Document ID: FAA-2020-0171-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Bell Helicopter Textron, Inc. Helicopters
Posted Date: 2020-02-26T05:00Z

[Federal Register Volume 85, Number 38 (Wednesday, February 26, 2020)]
[Proposed Rules]
[Pages 11003-11005]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-03851]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0171; Product Identifier 2018-SW-028-AD]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron, Inc. 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Bell Helicopter Textron, Inc. (Bell) Model 214ST helicopters. This 
proposed AD was prompted by the discovery of bolts with nonconforming 
external thread root radii. This proposed AD would require removing the 
affected bolts from service and would prohibit installing an affected 
bolt on any helicopter. 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 April 13, 
2020.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Bell 
Helicopter 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.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0171; 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. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Haytham Alaidy, Aviation Safety 
Engineer, DSCO Branch, Compliance and Airworthiness Division, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; phone: 817-222-5224; fax: 
817-222-4960; email haytham.alaidy@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 the ADDRESSES section. Include ``FAA-2020-0171; Product 
Identifier 2018-SW-028-AD'' at the beginning of your comments. The FAA 
specifically invites comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. The FAA will consider 
all comments received by the closing date and may amend this NPRM 
because of those comments.
    The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Discussion

    The FAA proposes to adopt a new AD for Bell Model 214ST helicopters 
with certain serial-numbered spindle to yoke bolts (bolts) part number 
(P/N) 214-010-262-103 installed. Bell indicates that a former bolt 
supplier manufactured a number of P/N 214-010-262-103 bolts with 
nonconforming external thread root radii. This proposed AD would apply 
to Model 214ST helicopters with a non-conforming bolt installed and 
would require removing each bolt from service. The proposed AD would 
also prohibit installing a non-conforming bolt on any helicopter. The 
proposed actions are intended to prevent the spindle separating from 
the yoke and subsequent loss of control of the helicopter.

Related Service Information

    The FAA reviewed Bell Helicopter Textron Alert Service Bulletin 
214ST-

[[Page 11004]]

18-93 Revision A, dated April 17, 2019, for Model 214ST helicopters. 
This service information specifies inspecting the historical records 
and spare parts to determine the serial number (S/N) of each bolt. If 
the S/N of the bolt indicates it is a non-conforming bolt, the service 
information specifies torque checking the bolt every 25 hours until the 
bolt reaches its life limit.

FAA's Determination

    The FAA is proposing this AD after evaluating all the relevant 
information and determining that the unsafe condition described 
previously is likely to exist or develop in other products of the same 
type design.

Proposed AD Requirements

    This proposed AD would apply to Model 214ST helicopters with a bolt 
P/N 214-010-262-103 with S/N BH179163, BH179164, BH179169, BH179170, 
BH179171, BH179175, BH179176, BH179178, BH224783, BH224751, BH224756, 
BH224764, BH224765, BH383851, BH383853, BH383855, BH383856, BH383857, 
BH383858, BH383860, BH383861, BH383862, BH383864, BH383865, BH383868, 
BH383872, BH383873, BH383878, or BH383879 installed. This proposed AD 
would require, within 25 hours time-in-service (TIS), removing each 
affected bolt from service. This proposed AD would also prohibit, after 
the effective date of this AD, installing an affected bolt on any 
helicopter.

Differences Between This Proposed AD and the Service Information

    The service information specifies torque checking the bolt every 25 
hours until it is replaced upon reaching its life limit, while this 
proposed AD would require removing each bolt from service within 25 
hours TIS.

Costs of Compliance

    The FAA estimates that this proposed AD would affect 16 helicopters 
of U.S. registry. The FAA estimates that operators may incur the 
following costs in order to comply with this proposed AD. Labor costs 
are estimated at $85 per work-hour.
    Replacing 1 bolt would take about 8 work-hours and parts would cost 
about $7,073 for an estimated cost of $7,753 per helicopter.
    The FAA has no way of determining the number of bolts that might 
need to be replaced.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. The FAA does not control warranty coverage for 
affected individuals. As a result, all costs are included in this cost 
estimate.

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

    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) 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 Proposed 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 (AD):

Bell Helicopter Textron, Inc.: Docket No. FAA-2020-0171; Product 
Identifier 2018-SW-028-AD.

(a) Comments Due Date

    The FAA must receive comments by April 13, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bell Helicopter Textron, Inc. Model 214ST 
helicopters, certificated in any category, with a spindle to yoke 
bolt (bolt) part number (P/N) 214-010-262-103 and serial number (S/
N) BH179163, BH179164, BH179169, BH179170, BH179171, BH179175, 
BH179176, BH179178, BH224783, BH224751, BH224756, BH224764, 
BH224765, BH383851, BH383853, BH383855, BH383856, BH383857, 
BH383858, BH383860, BH383861, BH383862, BH383864, BH383865, 
BH383868, BH383872, BH383873, BH383878, or BH383879 installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6200, Main Rotor.

(e) Unsafe Condition

    This AD was prompted by the discovery that bolts have 
nonconforming external thread root radii. The unsafe condition, if 
not addressed, could result in the spindle separating from the yoke 
and subsequent loss of control of the helicopter.

(f) Compliance

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

(g) Required Actions

    (1) Within 25 hours time-in-service, remove from service each 
bolt listed in paragraph (c) of this AD.
    (2) After the effective date of this AD, do not install on any 
helicopter a bolt with a P/N and S/N listed in paragraph (c) of this 
AD.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, DSCO Branch, Compliance and Airworthiness 
Division, 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 
(i)(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.

[[Page 11005]]

(i) Related Information

    (1) For more information about this AD, contact Haytham Alaidy, 
Aviation Safety Engineer, DSCO Branch, Compliance and Airworthiness 
Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; phone: 
817-222-5224; fax: 817-222-4960; email: haytham.alaidy@faa.gov.
    (2) For information about AMOCs, contact 9-ASW-190-COS@faa.gov.

    Issued in Fort Worth, Texas, on February 13, 2020.

Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-03851 Filed 2-25-20; 8:45 am]
BILLING CODE 4910-13-P