[Federal Register Volume 86, Number 148 (Thursday, August 5, 2021)]
[Proposed Rules]
[Pages 42754-42758]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-16468]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0612; Project Identifier MCAI-2021-00650-R]
RIN 2120-AA64


Airworthiness Directives; Leonardo S.p.a. Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to issue a new AD to supersede emergency 
Airworthiness Directive (AD) 2018-23-52, which applies to all Leonardo 
S.p.a. Model AW169 and AW189 helicopters. AD 2018-23-52 requires 
inspecting the nut, cotter pin, lock-wire, and hinge bracket connected 
to the tail rotor servo-actuator (TRA) feedback lever link, and each 
connection of the TRA feedback lever link, and repair if necessary. AD 
2018-23-52 also requires applying a paint stripe or torque seal on the 
nut and reporting certain information. Since the FAA issued AD 2018-23-
52, the FAA has determined certain inspections and checks of the tail 
rotor duplex bearings (TR DB), installation of an improved TRA and TR 
DB, certain other actions, and applicable corrective actions are 
necessary to address the unsafe condition. This proposed AD would 
require repetitive inspections of the TRA, repetitive inspections and 
checks of the TR DB, installation of an improved TRA and TR DB, 
repetitive installations and checks of thermal strips, replacement of 
improved TR DB (life limit), and applicable corrective actions, as 
specified in a European Union Aviation Safety Agency (EASA) AD, which 
is proposed for incorporation by reference (IBR). 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 
20, 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 material that is proposed for IBR in this AD, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 
000; email [email protected]; internet www.easa.europa.eu. You may 
find this IBR material on the EASA website at https://ad.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. It is also available in the AD 
docket on the internet at https://www.regulations.gov by searching for 
and locating Docket No. FAA-2021-0612.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0612; 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, the EASA AD, 
any comments received, and other information. The street address for 
Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, 
COS Program Management Section, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 
11590; telephone (516) 228-7330; 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-2021-0612; Project Identifier 
MCAI-2021-00650-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 
Andrea Jimenez, Aerospace Engineer, COS Program Management Section, 
Operational Safety Branch, Compliance & Airworthiness Division, FAA, 
1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email [email protected]. Any commentary that the FAA 
receives that is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Background

    The FAA issued Emergency AD 2018-23-52, Product Identifier 2018-SW-

[[Page 42755]]

093-AD, dated November 8, 2018 (Emergency AD 2018-23-52), which applies 
to all Leonardo S.p.a. Model AW169 and AW189 helicopters. Emergency AD 
2018-23-52 requires inspecting the nut, cotter pin, lock-wire, and 
hinge bracket connected to the TRA feedback lever link, and each 
connection of the TRA feedback lever link, and repair if necessary. 
Emergency AD 2018-23-52 also requires applying a paint stripe or torque 
seal on the nut and reporting certain information. The FAA issued 
Emergency AD 2018-23-52 to address failure of the TRA feedback lever. 
This condition could result in loss of tail rotor (TR) control and 
subsequent loss of control of the helicopter.

Actions Since AD 2018-23-52 Was Issued

    Since the FAA issued Emergency AD 2018-23-52, the agency determined 
certain inspections and checks of the TR DB, installation of an 
improved TRA and an improved TR DB, certain other actions, and 
applicable corrective actions are necessary to address the unsafe 
condition.
    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2020-0197, dated September 10, 2020 
(EASA AD 2020-0197), to correct an unsafe condition for all Leonardo 
S.p.A. (formerly Finmeccanica S.p.A., AgustaWestland S.p.A.) Model 
AW169 and AW189 helicopters.
    This proposed AD was prompted by a report of an accident of a Model 
AW169 helicopter, which was observed to have lost yaw control prior to 
the accident and a determination that additional actions are necessary 
to address the unsafe condition identified in Emergency AD 2018-23-52. 
The FAA is proposing this AD to address failure of the TRA feedback 
lever. This condition could result in loss of TR control and subsequent 
loss of control of the helicopter. See EASA AD 2020-0197 for additional 
background information.

Related Service Information Under 1 CFR Part 51

    EASA AD 2020-0197 requires the following actions:

--Repetitive inspections of the slippage marking of the castellated nut 
installed on the back-end of the affected TRA.
--Repetitive inspections of the roughness and breakaway force of the 
affected TR DB.
--Repetitive installations of a thermal strip on the spacer next to the 
TR DB.
--Repetitive checks of the condition of the thermal strip and the 
indicated temperature.
--Repetitive inspections/checks for particles and additional roughness 
of the TR DB.
--Installation of an improved TRA.
--Installation of an improved TR DB.
--Repetitive replacements of the improved TR DB (life limit).
--An inspection of an affected TR DB if the thermal strip is detached, 
partially detached or unreadable.
--Reporting information to the manufacturer.
--Sending parts to the manufacturer.
--Applicable corrective actions.

    Corrective actions include accomplishing instructions to address 
the following findings: Evidence of rotation of an affected TRA nut; 
thermal strip temperatures that exceed specified values; and any 
discrepancies found during the inspection of an affected TR DB. 
Discrepancies include roughness (meaning lack of free and easy 
rotation), measured breakaway force(s) outside the allowed range, any 
wear or other damage (including, but not limited to, broken seals), and 
the presence of particles.
    EASA AD 2020-0197 also prohibits (re)installation of an affected 
TRA and an affected TR DB on a helicopter. EASA AD 2020-0197 also 
specifies, for certain helicopters, terminating action for the 
repetitive inspections of the slippage marking of the castellated nut.
    This material is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA about the 
unsafe condition described in its AD. The FAA is proposing this AD 
after evaluating all known relevant information and determining that 
the unsafe condition described previously is likely to exist or develop 
on other helicopters of these same type designs.

Proposed AD Requirements in This NPRM

    This proposed AD would require accomplishing the actions specified 
EASA AD 2020-0197, described previously, as incorporated by reference, 
except for any differences identified as exceptions in the regulatory 
text of this proposed AD and except as discussed under ``Differences 
Between this Proposed AD and EASA AD 2020-0197.''

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use some civil aviation 
authority (CAA) ADs as the primary source of information for compliance 
with requirements for corresponding FAA ADs. The FAA has been 
coordinating this process with manufacturers and CAAs. As a result, the 
FAA proposes to incorporate EASA AD 2020-0197 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2020-0197 in its entirety through that incorporation, except 
for any differences identified as exceptions in the regulatory text of 
this proposed AD. Using common terms that are the same as the heading 
of a particular section in EASA AD 2020-0197 does not mean that 
operators need comply only with that section. For example, where the AD 
requirement refers to ``all required actions and compliance times,'' 
compliance with this AD requirement is not limited to the section 
titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2020-
0197. Service information required by EASA AD 2020-0197 for compliance 
will be available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2021-0612 after the FAA final rule is 
published.

Differences Between This Proposed AD and EASA AD 2020-0197

    EASA AD 2020-0197 requires sending parts to the manufacturer. This 
proposed AD would not require that action.
    EASA AD 2020-0197 specifies the earlier revisions of Leonardo 
S.p.A. Emergency Alert Service Bulletin (EASB) 169-148, Revision D, 
dated August 4, 2020; and Leonardo S.p.A. EASB 189-237, Revision D, 
dated August 4, 2020; are acceptable for compliance for certain 
actions. This proposed AD would not allow credit for the earlier 
revisions.
    Where Note 1 of EASA AD 2020-0197 allows a non-cumulative tolerance 
of 10 percent to be applied to the compliance times for the actions to 
allow for synchronization of the required actions with other 
maintenance tasks, this proposed AD would not allow that tolerance.

Interim Action

    The FAA considers this proposed AD to be an interim action and 
further AD action might follow.

[[Page 42756]]

Costs of Compliance

    The FAA estimates that this proposed AD affects 10 helicopters of 
U.S. registry. The FAA estimates the following costs to comply with 
this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections and checks..........  Up to 9 work-hours  $0................  Up to $765, per     Up to $7,650, per
                                   x $85 per hour =                        inspection/check    inspection/check
                                   $765, per                               cycle.              cycle.
                                   inspection/check
                                   cycle.
Thermal strip installation......  1 work-hour x $85   $4................  $89, per            $890, per
                                   per hour = $85,                         installation        installation
                                   per installation                        cycle.              cycle.
                                   cycle.
Installation of improved TRA and  Up to 18 work-      Up to $39,000.....  Up to $40,530.....  Up to $405,300.
 TR DB.                            hours x $85 per
                                   hour = $1,530.
Replacement of improved TR DB...  10 work-hours x     $1,500............  $2,350, per         $23,500, per
                                   $85 per hour =                          replacement cycle.  replacement
                                   $850, per                                                   cycle.
                                   replacement cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates that it would take about 1 hour per product to 
comply with the proposed on-condition reporting requirement in this 
proposed AD. The average labor rate is $85 per hour. Based on these 
figures, the FAA estimates the cost of reporting the inspection and 
check results on U.S. operators to be $85 per product.
    The FAA estimates the following costs to do any necessary on-
condition inspections and thermal strip installations that would be 
required based on the results of any required actions. The FAA has no 
way of determining the number of helicopters that might need these on-
condition actions:

      Estimated Costs of On-Condition Inspections and Installations
------------------------------------------------------------------------
                                                              Cost per
                 Labor cost                    Parts cost      product
------------------------------------------------------------------------
4 work-hours x $85 per hour = $340..........           $0          $340
------------------------------------------------------------------------

    The FAA has received no definitive data that would enable the 
agency to provide cost estimates for the other on-condition actions 
specified in this proposed AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to take 
approximately 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, and completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Send comments regarding this burden estimate 
or any other aspect of this collection of information, including 
suggestions for reducing this burden, to: Information Collection 
Clearance Officer, Federal Aviation Administration, 10101 Hillwood 
Parkway, Fort Worth, TX 76177-1524.

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) 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.

[[Page 42757]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

Leonardo S.p.a.: Docket No. FAA-2021-0612; Project Identifier MCAI-
2021-00650-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by September 20, 2021.

(b) Affected ADs

    This AD replaces Emergency AD 2018-23-52, Product Identifier 
2018-SW-093-AD, dated November 8, 2018 (Emergency AD 2018-23-52).

(c) Applicability

    This AD applies to all Leonardo S.p.a. Model AW169 and AW189 
helicopters, certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code 6400, Tail Rotor 
System.

 (e) Unsafe Condition

    This AD was prompted by a report of an accident of a Model AW169 
helicopter, which was observed to have lost yaw control prior to the 
accident. The FAA is issuing this AD to address failure of the tail 
rotor servo-actuator (TRA) feedback lever. This condition could 
result in loss of tail rotor control and subsequent loss of control 
of the helicopter.

(f) Compliance

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

(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, European Union Aviation Safety Agency (EASA) AD 
2020-0197, dated September 10, 2020 (EASA AD 2020-0197).

(h) Exceptions to EASA AD 2020-0197

    (1) Where EASA AD 2020-0197 requires compliance in terms of 
flight hours, this AD requires using hours time-in-service.
    (2) This AD does not allow the compliance time tolerance 
specified in Note 1 of EASA AD 2020-0197.
    (3) The initial compliance time for the inspection specified in 
paragraph (1) of EASA AD 2020-0197 is within the compliance time 
specified in paragraph (1) of EASA AD 2020-0197, except for Group 1 
helicopters on which the inspection identified in paragraph (1) of 
EASA AD 2020-0197 has not been done, the initial inspection is 
within 10 hours time-in-service after the effective date of this AD.
    (4) The initial compliance time for the inspection specified in 
paragraph (2) of EASA AD 2020-0197 is within the compliance time 
specified in paragraph (2) of EASA AD 2020-0197, except for Group 1 
and 2 helicopters on which the inspection identified in paragraph 
(2) of EASA AD 2020-0197 has not been done, the initial compliance 
time is within 50 hours time-in-service after the effective date of 
this AD.
    (5) The initial compliance time for the installation specified 
in paragraph (3) of EASA AD 2020-0197 is within the compliance time 
specified in paragraph (3) of EASA AD 2020-0197, except for Group 1 
and 2 helicopters on which the installation identified in paragraph 
(3) of EASA AD 2020-0197 has not been done, the initial compliance 
time is within 20 hours time-in-service after the effective date of 
this AD.
    (6) The initial compliance time for the check (inspection) 
specified in paragraph (4) of EASA AD 2020-0197 is within the 
compliance time specified in paragraph (4) of EASA AD 2020-0197, 
except for Group 1 and 2 helicopters on which the check (inspection) 
identified in paragraph (4) of EASA AD 2020-0197 has not been done, 
the initial compliance time is within 10 hours time-in-service after 
the effective date of this AD.
    (7) The initial compliance time for the inspection/check 
specified in paragraph (5) of EASA AD 2020-0197 is within the 
compliance time specified in paragraph (5) of EASA AD 2020-0197 
except for Group 1 and 2 helicopters on which the inspection 
identified in paragraph (5) of EASA AD 2020-0197 has not been done, 
the initial compliance time is within 10 hours time-in-service after 
the effective date of this AD.
    (8) Where paragraphs (6), (8), (9), and (11) of EASA AD 2020-
0197 specify contacting Leonardo for corrective action instructions, 
the corrective action instructions must be accomplished in 
accordance with FAA-approved procedures.
    (9) Where paragraphs (9) and (10) of EASA AD 2020-0197 use the 
term ``discrepancy,'' for this AD, discrepancies include roughness 
(meaning lack of free and easy rotation), measured breakaway 
force(s) outside the allowed range specified in the service 
information identified in paragraphs (2) and (7) of EASA AD 2020-
0197, any wear or other damage (including, but not limited to, 
broken seals), and the presence of particles.
    (10) Where paragraph (12) of EASA AD 2020-0197 requires 
reporting results to the manufacturer ``as required by paragraphs 
(12.1) and (12.2) of this [EASA] AD'', for this AD, only report the 
inspection and check results specified in paragraph (12.1) of EASA 
AD 2020-0197. Submit the report at the applicable time in paragraph 
(h)(10)(i) or (ii) of this AD.
    (i) If the inspection or check was done on or after the 
effective date of this AD: Submit the report within 2 days after the 
inspection or check.
    (ii) If the inspection or check was done before the effective 
date of this AD: Submit the report within 2 days after the effective 
date of this AD.
    (11) Where paragraph (13) of EASA AD 2020-0197, and the service 
information specified in EASA AD 2020-0197, specify returning parts 
and grease containers to the manufacturer, this AD does not include 
those requirements.
    (12) Where EASA AD 2020-0197 requires compliance from March 20, 
2020 (the effective date of EASA AD 2020-0048, dated March 6, 2020), 
this AD requires using the effective date of this AD.
    (13) Where EASA AD 2020-0197 requires compliance from its 
effective date, this AD requires using the effective date of this 
AD.
    (14) This AD does not allow credit for the actions specified in 
EASA AD 2020-0197 if those actions were done using the service 
information specified in paragraphs (h)(14)(i) through (ix) of this 
AD:
    (i) Leonardo S.p.A. Emergency Alert Service Bulletin (EASB) 169-
148, dated May 29, 2019;
    (ii) Leonardo S.p.A. EASB 169-148, Revision A, dated September 
5, 2019;
    (iii) Leonardo S.p.A. EASB 169-148, Revision B, dated February 
4, 2020;
    (iv) Leonardo S.p.A. EASB 169-148, Revision C, dated April 6, 
2020;
    (v) Leonardo S.p.A. EASB 189-237, dated May 29, 2019;
    (vi) Leonardo S.p.A. EASB 189-237, Revision A, dated September 
5, 2019;
    (vii) Leonardo S.p.A. EASB 189-237, Revision B, dated February 
4, 2020;
    (viii) Leonardo S.p.A. EASB 189-237, Revision B, dated February 
4, 2020, with Errata Corrige;
    (ix) Leonardo S.p.A. EASB 189-237, Revision C, dated April 6, 
2020.
    (15) This AD does not require the ``Remarks'' section of EASA AD 
2020-0197.

(i) 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 (j)(2) of 
this AD. Information may be emailed to: [email protected].
    (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

    (1) For EASA AD 2020-0197, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email 
[email protected]; 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-2021-0612.
    (2) For more information about this AD, contact Andrea Jimenez, 
Aerospace Engineer, COS Program Management Section, Operational 
Safety Branch, Compliance & Airworthiness Division, FAA, 1600 
Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email [email protected].


[[Page 42758]]


    Issued on July 27, 2021.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-16468 Filed 8-4-21; 8:45 am]
BILLING CODE 4910-13-P