10772 Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations 

(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: 

2021–04–07 Piper Aircraft, Inc.: 

Amendment 39–21428; Docket No. 

FAA–2020–0830; Project Identifier 

2020–CE–002–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 30, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

(c) This AD applies to the following Piper 

Aircraft, Inc., airplanes, certificated in any 

category: 

(1) Model PA–46–350P (Malibu Mirage) 

airplanes, serial numbers (S/Ns) 4622041, 

4636041, 4636142, 4636143, 4636313, 

4636341, and 4636379; 

(2) Model PA–46–500TP (Malibu Meridian) 

airplanes, S/Ns 4697141, 4697161, 4697086, 

and 4697020; and 

(3) Models PA–46–350P (Malibu Mirage), 

PA–46R–350T (Malibu Matrix), and PA–46– 

500TP (Malibu Meridian) airplanes, all serial 

numbers, if the left wing has been replaced 

with a serviceable (more than zero hours 

time-in-service) wing. 

(d) Subject 

Joint Aircraft System Component (JASC) 

3700, VACUUM SYSTEM. 

(e) Unsafe Condition 

This AD was prompted by nonconforming 

stall warning heat control systems, utilizing 

a left wing assembly without the proper stall 

warning modification design. Without the 

proper stall warning heat control 

modification kit during flights into icing 

conditions with the landing gear down, ice 

can form on the stall vane, which may result 

in failure of the stall warning system. The 

FAA is issuing this AD to identify and 

correct nonconforming stall warning heat 

control systems. The unsafe condition, if not 

addressed, could result in the pilot being 

unaware of an approaching stall situation. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Actions 

(1) Within 100 hours time-in-service (TIS) 

after the effective date of this AD or within 

12 months after the effective date of this AD, 

whichever occurs first, inspect the 

configuration of stall warning heat control 

system and, if required, install stall warning 

heat control modification kit part number 

(P/N) 8452–002 before further flight in 

accordance with steps 2 and 3 of the 

Instructions in Piper Aircraft, Inc., Service 

Letter No. 1261, dated July 19, 2019. 

(2) As of the effective date of this AD, do 

not install a wing on any Model PA–46–350P 

(Malibu Mirage), PA–46R–350T (Malibu 

Matrix), or PA–46–500TP (Malibu Meridian) 

airplane unless you have determined that the 

wing has the correct stall warning heat 

control system as required by paragraph 

(g)(1) of this AD. 

(h) Special Flight Permit 

A special flight permit may be issued to 

operate the airplane to a location where the 

requirements of this AD can be accomplished 

provided flight into known icing conditions 

is prohibited. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta ACO 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. 

(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by a Piper Aircraft, Inc. 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Atlanta ACO Branch to make those 

findings. To be approved, the repair method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

For more information about this AD, 

contact John Lee, Aviation Safety Engineer, 

Atlanta ACO Branch, FAA, 1701 Columbia 

Avenue, College Park, GA 30337; phone: 

(404) 474–5568; email: john.lee@faa.gov. 

(k) 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) Piper Service Letter No. 1261, dated July 

19, 2019. 

(ii) [Reserved] 

(3) For Piper Aircraft, Inc. service 

information identified in this AD, contact 

Piper Aircraft Inc., 2926 Piper Drive, Vero 

Beach, FL 32960; phone: 772–299–2686; 

email: customerservice@piper.com; website: 

https://www.piper.com/. 

(4) You may view this service information 

at FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call 816–329–4148. 

(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: fedreg.legal@nara.gov, or go to: 

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

ibr-locations.html. 

Issued on February 4, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03499 Filed 2–22–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0969; Project 

Identifier MCAI–2020–00853–T; Amendment 

39–21393; AD 2021–02–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations 10773 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus SAS Model A350–941 and –1041 

airplanes. This AD was prompted by a 

report that certain retaining rings could 

cause damage to frame forks, brackets 

and edge frames, and their surface 

protection; subsequent investigation 

showed that the depth of the frame fork 

spotfacing on structural parts is 

inadequate to accommodate the 

retaining ring. This AD requires 

repetitive inspections of certain areas of 

each cargo door for damage and 

corrective action. This AD also provides 

an optional terminating modification, as 

specified in a European Union Aviation 

Safety Agency (EASA) AD, which is 

incorporated by reference. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective March 30, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 30, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

the EASA, Konrad-Adenauer-Ufer 3, 

50668 Cologne, Germany; telephone +49 

221 8999 000; email ADs@

easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

IBR material on the EASA website at 

https://ad.easa.europa.eu. You may 

view this IBR material at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available in the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0969. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0969; 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: 

Kathleen Arrigotti, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3218; email 

kathleen.arrigotti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2020–0144, dated June 29, 2020 (EASA 

AD 2020–0144) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for all Airbus SAS 

Model A350–941 and –1041 airplanes. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus SAS Model A350– 

941 and –1041 airplanes. The NPRM 

published in the Federal Register on 

October 26, 2020 (85 FR 67696). The 

NPRM was prompted by a report that 

certain retaining rings could cause 

damage to frame forks, brackets and 

edge frames, and their surface 

protection; subsequent investigation 

showed that the depth of the frame fork 

spotfacing on structural parts is 

inadequate to accommodate the 

retaining ring. The NPRM proposed to 

require repetitive inspections of certain 

areas of each cargo door for damage and 

corrective action. The NPRM also 

proposed to provide an optional 

terminating modification, as specified in 

an EASA AD. 

The FAA is issuing this AD to address 

inadequate frame fork spotfacing depth 

for the retaining rings, which could 

reduce the structural integrity of the 

airplane. See the MCAI for additional 

background information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. The FAA has 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2020–0144 describes 

procedures for repetitive inspections of 

the edge frames, brackets, frame forks, 

and the access cover on the internal side 

of each cargo door for damage 

(including cracks and corrosion) and 

corrective actions. Corrective actions 

include repair or rework. EASA AD 

2020–0144 also describes procedures for 

an optional modification of each 

affected cargo door, which terminates 

the repetitive inspections. This material 

is reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

The FAA estimates that this AD 

affects 13 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

24 work-hours × $85 per hour = $2,040 ..................................................................................... $0 $2,040 $26,520 

ESTIMATED COSTS FOR OPTIONAL ACTIONS

Labor cost Parts cost Cost per product 

9 work-hours × $85 per hour = $765 ................................................................................................................ Up to $8,570 ..... Up to $9,335. 

10774 Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition actions specified in 

this AD. 

According to the manufacturer, some 

or all of the costs of this AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

operators. The FAA does not control 

warranty coverage for affected operators. 

As a result, the FAA has included all 

known costs in the cost estimate. 

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, 

(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. 

Adoption of 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: 

2021–02–10 Airbus SAS: Amendment 39– 

21393; Docket No. FAA–2020–0969; 

Project Identifier MCAI–2020–00853–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 30, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus SAS Model 

A350–941 and –1041 airplanes, certificated 

in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Reason 

This AD was prompted by a report that 

certain retaining rings could cause damage to 

frame forks, brackets and edge frames, and 

their surface protection; subsequent 

investigation showed that the depth of the 

frame fork spotfacing on structural parts is 

inadequate to accommodate the retaining 

ring. The FAA is issuing this AD to address 

inadequate frame fork spotfacing depth for 

the retaining rings, which could reduce the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, European Union Aviation 

Safety Agency (EASA) AD 2020–0144, dated 

June 29, 2020 (EASA AD 2020–0144). 

(h) Exceptions to EASA AD 2020–0144 

(1) Where EASA AD 2020–0144 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) The ‘‘Remarks’’ section of EASA AD 

2020–0144 does not apply to this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, 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 responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (j) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (i)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

For more information about this AD, 

contact Kathleen Arrigotti, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3218; email 

kathleen.arrigotti@faa.gov. 

(k) 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0144, dated June 29, 2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0144, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; Internet 

www.easa.europa.eu. You may find this 

EASA AD on the EASA website at https://

ad.easa.europa.eu. 

(4) You may view this material at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. This material may be found 

Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations 10775 

in the AD docket on the internet at https:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–0969. 

(5) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, email fedreg.legal@

nara.gov, or go to: https://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued on January 12, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03568 Filed 2–22–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0818; Project 

Identifier MCAI–2020–00987–A; Amendment 

39–21381; AD 2021–01–05] 

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– 

24 airplanes. This AD results from 

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 

electrical harness installations on PC–24 

airplanes that are not in compliance 

with the approved design. This unsafe 

condition could lead to wire chafing 

and potential arcing or failure of wires 

having the incorrect length, possibly 

resulting in loss of system redundancy, 

or generation of smoke and smell, or 

loss of power plant fire protection 

function. This AD requires modifying 

the electrical harness installation. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective March 30, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 30, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Pilatus Aircraft Ltd., CH–6371, Stans, 

Switzerland; phone: +41 848 24 7 365; 

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

www.pilatus-aircraft.com/. You may 

view this service information at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. 

It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0818. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0818; 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, FAA, General Aviation & 

Rotorcraft Section, International 

Validation Branch, 901 Locust, Room 

301, Kansas City, Missouri 64106; 

phone: (816) 329–4059; fax: (816) 329– 

4090; 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–24 airplanes. The NPRM 

published in the Federal Register on 

September 17, 2020 (85 FR 58002). The 

NPRM was prompted by MCAI 

originated by the European Union 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union. EASA has 

issued EASA AD No. 2020–0158, dated 

July 16, 2020 (referred to after this as 

‘‘the MCAI’’), to address the unsafe 

condition on these products. The MCAI 

states: 

During production, electrical harness 

installations on some PC–24 aeroplanes were 

found not to comply with the approved 

design. 

This condition, if not corrected, could lead 

to wire chafing and potential arcing, or to 

failure of wires having the incorrect length, 

possibly resulting in loss of system 

redundancy, or generation of smoke and 

smell, or loss of power plant fire protection 

function. 

To address this potential unsafe condition, 

Pilatus issued the [service bulletin] SB, 

providing instructions to improve the 

electrical harness installations in the nose 

bay, cockpit, fuselage, wing fairing and rear 

fuselage areas. 

For the reason described above, this 

[EASA] AD requires modification of the 

electrical harness installations. 

The incorrect length wires are too 

short in length and do not have 

appropriate slack, which could lead to 

wires being pulled loose from the 

terminals during flight or ground 

operation. Generation of smell refers to 

the smell from electrical arcing. You 

may examine the MCAI in the AD 

docket at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2020–0818. 

In the NPRM, the FAA proposed to 

require modifying the electrical harness 

installation. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

This product has been approved by 

the aviation authority of another 

country and is approved for operation in 

the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI and service information 

referenced above. The FAA reviewed 

the relevant data and determined that 

air safety and the public interest require 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. This AD is adopted as 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Pilatus PC–24 

Service Bulletin No. 91–001, dated 

April 7, 2020. The service information 

specifies procedures necessary to 

improve the electrical harness 

installation in the nose bay, cockpit, 

avionics rack, fuselage, wing fairing, 

and rear fuselage. 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 will 

affect 36 products of U.S. registry. The 

FAA also estimates that it will take 20