Airworthiness Directives; Brantly Helicopters Industries U.S.A. Co., Ltd., and Brantly International, Inc., Helicopters, 71134-71135 [2021-27052]

Download as PDF 71134 Federal Register / Vol. 86, No. 238 / Wednesday, December 15, 2021 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0610; Project Identifier AD–2021–00126–R; Amendment 39–21868; AD 2021–26–09] RIN 2120–AA64 Airworthiness Directives; Brantly Helicopters Industries U.S.A. Co., Ltd., and Brantly International, Inc., Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting 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 AD was prompted by a report of a crack in the tail rotor (T/R) hub. This AD requires repetitive inspections of the T/ R hub and depending on the results, removing the T/R hub from service. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 19, 2022. ADDRESSES: For service information identified in this final rule, contact Brantly International, Inc., Bill Ross, 621 S Royal Lane, Suite 100, Coppell, TX 75019, United States; 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: khammond on DSKJM1Z7X2PROD with 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 final rule, any comments received, and other information. The address for Docket Operations 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: Marc Belhumeur, Senior Project Engineer, Certification Section, Fort Worth ACO Branch, Compliance & VerDate Sep<11>2014 16:21 Dec 14, 2021 Jkt 256001 Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5177; email 9ASW-FWACO@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 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. The NPRM published in the Federal Register on July 30, 2021 (86 FR 40967). The NPRM was prompted by a report of a crack in T/R hub part number (P/N) 2951. In the NPRM, the FAA proposed to 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 NPRM also proposed to 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. This condition, if not addressed, could result in loss of T/R control and subsequent loss of control of the helicopter. 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 individual. The commenter supports the proposal but recommended the FAA acquire sufficient data regarding the unsafe condition and investigate to determine if this unsafe condition exists on the T/R hub of other helicopters. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request Regarding the FAA’s Justification of the Unsafe Condition The individual recommended that prior to implementing the proposed rule, the FAA ensure adequate data has been acquired and proceed if the frequency of incident is proven to be material. Prior to issuing the NPRM, the FAA reviewed the report and associated data for a crack in the T/R hub. In accordance with FAA Order 8110.107A Monitor Safety/Analyze Data, the FAA has determined that an unsafe condition exists that supports AD action. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Request Pertaining to Other Model Helicopters The individual stated that the FAA should investigate whether issues exist in the T/R hub of other model helicopters. No data has been provided to substantiate the individual’s comment; however, available data for this unsafe condition is limited to T/R hub P/N 161–1 and 2951, which are only approved for installation on Brantly Helicopters Industries U.S.A. Co., Ltd., Model 305 helicopters and Brantly International, Inc., Model B–2, B–2A, and B–2B helicopters. Conclusion The FAA reviewed the relevant data, considered any comments received, 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 a minor editorial change to paragraph (e) of this AD, this AD is adopted as proposed in the NPRM. This change will not increase the economic burden on any operator. 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. Differences Between This AD and the Service Information SL 102 applies to all Brantly helicopters, whereas this AD applies to helicopters with T/R hub P/N 2591 or 161–1 installed. This AD requires 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 AD requires 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 AD does not require reporting any information. E:\FR\FM\15DER1.SGM 15DER1 Federal Register / Vol. 86, No. 238 / Wednesday, December 15, 2021 / Rules and Regulations 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 AD. Cleaning and inspecting the T/R hub with a magnifying glass takes 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 takes 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 takes about 0.5 work-hour and parts 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 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. khammond on DSKJM1Z7X2PROD with RULES 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. VerDate Sep<11>2014 16:21 Dec 14, 2021 Jkt 256001 71135 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (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. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (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. 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: ■ 2021–26–09 Brantly Helicopters Industries U.S.A. Co., Ltd., and Brantly International, Inc.: Amendment 39– 21868; Docket No. FAA–2021–0610; Project Identifier AD–2021–00126–R. (a) Effective Date This airworthiness directive (AD) is effective January 19, 2022. (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 a 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. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 (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. (j) Material Incorporated by Reference None. Issued on December 9, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–27052 Filed 12–14–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0655; Project Identifier MCAI–2020–01497–E; Amendment 39–21846; AD 2021–25–03] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by RollsRoyce plc) Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd. & Co KG (RRD) Trent 7000–72 and Trent 7000– 72C model turbofan engines. This AD was prompted by the manufacturer revising the engine Time Limits Manual (TLM) life limits of certain critical rotating parts and updating certain SUMMARY: E:\FR\FM\15DER1.SGM 15DER1

Agencies

[Federal Register Volume 86, Number 238 (Wednesday, December 15, 2021)]
[Rules and Regulations]
[Pages 71134-71135]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-27052]



[[Page 71134]]

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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; 
Amendment 39-21868; AD 2021-26-09]
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:  Final rule.

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

SUMMARY:  The FAA is adopting 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 AD was prompted by a report of a crack in the tail 
rotor (T/R) hub. This AD requires repetitive inspections of the T/R hub 
and depending on the results, removing the T/R hub from service. The 
FAA is issuing this AD to address the unsafe condition on these 
products.

DATES:  This AD is effective January 19, 2022.

ADDRESSES:  For service information identified in this final rule, 
contact Brantly International, Inc., Bill Ross, 621 S Royal Lane, Suite 
100, Coppell, TX 75019, United States; 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.

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 final rule, any 
comments received, and other information. The address for Docket 
Operations 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:  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:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to 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. The 
NPRM published in the Federal Register on July 30, 2021 (86 FR 40967). 
The NPRM was prompted by a report of a crack in T/R hub part number (P/
N) 2951. In the NPRM, the FAA proposed to 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 NPRM also proposed to 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.
    This condition, if not addressed, could result in loss of T/R 
control and subsequent loss of control of the helicopter. 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 individual. The commenter 
supports the proposal but recommended the FAA acquire sufficient data 
regarding the unsafe condition and investigate to determine if this 
unsafe condition exists on the T/R hub of other helicopters. The 
following presents the comments received on the NPRM and the FAA's 
response to each comment.

Request Regarding the FAA's Justification of the Unsafe Condition

    The individual recommended that prior to implementing the proposed 
rule, the FAA ensure adequate data has been acquired and proceed if the 
frequency of incident is proven to be material.
    Prior to issuing the NPRM, the FAA reviewed the report and 
associated data for a crack in the T/R hub. In accordance with FAA 
Order 8110.107A Monitor Safety/Analyze Data, the FAA has determined 
that an unsafe condition exists that supports AD action.

Request Pertaining to Other Model Helicopters

    The individual stated that the FAA should investigate whether 
issues exist in the T/R hub of other model helicopters.
    No data has been provided to substantiate the individual's comment; 
however, available data for this unsafe condition is limited to T/R hub 
P/N 161-1 and 2951, which are only approved for installation on Brantly 
Helicopters Industries U.S.A. Co., Ltd., Model 305 helicopters and 
Brantly International, Inc., Model B-2, B-2A, and B-2B helicopters.

Conclusion

    The FAA reviewed the relevant data, considered any comments 
received, 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 a minor editorial change to 
paragraph (e) of this AD, this AD is adopted as proposed in the NPRM. 
This change will not increase the economic burden on any operator.

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.

Differences Between This AD and the Service Information

    SL 102 applies to all Brantly helicopters, whereas this AD applies 
to helicopters with T/R hub P/N 2591 or 161-1 installed. This AD 
requires 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 AD requires 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 AD does not require reporting any information.

[[Page 71135]]

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 AD.
    Cleaning and inspecting the T/R hub with a magnifying glass takes 
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 takes 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 takes about 0.5 
work-hour and parts 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 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:

2021-26-09 Brantly Helicopters Industries U.S.A. Co., Ltd., and 
Brantly International, Inc.: Amendment 39-21868; Docket No. FAA-
2021-0610; Project Identifier AD-2021-00126-R.

(a) Effective Date

    This airworthiness directive (AD) is effective January 19, 2022.

(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 a 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].

(j) Material Incorporated by Reference

    None.

    Issued on December 9, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-27052 Filed 12-14-21; 8:45 am]
BILLING CODE 4910-13-P