Document ID: FAA-2021-0454-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bell Textron Inc. (Type Certificate Previously Held by Bell Helicopter Textron Inc.) Helicopters
Posted Date: 2021-09-23T04:00Z

[Federal Register Volume 86, Number 182 (Thursday, September 23, 2021)]
[Rules and Regulations]
[Pages 52821-52822]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-20408]

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 Rules and Regulations
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  Federal Register / Vol. 86, No. 182 / Thursday, September 23, 2021 / 
Rules and Regulations  

[[Page 52821]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0454; Project Identifier AD-2021-00006-R; 
Amendment 39-21740; AD 2021-20-02]
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 
certain Bell Textron Inc. (type certificate previously held by Bell 
Helicopter Textron Inc.) Model 205B helicopters. This AD was prompted 
by a notification of certain parts needing a life limit. This AD 
requires determining the total hours time-in-service (TIS) of certain 
part-numbered main rotor grip assemblies (grip assemblies), 
establishing a life limit for certain part-numbered grip assemblies, 
removing from service any grip assembly that has reached or exceeded 
its retirement life, creating a component history card, and removing 
any grip assembly from service before reaching its retirement life. 
This AD also prohibits installing certain grip assemblies unless the 
life limit was established in accordance with this AD. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective October 28, 2021.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0454; 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, Certification & Program Management Section, DSCO 
Branch, Compliance & Airworthiness Division, FAA, 10101 Hillwood Pkwy., 
Fort Worth, TX 76177; telephone (817) 222-5198; email 
kuethe.harmon@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 Bell Textron Inc. Model 
205B helicopters with grip assembly part number (P/N) 204-011-121-005, 
P/N 204-011-121-113, or P/N 204-011-121-117 installed. The NPRM 
published in the Federal Register on June 10, 2021 (86 FR 30824). The 
NPRM was prompted by a notification from Bell of established life 
limits for certain part numbered grip assemblies that were not included 
in Chapter 4, Airworthiness Limitations Schedule (ALS) of Bell 
Helicopter 205B Maintenance Manual BHT-205B-MM-1, Revision 1, dated 
July 15, 1993. Bell states the life limit of 9,000 hours TIS for grip 
assembly part number (P/N) 204-011-121-005, P/N 204-011-121-113, and P/
N 204-011-121-117 was left out of the ALS for Model 205B helicopters. 
Bell states this may suggest that these part numbers have an unlimited 
life when installed on Model 205B helicopters, whereas the retirement 
life is 9,000 hours TIS. This condition, if not addressed, could result 
in fatigue and failure of the grip assembly and loss of control of the 
helicopter.
    Accordingly, Bell specifies updating the existing ALS to establish 
a life limit of 9,000 hours TIS for grip assembly P/N 204-011-121-005, 
P/N 204-011-121-113, and P/N 204-011-121-117. The FAA is issuing this 
AD to address the unsafe condition on these products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from one commenter. The following 
presents the comment received on the NPRM and the FAA's response.

Request To Correct a Typographical Error

    The European Union Aviation Safety Agency requested the FAA revise 
references made to a certain grip assembly P/N, which is listed 
incorrectly in two instances in the Background section of the NPRM. The 
FAA agrees. The Background section of the NPRM contained two 
typographical errors in which the FAA incorrectly stated the affected 
grip assemblies with life limits omitted from the ALS for Model 205B 
helicopters are grip assembly P/N 204-011-121-005, P/N 204-011-121-113, 
and P/N 204-011-121-005. However, the affected grip assembly part 
numbers are P/N 204-011-121-005, P/N 204-011-121-113, and P/N 204-011-
121-117. The FAA has revised the Background paragraph of this final 
rule accordingly.

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 
the minor editorial change described above, this AD is adopted as 
proposed in the NPRM. This change, which corrects a typographical error 
in the Background section of the NPRM, does not increase the scope of 
the AD.

Costs of Compliance

    The FAA estimates that this AD affects 2 helicopters of U.S. 
registry. The FAA estimates that operators may incur the following 
costs to comply with this AD. Labor costs are estimated at $85 per 
work-hour.
    Determining the total hours TIS of each grip assembly and updating 
the helicopter records takes about 1 work-hour for each grip assembly, 
for an estimated cost of $85 per helicopter and $170 for the U.S fleet.
    Replacing each grip assembly takes about 16 work-hours and parts 
cost about $50,000, for an estimated cost of $51,360 per grip assembly.

[[Page 52822]]

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:

2021-20-02 Bell Textron Inc. (Type Certificate Previously Held by 
Bell Helicopter Textron Inc.): Amendment 39-21740; Docket No. FAA-
2021-0454; Project Identifier AD-2021-00006-R.

(a) Effective Date

    This airworthiness directive (AD) is effective October 28, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bell Textron Inc. (type certificate 
previously held by Bell Helicopter Textron Inc.) Model 205B 
helicopters, certificated in any category, with main rotor grip 
assembly (grip assembly) part number (P/N) 204-011-121-005, P/N 204-
011-121-113, or P/N 204-011-121-117 installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code: 6220, Main Rotor 
Head.

(e) Unsafe Condition

    This AD was prompted by a notification of certain parts needing 
a life limit. The FAA is issuing this AD to prevent a grip assembly 
remaining in service beyond its fatigue life. The unsafe condition, 
if not addressed, could result in fatigue and failure of the grip 
assembly and loss of helicopter control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Before further flight after the effective date of this AD, 
determine the total hours time-in-service (TIS) of any grip assembly 
having P/N 204-011-121-005, P/N 204-011-121-113, or P/N 204-011-121-
117. Remove from service any grip assembly that has accumulated or 
exceeded 9,000 total hours TIS. For each grip assembly that has 
accumulated less than 9,000 total hours TIS, do the following:
    (i) Create a component history card or equivalent record to 
establish a life limit of 9,000 total hours TIS.
    (ii) Thereafter, remove from service any grip assembly before it 
accumulates 9,000 total hours TIS.
    (2) Thereafter, no alternative life limits may be approved for 
any grip assembly P/N 204-011-121-005, P/N 204-011-121-113, or P/N 
204-011-121-117.
    (3) As of the effective date of this AD, do not install any grip 
assembly having P/N 204-011-121-005, P/N 204-011-121-113, or P/N 
204-011-121-117 on any Model 205B helicopter unless the life limit 
is established in accordance with this AD.

(h) Special Flight Permits

    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 
DSCO Branch, send it to the attention of the person identified in 
paragraph (j) 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

    For more information about this AD, contact Kuethe Harmon, 
Safety Management Program Manager, Certification & Program 
Management Section, DSCO Branch, Compliance & Airworthiness 
Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 
(817) 222-5198; email kuethe.harmon@faa.gov.

(k) Material Incorporated by Reference

    None.

    Issued on September 15, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-20408 Filed 9-22-21; 8:45 am]
BILLING CODE 4910-13-P