Federal Register / Vol. 87, No. 98 / Friday, May 20, 2022 / Rules and Regulations 30797 

(C) Within 50 FCs after the inspections 

required by paragraphs (g)(2)(i) and (ii) of 

this AD, replace any link rod hardware found 

to be outside the inspection criteria. Until the 

worn link rod hardware is replaced, the OBV 

fuel fittings must be inspected before the first 

flight of each day for leakage and looseness 

in accordance with the inspection criteria. If 

the OBV fuel fittings fail to meet the 

inspection criteria, before further flight, 

replace the OBV and worn link rod hardware. 

(3) For all affected engines with an 

installed OBV, VIN 5000728–104 part 

number (P/N) (P/N 4123T71P02), VIN 

5000728–106 (P/N 4123T71P03), or VIN 

5080046–101 (P/N 4123T71P04), having an 

OBV S/N listed in Appendix A, paragraph 4., 

of GE CF34–8C SB 75–0025 R01, dated 

August 1, 2019 (GE SB 75–0025), or 

Appendix A, paragraph 4., of GE CF34–8E SB 

75–0019 R01, dated August 1, 2019 (GE SB 

75–0019), respectively, within 180 days after 

the effective date of this AD, remove the OBV 

and replace with a part eligible for 

installation. 

(4) For all affected engines with an 

installed OBV, VIN 5000728–104 (P/N 

4123T71P02), VIN 5000728–106 (P/N 

4123T71P03), or VIN 5080046–101 (P/N 

4123T71P04), having an OBV S/N not listed 

in Appendix A, paragraph 4., of GE SB 75– 

0025 or Appendix A, paragraph 4., of GE SB 

75–0019, respectively, remove the OBV and 

replace with a part eligible for installation 

within the following compliance times: 

(i) For an OBV that has accumulated more 

than 25,000 FHs since new as of the effective 

date of this AD, remove and replace the OBV 

within 16 months of the effective date of this 

AD. 

(ii) For an OBV that has accumulated 

between 12,500 to 25,000 FHs since new, 

inclusive, as of the effective date of this AD, 

remove and replace the OBV within 32 

months of the effective date of this AD. 

(iii) For an OBV with fewer than 12,500 

FHs since new as of the effective date of this 

AD, remove and replace the OBV within 48 

months of the effective date of this AD. 

(5) For all affected engines with an 

installed OBV, VIN 5080046–102 (P/N 

4123T71P05), before the OBV accumulates 

25,000 FHs since new or within 10 years of 

the effective date of this AD, whichever 

occurs first, remove the OBV and replace 

with a part eligible for installation. 

(6) For all affected engines with an 

installed OBV, if the accumulated FHs since 

new of the OBV is unknown, use the FHs 

since new of the engine. 

(7) If the OBV was upgraded or the OBV 

cap was replaced using the service 

information identified in paragraph 1., 

Planning Information, paragraph C., 

Compliance, of GE CF34–8E SB 75–0021 R00, 

dated February 21, 2020, the accumulated 

FHs since the OBV was upgraded or 

accumulated FHs since the OBV cap was 

replaced, as applicable, may be used instead 

of accumulated FHs since new of the OBV. 

(h) Terminating Action 

Installation of an OBV that meets the 

definition of a part eligible for installation in 

paragraph (i) of this AD constitutes 

terminating action for the inspections 

required by paragraphs (g)(1) and (2) of this 

AD. 

(i) Definition 

For the purpose of this AD, a ‘‘part eligible 

for installation’’ is an OBV VIN 5080046–103 

(P/N 4123T71P06) or an OBV reworked to 

VIN 5080046–103 (P/N 4123T71P06). 

(j) No Reporting Requirement 

The reporting instructions specified in GE 

SB 75–0020 are not required by this AD. 

(k) Credit for Previous Actions 

You may take credit for the initial 

inspection required by paragraph (g)(1)(i) or 

(2)(i) of this AD if you performed this initial 

inspection before the effective of this AD 

using GE CF34–8C SB 75–0019 R01, dated 

October 24, 2017, or R00, dated August 4, 

2017; or GE CF34–8C–AL S/B 75–0020, 

Revision 03, dated December 14, 2018, as 

applicable. 

(l) 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 ECO Branch, send it to 

the attention of the person identified in 

paragraph (m) of this AD and email to: ANEAD-AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(m) 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; fax: (781) 238–7199; email: 

Scott.M.Stevenson@faa.gov. 

(n) 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. 

(3) The following service information was 

approved for IBR on June 24, 2022. 

(i) GE CF34–8C Service Bulletin (SB) 75– 

0025 R01, dated August 1, 2019. 

(ii) GE CF34–8E SB 75–0019 R01, dated 

August 1, 2019. 

(4) The following service information was 

approved for IBR on December 23, 2019 (84 

FR 63569, November 18, 2019). 

(i) GE CF34–8C SB 75–0020 R04, dated 

May 10, 2019. 

(ii) [Reserved] 

(5) For service information identified in 

this AD, contact General Electric Company, 

1 Neumann Way, Cincinnati, OH 45215; 

phone: (513) 552–3272; email: 

aviation.fleetsupport@ge.com; website: 

https://www.ge.com. 

(6) 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. 

(7) 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: fr.inspection@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on May 16, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–10782 Filed 5–19–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0092; Project 

Identifier MCAI–2020–01428–A; Amendment 

39–22039; AD 2022–10–01] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Pilatus Aircraft Ltd. (Pilatus) Model PC– 

12/47E airplanes. This AD was 

prompted by mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI identifies the unsafe 

condition as a batch of incorrectly sized 

fuel transfer ejector nozzles that were 

installed on Model PC–12/47E airplanes 

during production. This AD requires 

removing the affected fuel transfer 

ejectors from service and prohibits 

installation of the affected fuel transfer 

ejectors. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective June 24, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 24, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

Pilatus Aircraft Ltd., Customer Support 


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30798 Federal Register / Vol. 87, No. 98 / Friday, May 20, 2022 / Rules and Regulations 

General Aviation, CH–6371 Stans, 

Switzerland; phone: +41 848 24 7 365; 

email: techsupport.ch@pilatusaircraft.com; website: https://

www.pilatus-aircraft.com. You may 

view this service information at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. 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–2022–0092. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0092; 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, the MCAI, any comments 

received, and other information. The 

address for 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: 

Doug Rudolph, Aviation Safety 

Engineer, General Aviation & Rotorcraft 

Section, International Validation 

Branch, FAA, 901 Locust, Room 301, 

Kansas City, MO 64106; phone: (816) 

329–4059; email: doug.rudolph@

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 serial-numbered Pilatus 

Model PC–12/47E airplanes. The NPRM 

published in the Federal Register on 

February 10, 2022 (87 FR 7774). The 

NPRM was prompted by MCAI from the 

European Union Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union. EASA issued AD 2020–0229, 

dated October 20, 2020 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition on Pilatus Model PC–12/47E 

airplanes with serial number 2001 and 

larger. The MCAI states: 

An occurrence was reported where, on the 

production line, a batch of fuel transfer 

ejectors with an incorrect (too small) nozzle 

diameter were installed on some PC–12/47E 

aeroplanes. Such fuel transfer ejectors are not 

in compliance with the latest approved 

design data. 

This condition, if not corrected, could 

result in a restriction of the motive fuel flow 

due to ice accumulation, possibly resulting in 

a reduction of safety margins in the fuel 

system. 

To address this potential unsafe condition, 

Pilatus issued the SB [Service Bulletin] to 

provide replacement instructions. 

For the reason described above, this 

[EASA] AD requires replacement of the 

affected parts with serviceable parts, as 

defined in the [EASA] AD. This [EASA] AD 

also prohibits (re-)installation of affected 

parts. 

You may examine the MCAI in the 

AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0092. 

In the NPRM, the FAA proposed to 

require removing the affected fuel 

transfer ejectors from service and 

proposed to prohibit installation of an 

affected fuel transfer ejector. 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 

Pilatus and the Airline Pilots 

Association, International (ALPA). The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

ALPA supported the NPRM without 

change. 

Pilatus requested the FAA clarify the 

unsafe condition statement in paragraph 

(e) of the proposed AD. Pilatus 

disagreed with the conclusion that 

reduction in safety margins in the fuel 

system could result in loss of control of 

the airplane. Pilatus explained that a 

reduction in safety margins would not 

lead to loss of control of the airplane; in 

the event the engine is starved of fuel, 

it will shut down but not necessarily 

lead to a loss of control because the 

airplane could glide controllably for a 

period of time. 

The FAA agrees and has revised 

paragraph (e) of this AD to state that the 

unsafe condition could lead to ‘‘loss of 

engine power or engine shutdown.’’ 

Conclusion 

This model has been approved by the 

aviation authority of another country 

and is approved for operation in the 

United States. Pursuant to the FAA’s 

bilateral agreement with this State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI referenced above. The FAA 

reviewed the relevant data, considered 

the comments received, and determined 

that, except for the changes described 

previously, air safety requires adopting 

this AD as proposed. Accordingly, the 

FAA is issuing this AD to address the 

unsafe condition on this product. 

Except for any 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 Under 1 

CFR Part 51 

The FAA reviewed Pilatus PC–12 

Service Bulletin No. 28–014, dated 

August 12, 2020. This service 

information contains the serial numbers 

of the affected fuel transfer ejectors and 

specifies procedures for replacing the 

affected fuel transfer ejectors. 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 the ADDRESSES section. 

Costs of Compliance 

The FAA estimates that this AD 

affects 10 airplanes of U.S. Registry. 

Although there are 54 affected fuel 

transfer ejectors worldwide, the FAA 

has no way of knowing how many 

affected parts may be installed on 

airplanes of U.S. Registry. The estimated 

cost on U.S. operators reflects the 

maximum possible cost based on the 10 

airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

airplane 

Cost on U.S. 

operators 

Replace fuel transfer ejector ........................... 5.5 work-hours × $85 per hour = $467.50 ..... $2,109 $2,576.50 $25,765 


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Federal Register / Vol. 87, No. 98 / Friday, May 20, 2022 / Rules and Regulations 30799 

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 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 

■ 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: 

2022–10–01 Pilatus Aircraft Ltd.: 

Amendment 39–22039; Docket No. 

FAA–2022–0092; Project Identifier 

MCAI–2020–01428–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 24, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pilatus Aircraft Ltd. 

Model PC–12/47E airplanes, serial numbers 

2001 and larger, certificated in any category. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2800, Aircraft Fuel System. 

(e) Unsafe Condition 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as a batch of 

incorrectly sized fuel transfer ejector nozzles 

that were installed on Model PC–12/47E 

airplanes during production. The FAA is 

issuing this AD to correct the installation of 

incorrectly sized fuel transfer ejectors 

nozzles. If not addressed, this unsafe 

condition could result in a restriction of 

motive fuel flow due to ice accumulation and 

lead to a reduction of safety margins in the 

fuel system with loss of engine power or 

engine shutdown. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definitions 

(1) For purposes of this AD, an ‘‘affected 

fuel transfer ejector’’ is a fuel transfer ejector 

part number (P/N) 968.84.71.112 with a serial 

number listed in the table on page 1 in 

section 1.C. of Pilatus PC–12 Service Bulletin 

No. 28–014, dated August 12, 2020 (Pilatus 

SB 28–014). 

(2) For purposes of this AD, a ‘‘Group 1 

airplane’’ is an airplane with an affected fuel 

transfer ejector installed. 

(3) For purposes of this AD, a ‘‘Group 2 

airplane’’ is an airplane without an affected 

fuel transfer ejector installed. 

(h) Required Actions 

For Group 1 airplanes: Within 4 months 

after the effective date of this AD, remove 

each fuel transfer ejector from service and 

install a serviceable part in accordance with 

Paragraph 3.B.(1) of the Accomplishment 

Instructions in Pilatus SB 28–014. 

(i) Parts Installation Prohibition 

As of the applicable time specified in 

paragraph (i)(1) or (2) of this AD, do not 

install an affected fuel transfer ejector on any 

airplane. 

(1) For Group 1 airplanes: After replacing 

the fuel transfer ejector as required by 

paragraph (h) of this AD. 

(2) For Group 2 airplanes: As of the 

effective date of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

Branch, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (k)(1) of this AD and 

email to: 9-AVS-AIR-730-AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(k) Related Information 

(1) For more information about this AD, 

contact Doug Rudolph, Aviation Safety 

Engineer, General Aviation & Rotorcraft 

Section, International Validation Branch, 

FAA, 901 Locust, Room 301, Kansas City, 

MO 64106; phone: (816) 329–4059; email: 

doug.rudolph@faa.gov. 

(2) Refer to European Union Aviation 

Safety Agency (EASA) AD 2020–0229, dated 

October 20, 2020, for more information. You 

may examine the EASA AD in the AD docket 

at https://www.regulations.gov by searching 

for and locating Docket No. FAA–2022–0092. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Pilatus PC–12 Service Bulletin No. 28– 

014, dated August 12, 2020. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Pilatus Aircraft Ltd., 

Customer Support General Aviation, CH– 

6371 Stans, Switzerland; phone: +41 848 24 

7 365; email: techsupport.ch@pilatusaircraft.com; website: https://www.pilatusaircraft.com. 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. 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: fr.inspection@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on April 30, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–10761 Filed 5–19–22; 8:45 am] 

BILLING CODE 4910–13–P 


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