[Federal Register Volume 87, Number 135 (Friday, July 15, 2022)]
[Rules and Regulations]
[Pages 42308-42312]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-15131]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0384; Project Identifier AD-2022-00027-E; 
Amendment 39-22122; AD 2022-15-03]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2021-14-06 
for all Pratt & Whitney (PW) PW1519G, PW1521G, PW1521G-3, PW1521GA, 
PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, PW1922G, 
PW1923G, and PW1923G-A model turbofan engines. AD 2021-14-06 required 
repetitive borescope inspections (BSI) of certain low-pressure 
compressor (LPC) rotor 1 (R1) until replacement of electronic engine 
control (EEC) full authority digital electronic control (FADEC) 
software with updated software. AD 2021-14-06 also required a BSI after 
installation of the updated EEC FADEC software if certain Onboard 
Maintenance Message fault codes are displayed and meet specified 
criteria. AD 2021-14-06 also required, depending on the results of the 
BSI, replacement of the LPC R1. Since the FAA issued AD 2021-14-06, the 
manufacturer redesigned the compressor intermediate case (CIC) assembly 
to incorporate a shortened bleed duct configuration and updated the EEC 
FADEC software. This AD continues to require repetitive BSI of certain 
LPC R1s until replacement of EEC FADEC software with updated software 
and also a BSI after installation of the updated EEC FADEC software if 
certain Onboard Maintenance Message fault codes are displayed and meet 
specified criteria. This AD continues to require, depending on the 
results of the BSI, replacement of the LPC R1. This AD also requires 
removal and replacement of the existing CIC assembly with a CIC 
assembly eligible for installation. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective August 19, 2022.

ADDRESSES: For service information identified in this final rule, 
contact Pratt & Whitney, 400 Main Street, East Hartford, CT 06118; 
phone: (800) 565-0140; email: [email protected]; website: http://fleetcare.pw.utc.com. You may view this service information at the 
Airworthiness Products Section, FAA, 1200 District Avenue, Burlington, 
MA 01803. 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-2022-0384; 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

[[Page 42309]]

Docket Operations is 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: Mark Taylor, Aviation Safety Engineer, 
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 
(781) 238-7229; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2021-14-06, Amendment 39-21633 (86 FR 
36061, July 8, 2021), (AD 2021-14-06). AD 2021-14-06 applied to all PW 
PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-3, PW1525G, 
PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model 
turbofan engines. The NPRM published in the Federal Register on April 
04, 2022 (87 FR 19405). The NPRM was prompted by reports of inflight 
shutdowns due to failure of the LPC R1 and by subsequent findings of 
cracked LPC R1s during inspection. Additionally, the manufacturer 
redesigned the CIC assembly to incorporate a shortened bleed duct 
configuration. The shortened bleed duct addresses the unsafe condition 
by preventing the coincidence between bleed and the acoustic 
excitation. The manufacturer also updated the EEC FADEC software to 
provide compatibility with both current and future operation of engines 
and airplanes with the redesigned CIC assembly installed. In the NPRM, 
the FAA proposed to continue to require removal from service of certain 
EEC FADEC software and the installation of a software version eligible 
for installation. The NPRM proposed to require a BSI of LPC R1 for 
damage and cracks after replacing certain EEC FADEC software versions. 
The NPRM proposed to continue to require a BSI of LPC R1 after 
installation of an eligible EEC FADEC software version if certain 
Onboard Maintenance Message fault codes are displayed and meet 
specified criteria. The NPRM proposed to continue to require, depending 
on the results of the BSI, replacement of the LPC R1. The NPRM also 
proposed to require removal and replacement of certain CIC assemblies, 
identified by part number, with a CIC assembly eligible for 
installation.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from three commenters. The commenters 
were Air Line Pilots Association, International (ALPA), Delta Air 
Lines, Inc, (DAL), and an individual commenter. One commenter, ALPA, 
supported the proposal without change. Two commenters, DAL and an 
individual commenter, requested changes. The following presents the 
comments received on the NPRM and the FAA's response to each comment.

Request To Revise the Required Action Proposed in Paragraph (g)(3)

    DAL requested that the FAA remove the following language as 
proposed in paragraph (g)(3) of the NPRM: ``after installation of the 
EEC FADEC software version eligible for installation as required by 
paragraphs (g)(1) and (g)(2) of this AD.'' DAL noted that this 
requirement would create an unnecessary restriction on when the BSI of 
the LPC R1 can be accomplished and may cause operators to perform a 
second BSI if the BSI of the LPC R1 was performed prior to the software 
upgrade.
    The FAA agrees and has revised paragraph (g)(3) of this AD as 
requested by DAL.
    DAL also requested that the FAA revise paragraph (g)(3) of this AD 
by changing the language from ``For the model turbofan engines 
identified in paragraphs (g)(1) and (g)(2) . . .'' to ``For the model 
turbofan engines identified in paragraphs (g)(1) or (g)(2). . . .'' DAL 
noted that there is no overlap in turbofan engine models between 
paragraphs (g)(1) and (g)(2), thus it is not possible for an engine 
model to be identified in both paragraphs.
    The FAA disagrees with changing this AD as requested by DAL. 
Paragraph (g)(3) of this AD applies to the model turbofan engines 
identified in paragraph (g)(1) and the model turbofan engines 
identified in paragraph (g)(2). The FAA did not change the AD as a 
result of this comment.

Request To Include Future Revisions to Service Information

    DAL requested that the FAA add ``or later'' to Note 1 to paragraph 
(g)(4) to allow for the use of future revisions to PW Service Bulletins 
(SBs) PW1000G-A-72-00-0125-00A-930A-D, Issue No. 004, dated October 13, 
2021, and PW1000G-A-72-00-0075-00B-930A-D, Issue No. 004, dated July 
21, 2021. DAL noted that this would ensure that any LPC R1 serial 
numbers added in subsequent revisions to these SBs would be included in 
the applicability of this AD. DAL also requested that the FAA add ``or 
later'' to Note 2 to paragraph (g)(5) to allow for the use of future 
revisions to PW engine maintenance manual (EMM) PW1000G-A-72-00-00-02A-
0B5A-A. DAL noted that this would ensure that any changes made to the 
guidance on determining N1 exceedance duration would be applicable 
within the AD. DAL also requested that the FAA add ``or later'' to Note 
3 to paragraph (g)(5) to allow for the use of future revisions to PW 
EMM PW1000G-A-72-31-00-00A-312A-D, Issue No. 017, dated March 19, 2021. 
DAL noted that this would ensure that any changes made to the guidance 
on performing the BSI of the LPC R1 will be applicable within the AD. 
DAL also requested that the FAA add a reference to A220 aircraft 
maintenance publication (AMP) Task BD500-A-J72-00-00-02AAA-0B5A-A to 
help ensure consistency across different manuals used by on-wing 
maintenance personnel.
    The FAA disagrees with adding ``or later'' to the service 
information referenced in notes to paragraph (g) of this AD. The use of 
notes in the regulatory text is for informational purposes only, and 
the use of this service information is not required by this AD, but may 
assist the operator while complying with this AD. Therefore, including 
future revisions of the service information referenced in the notes 
would not affect the applicability of this AD. Additionally, future 
revisions of the service information have not yet been published by the 
manufacturer or reviewed by the FAA. The FAA disagrees with the need to 
add reference to future PW EMM revisions within Note 2 to paragraph 
(g)(5) of this AD, as the currently cited documents provide the 
appropriate guidance. The FAA did not change the AD as a result of 
these comments.

Request To Correct Reference to EEC FADEC Software Version

    DAL and an individual commenter requested that the FAA revise 
paragraph (h)(1) of this AD to change the EEC FADEC software version 
eligible for installation from version V2.11.12.4 to version 
V2.11.12.1. Both commenters noted that PW SB PW1000G-A-73-00-0052-00A-
930A-D, Issue No. 001, dated October 7, 2021, defines EEC FADEC 
software version V2.11.12.1 as the software version that is eligible 
for installation on PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G-3, 
PW1525G, and PW1525G-3 model turbofan engines.

[[Page 42310]]

    The FAA agrees and has updated paragraph (h)(1) of this AD.

Conclusion

    The FAA reviewed the relevant data, considered any comments 
received, and determined that air safety requires adopting the AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these products. Except for minor editorial changes, and 
any other changes described previously, this AD is adopted as proposed 
in the NPRM. None of the changes will increase the economic burden on 
any operator.

Related Service Information

    The FAA reviewed PW SB PW1000G-A-73-00-0025-00B-930A-D, Issue No. 
001, dated November 23, 2021; PW SB PW1000G-A-72-00-0125-00A-930A-D, 
Issue No. 004, dated October 13, 2021; PW SB PW1000G-A-72-00-0075-00B-
930A-D, Issue No. 004, dated July 21, 2021; PW SB PW1000G-A-73-00-0052-
00A-930A-D, Issue No. 001, dated October 7, 2021; PW SB PW1000G-A-72-
00-0121-00B-930A-D, Issue No. 001, dated July 9, 2021; PW SB PW1000G-A-
72-00-0175-00A-930A-D, Issue No. 001, dated July 1, 2021.
    PW SB PW1000G-A-73-00-0025-00B-930A-D, Issue No. 001, dated 
November 23, 2021, describes procedures for replacing or modifying the 
EEC to incorporate EEC FADEC software version V9.6.5.6 in PW1919G, 
PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines. PW SBs 
PW1000G-A-72-00-0125-00A-930A-D, Issue No. 004, dated October 13, 2021, 
and PW1000G-A-72-00-0075-00B-930A-D, Issue No. 004, dated July 21, 
2021, describe procedures for performing repetitive BSIs of LPC R1s. PW 
SB PW1000G-A-73-00-0052-00A-930A-D, Issue No. 001, dated October 7, 
2021, describes procedures for replacing or modifying the EEC to 
incorporate EEC FADEC software version V2.11.12 in PW1519G, PW1521G, 
PW1521G-3, PW1521GA, PW1524G, PW1524G-3, PW1525G, PW1525G-3 model 
turbofan engines. PW SBs PW1000G-A-72-00-0121-00B-930A-D, Issue No. 
001, dated July 9, 2021, and PW1000G-A-72-00-0175-00A-930A-D, Issue No. 
001, dated July 1, 2021, describe procedures for replacing or modifying 
the CIC assembly.
    The FAA also reviewed Section PW1000G-A-72-00-00-02A-0B5A-A of PW 
EMM, Issue No. 016, dated January 15, 2021; and Section PW1000G-A-72-
31-00-00A-312A-D of PW EMM, Issue No. 017, dated March 19, 2021. 
Section PW1000G-A-72-00-00-02A-0B5A-A of PW EMM, Issue No. 016, dated 
January 15, 2021, describes procedures for inspecting the engine for 
possible engine damage after receiving notification of an N1 or N2 
overspeed operation. Section PW1000G-A-72-31-00-00A-312A-D of PW EMM, 
Issue No. 017, dated March 19, 2021, describes procedures for 
performing a BSI of the LPC.

Costs of Compliance

    The FAA estimates that this AD affects 114 engines installed on 
airplanes of U.S. registry. The FAA estimates that five percent of 
engines installed on airplanes of U.S. registry will require EEC FADEC 
software upgrade and BSI of the LPC R1.
    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
----------------------------------------------------------------------------------------------------------------
Replace EEC FADEC software............  2 work-hours x $85 per                $0            $170         $19,380
                                         hour = $170.
BSI of the LPC R1.....................  2 work-hours x $85 per                 0             170             969
                                         hour = $170.
Replace CIC assembly..................  428 work-hours x $85 per         124,522         160,902      18,342,828
                                         hour = $36,380.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
inspection if certain Onboard Maintenance Message fault codes are 
displayed or if any necessary replacement is required based on the 
results of the inspection. The agency has no way of determining the 
number of aircraft that might need these replacements or inspections:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost           Cost per  product
----------------------------------------------------------------------------------------------------------------
Replace LPC R1.......................  40 work-hours x $85 per  $156,000...............  $159,400
                                        hour = $3,400.
BSI of the LPC R1 if Onboard           2 work-hours x $85 per   $0.....................  $170
 Maintenance Message fault codes are    hour = $170.
 displayed and meet specified
 criteria.
----------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected individuals.

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.

[[Page 42311]]

Regulatory Findings

    The FAA has determined that 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:
0
a. Removing Airworthiness Directive 2021-14-06, Amendment 39-21633 (86 
FR 36061, July 8, 2021); and
0
b. Adding the following new airworthiness directive:

2022[dash]15-03 Pratt & Whitney: Amendment 39-22122; Docket No. FAA-
2022-0384; Project Identifier AD-2022-00027-E.

(a) Effective Date

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

(b) Affected ADs

    This AD replaces AD 2021-14-06, Amendment 39-21633 (86 FR 36061, 
July 8, 2021).

(c) Applicability

    This AD applies to Pratt & Whitney PW1519G, PW1521G, PW1521G-3, 
PW1521GA, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, 
PW1922G, PW1923G, and PW1923G-A model turbofan engines.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of in-flight shutdowns due to 
failure of the low-pressure compressor (LPC) rotor 1 (R1) and by 
subsequent findings of cracked LPC R1s during inspection. The FAA is 
issuing this AD to prevent failure of the LPC R1. The unsafe 
condition, if not addressed, could result in an uncontained release 
of the LPC R1, damage to the engine, damage to the airplane, and 
loss of the airplane.

(f) Compliance

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

(g) Required Actions

    (1) For PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-
3, PW1525G, and PW1525G-3 model turbofan engines with installed 
electronic engine control (EEC) full authority digital electronic 
control (FADEC) software earlier than EEC FADEC software version 
V2.11.10.4, before further flight, remove the EEC FADEC software and 
install EEC FADEC software version eligible for installation.
    (2) For PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model 
turbofan engines with installed EEC FADEC software earlier than EEC 
FADEC software version V9.5.6.7, before further flight, remove the 
EEC FADEC software and install EEC FADEC software version eligible 
for installation.
    (3) For the model turbofan engines identified in paragraphs 
(g)(1) and (g)(2) of this AD, before further flight, perform a one-
time borescope inspection (BSI) of the LPC R1 for damage and cracks 
at the following LPC R1 locations:
    (i) The blade tip;
    (ii) The leading edge;
    (iii) The leading edge fillet to rotor platform radius; and
    (iv) The airfoil convex side root fillet to rotor platform 
radius.
    (4) Based on the results of the BSI required by paragraph (g)(3) 
of this AD, before further flight, remove and replace the LPC R1 if:
    (i) There is damage on an LPC R1 that exceeds serviceable 
limits; or
    (ii) Any crack in the LPC R1 exists.
    Note 1 to paragraph (g)(4): Guidance on determining the 
serviceable limits in paragraphs (g)(4) and (6) of this AD can be 
found in Pratt & Whitney (PW) Service Bulletin (SB) PW1000G-A-72-00-
0125-00A-930A-D, Issue No. 004, dated October 13, 2021, and PW SB 
PW1000G-A-72-00-0075-00B-930A-D, Issue No. 004, dated July 21, 2021.
    (5) For PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-
3, PW1525G, and PW1525G-3 model turbofan engines with EEC FADEC 
software version V2.11.10.4 or later installed, within 15 flight 
cycles after receipt of Onboard Maintenance Message fault code 
7100F0029 or 7100F0030, perform a BSI of the LPC R1 for damage and 
cracks at the locations specified in paragraph (g)(3) of this AD if 
the fault code is displayed on the Active Failure Messages and meets 
the following criteria:
    (i) N1 Exceedance is above 95.2%;
    (ii) N1 Exceedance occurred above 29,100 feet;
    (iii) N1 Exceedance occurs for a duration of 40 seconds (15 
seconds of cockpit display) or more during any flight; and
    (iv) Compressor intermediate case (CIC) assembly installed has 
part number (P/N) 5379926, P/N 5379940, P/N 5379946, or P/N 5379926-
001.
    Note 2 to paragraph (g)(5): Guidance on determining the N1 
Exceedance duration can be found in Section PW1000G-A-72-00-00-02A-
0B5A-A of PW engine maintenance manual (EMM), Issue No. 016, dated 
January 15, 2021.
    Note 3 to paragraph (g)(5): Guidance on performing the BSI can 
be found in Section PW1000G-A-72-31-00-00A-312A-D of PW EMM, Issue 
No. 017, dated March 19, 2021.
    (6) Based on the results of the BSI required by paragraph (g)(5) 
of this AD, before further flight, remove and replace the LPC R1 if:
    (i) There is damage on an LPC R1 that exceeds serviceable 
limits; or
    (ii) Any crack in the LPC R1 exists.
    (7) For all affected model turbofan engines, at the next engine 
shop visit after the effective date of this AD, remove CIC assembly 
with P/N 5379926, P/N 5379940, P/N 5379946, or P/N 5379926-001 and 
replace with a CIC assembly eligible for installation.
    (8) For PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-
3, PW1525G, and PW1525G-3 model turbofan engines with installed EEC 
FADEC software version V2.11.10.4, at the next engine shop visit 
after the effective date of this AD, remove the EEC FADEC software 
and install EEC FADEC software version eligible for installation.
    (9) For PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model 
turbofan engines with installed EEC FADEC software version V9.5.6.7, 
at the next engine shop visit after the effective date of this AD, 
remove the EEC FADEC software and install EEC FADEC software version 
eligible for installation.

(h) Definitions

    (1) For the purpose of this AD, ``EEC FADEC software version 
eligible for installation'' is EEC FADEC software version V2.11.12.1 
or later for PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, 
PW1524G-3, PW1525G, and PW1525G-3 model turbofan engines, and EEC 
FADEC software version V9.6.5.6 or later for PW1919G, PW1921G, 
PW1922G, PW1923G, and PW1923G-A model turbofan engines.
    (2) For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of the LPC Flange 1 or separation of the LPC Flange 4, 
except for the following situations, which do not constitute an 
engine shop visit.
    (i) Separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance.
    (ii) Separation of engine flanges solely for the purpose of 
replacing the fan without subsequent maintenance.
    (3) For the purpose of this AD, a ``CIC assembly eligible for 
installation'' is any CIC assembly that does not have P/N 5379926, 
P/N 5379940, P/N 5379946, or P/N 5379926-001.

[[Page 42312]]

(i) 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 (j)(1) of this AD and email 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 more information about this AD, contact Mark Taylor, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7229; email: 
[email protected].
    (2) For service information identified in this AD, contact Pratt 
& Whitney, 400 Main Street, East Hartford, CT 06118; phone: (800) 
565-0140; email: [email protected]; website: http://fleetcare.pw.utc.com.
    (3) You may view this referenced 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.

(k) Material Incorporated by Reference

    None.

    Issued on July 7, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-15131 Filed 7-14-22; 8:45 am]
BILLING CODE 4910-13-P