Federal Register / Vol. 87, No. 64 / Monday, April 4, 2022 / Rules and Regulations 19369 

You may examine the EASA AD in the AD 

docket at https://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2021–1170. 

(j) 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) Schempp-Hirth Flugzeugbau GmbH 

Technical Note No. 278–40/286–36/295–33/ 

328–14/798–4, Revision 1, dated November 

12, 2020 (issued as one document). 

Note 1 to paragraph (j)(2)(i): This service 

information contains German to English 

translation. EASA used the English 

translation in referencing the document from 

Schempp-Hirth Flugzeugbau GmbH. For 

enforceability purposes, the FAA will cite 

references to the service information in 

English as it appears on the document. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Schempp-Hirth Flugzeugbau 

GmbH, Krebenstrasse 25, 73230 Kirchheim/ 

Teck, Germany; phone: +49 7021 7298–0; fax: 

+49 7021 7298–199; email: info@schempphirth.com; website: https://www.schempphirth.com. 

(4) You may view this 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. 

(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 March 10, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–06959 Filed 4–1–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0006; Project 

Identifier AD–2021–01298–R; Amendment 

39–21989; AD 2022–07–02] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Inc. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bell Textron Inc. Model 205A, 205A–1, 

205B, 210, 212, 412, 412CF, and 412EP 

helicopters with a certain partnumbered tailboom left hand fin spar 

cap (spar cap) installed. This AD was 

prompted by reports of cracked spar 

caps. This AD requires inspecting each 

spar cap and depending on the 

inspection results, removing the spar 

cap from service. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective May 9, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 9, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact Bell 

Textron, Inc., P.O. Box 482, Fort Worth, 

TX 76101, United States; phone: (450) 

437–2862 or (800) 363–8023; fax (450) 

433–0272; email productsupport@

bellflight.com; or at https://

www.bellflight.com/support/contactsupport. 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–2022–0006. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0006; 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: 

Ameet Shrotriya, Aviation Safety 

Engineer, DSCO Branch, Compliance & 

Airworthiness Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177– 

1524; phone: (817) 222–5525; email: 

Ameet.Shrotriya@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 certain serial-numbered Bell 

Textron Inc. Model 205A, 205A–1, 

205B, 210, 212, 412, 412CF, and 412EP 

helicopters with a spar cap part number 

212–030–447–117 installed. The NPRM 

published in the Federal Register on 

January 21, 2022 (87 FR 3244). The 

NPRM was prompted by multiple 

reports of fatigue cracking in the spar 

caps. Metallurgical lab reports identified 

that the cracks originate at the rivet 

holes, possibly from mechanical damage 

caused during deburring. In the NPRM, 

the FAA proposed to require inspecting 

each spar cap and depending on the 

inspection results, removing the spar 

cap from service before further flight. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety requires 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. 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 the following Bell 

Alert Service Bulletins, each dated April 

15, 2020 (ASB): 

• ASB 205–20–116 for Model 205A 

and 205A–1 helicopters, serial numbers 

(S/N) 30001 through 30065, 30067 

through 30165, 30167 through 30187, 

30189 through 30296, and 30298 

through 30332; 

• ASB 205B–20–69 for Model 205B 

helicopters, S/N 30066, 30166, 30188, 

and 30297; 

• ASB 210–20–13 for all serialnumbered Model 210 helicopters; 

• ASB 212–20–162 for Model 212 

helicopters, S/N 30502 through 30603, 

30611 through 30999, 31101 through 

31311, 32101 through 32142, and 35001 

through 35103; 

• ASB 412–20–180 for Model 412 and 

412EP helicopters, S/N 33001 through 

33213, 34001 through 34036, 36001 

through 36999, 37002 through 37999, 

38001 through 38999, and 39101 

through 39999; and 

• ASB 412CF–20–67 for Model 412CF 

helicopters, S/N 46400 through 46499. 

Bell received a report of a fractured 

fin spar cap that occurred at vertical fin 

station (F.S.) 71 through the first rivet 

hole attaching the skin to the spar cap. 

Bell states that if undetected, the spar 


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19370 Federal Register / Vol. 87, No. 64 / Monday, April 4, 2022 / Rules and Regulations 

cap cracking may lead to additional 

structural damage. Each ASB specifies 

procedures for inspecting both flanges 

of the spar cap between F.S. 50 and F.S. 

71 for cracks, loose rivets, and other 

damage using a 10x magnifying glass 

and flashlight and inspecting the 

exterior of the fin skin where it contacts 

the spar cap for cracks, loose rivets, 

and/or distortion. If no cracks or other 

damage are found, each ASB specifies 

returning the helicopter to service; if a 

crack or other damage is found, each 

ASB specifies contacting Bell’s Product 

Support Engineering before further 

flight. Additionally, each ASB specifies 

that these inspections are to be 

accomplished within the next 100 flight 

hours or 90 days after the ASB’s release, 

whichever occurs first, and every 100 

flight hours thereafter. 

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. 

Interim Action 

The FAA considers this AD to be an 

interim action. The design approval 

holder may develop a modification that 

will address the unsafe condition 

identified in this AD. Once this 

modification is developed, approved, 

and available, the FAA might consider 

additional rulemaking. 

Costs of Compliance 

The FAA estimates that this AD 

affects 226 helicopters of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD, using an 

average labor rate of $85 per work-hour. 

Each inspection takes about 1 workhour, and there are no parts costs, for an 

estimated cost of $85 per inspection and 

$19,210 for the U.S. fleet per inspection 

cycle. Replacing a spar cap, if required, 

takes about 50 work-hours and parts 

costs about $2,000, for an estimated cost 

of $6,250 per spar cap replacement. 

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: 

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: 

2022–07–02 Bell Textron Inc.: Amendment 

39–21989; Docket No. FAA–2022–0006; 

Project Identifier AD–2021–01298–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 9, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following Bell 

Textron Inc. helicopters certificated in any 

category, with a tailboom left hand fin spar 

cap (spar cap) part number 212–030–447–117 

installed. 

(1) Model 205A and 205A–1 helicopters, 

serial number (S/N) 30001 through 30065 

inclusive, 30067 through 30165 inclusive, 

30167 through 30187 inclusive, 30189 

through 30296 inclusive, and 30298 through 

30332 inclusive; 

(2) Model 205B helicopters, S/N 30066, 

30166, 30188, and 30297; 

(3) Model 210 helicopters, all S/Ns; 

(4) Model 212 helicopters, S/N 30502 

through 30603 inclusive, 30611 through 

30999 inclusive, 31101 through 31311 

inclusive, 32101 through 32142 inclusive, 

and 35001 through 35103 inclusive; 

(5) Model 412 and 412EP helicopters, S/N 

33001 through 33213 inclusive, 34001 

through 34036 inclusive, 36001 through 

36999 inclusive, 37002 through 37999 

inclusive, 38001 through 38999 inclusive, 

and 39101 through 39999 inclusive; and 

(6) Model 412CF helicopters, S/N 46400 

through 46499 inclusive. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 5302, Rotorcraft Tail Boom. 

(e) Unsafe Condition 

This AD was prompted by the discovery of 

fatigue cracking in the spar cap. A crack in 

the spar cap, if not detected and corrected, 

could create stress concentrations at the edge 

of the rivet holes, resulting in reduced 

structural integrity of the helicopter and 

subsequent loss of control of the helicopter. 

The FAA is issuing this AD to detect and 

prevent this unsafe condition. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 100 hours time-in-service (TIS) 

after the effective date of this AD, and 

thereafter at intervals not to exceed 100 hours 

TIS: 

(1) Using a 10x or higher power magnifying 

glass and a flashlight, inspect both flanges of 

the spar cap between fin station (F.S.) 50 and 

F.S. 71 for any crack, loose rivet, and other 

damage such as a scratch, dent, spalling, or 

corrosion, as depicted in Figure 1 of Bell 

Alert Service Bulletin (ASB) 205–20–116, 

ASB 205B–20–69, ASB 210–20–13, ASB 212– 

20–162, ASB 412–20–180, or ASB 412CF– 

20–67, each dated April 15, 2020, as 

applicable to your helicopter. If either spar 

cap flange is cracked, has a loose rivet, or has 

other damage, remove the spar cap from 

service before further flight. 

(2) Inspect the exterior of the fin skin in the 

area that contacts the spar cap for any crack, 

loose rivets, and distortion. If there is any 

crack, loose rivet, or distortion in the fin skin 

in the area that contacts the spar cap, remove 

the spar cap from service before further 

flight. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, DSCO 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, 


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Federal Register / Vol. 87, No. 64 / Monday, April 4, 2022 / Rules and Regulations 19371 

send it to the attention of the person 

identified in paragraph (i) of this AD. 

Information may be emailed to: 9-ASW-190- 

COS@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 

For more information about this AD, 

contact Ameet Shrotriya, Aviation Safety 

Engineer, DSCO Branch, Compliance & 

Airworthiness Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177– 

1524; phone: (817) 222–5525; email: 

Ameet.Shrotriya@faa.gov. 

(j) 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) Bell Alert Service Bulletin 205–20–116, 

dated April 15, 2020. 

(ii) Bell Alert Service Bulletin 205B–20–69, 

dated April 15, 2020. 

(iii) Bell Alert Service Bulletin 210–20–13, 

dated April 15, 2020. 

(iv) Bell Alert Service Bulletin 212–20– 

162, dated April 15, 2020. 

(v) Bell Alert Service Bulletin 412–20–180, 

dated April 15, 2020. 

(vi) Bell Alert Service Bulletin 412CF–20– 

67, dated April 15, 2020. 

(3) For service information identified in 

this AD, contact Bell Textron Inc., P.O. Box 

482, Fort Worth, TX 76101; telephone (450) 

437–2862 or (800) 363–8023; fax (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, 

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

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

ibr-locations.html. 

Issued on March 15, 2022. 

Derek Morgan, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–06973 Filed 4–1–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0005; Project 

Identifier MCAI–2021–01062–R; Amendment 

39–21983; AD 2022–06–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Helicopters Model EC130T2 

helicopters. This AD was prompted by 

the determination of a certain part 

needing a life limit and reidentification. This AD requires reidentifying a certain part-numbered 

engine-to-main gearbox (engine-MGB) 

coupling shaft, and creating a log card 

or equivalent record, 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 9, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 9, 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. 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. It is also available in the AD 

docket at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2022–0005. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0005; 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: 

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 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0216, 

dated September 23, 2021 (EASA AD 

2021–0216), to correct an unsafe 

condition for Airbus Helicopters (AH), 

formerly Eurocopter, Model EC 130 T2 

helicopters, all serial numbers. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus Helicopters Model 

EC130T2 helicopters. The NPRM 

published in the Federal Register on 

January 20, 2022 (87 FR 3050). The 

NPRM was prompted by the 

determination from recent analysis 

related to service life, for the need to 

introduce a service life limit (life limit) 

in torque cycles for engine-MGB 

coupling shaft part number (P/N) 

350A35–1100–21. The NPRM proposed 

to require re-identifying a certain partnumbered engine-MGB coupling shaft 

by crossing out the old P/N and marking 

a new P/N and serial number (S/N) on 

the engine-MGB coupling shaft. The 

NPRM also proposed to require creating 

a log card or equivalent record 

indicating the new P/N, S/N, and the 

initial value of accumulated torque 

cycles for the engine-MGB coupling 

shaft. The NPRM also proposed to 

prohibit installing an affected engineMGB coupling shaft on any helicopter. 

The FAA is issuing this AD to prevent 

fatigue failure of the engine-MGB 

coupling shaft, which if not corrected, 

could result in loss of control of the 

helicopter. See EASA AD 2021–0216 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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