This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

13443 

Vol. 86, No. 44 

Tuesday, March 9, 2021 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0270; Product 

Identifier 2019–SW–018–AD; Amendment 

39–21441; AD 2021–04–19] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Inc. (Type Certificate Previously Held 

by Bell Helicopter Textron Inc.) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Bell 

Textron Inc. (Bell) Model 205B 

helicopters. This AD was prompted by 

flight testing and fatigue analysis 

results. This AD requires reducing the 

life limit of certain tail rotor (T/R) 

blades and re-identifying them with a 

new part number (P/N). The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective April 13, 

2021. 

ADDRESSES: For service information 

identified in this final rule contact, Bell 

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

TX 76101; telephone 817–280–3391; fax 

817–280–6466; or at https://

www.bellcustomer.com. You may view 

the referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. Docket No. FAA–2020–0270. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0270; 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: 

Kuethe Harmon, Safety Management 

Program Manager, DSCO Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone 817–222–5198; email 

kuethe.harmon@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to Bell Model 205B helicopters 

with a T/R blade P/N 212–010–750–009 

or 212–010–750–105 installed. The 

NPRM published in the Federal 

Register on March 25, 2020 (85 FR 

16916). Flight testing and fatigue 

analysis by Bell indicated that these 

part-numbered T/R blades sustain 

greater loads when installed on Bell 

Model 205B helicopters compared to 

their use on other model helicopters. In 

the NPRM, the FAA proposed to 

require, before further flight, reducing 

the life limit of each affected T/R blade 

from 5,000 hours time-in-service (TIS) 

to 2,500 hours TIS; re-identifying the 

T/R blade P/N on its data plate by vibroetching to change the last three digits of 

the existing P/N; creating a component 

history card or equivalent record; and 

revising the Airworthiness Limitations 

section of the existing maintenance 

manual for your helicopter to annotate 

the new P/N and revised life limit. 

Finally, the NPRM proposed to prohibit 

installing any affected T/R blade that 

has not met the AD requirements. 

The FAA issued a supplemental 

notice of proposed rulemaking (SNPRM) 

to amend 14 CFR part 39 by adding an 

AD that would apply to Bell Model 

205B helicopters. The SNPRM 

published in the Federal Register on 

December 8, 2020 (85 FR 78977). The 

SNPRM was prompted by a comment 

received on the NPRM requesting that 

the applicability paragraph be updated 

to include newly identified T/R blade 

part numbers. The FAA determined the 

NPRM should be revised to include the 

additional part-numbered T/R blades 

and the re-identification and life limit 

requirements for those additional partnumbered T/R blades. 

Since the FAA issued the NPRM, Bell 

Helicopter Textron Inc., has changed its 

name to Bell Textron Inc. This final rule 

reflects that change and updates the 

contact information to obtain service 

documentation. 

Comments 

The FAA received no comments on 

the SNPRM 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. 

Related Service Information 

The FAA reviewed Bell Helicopter 

Textron Alert Service Bulletin No. 

205B–20–70, dated August 6, 2020, for 

Model 205B helicopters. This service 

information specifies reducing the life 

limit of T/R blade P/N 212–010–750– 

109, 212–010–750–111, 212–010–750– 

113, 212–010–750–117, 212–010–750– 

133, 212–010–750–135, 212–010–750– 

117FM, and 212–010–750–135FM to 

2,500 hours time-in-service (TIS). This 

service information also specifies reidentifying certain T/R blade P/Ns by 

assigning a new dash number by vibroetching a new P/N on the T/R blade data 

plate and annotating the historical 

record card. 

The FAA also reviewed Bell 

Helicopter Textron Alert Service 

Bulletin No. 205B–98–27, dated June 1, 

1998, for Model 205B helicopters. This 

service information specifies reducing 

the life limit of T/R blade P/N 212–010– 

750–009 and 212–010–750–105 to 2,500 

hours TIS and assigning these T/R 

blades a new dash number by vibroetching a new P/N on the T/R blade data 

plate and annotating the historical 

record card. 

Costs of Compliance 

The FAA estimates that this AD 

affects approximately 2 helicopters of 

U.S. Registry. The FAA estimates that 

operators may incur the following costs 

in order to comply with this AD. Labor 

costs are estimated at $85 per workhour. 

Determining the total hours TIS of a 

T/R blade, re-identifying the P/N, and 


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13444 Federal Register / Vol. 86, No. 44 / Tuesday, March 9, 2021 / Rules and Regulations 

updating the helicopter records takes 

about 1 work-hour for each T/R blade, 

for an estimated cost of $170 per 

helicopter and $340 for the U.S fleet. 

Replacing a T/R blade takes about 8 

work-hours and parts cost about $29,110 

for an estimated cost of $29,790 per T/ 

R blade. 

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: 

2021–04–19 Amendment 39–21441; Docket 

No. FAA–2020–0270; Product Identifier 

2019–SW–018–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 13, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bell Textron Inc. (Bell) 

Model 205B helicopters, certificated in any 

category, with a tail rotor (T/R) blade part 

number (P/N) 212–010–750–009, 212–010– 

750–105, 212–010–750–109, 212–010–750– 

111, 212–010–750–113, 212–010–750–117, 

212–010–750–133, 212–010–750–135, 212– 

010–750–117FM, or 212–010–750–135FM 

installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 6410, Tail Rotor Blades. 

(e) Unsafe Condition 

This AD was prompted by flight testing 

and fatigue analysis that indicates that these 

part-numbered T/R blades sustain greater 

loads when used on Bell Model 205B 

helicopters compared to their use on other 

model helicopters. The FAA is issuing this 

AD to prevent a T/R blade from remaining in 

service beyond its fatigue life, resulting in 

failure of the T/R blade and subsequent loss 

control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Before further flight: 

(i) Determine the total hours time-inservice (TIS) of each T/R blade and remove 

from service each T/R blade that has 

accumulated 2,500 or more hours TIS. For 

each T/R blade that has accumulated less 

than 2,500 hours TIS, do the following: 

(ii) Re-identify the P/N on the T/R blade 

data plate by vibro-etching to change the last 

three digits of the existing P/N as follows: 

(A) For T/R blade P/N 212–010–750–009, 

re-identify the P/N as 212–010–750–111. 

(B) For T/R blade P/N 212–010–750–105, 

re-identify the P/N as 212–010–750–109. 

(C) For T/R blade P/N 212–010–750–113, 

re-identify the P/N as 212–010–750–117FM. 

(D) For T/R blade P/N 212–010–750–133, 

re-identify the P/N as 212–010–750–135FM. 

(iii) Create a component history card or 

equivalent record to reflect the change in P/ 

N for each T/R blade, and establish a life 

limit of 2,500 hours TIS. 

(iv) Revise the Airworthiness Limitations 

Section of the existing maintenance manual 

or the Instructions for Continued 

Airworthiness for your helicopter to establish 

a life limit of 2,500 hours TIS for each T/R 

blade P/N 212–010–750–109, P/N 212–010– 

750–111, P/N 212–010–750–117, P/N 212– 

010–750–135, P/N 212–010–750–117FM, and 

P/N 212–010–750–135FM. 

(2) Thereafter, except as provided in 

paragraph (i), no alternative life limits may 

be approved for T/R blade P/N 212–010–750– 

009, P/N 212–010–750–105, P/N 212–010– 

750–113, or P/N 212–010–750–133. 

(3) After the effective date of this AD, do 

not install a T/R blade P/N 212–010–750– 

009, P/N 212–010–750–105, P/N 212–010– 

750–113, or P/N 212–010–750–133 on any 

Model 205B helicopter unless the part 

number has been changed and the life limit 

reduced in accordance with this AD. 

(4) After the effective date of this AD do 

not install a T/R blade P/N 212–010–750– 

109, P/N 212–010–750–111, P/N 212–010– 

750–117, P/N 212–010–750–135, P/N 212– 

010–750–117FM, or P/N 212–010–750– 

135FM, on any Model 205B helicopter unless 

the life limit has been reduced in accordance 

with this AD. 

(h) Special Flight Permit 

Special flight permits are prohibited. 

(i) 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 paragraph (j)(1) 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Kuethe Harmon, Safety Management 

Program Manager, DSCO Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone 817–222–5198; email 

Kuethe.harmon@faa.gov. 

(2) For service information identified in 

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

482, Fort Worth, TX 76101; telephone 817– 

280–3391; fax 817–280–6466; or at https://

www.bellcustomer.com. You may view 

service information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy., Room 6N–321, Fort Worth, 

TX 76177. 


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Federal Register / Vol. 86, No. 44 / Tuesday, March 9, 2021 / Rules and Regulations 13445 

Issued on February 25, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–04503 Filed 3–8–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0136; Project 

Identifier AD–2021–00188–E; Amendment 

39–21470; AD 2021–05–51] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Pratt & Whitney Division (PW) PW4074, 

PW4074D, PW4077, PW4077D, 

PW4084D, PW4090, and PW4090–3 

model turbofan engines. This AD was 

prompted by the in-flight failure of a 

1st-stage low-pressure compressor (LPC) 

blade on a PW4077 model turbofan 

engine resulting in an engine fire during 

flight. This AD requires performing a 

thermal acoustic image (TAI) inspection 

for cracks in certain 1st-stage LPC 

blades and removal of those blades that 

fail inspection. The FAA previously 

sent an emergency AD to all known U.S. 

owners and operators of these engines 

and is now issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective March 24, 

2021. Emergency AD 2021–05–51, 

issued on February 23, 2021, which 

contained the requirements of this 

amendment, was effective with actual 

notice. 

The FAA must receive comments on 

this AD by April 23, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this final rule, contact Pratt & Whitney 

Division, 400 Main Street, East Hartford, 

CT 06118; phone: (860) 565–0140; 

email: help24@pw.utc.com; website: 

https://fleetcare.pw.utc.com. You may 

view this service information at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (781) 238– 

7759. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0136. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0136; 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 street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Carol Nguyen, Aviation Safety Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

(781) 238–7655; fax: (781) 238–7199; 

email: carol.nguyen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

On February 23, 2021, the FAA issued 

Emergency AD 2021–05–51 (the 

emergency AD), which requires 

performing a TAI inspection for cracks 

in certain 1st-stage LPC blades and 

removal of those blades that fail 

inspection. The FAA sent the 

emergency AD to all known U.S. owners 

and operators of these engines. That 

action was prompted by the in-flight 

failure of a 1st-stage LPC blade on a 

PW4077 model turbofan engine 

resulting in an engine fire during flight. 

This condition, if not addressed, could 

result in 1st-stage LPC blade release, 

damage to the engine, and damage to the 

airplane. 

FAA’s Determination 

The FAA is issuing this AD because 

the agency evaluated all the relevant 

information and determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. 

Related Service Information 

The FAA reviewed Pratt & Whitney 

Alert Service Bulletin (ASB) PW4G– 

112–A72–268, Revision No. 7, dated 

September 6, 2018. The ASB describes 

procedures for performing TAI 

inspections of 1st-stage LPC blades. 

AD Requirements 

This AD requires performing a TAI 

inspection for cracks in certain 1st-stage 

LPC blades and removal of those blades 

that fail inspection. 

Interim Action 

The FAA considers this AD to be an 

interim action. The FAA anticipates that 

further AD action will follow. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (APA) (5 

U.S.C. 551 et seq.) authorizes agencies 

to dispense with notice and comment 

procedures for rules when the agency, 

for ‘‘good cause,’’ finds that those 

procedures are ‘‘impracticable, 

unnecessary, or contrary to the public 

interest.’’ Under this section, an agency, 

upon finding good cause, may issue a 

final rule without providing notice and 

seeking comment prior to issuance. 

Further, section 553(d) of the APA 

authorizes agencies to make rules 

effective in less than thirty days, upon 

a finding of good cause. 

An unsafe condition exists that 

required the immediate adoption of 

Emergency AD 2021–05–51, issued on 

February 23, 2021, to all known U.S. 

owners and operators of these engines. 

The FAA found that the risk to the 

flying public justified waiving notice 

and comment prior to adoption of this 

rule. On February 20, 2021, a United 

Airlines Boeing Model 777–222 

airplane, equipped with two PW4077 

model turbofan engines, on a flight from 

Denver, Colorado to Honolulu, Hawaii, 

experienced a 1st-stage LPC blade 

failure on the number 2 engine. This 

engine failure resulted in the separation 

of the fan inlet and cowling from the 

airplane, an engine fire, and damage to 

the airplane. The airplane was forced to 

return to the airport of departure. The 

unsafe condition, caused by the failure 

of the 1st-stage LPC blade, could result 

in 1st-stage LPC blade release, damage 

to the engine, and damage to the 

airplane. 

The FAA considers inspection and 

removal of those blades that fail 

inspection to be an urgent safety issue. 

Inspection of the 1st-stage LPC blade for 

cracks must be accomplished before 

further flight after the effective date of 

this AD. These conditions still exist, 

therefore, notice and opportunity for 

prior public comment are impracticable 

and contrary to the public interest 

pursuant to 5 U.S.C. 553(b)(3)(B). 


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