[Federal Register Volume 87, Number 72 (Thursday, April 14, 2022)]
[Rules and Regulations]
[Pages 22122-22126]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-08037]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0400; Project Identifier AD-2022-00179-E; 
Amendment 39-22009; AD 2022-08-06]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain General Electric Company (GE) CF34-8C and CF34-8E model 
turbofan engines. This AD was prompted by an ``Engine Degraded'' 
message received in-flight from the Engine Indicating and Crew Alerting 
System (EICAS), and a subsequent investigation by the manufacturer that 
revealed corrosion of the variable geometry (VG) system actuator, which 
can cause the full authority digital engine control (FADEC) software to 
command and lock the engine at idle until it is restarted. This AD 
requires performing a rotational torque check on the actuating linkage 
assembly and, depending on the results of the rotational torque check, 
replacement of the compressor inlet guide vane (IGV) outer shroud 
bushing and vane spindle bushing with parts eligible for installation. 
This AD also requires reporting the results of the rotational torque 
check to GE. The FAA is issuing this AD to address the unsafe condition 
on these products.

DATES:  AD is effective April 29, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 29, 
2022.
    The FAA must receive comments on this AD by May 31, 2022.

[[Page 22123]]


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 final rule, contact 
General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; phone: 
(513) 552-3272; email: [email protected]; website: https://www.ge.com. You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call (817) 222-5110. It is 
also available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2022-0400.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-0400; 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 street address for the 
Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Scott Stevenson, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: (781) 238-7132; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    On August 11, 2021, a Bombardier CRJ1000 airplane, powered by GE 
CF34-8C5 model turbofan engines, experienced an in-flight engine 
shutdown that resulted in a diversion. The manufacturer's investigation 
found that this airplane was parked outdoors for extended lengths of 
time within 10 miles (16 km) from a saltwater coastline, causing 
corrosion to develop on the CF34-8C5 engines' compressor VG actuator 
rod, seizure of the rod end bearing, and fracture of the rod end. Based 
on the manufacturer's investigation, on November 4, 2021, the FAA 
issued Emergency AD 2021-23-51 (followed by publication in the Federal 
Register on December 14, 2021, as a Final Rule, Request for Comments 
(86 FR 70969)), which requires performing an inspection of the master 
compressor VG actuator and slave compressor VG actuator on certain GE 
CF34-8C and CF34-8E model turbofan engines and, depending on the 
results of the inspection, replacement of the part with a part eligible 
for installation.
    Since the FAA issued AD 2021-23-51, the manufacturer determined 
that two additional in-flight events occurred that were related to this 
unsafe condition. On September 7, 2021 and October 26, 2021, two 
Bombardier CRJ-900 airplanes powered by GE CF34-8C5 model turbofan 
engines received ``Engine Degraded'' messages from the EICAS during 
flight. A subsequent investigation by the manufacturer found that these 
engines were operated infrequently over the past 2 years, with one 
engine showing corrosion findings after being stored approximately 45 
miles (72 km) from a saltwater coastline, and another engine showing 
corrosion findings after being installed on an airplane parked for over 
250 days. The manufacturer's investigation concluded that engines 
stored outdoors for 250 or more days are at risk of the excessive 
corrosion build up, with the risk increasing if the engines were stored 
outdoors in close proximity to a saltwater coastline. These conditions 
caused corrosion to develop between the high-pressure compressor case 
and vane bushings, increasing the VG actuation loads and slowing the VG 
response. As a result, the VG command and actual positions exceeded 
acceptable disagreement parameters, triggering an EICAS ``Engine 
Degraded'' message. In response to the ``Engine Degraded'' message, all 
versions of the full authority digital engine control (FADEC) software 
on GE CF34-8E engines, and FADEC software earlier than Version 6.60 on 
GE CF34-8C engines automatically reduces the engine to idle and locks 
the throttle until the engine is shut down and restarted. This 
condition, if not addressed, could result in failure of one or more 
engines, loss of engine thrust control, and reduced control of the 
airplane. The FAA is issuing this AD to address the unsafe condition on 
these products.

FAA's Determination

    The FAA is issuing this AD because the agency has determined the 
unsafe condition described previously is likely to exist or develop in 
other products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed GE CF34-8C Service Bulletin (SB) 72-0356 R00 and 
GE CF34-8E SB 72-0244 R00, both dated February 15, 2022. These SBs 
specify procedures for performing a one-time rotational torque check of 
the actuating linkage assembly, differentiated by engine model, to 
identify possible interface corrosion or seizure on the compressor 
case, compressor IGV outer shroud bushing, vane spindle bushing, 
compressor stator IGV variable vane, compressor stator stage 1 variable 
vane, compressor stator stage 2 variable vane, compressor stator stage 
3 variable vane, and compressor stator stage 4 variable vane. These SBs 
also specify instructions for operators to report the rotational torque 
check results to GE. This service information is reasonably available 
because the interested parties have access to it through their normal 
course of business or by the means identified in ADDRESSES.

AD Requirements

    This AD requires performing a rotational torque check on the 
actuating linkage assembly and, depending on the results of the 
rotational torque check, replacement of the compressor IGV outer shroud 
bushing and vane spindle bushing with parts eligible for installation. 
This AD also requires reporting the results of the rotational torque 
check to GE.

Interim Action

    The FAA considers this AD to be an interim action. The inspection 
reports that are required by this AD will enable the manufacturer to 
obtain better insight into the nature, cause, and extent of the 
corrosion, and eventually to develop final action to address the unsafe 
condition. Once final action has been identified, the FAA might 
consider further rulemaking.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance.

[[Page 22124]]

Further, section 553(d) of the APA authorizes agencies to make rules 
effective in less than thirty days, upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies foregoing notice and comment prior to adoption of this rule. 
The FAA considers corrosion of the VG system actuator to be an urgent 
safety issue. Performance of a rotational torque check of the actuating 
linkage assembly will detect excessive corrosion build up on the VG 
system actuator. This rotational torque check is necessary to prevent 
failure of one or more engines, loss of engine thrust control, and 
reduced control of the airplane. Engines installed on airplanes parked 
outdoors for 250 or more days are at risk of excessive corrosion build 
up. The risk of the excessive corrosion build up increases if the 
engines are stored outdoors in close proximity to a saltwater 
coastline. For affected engines installed on airplanes that were parked 
outdoors within 10 miles of a saltwater coastline, a rotational torque 
check on the actuating linkage assembly must be accomplished within 30 
flight hours or 5 calendar days after the effective date of this AD. 
For affected engines installed on airplanes that were parked outdoors 
within 50 miles of a saltwater coastline, a rotational torque check of 
the actuating linkage assembly must be accomplished within 200 FHs or 
35 calendar days after the effective date of this AD. Additionally, for 
all other affected engines installed on airplanes that were parked 
outdoors, the rotational torque check on the actuating linkage assembly 
must be accomplished before exceeding 880 FHs. According to fleet data, 
880 FHs is approximately 100 calendar days. For affected engines with 
an actuating linkage assembly that does not pass the rotational torque 
check, this AD requires replacement of the compressor IGV outer shroud 
bushing and vane spindle bushing before further flight. Accordingly, 
notice and opportunity for prior public comment are impracticable and 
contrary to the public interest pursuant to 5 U.S.C. 553(b)(3)(B).
    In addition, the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days, 
for the same reasons the FAA found good cause to forego notice and 
comment.

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2022-0400 and Project Identifier 
AD-2022-00179-E'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the final rule, 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 final rule 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 final rule.

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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to Scott 
Stevenson, Aviation Safety Engineer, ECO Branch, FAA, 1200 District 
Avenue, Burlington, MA 01803. Any commentary that the FAA receives 
which is not specifically designated as CBI will be placed in the 
public docket for this rulemaking.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 617 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Rotation torque check of actuating      2 work-hours x $85 per                $0            $170        $104,890
 linkage assembly.                       hour = $170.
Report results of rotational torque     1 work-hour x $85 per                  0              85          52,445
 check.                                  hour = $85.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacement that would be required based on the results of the 
rotational torque check. The agency has no way of determining the 
number of aircraft that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace compressor IGV outer shroud bushing     2 work-hours x $85 per hour =            $25,622         $25,792
 and vane spindle bushing.                       $170.
----------------------------------------------------------------------------------------------------------------


[[Page 22125]]

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 currently 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 be 
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

    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, and
    (2) Will not affect intrastate aviation in Alaska.

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:

2022-08-06 General Electric Company: Amendment 39-22009; Docket No. 
FAA-2022-0400; Project Identifier AD-2022-00179-E.

(a) Effective Date

    This airworthiness directive (AD) is effective April 29, 2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) CF34-8C1, CF34-
8C5, CF34-8C5A1, CF34-8C5A2, CF34-8C5A3, CF34-8C5B1, CF34-8E2, CF34-
8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1 
model turbofan engines installed on an airplane that has accumulated 
250 or more parked days outdoors within the 24 months prior to the 
effective date of this AD.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7230, Turbine Engine 
Compression Section.

(e) Unsafe Condition

    This AD was prompted by an ``Engine Degraded'' message received 
in-flight from the Engine Indicating and Crew Alerting System 
(EICAS), and a subsequent investigation by the manufacturer that 
revealed corrosion of the variable geometry (VG) system actuator. 
The FAA is issuing this AD to detect corrosion of the VG system 
actuator. The unsafe condition, if not addressed, could result in 
failure of one or more engines, loss of engine thrust control, and 
reduced control of the airplane.

(f) Compliance

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

(g) Required Actions

(1) Torque Check: CF34-8C Model Turbofan Engines With Full 
Authority Digital Engine Control (FADEC) Software (SW) Below 
Version 6.60, and All Affected CF34-8E Model Turbofan Engines

    (i) If the affected engine is installed on an airplane that was 
parked less than or equal to 10 miles from a saltwater coastline for 
250 or more parked days, within 30 flight hours (FHs) or 5 calendar 
days, whichever occurs first after the effective date of this AD, 
perform a rotational torque check of the actuating linkage assembly. 
If an airplane has two affected engines installed while parked less 
than or equal to 10 miles from a saltwater coastline for 250 or more 
parked days, operators may perform the rotational torque check of 
the actuating linkage assembly on the second engine before the 
second engine exceeds 440 FHs after the effective date of this AD.
    (ii) For affected engines not requiring the performance of a 
rotational torque check by paragraph (g)(1)(i) of this AD, if the 
affected engine is installed on an airplane that was parked less 
than or equal to 50 miles from a saltwater coastline for 250 or more 
parked days, within 200 FHs or 35 calendar days, whichever occurs 
first after the effective date of this AD, perform a rotational 
torque check of the actuating linkage assembly. If an airplane has 
two affected engines installed while parked less than or equal to 50 
miles from a saltwater coastline for 250 or more parked days, 
operators may perform the rotational torque check of the actuating 
linkage assembly on the second engine before the second engine 
exceeds 880 FHs after the effective date of this AD.
    (iii) For affected engines not requiring the performance of a 
rotational torque check by paragraphs (g)(1)(i) or (g)(1)(ii) of 
this AD, before exceeding 880 FHs after the effective date of this 
AD, perform a rotational torque check of the actuating linkage 
assembly. If an airplane has two affected engines installed, 
operators may perform the rotational torque check of the actuating 
linkage assembly on the second engine before the second engine 
exceeds 1,680 FHs after the effective date of this AD.

(2) Torque Check: CF34-8C Model Turbofan Engines With FADEC SW 
Version 6.60 or Above Installed on an Airplane That Is in Service 
as of the Effective Date of This AD

    (i) If the affected engine is installed on an airplane that was 
parked less than or equal to 10 miles from a saltwater coastline for 
250 or more parked days, within 200 FHs or 35 calendar days, 
whichever occurs first after the effective date of this AD, perform 
a rotational torque check of the actuating linkage assembly. If an 
airplane has two affected engines installed while parked less than 
or equal to 10 miles from a saltwater coastline for 250 or more 
parked days, operators may perform the rotational torque check of 
the actuating linkage assembly on the second engine before the 
second engine

[[Page 22126]]

exceeds 880 FHs after the effective date of this AD.
    (ii) For affected engines not requiring the performance of a 
rotational torque check by paragraph (g)(2)(i) of this AD, if the 
affected engine is installed on an airplane that was parked less 
than or equal to 50 miles from a saltwater coastline for 250 or more 
parked days, before exceeding 440 FHs after the effective date of 
this AD, perform a rotational torque check of the actuating linkage 
assembly. If an airplane has two affected engines installed while 
parked less than or equal to 50 miles from a saltwater coastline for 
250 or more parked days, operators may perform the rotational torque 
check of the actuating linkage assembly on the second engine before 
the second engine exceeds 880 FHs after the effective date of this 
AD.
    (iii) For affected engines not requiring the performance of a 
rotational torque check by paragraphs (g)(2)(i) or (g)(2)(ii) of 
this AD, before exceeding 880 FHs after the effective date of this 
AD, perform a rotational torque check of the actuating linkage 
assembly. If an airplane has two affected engines installed, 
operators may perform the rotational torque check of the actuating 
linkage assembly on the second engine before the second engine 
exceeds 1,680 FHs after the effective date of this AD.

(3) Torque Check: All Affected Engines That Are Not currently in 
Service

    If the affected engine is installed on an airplane that was 
parked outdoors for 250 or more parked days within the 24 months 
prior to re-entering service, or if the engine was off-wing and 
stored outdoors for 250 or more days within the 24 months prior to 
reentering service, before further flight, perform a rotational 
torque check of the actuating linkage assembly.

(4) Replacement of the Compressor Inlet Guide Vane (IGV) Outer 
Shroud Bushing and Vane Spindle Bushing

    If the actuating linkage assembly does not pass any rotational 
torque check required by paragraphs (g)(1) through (3) of this AD, 
before further flight, remove the compressor IGV outer shroud 
bushing and vane spindle bushing and replace with a zero cycles 
since new compressor IGV outer shroud bushing and vane spindle 
bushing.

(5) Service Information for Performance of the Rotational Torque 
Check and Replacement of the Compressor IGV Outer Shroud Bushing 
and Vane Spindle Bushing

    Use the Accomplishment Instructions, paragraph 3.A.(1)(c), of GE 
CF34-8C Service Bulletin (SB) 72-0356 R00 or GE CF34-8E SB 72-0244 
R00, both dated February 15, 2022, as applicable to the engine 
model, to perform the actions required by paragraphs (g)(1) through 
(4) of this AD.

(h) Reporting Requirements

    Within 10 days after performing the rotational torque check 
required by paragraphs (g)(1) through (3) of this AD, in accordance 
with paragraph 3.A.(1)(c), of GE CF34-8C SB 72-0356 or GE CF34-8E SB 
72-0244, send your inspection report form, pictures, or report 
findings to GE at [email protected].

(i) Definition

    (1) For the purpose of this AD, a ``parked day'' is 24 
consecutive hours without engine operation.
    (2) For the purpose of this AD, ``outdoors'' is any location 
that is not environmentally controlled, including any non-
environmentally controlled facility.

(j) Special Flight Permit

    Special flight permits are prohibited.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO 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 (l) of this AD and email it 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.

(l) Related Information

    For more information about this AD, contact Scott Stevenson, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7132; email: 
[email protected].

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) GE CF34-8C Service Bulletin (SB) 72-0356 R00, dated February 
15, 2022.
    (ii) GE CF34-8E SB 72-0244 R00, dated February 15, 2022.
    (3) For GE service information identified in this AD, contact 
General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; 
phone: (513) 552-3272; email: [email protected]; website: 
https://www.ge.com.
    (4) You may view this service information at FAA, Airworthiness 
Products Section, Operational Safety Branch, 1200 District Avenue, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on April 4, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2022-08037 Filed 4-11-22; 4:15 pm]
BILLING CODE 4910-13-P