Federal Register / Vol. 87, No. 80 / Tuesday, April 26, 2022 / Rules and Regulations 24401 

FAA–2022–0022; Project Identifier AD– 

2020–01264–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 31, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Piper Aircraft, Inc. 

Model PA–34–200 airplanes, serial numbers 

34–7250001 through 34–7450220, certificated 

in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 3220, Nose/Tail Landing Gear. 

(e) Unsafe Condition 

This AD was prompted by the 

determination that the life limit for alternate 

bolts that attach the drag link to the nose gear 

were not included as airworthiness 

limitations. The FAA is issuing this AD to 

establish a life limit on bolt part numbers 

693–215 and NAS6207–50D that attach the 

drag link to the nose gear trunnion. The 

unsafe condition, if not addressed, could 

result in failure of the nose landing gear and 

lead to loss of airplane control during takeoff, landing, or taxi operations. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Actions 

(1) Within 90 days after the effective date 

of this AD, incorporate into the maintenance 

records required by 14 CFR 91.417(a)(2) or 

135.439(a)(2) for your airplane a life limit of 

500 hours for bolt part numbers 693–215 and 

NAS6207–50D. 

Note to paragraph (g)(1): Piper Seneca 

Service Manual, Airworthiness Limitations, 

753–817, page 1–1, dated November 30, 

2019, contains the life limit in paragraph 

(g)(1) of this AD. 

(2) Thereafter, except as provided in 

paragraph (h)(1) of this AD, no alternative 

replacement times may be approved for these 

bolts. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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 local Flight Standards 

District Office, as appropriate. If sending 

information directly to the manager of the 

certification office, send it to the attention of 

the person identified in paragraph (i)(1) of 

this AD. 

(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 Fred Caplan, Aviation Safety 

Engineer, Atlanta ACO Branch, FAA, 1701 

Columbia Avenue, College Park, GA 30337; 

phone: (404) 474–5507; email: 

frederick.n.caplan@faa.gov. 

(2) For service information identified in 

this AD that is not incorporated by reference, 

contact Piper Aircraft, Inc., 2926 Piper Drive, 

Vero Beach, FL 32960; phone: (772) 299– 

2141; website: https://www.piper.com. You 

may view this referenced service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. For information on 

the availability of this material at the FAA, 

call (817) 222–5110. 

(j) Material Incorporated by Reference 

None. 

Issued on April 21, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–08852 Filed 4–25–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0145; Project 

Identifier MCAI–2021–00522–R; Amendment 

39–22027; AD 2022–09–07] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Canada Limited (Type Certificate 

Previously Held by Bell Helicopter 

Textron Canada Limited) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2019–11– 

05 for certain Bell Helicopter Textron 

Canada Limited (now Bell Textron 

Canada Limited) Model 429 helicopters. 

AD 2019–11–05 required inspecting the 

tail rotor (TR) pitch link assemblies, and 

replacing certain pitch link bearings. 

This AD was prompted by a report of a 

worn pitch link, and the FAA’s 

determination that all TR pitch link 

assemblies are affected by the unsafe 

condition. This AD continues to require 

the actions specified in AD 2019–11–05, 

and revises the applicability and 

requires inspections of certain other TR 

pitch link assemblies. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective May 31, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 31, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact Bell 

Textron Canada Limited, 12,800 Rue de 

l’Avenir, Mirabel, Quebec J7J 1R4, 

Canada; phone: 1–450–437–2862 or 1– 

800–363–8023; fax: 1–450–433–0272; 

email: productsupport@bellflight.com; 

or at https://www.bellflight.com/ 

support/contact-support. 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. It is also available 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0145. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0145; 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 Transport Canada Civil 

Aviation (TCCA) 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: Hal 

Jensen, Aerospace Engineer, Operational 

Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 

L’Enfant Plaza N SW, Washington, DC 

20024; phone: (202) 267–9167; email: 

hal.jensen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2019–11–05, 

Amendment 39–19651 (84 FR 26546, 

June 7, 2019) (AD 2019–11–05). AD 

2019–11–05 applied to certain Bell 

Helicopter Textron Canada Limited 

Model 429 helicopters. The NPRM 

published in the Federal Register on 

February 23, 2022 (87 FR 10107). In the 

NPRM, the FAA proposed to continue to 

require inspecting the TR pitch link 

assemblies, and replacing certain pitch 

link bearings, as well as proposed to 

revise the applicability and require 

inspections of certain other TR pitch 

link assemblies. The NPRM was 

prompted by TCCA AD CF–2015–16R3, 

dated April 30, 2021 (TCCA AD CF– 


jspears on DSK121TN23PROD with RULES1
24402 Federal Register / Vol. 87, No. 80 / Tuesday, April 26, 2022 / Rules and Regulations 

2015–16R3), issued by TCCA, which is 

the aviation authority for Canada, to 

correct an unsafe condition for certain 

Bell Helicopter Textron Canada Limited 

Model 429 helicopters. TCCA AD CF– 

2015–16R3 retains the requirements of 

TCCA AD CF–2015–16R2, dated April 

3, 2017, and revises the applicability by 

specifying certain helicopter serial 

numbers to account for new production 

helicopters, which have already 

incorporated the new pitch link 

assemblies and corrected the unsafe 

condition. TCCA AD CF–2015–16R3 

also specifies that installing a new pitch 

link assembly terminates the repetitive 

inspections. This condition, if not 

addressed, could result in pitch link 

failure and subsequent loss of control of 

the 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 the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to the FAA’s bilateral 

agreement with Canada, TCCA, its 

technical representative, has notified 

the FAA of 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. Except 

for minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Bell Alert Service 

Bulletin No. 429–15–16, Revision C, 

dated October 16, 2020. This service 

information contains procedures for 

inspecting the TR pitch link assemblies, 

replacing certain pitch link bearings, 

and replacement of the pitch link 

assemblies. 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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 120 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. 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product Cost on U.S. operators 

Retained inspections from 

AD 2019–11–05.

2 work-hours × $85 per hour = $170 

per inspection cycle.

$0 $170 per inspection cycle $20,400 per inspection 

cycle. 

New inspections ................ 2 work-hours × $85 per hour = $170 

per inspection cycle.

0 $170 per inspection cycle $20,400 per inspection 

cycle. 

The FAA estimates the following 

costs to do any necessary on-condition 

replacements that would be required 

based on the results of any required 

actions. The FAA has no way of 

determining the number of helicopters 

that might need these on-condition 

actions: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Bearing replacements ...................... 3 work-hours × $85 per hour = $255 ............................ $3,340 $3,343 $401,160 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected operators. The 

FAA does not control warranty coverage 

for affected operators. As a result, the 

FAA has included all known costs in 

the cost estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 


jspears on DSK121TN23PROD with RULES1
Federal Register / Vol. 87, No. 80 / Tuesday, April 26, 2022 / Rules and Regulations 24403 

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 

(AD) 2019–11–05, Amendment 39– 

19651 (84 FR 26546, June 7, 2019); and 

■ b. Adding the following new AD: 

2022–09–07 Bell Textron Canada Limited 

(Type Certificate Previously Held by Bell 

Helicopter Textron Canada Limited): 

Amendment 39–22027; Docket No. 

FAA–2022–0145; Project Identifier 

MCAI–2021–00522–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 31, 2022. 

(b) Affected ADs 

(1) This AD replaces AD 2019–11–05, 

Amendment 39–19651 (84 FR 26546, June 7, 

2019) (AD 2019–11–05). 

(2) This AD affects AD 2020–17–10, 

Amendment 39–21215 (85 FR 49941, August 

17, 2020) (AD 2020–17–10). 

(c) Applicability 

This AD applies to Bell Textron Canada 

Limited (type certificate previously held by 

Bell Helicopter Textron Canada Limited) 

Model 429 helicopters, certificated in any 

category, serial numbers 57001 through 

57401 inclusive. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720, Tail Rotor Control System. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

worn pitch link. The FAA is issuing this AD 

to address a worn pitch link, which if not 

corrected, could result in pitch link failure 

and subsequent loss of control of the 

helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Requirements 

(1) For pitch link assembly part number 

(P/N) 429–012–112–101, 429–012–112–103, 

429–012–112–101FM, and 429–012–112– 

103FM: Within 50 hours time-in-service (TIS) 

after July 12, 2019 (the effective date of AD 

2019–11–05) and thereafter at intervals not to 

exceed 50 hours TIS: 

(i) Perform a dimensional inspection of 

each inboard and outboard pitch link 

assembly for axial and radial bearing play. 

With a 10X or higher power magnifying glass, 

inspect the bearing liner for a crack, 

deterioration of the liner, and extrusion of 

the liner from the plane. If there is axial or 

radial play that exceeds allowable limits, or 

if there is a crack, deterioration of the liner, 

or extrusion of the liner, before further flight, 

replace the bearing. 

(ii) Inspect the pitch link assembly sealant 

for pin holes and voids and to determine if 

the sealant thickness is 0.025 inch (0.64 mm) 

or less, extends over the roll staked lip by 

0.030 inch (0.76 mm) or more, and is clear 

of the bearing ball. If there is a pin hole or 

void, or if the sealant exceeds 0.026 inch 

(0.66 mm), does not extend over the roll 

staked lip by 0.030 inch (0.76 mm) or more, 

or is not clear of the bearing ball, before 

further flight, replace the bearing. 

(2) For pitch link assembly P/N 429–012– 

112–101, 429–012–112–103, 429–012–112– 

101FM, and 429–012–112–103FM, within 

200 hours TIS following the initial inspection 

required by paragraph (g)(1) of this AD, or if 

the hours TIS of a pitch link assembly exceed 

250 hours TIS or are unknown, at the next 

50-hour-TIS inspection required by 

paragraph (g)(1) of this AD: 

(i) Replace each bearing P/N 429–312–107– 

103 with a date of manufacture before 

January 13, 2015, with a bearing P/N 429– 

312–107–103 that was manufactured on or 

after January 13, 2015. 

(ii) Using a white permanent fine point 

marker or equivalent, re-identify the pitch 

link assembly: 

(A) Re-identify P/N 429–012–112–101 and 

429–012–112–101FM as 429–012–112– 

111FM. 

(B) Re-identify P/N 429–012–112–103 and 

429–012–112–103FM as 429–012–112– 

113FM. 

(iii) Apply a coating of DEVCON 2–TON 

(C–298) or equivalent over the new P/N. 

(h) New Requirements 

For pitch link assemblies other than P/N 

429–012–112–101, 429–012–112–103, 429– 

012–112–101FM, and 429–012–112–103FM: 

Within 50 hours TIS after the effective date 

of this AD and thereafter at intervals not to 

exceed 50 hours TIS: 

(1) Perform a dimensional inspection of 

each inboard and outboard pitch link 

assembly for axial and radial bearing play. 

With a 10× or higher power magnifying glass, 

inspect the bearing liner for a crack, 

deterioration of the liner, and extrusion of 

the liner from the plane. If there is axial or 

radial play that exceeds allowable limits, or 

if there is a crack, deterioration of the liner, 

or extrusion of the liner, before further flight, 

replace the bearing. 

(2) Inspect the pitch link assembly sealant 

for pin holes and voids and to determine if 

the sealant thickness is 0.025 inch (0.64 mm) 

or less, extends over the roll staked lip by 

0.030 inch (0.76 mm) or more, and is clear 

of the bearing ball. If there is a pin hole or 

void, or if the sealant exceeds 0.026 inch 

(0.66 mm), does not extend over the roll 

staked lip by 0.030 inch (0.76 mm) or more, 

or is not clear of the bearing ball, before 

further flight, replace the bearing. 

(i) Terminating Action for Certain Actions in 

AD 2020–17–10 

Accomplishing the initial inspection 

required by paragraph (g)(1) or (h) of this AD 

constitutes terminating action for the 

inspections required by paragraph (f)(2) of 

AD 2020–17–10 for that pitch link assembly 

only. 

(j) Optional Terminating Action 

The repetitive inspections required by 

paragraph (h) of this AD are no longer 

required for helicopters that incorporate 

pitch link assemblies, P/N 429–012–212–105 

or 429–012–212–107, in accordance with Part 

III of the Accomplishment Instructions of 

Bell Alert Service Bulletin No. 429–15–16, 

Revision C, dated October 16, 2020. 

(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 

of the local flight standards district office/ 

certificate holding district office. 

(l) Related Information 

(1) For more information about this AD, 

contact Hal Jensen, Aerospace Engineer, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 L’Enfant 

Plaza N SW, Washington, DC 20024; phone: 

(202) 267–9167; email: hal.jensen@faa.gov. 

(2) The subject of this AD is addressed in 

Transport Canada Civil Aviation AD CF– 

2015–16R3, dated April 30, 2021. You may 

view the Transport Canada AD at https://

www.regulations.gov in Docket No. FAA– 

2022–0145. 

(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. 

(i) Bell Alert Service Bulletin No. 429–15– 

16, Revision C, dated October 16, 2020. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Bell Textron Canada 

Limited, 12,800 Rue de l’Avenir, Mirabel, 

Quebec J7J 1R4, Canada; phone: 1–450–437– 

2862 or 1–800–363–8023; fax: 1–450–433– 

0272; email: productsupport@bellflight.com; 

or at https://www.bellflight.com/support/ 

contact-support. 

(4) 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. 

(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, 


jspears on DSK121TN23PROD with RULES1
24404 Federal Register / Vol. 87, No. 80 / Tuesday, April 26, 2022 / Rules and Regulations 

email: fr.inspection@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on April 15, 2022. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–08797 Filed 4–25–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0102; Project 

Identifier MCAI–2021–00841–R; Amendment 

39–22024; AD 2022–09–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

airworthiness directive (AD) for 2021– 

05–05 which applied to all Airbus 

Helicopters Model SA–365N1, AS– 

365N2, AS 365 N3, SA–366G1, EC 155B, 

and EC155B1 helicopters. AD 2021–05– 

05 required modifying the helicopter by 

replacing the tail rotor gearbox (TGB) 

control shaft guide bushes; repetitive 

inspections (checks) of the oil level of 

the TGB and, if necessary, filling the oil 

to the maximum level; repetitive 

inspections of the TGB magnetic plug 

and corrective actions if necessary; 

repetitive replacements of a certain 

control rod double bearing (bearing); 

and modifying the helicopter by 

replacing the TGB. This AD was 

prompted by a report where during a 

landing phase, a helicopter lost tail rotor 

pitch control, which was caused by 

significant damage to the TGB bearing. 

This AD retains some of the 

requirements of AD 2021–05–05, and 

reduces the intervals of the magnetic 

plug inspection, revises the corrective 

actions if particles are detected, and 

revises the compliance time for 

replacement of the affected part, as 

specified in a European Union Aviation 

Safety Agency (EASA) AD, which is 

incorporated by reference. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective May 31, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 31, 2022. 

ADDRESSES: For EASA material 

incorporated by reference (IBR) in this 

final rule, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +49 221 8999 000; 

email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find the 

EASA material on the EASA website at 

https://ad.easa.europa.eu. For Airbus 

Helicopters and Eurocopter service 

information identified in this final rule, 

contact Airbus Helicopters, 2701 North 

Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at https:// 

www.airbus.com/helicopters/services/ 

technical-support.html. You may view 

this material 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 IBRed is also 

available in the AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0102. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0102; 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 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: Hal 

Jensen, Aerospace Engineer, Operational 

Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 

L’Enfant Plaza N SW, Washington, DC 

20024; telephone (202) 267–9167; email 

hal.jensen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2021–05–05, 

Amendment 39–21448 (86 FR 13972, 

March 12, 2021) (AD 2021–05–05). AD 

2021–05–05 applied to all Airbus 

Helicopters Model SA–365N1, AS– 

365N2, AS 365 N3, SA–366G1, EC 155B, 

and EC155B1 helicopters. AD 2021–05– 

05 required repetitive checks of the oil 

level of the TGB and if necessary, filling 

the oil to the maximum level. AD 2021– 

05–05 also required modifying the 

helicopter by replacing the TGB control 

shaft guide bushes; repetitive 

inspections of the TGB magnetic plug 

and corrective actions if necessary; 

repetitive replacements of the bearing; 

and modifying the helicopter by 

replacing the TGB. The NPRM 

published in the Federal Register on 

February 18, 2022 (87 FR 9277). The 

NPRM was prompted by a report where 

during a landing phase, a helicopter lost 

tail rotor pitch control, which was 

caused by significant damage to the TGB 

bearing. The NPRM was also prompted 

by the determination that reduced 

inspection intervals, updated corrective 

actions, and a revised compliance time 

for replacement of affected parts are 

necessary to address the unsafe 

condition. Furthermore, the FAA 

determined that the magnetic plug 

inspection interval must be reduced 

based on additional testing of the 

affected part by the manufacturer, and 

the compliance time for replacement of 

the affected part must be reduced. 

The NPRM proposed to retain certain 

actions in AD 2021–05–05; reduce the 

intervals of the magnetic plug 

inspection; revise the corrective actions 

if particles are detected; and revise the 

compliance time for replacement of the 

affected part. The NPRM also proposed 

to allow the oil level inspections 

(checks) to be performed by the owner/ 

operator (pilot) holding at least a private 

pilot certificate and must be entered 

into the aircraft records showing 

compliance with the proposed AD in 

accordance with 14 CFR 43.9 (a)(1) 

through (4) and 14 CFR 91.417(a)(2)(v). 

The record must be maintained as 

required by 14 CFR 91.417 or 135.439. 

The NPRM was prompted by EASA 

AD 2021–0171, dated July 19, 2021 

(EASA AD 2021–0171), issued by 

EASA, which is the Technical Agent for 

the Member States of the European 

Union, to correct an unsafe condition 

for Airbus Helicopters (AH), formerly 

Eurocopter (EC), Eurocopter France, 

Aerospatiale, Sud Aviation, Model SA 

365 N1, AS 365 N2, AS 365 N3, EC 155 

B, and EC 155 B1 helicopters, all serial 

numbers. 

The FAA is issuing this AD to prevent 

damage to the bearing, which if not 

addressed, could result in loss of yaw 

control of the helicopter. See EASA AD 

2021–0171 for additional background 

information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 


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