRH or 

swashplate guide, with rotating or nonrotating scissor fitting P/N G12–00–200 

installed, respectively, on any helicopter, 

even if new, unless the actions required by 

paragraph (g)(1) of this AD have been 

accomplished. 

(2) For any post-HG mod 20–040 

helicopter: As of the effective date of this AD, 

do not install an MRH or swashplate guide, 

with rotating or non-rotating scissor fitting P/ 

N G12–00–200 installed, respectively, on any 

helicopter. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD if you accomplished Guimbal Service 

Bulletin SB 20–012, Revision A, dated 

September 1, 2020, before February 22, 2021 

(the effective date of AD 2021–02–20). 

(2) This paragraph provides credit for the 

first instance of the actions required by 

paragraph (g)(2) of this AD if you 

accomplished Guimbal Service Bulletin SB 

20–011, Revision B, dated September 1, 2020, 

before February 22, 2021 (the effective date 

of AD 2021–02–20). 

(3) This paragraph provides credit for the 

actions required by paragraph (g)(2) of this 

AD if you accomplished Guimbal Service 

Bulletin SB 20–011, Revision C, dated 

October 5, 2020, before the effective date of 

this AD. 

(4) This paragraph provides credit for the 

actions required by paragraph (g)(3) of this 

AD if you accomplished Guimbal Service 

Bulletin SB 21–007, Revision B, dated April 

4, 2021, before the effective date of this AD. 

(j) Special Flight Permits 

A special flight permit may be permitted 

provided that there are no passengers 

onboard, and the flight is operating under 

day Visual Flight Rules, for the purpose of 

ferrying the helicopter to an authorized 

maintenance facility. 

(k) 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 (l)(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 


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of the local flight standards district office/ 

certificate holding district office. 

(l) Related Information 

(1) For more information about this AD, 

contact Darren Gassetto, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave., Suite 410, Westbury, NY 11590; 

telephone (516) 228–7323; email 

Darren.Gassetto@faa.gov. 

(2) Service information identified in this 

AD is available at the contact information 

specified in paragraphs (m)(5) and (6). 

(3) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2021–0155, dated July 2, 2021. 

You may view the EASA AD on the internet 

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

FAA–2022–0020. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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. 

(3) The following service information was 

approved for IBR on May 10, 2022. 

(i) Guimbal Service Bulletin SB 20–011, 

Revision D, dated July 22, 2021. 

(ii) Guimbal Service Bulletin SB 20–012, 

Revision C, dated July 22, 2021. 

(iii) Guimbal Service Bulletin SB 21–007 

Revision C, dated July 22, 2021. 

(4) The following service information was 

approved for IBR on February 22, 2021 (86 

FR 8299, February 5, 2021). 

(i) Guimbal Service Bulletin SB 20–012, 

Revision B, dated October 5, 2020. 

(ii) [Reserved] 

(5) For He ́licopte`res Guimbal service 

information identified in this AD, contact 

He ́licopte`res Guimbal, 1070, rue du 

Lieutenant Parayre, Ae ́rodrome d’Aix-enProvence, 13290 Les Milles, France; 

telephone 33–04–42–39–10–88; email 

support@guimbal.com; web https:// 

www.guimbal.com. 

(6) 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. 

(7) 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 March 24, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–07094 Filed 4–4–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1068; Project 

Identifier MCAI–2021–00383–T; Amendment 

39–21981; AD 2022–06–15] 

RIN 2120–AA64 

Airworthiness Directives; De Havilland 

Aircraft of Canada Limited (Type 

Certificate Previously Held by 

Bombardier, Inc.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all De 

Havilland Aircraft of Canada Limited 

Model DHC–8–401 and –402 airplanes. 

This AD was prompted by reports of 

bleed air leaks in the wing box area and 

failure of the leak detection shroud. 

This AD requires removing and 

inspecting the affected V-band coupling 

and check valve seals, doing corrective 

actions if necessary, and replacing the 

coupling and seals with a redesigned 

assembly. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective May 10, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 10, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact De 

Havilland Aircraft of Canada Limited, 

Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email thd@

dehavilland.com; internet https://

dehavilland.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. 

It is also available on the internet at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1068. 

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–2021– 

1068; 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: 

Elizabeth Dowling, Aerospace Engineer, 

Mechanical Systems and Administrative 

Services Section, FAA, New York ACO 

Branch, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 

516–228–7300; email 9-avs-nyaco-cos@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued TCCA AD CF– 

2021–11, dated March 29, 2021 (TCCA 

AD CF–2021–11) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for all De Havilland 

Aircraft of Canada Limited Model DHC– 

8–401 and –402 airplanes. You may 

examine the MCAI in the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

1068. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all De Havilland Aircraft of 

Canada Limited Model DHC–8–401 and 

–402 airplanes. The NPRM published in 

the Federal Register on December 17, 

2021 (86 FR 71594). The NPRM was 

prompted by reports of bleed air leaks 

in the wing box area and failure of the 

leak detection shroud. The NPRM 

proposed to require removing and 

inspecting the affected V-band coupling 

and check valve seals, doing corrective 

actions if necessary, and replacing the 

coupling and seals with a redesigned 

assembly. The FAA is issuing this AD 

to address the possibility of undetected 

hot engine bleed air being directed onto 

aircraft structure, the main landing gear 

(MLG) emergency release cable, and the 

static air temperature (SAT) sensor, 

which could cause the main landing 

gear emergency release cable to 

malfunction. See the MCAI for 

additional background information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA has considered 

the comment received. The Air Line 


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