Airworthiness Directives; Brantly Helicopters Industries U.S.A. Co., Ltd., and Brantly International, Inc., Helicopters, 40967-40969 [2021-16219]

Download as PDF Federal Register / Vol. 86, No. 144 / Friday, July 30, 2021 / Proposed Rules Leonardo S.p.a.: Docket No. FAA–2021– 0606; Project Identifier 2019–SW–070– AD. (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 Leonardo S.p.a. Model A109E, A109S, and AW109SP helicopters, certificated in any category, with an affected assembly as identified in European Union Aviation Safety Agency (EASA) AD 2019– 0182, dated July 26, 2019 (EASA AD 2019– 0182) installed. (d) Subject Joint Aircraft Service Component (JASC) Code: 3213, Main Landing Gear Strut/Axle/ Truck. (e) Unsafe Condition This AD was prompted by reports of main landing gear (MLG) wheel assembly failure. The FAA is issuing this AD to address stress corrosion and hydrogen embrittlement on the threaded end of the MLG strut in the MLG wheel assembly. This condition, if not addressed, could lead to cracks on the affected MLG assembly, resulting in damage or failure of the MLG and consequent damage to the helicopter and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. lotter on DSK11XQN23PROD with PROPOSALS1 (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2019–0182. (h) Exceptions to EASA AD 2019–0182 (1) Where EASA AD 2019–0182 refers to flight hours (FH), this AD requires using hours time-in-service. (2) Where EASA AD 2019–0182 refers to its effective date, this AD requires using the effective date of this AD. (3) Where the service information referenced in EASA AD 2019–0182 specifies to return a certain part, this AD does not include that requirement. (4) The ‘‘Remarks’’ section of EASA AD 2019–0182 does not apply to this AD. (5) Where the service information referenced in EASA AD 2019–0182 specifies to discard certain parts, this AD requires removing those parts from service. (6) Where Annex A of the service information referenced in EASA AD 2019– 0182 specifies to contact the manufacturer if there is any indication of cracking due to ‘‘some burr’’; and Annex B of the service information specifies to contact the manufacturer if there are signs of arcing or burning on a part; before further flight, the instructions or corrective actions (including part replacement if necessary) must be accomplished using a method approved by VerDate Sep<11>2014 21:28 Jul 29, 2021 Jkt 253001 the Manager, International Validation Branch, FAA; or EASA; or Leonardo S.p.A.’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. 40967 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 (i) No Reporting Requirement Although the service information referenced in EASA AD 2019–0182 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation 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 International Validation Branch, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@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. (k) Related Information (1) For EASA AD 2019–0182, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may view this material 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. This material may be found in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0606. (2) For more information about this AD, contact Darren Gassetto, Aerospace Engineer, COS Program Management Section, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228–7323; email Darren.Gassetto@faa.gov. Issued on July 21, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–16169 Filed 7–29–21; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 [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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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. SUMMARY: E:\FR\FM\30JYP1.SGM 30JYP1 40968 Federal Register / Vol. 86, No. 144 / Friday, July 30, 2021 / Proposed Rules 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 9ASW-FWACO@faa.gov. SUPPLEMENTARY INFORMATION: lotter on DSK11XQN23PROD with PROPOSALS1 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 VerDate Sep<11>2014 21:28 Jul 29, 2021 Jkt 253001 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 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 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 workhour 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 E:\FR\FM\30JYP1.SGM 30JYP1 Federal Register / Vol. 86, No. 144 / Friday, July 30, 2021 / Proposed Rules 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 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: ■ Brantly Helicopters Industries U.S.A. Co., Ltd., and Brantly International, Inc.: Docket No. FAA–2021–0610; Project Identifier AD–2021–00126–R. lotter on DSK11XQN23PROD with PROPOSALS1 (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 VerDate Sep<11>2014 21:28 Jul 29, 2021 Jkt 253001 (T/R) hub part number 161–1 or 2951, installed. 40969 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration (d) Subject Joint Aircraft System Component (JASC) Code 6420, Tail Rotor Head. 14 CFR Part 71 (e) Unsafe Condition [Docket No. FAA–2021–0596; Airspace Docket No. 20–AGL–15] 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 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 RIN 2120–AA66 Proposed Amendment of V–6, V–10, V–30, V–100, and V–233 in the Vicinity of Litchfield, MI Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to amend VHF Omnidirectional Range (VOR) Federal airways V–6, V–10, V–30, V–100, and V–233 in the vicinity of Litchfield, MI. The air traffic service (ATS) route modifications are necessary due to the planned decommissioning of the VOR portion of the Litchfield, MI, VOR/Distance Measuring Equipment (VOR/DME) navigational aid (NAVAID). The Litchfield VOR/DME NAVAID provides navigational guidance for portions of the affected VOR Federal airways listed above and is planned to be decommissioned as part of the FAA’s VOR Minimum Operational Network (MON) program. DATES: Comments must be received on or before September 13, 2021. ADDRESSES: Send comments on this proposal to the U.S. Department of Transportation, Docket Operations, 1200 New Jersey Avenue SE, West Building Ground Floor, Room W12–140, Washington, DC 20590; telephone: (800) 647–5527, or (202) 366–9826. You must identify FAA Docket No. FAA–2021– 0596; Airspace Docket No. 20–AGL–15 at the beginning of your comments. You may also submit comments through the internet at https://www.regulations.gov. FAA Order 7400.11E, Airspace Designations and Reporting Points, and subsequent amendments can be viewed online at https://www.faa.gov/air_ traffic/publications/. For further information, you can contact the Rules and Regulations Group, Federal Aviation Administration, 800 Independence Avenue SW, Washington, DC 20591; telephone: (202) 267–8783. The Order is also available for inspection at the National Archives and Records Administration (NARA). For information on the availability of FAA Order 7400.11E at NARA, email: fedreg.legal@nara.gov or go to https:// www.archives.gov/federal-register/cfr/ ibr-locations.html. SUMMARY: E:\FR\FM\30JYP1.SGM 30JYP1

Agencies

[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]


-----------------------------------------------------------------------

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).

-----------------------------------------------------------------------

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: [email protected]. 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 [email protected].

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 [email protected]. 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 [email protected].

    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