30794 Federal Register / Vol. 87, No. 98 / Friday, May 20, 2022 / Rules and Regulations 

conduct testing at the reduced input rate 

only. 

* * * * * 

[FR Doc. 2022–10373 Filed 5–19–22; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1167; Project 

Identifier AD–2021–00823–E; Amendment 

39–22034; AD 2022–09–14] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2019–22– 

05, which applied to all General Electric 

Company (GE) CF34–8C model turbofan 

engines. AD 2019–22–05 required initial 

and repetitive inspections of the 

operability bleed valve (OBV) fuel tubes, 

OBV bleed air manifold link rod 

assemblies, and the OBV fuel fittings. 

AD 2019–22–05 also required 

replacement of OBVs or related OBV 

link rod hardware that fail inspection. 

This AD was prompted by multiple 

reports of fuel leaks, some leading to 

engine fires, which have occurred as a 

result of malfunctions related to the 

OBV. Additionally, the manufacturer 

has redesigned the OBV, which 

terminates the need for the repetitive 

inspections. This AD requires initial 

and repetitive inspections of the OBV 

fuel tubes, OBV bleed air manifold link 

rod assemblies, and the OBV fuel 

fittings installed on GE CF34–8C model 

turbofan engines. This AD requires 

replacement of OBVs or related OBV 

link rod hardware that fail inspection. 

As a terminating action to the repetitive 

inspections, this AD requires 

replacement of certain OBVs installed 

on GE CF34–8C model turbofan engines. 

This AD also requires replacement of 

certain OBVs installed on GE CF34–8E 

model turbofan engines. 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 certain publications listed in this AD 

as of June 24, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of December 23, 2019 (84 FR 

63569, November 18, 2019). 

ADDRESSES: For service information 

identified in this final rule, contact 

General Electric Company, 1 Neumann 

Way, Cincinnati, OH 45215; phone: 

(513) 552–3272; email: 

aviation.fleetsupport@ge.com; website: 

https://www.ge.com. You may view this 

service information at the Airworthiness 

Products Section, Operational Safety 

Branch, FAA, 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–2021–1167. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1167; or in person at Docket 

Operations between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

final rule, any comments received, and 

other information. The address for 

Docket Operations 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: 

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. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2019–22–05, 

Amendment 39–19784 (84 FR 63569, 

November 18, 2019), (AD 2019–22–05). 

AD 2019–22–05 applied to all GE CF34– 

8C1, CF34–8C5, CF34–8C5A1, CF34– 

8C5B1, CF34–8C5A2, and CF34–8C5A3 

(CF34–8C) model turbofan engines. The 

NPRM published in the Federal 

Register on December 29, 2021 (86 FR 

73997). The NPRM was prompted by 

multiple reports of fuel leaks, some 

leading to engine fires, which have 

occurred as a result of malfunctions 

related to the OBV. Since the FAA 

issued AD 2019–22–05, the 

manufacturer redesigned the OBV, 

which terminates the need for the 

repetitive inspections of the OBV fuel 

tubes, OBV bleed air manifold link rod 

assemblies, and the OBV fuel fittings. 

Additionally, the FAA determined that 

GE CF34–8E2, CF34–8E2A1, CF34–8E5, 

CF34–8E5A1, CF34–8E5A2, CF34–8E6, 

and CF34–8E6A1 (CF34–8E) model 

turbofan engines are susceptible to the 

same unsafe condition as the CF34–8C 

model turbofan engines, and therefore, 

added the GE CF34–8E model turbofan 

engines to the applicability of this AD. 

GE published service information 

specifying procedures to replace certain 

OBVs installed on GE CF34–8C and 

CF34–8E model turbofan engines. In the 

NPRM, the FAA proposed to continue to 

require initial and repetitive inspections 

of the OBV fuel tubes, OBV bleed air 

manifold link rod assemblies, the OBV 

fuel fittings installed on GE CF34–8C 

model turbofan engines, and 

replacement of OBVs or related OBV 

link rod hardware that fail inspection. 

In the NPRM, the FAA proposed to 

require replacement of certain OBVs 

installed on GE CF34–8C model 

turbofan engines as a terminating action 

to the repetitive inspections. In the 

NPRM, the FAA also proposed to 

require replacement of certain OBVs 

installed on GE CF34–8E model 

turbofan engines. 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 

four commenters. The commenters were 

Air Line Pilots Association, 

International (ALPA), Horizon Air, 

Japan Airlines (JAL), and SkyWest 

Airlines, Inc. (SkyWest). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Request To Add Guidance for OBVs 

With Unknown Flight Hours (FHs) 

Since New 

Horizon Air requested that the FAA 

provide guidance for compliance with 

the Required Actions, paragraphs (g)(4) 

and (5), in the event the FHs since new 

of the OBV is unknown. Horizon Air 

commented that paragraphs (g)(4) and 

(5) of the NPRM would require 

replacement of the OBV with a part 

eligible for installation within 

prescribed periods, which are 

predicated on the FHs since new of the 

OBV. Horizon Air reasoned that the 

NPRM does not include guidance for 

replacing an OBV if the FHs since new 

of the OBV is unknown. 

In response to this comment, the FAA 

has added paragraph (g)(6) to this AD, 

allowing use of the FHs since new of the 

engine if the accumulated FHs since 

new of the OBV is unknown. 


khammond on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 87, No. 98 / Friday, May 20, 2022 / Rules and Regulations 30795 

Request To Clarify the Reference Date 

for OBV FHs Since New 

JAL requested that the FAA update 

paragraph (g)(4) of this AD to include a 

reference date for OBV FHs since new. 

JAL noted that although paragraph (g)(4) 

of the NPRM has the OBV FHs since 

new, it does not provide a reference 

date. 

The FAA revised paragraphs (g)(4)(i) 

through (iii) of this AD to identify the 

reference date as requested by the 

commenter. 

Request To Add Service Information 

Note to the Required Actions 

JAL requested that the FAA add a 

note referenced in GE CF34–8E Service 

Bulletin (SB) 75–0021 R00 to the 

Required Actions, which states, ‘‘For all 

OBVs, if the OBV was upgraded per S/ 

B 75–0018 or the OBV cap was replaced 

per GEK 117619, CF34–8E Component 

Maintenance Manual (CMM), 80–12–41, 

Revision 03 or higher, the flight hours 

since upgrade or flight hours since the 

cap was replaced, as applicable, can be 

used instead of flight hours since new.’’ 

In response to JAL’s request, the FAA 

added paragraph (g)(7) to this AD. 

Comments on the Costs of Compliance 

SkyWest commented that they have 

found the costs to convert part number 

(P/N) 4123T71P02 or P/N 4123T71P03 

are closer to $25,000 to $30,000 than the 

estimated $17,000 stated in the NPRM. 

SkyWest also commented that replacing 

the OBV on CF34–8E engines would 

take more than the 2 hours estimated in 

the NPRM. SkyWest reasoned that in 

their experience, it could take 8 hours 

to replace the OBV on CF34–8E engines. 

In response to SkyWest’s comment 

regarding the estimated costs to replace 

the OBV, the FAA updated the 

estimated parts costs from $17,230 to 

$20,330 in the Costs of Compliance 

section of this AD. The FAA disagrees 

with revising the estimated labor cost to 

replace the OBV. The cost analysis in 

AD rulemaking actions typically 

includes only the costs associated with 

complying with the AD and does not 

include secondary costs. The FAA’s cost 

estimate includes the estimated work 

hours and parts costs to perform the 

required actions. 

Comments on Part Supply Shortages 

SkyWest noted concerns with OBVs 

modified to P/N 4123T71P06 since only 

the original equipment manufacturer 

(OEM) could modify the OBVs. SkyWest 

also commented that the OEM is 

currently having parts supply shortages 

that could jeopardize modifying the 

OBVs in the required timeline as 

proposed in paragraphs (g)(3) and (4) of 

the NPRM. 

In response to SkyWest’s comments, 

GE has communicated with the supplier 

and confirmed there is sufficient 

capacity and margin to meet the 

compliance times required by this AD. 

GE has also requested that the supplier 

plan improvements for engagement and 

logistics with the operators. 

Support for the AD 

ALPA expressed support for the AD 

as written. 

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 Under 1 

CFR Part 51 

The FAA reviewed GE CF34–8C SB 

75–0020 R04, dated May 10, 2019 (GE 

SB 75–0020). This SB specifies 

procedures for inspecting the bleed air 

manifold link rod assemblies; the 

supply, return, and drain fuel fittings; 

and the fuel tubes on the OBV. This SB 

also specifies procedures for performing 

corrective actions and replacing any 

OBVs or related OBV link rod hardware 

that fail the inspection criteria. The 

Director of the Federal Register 

approved the incorporation by reference 

of GE SB 75–0020 as of December 23, 

2019 (84 FR 63569, November 18, 2019). 

The FAA reviewed GE CF34–8C SB 

75–0025 R01, dated August 1, 2019. 

This SB specifies procedures for 

replacing and upgrading the suspect 

population of OBVs VIN 5000728–104 

(P/N 4123T71P02), VIN 5000728–106 

(P/N 4123T71P03), and VIN 5080046– 

101 (P/N 4123T71P04). 

The FAA reviewed GE CF34–8E SB 

75–0019 R01, dated August 1, 2019. 

This SB specifies procedures for 

replacing and upgrading the suspect 

population of OBVs VIN 5000728–104 

(P/N 4123T71P02), VIN 5000728–106 

(P/N 4123T71P03), and VIN 5080046– 

101 (P/N 4123T71P04). 

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. 

Other Related Service Information 

The FAA reviewed GE CF34–8C SB 

75–0026 R00, dated February 21, 2020. 

This SB introduces OBV VIN 5080046– 

103 (P/N 4123T71P06). 

The FAA also reviewed GE CF34–8E 

SB 75–0021 R00, dated February 21, 

2020. This SB introduces OBV VIN 

5080046–103 (P/N 4123T71P06). 

Costs of Compliance 

The FAA estimates that this AD 

affects 1,172 engines installed on 

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 

product 

Cost on U.S. 

operators 

Replace OBV .................................................. 2 work-hours × $85 per hour = $170 ............. $20,330 $20,500 $24,026,000 

Inspect OBV fuel tubes, assemblies, and fittings.1 work-hour × $85 per hour = $85 ................. 0 85 99,620 

The FAA estimates the following 

costs to do any necessary replacements 

that would be required based on the 

results of the inspection. The agency has 

no way of determining the number of 

aircraft that might need this 

replacement. 


khammond on DSKJM1Z7X2PROD with RULES
30796 Federal Register / Vol. 87, No. 98 / Friday, May 20, 2022 / Rules and Regulations 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace OBV tubes, clamps, and link rod hardware ... 2.25 work-hours × $85 per hour = $191.25 ................. $3,786.25 $3,977.50 

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 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 

■ 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: 

■ a. Removing Airworthiness Directive 

2019–22–05, Amendment 39–19784 (84 

FR 63569, November 18, 2019); and 

■ b. Adding the following new 

airworthiness directive: 

2022–09–14 General Electric Company: 

Amendment 39–22034; Docket No. 

FAA–2021–1167; Project Identifier AD– 

2021–00823–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 24, 2022. 

(b) Affected ADs 

This AD replaces AD 2019–22–05, 

Amendment 39–19784 (84 FR 63569, 

November 18, 2019). 

(c) Applicability 

This AD applies to General Electric 

Company (GE) CF34–8C1, CF34–8C5, CF34– 

8C5A1, CF34–8C5B1, CF34–8C5A2, CF34– 

8C5A3, CF34–8E2, CF34–8E2A1, CF34–8E5, 

CF34–8E5A1, CF34–8E5A2, CF34–8E6, and 

CF34–8E6A1 model turbofan engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7532, Compressor Bleed Valve. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of fuel leaks, some leading to engine fires, 

which have occurred as a result of 

malfunctions related to the operability bleed 

valve (OBV). The FAA is issuing this AD to 

prevent failure of the OBV. The unsafe 

condition, if not addressed, could result in an 

engine fire and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For CF34–8C1, CF34–8C5, CF34– 

8C5A1, and CF34–8C5B1 model turbofan 

engines with serial numbers (S/Ns): 965101 

through 965670 inclusive; 194101 through 

194999 inclusive; and 195101 through 

195653 inclusive: 

(i) Within 880 flight hours (FHs) since the 

previous inspection, 500 FHs after December 

23, 2019 (the effective date of AD 2019–22– 

05), or 6,880 FHs since new, whichever 

occurs later, inspect the OBV bleed air 

manifold link rod assemblies, the OBV fuel 

fittings, and the OBV fuel tubes. 

(ii) Thereafter, within every 880 FHs since 

the previous inspection, perform additional 

repeat inspections of the OBV bleed air 

manifold link rod assemblies, the OBV fuel 

fittings, and the OBV fuel tubes. 

(iii) Use the Accomplishment Instructions, 

paragraph 3.B., of GE CF34–8C Service 

Bulletin (SB) 75–0020 R04, dated May 10, 

2019 (GE SB 75–0020), to perform 

inspections required by paragraphs (g)(1)(i) 

and (ii) of this AD and, per the inspection 

criteria in paragraph 3.B., of GE SB 75–0020 

(the inspection criteria), do the following: 

(A) Before further flight, if fuel leakage is 

observed at the OBV fuel fittings or the OBV 

fuel fittings are loose, replace the OBV with 

a part eligible for installation. 

(B) Before further flight, if any OBV fuel 

tube clamp is found to be outside the 

inspection criteria, re-torque the OBV fuel 

tube clamp or replace the OBV fuel tube 

clamp. 

(C) Within 50 flight cycles (FCs) after the 

inspections required by paragraphs (g)(1)(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. 

(2) For CF34–8C5B1 model turbofan 

engines with S/Ns not listed in paragraph 

(g)(1) of this AD and for all CF34–8C5A2 and 

CF34–8C5A3 model turbofan engines, 

perform the following: 

(i) Within 880 FHs after the effective date 

of this AD or prior to accumulating 6,880 FHs 

since new, whichever occurs later, perform 

an initial inspection of the OBV bleed air 

manifold link rod assemblies, OBV fuel 

fittings, and OBV fuel tubes. 

(ii) Thereafter, within every 880 FHs since 

the last inspection, repeat the inspection of 

the OBV bleed air manifold link rod 

assemblies, OBV fuel fittings, and OBV fuel 

tubes. 

(iii) Use the Accomplishment Instructions, 

paragraph 3.B., of GE SB 75–0020, to perform 

the inspections in paragraph (g)(2)(i) and (ii) 

of this AD and, per the inspection criteria in 

paragraph 3.B., of GE SB 75–0020, do the 

following: 

(A) Before further flight, if fuel leakage is 

observed at the OBV fuel fittings or the OBV 

fuel fittings are loose, replace the OBV with 

a part eligible for installation. 

(B) Before further flight, if any OBV fuel 

tube clamp is found to be outside the 

inspection criteria, re-torque the OBV fuel 

tube clamp or replace the OBV fuel tube 

clamp. 


khammond on DSKJM1Z7X2PROD with RULES
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 


khammond on DSKJM1Z7X2PROD with RULES