[Federal Register Volume 86, Number 144 (Friday, July 30, 2021)]
[Proposed Rules]
[Pages 40967-40969]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-16219]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0610; Project Identifier AD-2021-00126-R]
RIN 2120-AA64


Airworthiness Directives; Brantly Helicopters Industries U.S.A. 
Co., Ltd., and Brantly International, 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 certain Brantly Helicopters Industries U.S.A. Co., Ltd., Model 305 
helicopters and Brantly International, Inc., Model B-2, B-2A, and B-2B 
helicopters. This proposed AD was prompted by a report of a crack in 
the tail rotor (T/R) hub. This proposed AD would require repetitive 
inspections of the T/R hub and depending on the results, removing the 
T/R hub 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 September 
13, 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 NPRM, contact Brantly 
International, Inc., Bill Ross, 621 S Royal Lane, Suite 100, Coppell, 
TX 75019; phone: (972) 829-4699; email: bross@superiorairparts.com. 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.

[[Page 40968]]

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0610; 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: Marc Belhumeur, Senior Project 
Engineer, Certification Section, Fort Worth ACO Branch, Compliance & 
Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone (817) 222-5177; email 9-ASW-FWACO@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-2021-0610; Project Identifier 
AD-2021-00126-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 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 Marc 
Belhumeur, Senior Project Engineer, Certification Section, Fort Worth 
ACO Branch, Compliance & Airworthiness Division, FAA, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone (817) 222-5177; email 9-ASW-FWACO@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 proposes to adopt a new AD for Brantly Helicopters 
Industries U.S.A. Co., Ltd., Model 305 helicopters and Brantly 
International, Inc., Model B-2, B-2A, and B-2B helicopters with T/R hub 
part number (P/N) 161-1 or 2951 installed. This proposed AD was 
prompted by a report of a crack in T/R hub P/N 2951. The crack is 
considered fatigue cracking caused by corrosion pitting. T/R hub P/N 
161-1 is also affected by this unsafe condition due to design 
similarity. This condition, if not addressed, could result in loss of 
T/R control 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

    The FAA reviewed Brantly Helicopter Service Letter No. 102, dated 
July 11, 1974 (SL 102). SL 102 specifies repetitively cleaning and 
inspecting the areas where each T/R blade attaching arm extends from 
the T/R hub for a crack. SL 102 also specifies repetitively cleaning 
and dye penetrant inspecting the radius at the shoulder of each T/R hub 
spindle for a crack. If there is a crack, SL 102 specifies replacing 
the part and reporting any cracks to Brantly Operators, Inc.

Proposed AD Requirements in This NPRM

    This proposed AD would require repetitively cleaning, and using a 
10X or higher power magnifying glass, inspecting the areas where each 
T/R blade attaching arm extends from the T/R hub for a crack, 
corrosion, and pitting, and depending on the results, removing the T/R 
hub from service. This proposed AD would also require repetitively 
cleaning and dye penetrant inspecting the radius at the shoulder of 
each T/R hub spindle for a crack and pitting, and depending on the 
results, removing the T/R hub from service.

Differences Between This Proposed AD and the Service Information

    SL 102 applies to all Brantly helicopters, whereas this proposed AD 
would apply to helicopters with T/R hub P/N 2591 or 161-1 installed. 
This proposed AD would require using a 10X or higher power magnifying 
glass when inspecting the area where the T/R blade attaching arm 
extends from the T/R hub for a crack, corrosion, and pitting, whereas 
SL 102 does not specify using a magnifying glass and only specifies 
inspecting for a crack in that area. This proposed AD would require dye 
penetrant inspecting the radius at the shoulder of each T/R spindle for 
a crack and pitting, whereas SL 102 only specifies dye penetrant 
inspecting for a crack in those areas. SL102 specifies reporting any 
cracks to Brantly Operators, Inc., whereas this proposed AD would not 
require reporting any information.

Costs of Compliance

    The FAA estimates that this AD affects 57 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates that operators may incur the following 
costs in order to comply with this proposed AD.
    Cleaning and inspecting the T/R hub with a magnifying glass would 
take about 1 work-hour for an estimated cost of $85 per helicopter and 
$4,845 for the U.S. fleet, per inspection cycle. Cleaning and dye 
penetrant inspecting the T/R hub would take about 2 work-hours for an 
estimated cost of $170 per helicopter and $9,690 for the U.S. fleet, 
per inspection cycle. If required, replacing a T/R hub would take about 
0.5 work-hour and parts would cost about $500 for an estimated cost of 
$543 per 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 with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds

[[Page 40969]]

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

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:

Brantly Helicopters Industries U.S.A. Co., Ltd., and Brantly 
International, Inc.: Docket No. FAA-2021-0610; Project Identifier 
AD-2021-00126-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by September 13, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Brantly Helicopters Industries U.S.A. Co., 
Ltd., Model 305 helicopters and Brantly International, Inc., Model 
B-2, B-2A, and B-2B helicopters, certificated in any category, with 
a tail rotor (T/R) hub part number 161-1 or 2951, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6420, Tail Rotor 
Head.

(e) Unsafe Condition

    This AD was prompted by a report of crack in the T/R hub. The 
FAA is issuing this AD to address cracking of the T/R hub. The 
unsafe condition, if not addressed, could result in loss of T/R 
control 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

    Within 100 hours time-in-service (TIS) or at the next annual 
inspection after the effective date of this AD, whichever occurs 
first, and thereafter at intervals not to exceed 100 hours TIS and 
at each annual inspection:
    (1) Clean, and using a 10X or higher power magnifying glass, 
inspect the areas where each T/R blade attaching arm extends from 
the T/R hub for a crack, corrosion, and pitting. If there is a 
crack, corrosion, or pitting, before further flight, remove the T/R 
hub from service.
    (2) Clean and dye penetrant inspect the radius at the shoulder 
of each T/R hub spindle for a crack and pitting. If there is a crack 
or pitting, before further flight, remove the T/R hub from service.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Fort Worth ACO 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 (i) of this AD.
    (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

    For more information about this AD, contact Marc Belhumeur, 
Senior Project Engineer, Certification Section, Fort Worth ACO 
Branch, Compliance & Airworthiness Division, FAA, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone (817) 222-5177; email 9-ASW-FWACO@faa.gov.

    Issued on July 26, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-16219 Filed 7-29-21; 8:45 am]
BILLING CODE 4910-13-P


