Airworthiness Directives; Bell Textron Inc. (Type Certificate Previously Held by Bell Helicopter Textron Inc.) Helicopters, 13443-13445 [2021-04503]

Download as PDF 13443 Rules and Regulations Federal Register Vol. 86, No. 44 Tuesday, March 9, 2021 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. FOR FURTHER INFORMATION CONTACT: DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 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. 14 CFR Part 39 SUPPLEMENTARY INFORMATION: [Docket No. FAA–2020–0270; Product Identifier 2019–SW–018–AD; Amendment 39–21441; AD 2021–04–19] Discussion RIN 2120–AA64 Airworthiness Directives; Bell Textron Inc. (Type Certificate Previously Held by Bell Helicopter Textron Inc.) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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. SUMMARY: 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. ADDRESSES: khammond on DSKJM1Z7X2PROD with RULES 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. 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 VerDate Sep<11>2014 16:19 Mar 08, 2021 Jkt 253001 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 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 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 E:\FR\FM\09MRR1.SGM 09MRR1 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. khammond on DSKJM1Z7X2PROD with RULES 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: VerDate Sep<11>2014 16:19 Mar 08, 2021 Jkt 253001 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/ PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 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-190COS@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. E:\FR\FM\09MRR1.SGM 09MRR1 Federal Register / Vol. 86, No. 44 / Tuesday, March 9, 2021 / Rules and Regulations 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: 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 khammond on DSKJM1Z7X2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:19 Mar 08, 2021 Jkt 253001 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 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 13445 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). E:\FR\FM\09MRR1.SGM 09MRR1

Agencies

[Federal Register Volume 86, Number 44 (Tuesday, March 9, 2021)]
[Rules and Regulations]
[Pages 13443-13445]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-04503]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

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. 

========================================================================


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

[[Page 13443]]



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 [email protected].

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 vibro-etching 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 part-numbered 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 re-identifying certain T/R blade P/Ns by assigning a new 
dash number by vibro-etching 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 vibro-etching 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 work-hour.
    Determining the total hours TIS of a T/R blade, re-identifying the 
P/N, and

[[Page 13444]]

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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-in-service (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: [email protected].
    (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 
[email protected]
    (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.


[[Page 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