3244 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules 

Safety Agency (EASA) AD 2021–0179, dated 

July 27, 2021 (EASA AD 2021–0179). 

(h) Exceptions to EASA AD 2021–0179 

(1) Where EASA AD 2021–0179 requires 

compliance in terms of flight hours, this AD 

requires using hours time-in-service. 

(2) Where EASA AD 2021–0179 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(3) Where the service information 

referenced in EASA AD 2021–0179 specifies 

discarding parts, this AD requires removing 

those parts from service. 

(4) Where the service information 

referenced in EASA AD 2021–0179 specifies 

returning a part to the manufacturer, this AD 

requires removing that part from service. 

(5) Where the service information 

referenced in EASA AD 2021–0179 specifies 

submitting photographs to the manufacturer, 

this AD does not require that action. 

(6) Where the service information 

referenced in EASA AD 2021–0179 specifies 

attaching a label to the hoist support 

assembly, this AD does not require that 

action. 

(7) Where paragraph (2) of EASA AD 2021– 

0179 specifies contacting Leonardo S.p.a. for 

corrective action instructions, this AD 

requires replacing or repairing before further 

flight using a method approved by the 

Manager, General Aviation and Rotorcraft 

Section, International Validation Branch, 

FAA; or EASA; or Leonardo S.p.a.’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(8) This AD does not mandate compliance 

with the ‘‘Remarks’’ section of EASA AD 

2021–0179. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2021–0179 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Special Flight Permit 

Special flight permits may be permitted 

provided that there are no passengers on 

board. 

(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)(2) 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 EASA AD 2021–0179, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

www.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. 

This material may be found in the AD docket 

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

for and locating Docket No. FAA–2022–0008. 

(2) 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. 

Issued on January 14, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–01168 Filed 1–20–22; 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] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Inc. 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 Bell Textron Inc. Model 205A, 

205A–1, 205B, 210, 212, 412, 412CF, 

and 412EP helicopters with a certain 

part-numbered tailboom left hand fin 

spar cap (spar cap) installed. This 

proposed AD was prompted by reports 

of cracked spar caps. This proposed AD 

would require inspecting each spar cap 

and depending on the inspection 

results, removing the spar cap 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 March 7, 2022. 

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 Bell Textron, Inc., 

P.O. Box 482, Fort Worth, TX 76101; 

telephone 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. 

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 

NPRM, any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

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: 

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–2022–0006; Project Identifier AD– 

2021–01298–R’’ 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 


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Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules 3245 

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 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. Any commentary that the FAA 

receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

The FAA is proposing to adopt a new 

AD for certain serial-numbered Bell 

Textron Inc. Model 205A, 205A–1, 

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

helicopters with a spar cap part number 

(P/N) 212–030–447–117 installed. This 

proposed AD 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. This 

condition, if not addressed, could result 

in reduced structural integrity of the 

helicopter and subsequent loss of 

control of the helicopter. 

FAA’s Determination 

The FAA is issuing this NPRM after 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. 

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 fin 

spar 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 ADDRESSES. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require, 

within 100 hours time-in-service (TIS) 

after the effective date of the AD, and 

thereafter at intervals not to exceed 100 

hours TIS, using a 10x or higher power 

magnifying glass and flashlight, 

inspecting both flanges of the spar cap 

for any crack, loose rivet, and other 

damage (such as a scratch, dent, 

spalling, or corrosion). This proposed 

AD would also require inspecting the 

exterior of the fin skin in the area where 

it contacts the spar cap for any crack, 

loose rivet, and distortion. If there is any 

crack, loose rivet, or other damage in 

either flange, or if there is any crack, 

loose rivet, or distortion in the fin skin 

area, removing the spar cap from service 

would be required before further flight. 

Differences Between This Proposed AD 

and the Service Information 

The ASBs specify contacting Bell if 

there is a crack or other damage, where 

as this proposed AD would not. The 

ASBs also specify the compliance time 

for the initial inspection is within 100 

flight hours or 90 days after April 15, 

2020, whichever occurs first; whereas 

the initial inspection in this proposed 

AD would be required within 100 hours 

TIS after the effective date of this AD. 

Interim Action 

The FAA considers that this proposed 

AD would 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, if 

adopted as proposed, would affect 226 

helicopters of U.S. registry. The FAA 

estimates the following costs to comply 

with this proposed AD, using an average 

labor rate of $85 per work-hour. 

Each inspection would take about 1 

work-hour, and there would be 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, would take about 50 

work-hours and parts costs would be 

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 


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3246 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules 

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 above, 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: 

Bell Textron Inc.: Docket No. FAA–2022– 

0006; Project Identifier AD–2021–01298– 

R. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by March 7, 

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, 

send it to the attention of the person 

identified in Related Information. 

(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 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. 

(2) For service information identified in 

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

482, Fort Worth, TX 76101; telephone 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 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. 

Issued on January 11, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–00886 Filed 1–20–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1073; Project 

Identifier AD–2021–01252–T] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2017–24–10, which applies to certain 

The Boeing Company Model 757–200, 

–200PF, and –300 series airplanes. AD 

2017–24–10 requires repetitive 

inspections for any cracking of a certain 

fuselage frame inner chord; 

identification of the material of a certain 

fuselage frame inner chord for certain 


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