Federal Register / Vol. 86, No. 107 / Monday, June 7, 2021 / Rules and Regulations 30155 

For the reasons discussed, I certify 

that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 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: 

2021–12–10 Leonardo S.p.a.: Amendment 

39–21597; Docket No. FAA–2021–0452; 

Project Identifier MCAI–2021–00388–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 22, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Leonardo S.p.a. Model 

AB139 and AW139 helicopters, certificated 

in any category, with 3-stretcher kit part 

number 139084–501 installed. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 1100, Placards and Markings. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

design deficiency which affects the primary 

stretcher unit of the 3-stretcher kit. The FAA 

is issuing this AD to address a design 

deficiency which affects the primary 

stretcher unit of the 3-stretcher kit. The 

unsafe condition, if not addressed, could 

lead, in case of an emergency landing, to 

failure of the primary stretcher, possibly 

resulting in injury to helicopter occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 30 hours time-in-service (TIS) after 

the effective date of this AD, install a placard 

on the primary stretcher in accordance with 

the Accomplishment Instructions of Aerolite 

Alert Service Bulletin ASB–21–006, dated 

March 16, 2021. 

(h) 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 (i)(1) of this AD. 

Information may be emailed to: 9-AVS-AIR730-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. 

(i) Related Information 

(1) For more information about this AD, 

contact Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave., Mail Stop: Room 410, Westbury, NY 

11590; phone: (516) 228–7330; email: 

andrea.jimenez@faa.gov. 

(2) For service information identified in 

this AD, contact Aerolite AG, 

Aumu ̈hlestrasse 10, CH–6373 Ennetbu ̈rgen, 

Switzerland; phone: +41 (0)41 624 58 58; fax: 

+41 (0)41 624 58 59; email: info@aerolite.ch. 

You may view this referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy., Room 6N–321, Fort Worth, 

TX 76177. For information on the availability 

of this material at the FAA, call (817) 222– 

5110. 

(3) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2021–0095, dated March 31, 

2021. You may view the EASA AD at https:// 

www.regulations.gov in Docket No. FAA– 

2021–0452. 

(j) 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) Aerolite Alert Service Bulletin ASB–21– 

006, dated March 16, 2021. 

(ii) [Reserved] 

(3) For Aerolite AG service information 

identified in this AD, contact Aerolite AG, 

Aumu ̈hlestrasse 10, CH–6373 Ennetbu ̈rgen, 

Switzerland; phone: +41 (0)41 624 58 58; fax: 

+41 (0)41 624 58 59; email: info@aerolite.ch. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 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: fedreg.legal@nara.gov, or go to: 

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

ibr-locations.html. 

Issued on May 28, 2021. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–11961 Filed 6–3–21; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0857; Project 

Identifier MCAI–2020–00707–A; Amendment 

39–21570; AD 2021–11–08] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2014–25– 

04 for all Pilatus Aircraft Ltd. (Pilatus) 

Model PC–6, PC–6–H1, PC–6–H2, PC–6/ 

350, PC–6/350–H1, PC–6/350–H2, PC– 

6/A, PC–6/A–H1, PC–6/A–H2, PC–6/B– 

H2, PC–6/B1–H2, PC–6/B2–H2, PC–6/ 

B2–H4, PC–6/C–H2, and PC–6/C1–H2 

airplanes. AD 2014–25–04 required 

incorporating revised airworthiness 

limitations into the aircraft maintenance 

manual (AMM) for your FAA-approved 

maintenance program. This AD requires 

incorporating new airworthiness 

limitations and an eddy current 

inspection of each fuselage wing fitting 

if an earlier version of the service 

information was accomplished. This AD 

was prompted by a determination that 

the new life limits, revised 

airworthiness limitations, and new 

inspection procedures are necessary. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective July 12, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 12, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Pilatus Aircraft Ltd., Customer Support 

General Aviation, CH–6371 Stans, 

Switzerland; phone: +41 848 24 7 365; 

email: Techsupport@pilatusVerDate Sep<11>2014 16:24 Jun 04, 2021 Jkt 253001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\07JNR1.SGM 07JNR1

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30156 Federal Register / Vol. 86, No. 107 / Monday, June 7, 2021 / Rules and Regulations 

aircraft.com; website: https://

www.pilatus-aircraft.com/en. You may 

view this referenced 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 (816) 329– 

4148. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0857. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0857; 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: 

Doug Rudolph, Aviation Safety 

Engineer, FAA, General Aviation & 

Rotorcraft Section, International 

Validation Branch, 901 Locust, Room 

301, Kansas City, MO 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 to supersede AD 2014–25–04, 

Amendment 39–18045 (79 FR 73803, 

December 12, 2014) (AD 2014–25–04). 

AD 2014–25–04 applied to all Pilatus 

Model PC–6, PC–6–H1, PC–6–H2, PC–6/ 

350, PC–6/350–H1, PC–6/350–H2, PC– 

6/A, PC–6/A–H1, PC–6/A–H2, PC–6/B– 

H2, PC–6/B1–H2, PC–6/B2–H2, PC–6/ 

B2–H4, PC–6/C–H2, and PC–6/C1–H2 

airplanes and resulted from mandatory 

continuing airworthiness information 

(MCAI) issued by an aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product. AD 2014–25–04 

required incorporating revised 

airworthiness limitations into the AMM 

for your FAA-approved maintenance 

program. 

The NPRM published in the Federal 

Register on October 2, 2020 (85 FR 

62266). The NPRM was prompted by a 

MCAI issued by the European Union 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union. EASA 

superseded its previous MCAIs on this 

unsafe condition with EASA AD 2020– 

0120, dated May 27, 2020 (EASA AD 

2020–0120). The NPRM proposed to 

require revising the airworthiness 

limitation section of the existing 

maintenance manual or instructions for 

continued airworthiness to incorporate 

new airworthiness limitations, and 

performing an eddy current inspection 

of the fuselage wing fittings and wing to 

fuselage fittings. 

After the FAA issued the NPRM, 

EASA superseded EASA AD 2020–0120 

and issued EASA AD 2020–0278, dated 

December 14, 2020 (EASA AD 2020– 

0278) (also referred to after this as ‘‘the 

MCAI’’). According to EASA AD 2020– 

0278, an installation procedure 

specified in the service information 

identified in the NPRM contained an 

error and, therefore, did not adequately 

address the identified unsafe condition. 

Pilatus revised the airworthiness 

limitations and issued corrected service 

information, which includes installing 

certain bushes using grease instead of a 

bonding agent and an additional onetime eddy current inspection of the 

fuselage wing fittings and wing-tofuselage fittings if the last inspection 

was performed using an earlier version 

of the service information. You may 

examine the MCAI in the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0857. 

The FAA issued a supplemental 

notice of proposed rulemaking (SNPRM) 

to amend 14 CFR part 39 to supersede 

AD 2014–25–04. The SNPRM published 

in the Federal Register on March 8, 

2021 (86 FR 13222). The SNPRM 

proposed to add an eddy current 

inspection of each fuselage wing fitting 

if an earlier version of the service 

information was accomplished. The 

FAA is issuing this AD to address 

reduced airplane controllability due to 

possible loss of structural integrity of 

certain parts. 

Discussion of the Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the SNPRM 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 the 

FAA’s bilateral agreement with the State 

of Design Authority, the FAA has been 

notified of the unsafe condition 

described in the MCAI and service 

information referenced above. The FAA 

reviewed the relevant data and 

determined that air safety requires 

adoption of the 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 SNPRM. 

Related Service Information Under 1 

CFR Part 51 

Pilatus issued the Airworthiness 

Limitations Section of PC–6 

Airworthiness Limitations Document 

No. 02334, Revision 10, dated October 

30, 2020; and Section 04–00–00, 

Airworthiness Limitations of Chapter 

04, Airworthiness Limitations, of the 

Pilatus PC–6 Aircraft Maintenance 

Manual Document No. 01975, Revision 

30, dated October 30, 2020. This service 

information contains airworthiness 

limitations for the stabilizer trim 

actuator, fuselage wing fittings, and 

wing-to-fuselage fittings. These 

documents are distinct since they apply 

to different airplane models. 

Pilatus also issued Section 53–00–01, 

Fuselage Wing Fittings—Inspection/ 

Check, of the Pilatus PC–6 Aircraft 

Maintenance Manual Document No. 

01975, Revision 30, dated October 30, 

2020; Section 57–00–03, Wing to 

Fuselage Fittings—Inspection/Check, of 

the PC–6 Aircraft Maintenance Manual 

Document No. 01975, Revision 29, 

dated February 28, 2020; Appendix K, 

Fuselage Wing Fittings—Inspection/ 

Check, of the PC–6 Airworthiness 

Limitations Document No. 02334, 

Revision 10, dated October 30, 2020; 

and Appendix L, Wing to Fuselage 

Fittings—Inspection/Check, of the PC–6 

Airworthiness Limitations Document 

No. 02334, Revision 9, dated March 6, 

2020. This service information specifies 

procedures for repetitive eddy current 

inspections of the fuselage wing fittings 

and wing-to-fuselage fittings and, if 

necessary, installing the bush on the 

fuselage wing fittings using grease. 

These documents are distinct since they 

apply to different airplane models. 

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 30 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 


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Federal Register / Vol. 86, No. 107 / Monday, June 7, 2021 / Rules and Regulations 30157 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

ALS revision ......................................................... 1 work-hour × $85 per 

hour = $85.

$0 $85 ............................... $2,550. 

Eddy current inspection of the fuselage wing fittings and wing-to-fuselage fittings.7 work-hours × $85 per 

hour = $595.

1,860 2,455 per inspection 

cycle.

73,650 per inspection 

cycle. 

The FAA estimates the following 

costs to do the inspections and 

installation that would be required if an 

earlier version of the service 

information has been accomplished. 

The agency has no way of determining 

the number of aircraft that might need 

these inspections and installation: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Visual and eddy current inspection and installation for certain bushes .... 7 work-hours × $85 per hour = 

$595.

$1,860 $2,455 

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 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 

2014–25–04, Amendment 39–18045 (79 

FR 73803, December 12, 2014), and 

■ b. Adding the following new 

airworthiness directive: 

2021–11–08 Pilatus Aircraft Ltd.: 

Amendment 39–21570; Docket No. 

FAA–2020–0857; Project Identifier 

MCAI–2020–00707–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 12, 2021. 

(b) Affected ADs 

This AD replaces AD 2014–25–04, 

Amendment 39–18045 (79 FR 73803, 

December 12, 2014) (AD 2014–25–04). 

(c) Applicability 

This AD applies to Pilatus Aircraft Ltd. 

Model PC–6, PC–6–H1, PC–6–H2, PC–6/350, 

PC–6/350–H1, PC–6/350–H2, PC–6/A, PC–6/ 

A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1– 

H2, PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2, 

and PC–6/C1–H2 airplanes, all serial 

numbers, certificated in any category. 

Note 1 to paragraph (c): These airplanes 

may also be identified as Fairchild Republic 

Company airplanes, Fairchild Industries 

airplanes, Fairchild Heli Porter airplanes, or 

Fairchild-Hiller Corporation airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by a determination 

that new and more restrictive airworthiness 

limitations, new life limits, and new 

inspection procedures are necessary. The 

FAA is issuing this AD to address reduced 

airplane controllability due to possible loss 

of structural integrity of certain parts. 

(f) Airworthiness Limitations Revision 

Unless already done, before further flight, 

comply with the actions specified in 

paragraphs (f)(1) through (3) of this AD. 

(1) For Models PC–6/B2–H2 and PC–6/B2– 

H4 airplanes, revise the airworthiness 

limitations section (ALS) of the existing 

maintenance manual or instructions for 

continued airworthiness (ICA) for your 

airplane as follows: 

(i) Replace Section 04–00–00 with Section 

04–00–00, Airworthiness Limitations, of 

Chapter 04, Airworthiness Limitations, of the 

Pilatus PC–6 Aircraft Maintenance Manual 

Document No. 01975, Revision 30, dated 

October 30, 2020. 

(ii) Add (or replace, if applicable) Section 

53–00–01, Fuselage Wing Fittings— 

Inspection/Check, of the Pilatus PC–6 

Aircraft Maintenance Manual Document No. 

01975, Revision 30, dated October 30, 2020. 

(iii) Add Section 57–00–03, Wing to 

Fuselage Fittings—Inspection/Check, of the 

Pilatus PC–6 Aircraft Maintenance Manual 

Document No. 01975, Revision 29, dated 

February 28, 2020. 

(2) For all airplanes specified in paragraph 

(c) of this AD except Models PC–6/B2–H2 

and PC–6/B2–H4 airplanes, revise the ALS of 


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30158 Federal Register / Vol. 86, No. 107 / Monday, June 7, 2021 / Rules and Regulations 

the existing maintenance manual or ICA for 

your airplane as follows: 

(i) Replace the ALS with the Airworthiness 

Limitations Section of Pilatus PC–6 

Airworthiness Limitations Document No. 

02334, Revision 10, dated October 30, 2020. 

(ii) Add (or replace, if applicable) 

Appendix K, Fuselage Wing Fittings— 

Inspection/Check, of Pilatus PC–6 

Airworthiness Limitations Document No. 

02334, Revision 10, dated October 30, 2020. 

(iii) Add Appendix L, Wing to Fuselage 

Fittings—Inspection/Check, of Pilatus PC–6 

Airworthiness Limitations Document No. 

02334, Revision 9, dated March 6, 2020. 

(3) For all airplanes specified in paragraph 

(c) of this AD, after revising the ALS as 

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

AD, remove from service each part that has 

reached or exceeded its new life limit. 

(g) Inspections and Replacement 

(1) For airplanes with a bush part number 

(P/N) 6100.0020.01 that has been bonded as 

specified in Section 53–00–01, Fuselage 

Wing Fittings—Inspection/Check, of Pilatus 

PC–6 Aircraft Maintenance Manual 

Document No. 01975, Revision 29, dated 

February 28, 2020; or Appendix K, Fuselage 

Wing Fittings—Inspection/Check, of Pilatus 

PC–6 Airworthiness Limitations Document 

No. 02334, Revision 9, dated March 6, 2020: 

Within 50 hours time-in-service (TIS) after 

the effective date of this AD, perform a visual 

and eddy current inspection of each fuselage 

wing fitting on fuselage Frame 3, remove 

bush P/N 6100.0020.01 from service, and 

install a new (zero hours TIS) bush P/N 

6100.0020.01 into Frame 3 with grease by 

using the procedures specified in paragraph 

(f)(1)(ii) or (f)(2)(ii) of this AD, as applicable 

to your airplane. 

(2) Unless already done, within 1,100 

hours TIS after the effective date of this AD 

or within 12 months after the effective date 

of this AD, whichever occurs first, perform 

an eddy current inspection of each fuselage 

wing fitting and each wing-to-fuselage fitting 

using the procedures specified in paragraphs 

(f)(1)(ii) and (iii) of this AD, or paragraphs 

(f)(2)(ii) and (iii) of this AD, as applicable to 

your airplane. Thereafter, repeat the eddy 

current inspection of each fuselage wing 

fitting and each wing-to-fuselage fitting at the 

intervals specified in the ALS identified in 

paragraph (f)(1)(i) or (f)(2)(i), as applicable to 

your airplane. 

(h) No Alternative Actions or Intervals 

After the ALS has been revised as required 

by paragraph (f) of this AD, no alternative 

inspection intervals or procedures may be 

approved, except as provided in paragraph (i) 

of this AD. 

(i) Other FAA AD Provisions 

Alternative Methods of Compliance 

(AMOCs): 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. 

Send your request to the person identified in 

Related Information. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspection, the manager of the local Flight 

Standards District Office. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Union Aviation Safety Agency (EASA) AD 

2020–0120, dated May 27, 2020, and EASA 

AD 2020–0278, dated December 14, 2020, for 

related information. This MCAI may be 

found in the AD docket at https://

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–0857. 

(2) For more information about this AD, 

contact Doug Rudolph, Aviation Safety 

Engineer, FAA, General Aviation & Rotorcraft 

Section, International Validation Branch, 901 

Locust, Room 301, Kansas City, MO 64106; 

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

4090; email: doug.rudolph@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) Pilatus PC–6 Aircraft Maintenance 

Manual Document No. 01975, Revision 29, 

dated February 28, 2020. 

(A) Section 57–00–03, Wing to Fuselage 

Fittings—Inspection/Check. 

(B) [Reserved] 

(ii) Pilatus PC–6 Aircraft Maintenance 

Manual Document No. 01975, Revision 30, 

dated October 30, 2020. 

(A) Section 04–00–00, Airworthiness 

Limitations, of Chapter 04, Airworthiness 

Limitations. 

(B) Section 53–00–01, Fuselage Wing 

Fittings—Inspection/Check. 

(iii) Pilatus PC–6 Airworthiness 

Limitations Document No. 02334, Revision 9, 

dated March 6, 2020. 

(A) Appendix L, Wing to Fuselage 

Fittings—Inspection/Check. 

(B) [Reserved] 

(iv) Pilatus PC–6 Airworthiness 

Limitations Document No. 02334, Revision 

10, dated October 30, 2020. 

(A) Airworthiness Limitations Section. 

(B) Appendix K, Fuselage Wing Fittings— 

Inspection/Check. 

(3) For service information identified in 

this AD, contact Pilatus Aircraft Ltd., 

Customer Support General Aviation, CH– 

6371 Stans, Switzerland; telephone: +41 848 

24 7 365; email: Techsupport@

pilatusaircraft.com; website: https://

www.pilatusaircraft.com/en. 

(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 (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 May 15, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–11812 Filed 6–4–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0378; Project 

Identifier 2017–SW–122–AD; Amendment 

39–21576; AD 2021–11–14] 

RIN 2120–AA64 

Airworthiness Directives; Leonardo 

S.p.a. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Leonardo S.p.a. Model AW169 

helicopters. This AD was prompted by 

reports of failed nose landing gear (NLG) 

retraction actuators during the 

acceptance test procedures on the 

ground on the final assembly line. This 

AD requires depending on the 

helicopter configuration, various 

modifications, installation checks, 

inspections of the NLG and main 

landing gear (MLG) retraction actuators 

and of the plungers of the NLG and 

MLG up down lock actuators, and 

corrective actions if necessary. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD becomes effective June 

22, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of June 22, 2021. 

The FAA must receive comments on 

this AD by July 22, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 


khammond on DSKJM1Z7X2PROD with RULES