Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 30761 

(b) Affected Airworthiness Directives (ADs) 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model EC 155B, EC155B1, SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters, certificated in any category, as 

identified in European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD 2019–0008, dated 

January 22, 2019 (EASA AD 2019–0008). 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 7110, Engine Cowling System. 

(e) Reason 

This AD was prompted by a report of an 

in-flight loss of main gearbox (MGB) and 

engine cowlings. The FAA is issuing this AD 

to address a failure of the MGB fixed cowling 

front fitting, and subsequent MGB cowling or 

engine cowling detachment, which could 

result in damage to the helicopter, loss of 

helicopter control, and possible injury to 

persons on the ground. 

(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, EASA AD 2019–0008. 

(h) Exceptions to EASA AD 2019–0008 

(1) Where EASA AD 2019–0008 refers to 

April 14, 2017 (the effective date of EASA 

AD 2017–0055, dated March 31, 2017), this 

AD requires using the effective date of this 

AD. 

(2) Where EASA AD 2019–0008 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(3) Where EASA AD 2019–0008 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(4) Where EASA AD 2019–0008 requires 

the modification within 660 flight hours or 

23 months, whichever occurs first, this AD 

requires the modification within 660 hours 

time-in-service instead. 

(5) Although the service information 

referenced in EASA AD 2019–0008 specifies 

to discard certain parts, this AD requires 

removing those parts from service instead. 

(6) Where the service information 

referenced in EASA AD 2019–0008 specifies 

to use tooling, equivalent tooling may be 

used. 

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

2019–0008 does not apply to this AD. 

(8) Where paragraph (1) of EASA AD 2019– 

0008 states to, ‘‘inspect the MGB fixed 

cowling front fittings in accordance with the 

instructions of paragraph 1.E.2 of the 

applicable inspection ASB or in accordance 

with the instructions of the applicable 

modification ASB,’’ this AD requires 

determining if Airbus Helicopters Alert 

Service Bulletin No. 53.00.55, Revision 0, 

dated March 13, 2017, or Revision 1, dated 

December 20, 2018, has or has not been 

complied with and following the 

instructions, ‘‘For helicopters on which 

ALERT SERVICE BULLETIN No. 53.00.55 

has not been complied with’’ or ‘‘For 

helicopters on which ALERT SERVICE 

BULLETIN No. 53.00.55 has been complied 

with,’’ as applicable, in paragraph 1.E.2, of 

Airbus Helicopters Alert Service Bulletin 

ASB No. AS365–53.00.62 or ASB No. EC155– 

53A038, each Revision 0 and dated December 

20, 2018 (ASB AS365–53.00.62 or ASB 

EC155–53A038), as applicable to your model 

helicopter. 

(9) Where paragraph (2) of EASA AD 2019– 

0008 states to, ‘‘accomplish the applicable 

corrective action(s) in accordance with 

paragraph 1.E.2 of the applicable inspection 

ASB or in accordance with the instructions 

of the applicable modification ASB,’’ this AD 

requires accomplishing the applicable 

corrective actions by following ASB AS365– 

53.00.62 or ASB EC155–53A038, as 

applicable to your model helicopter. 

(10) Where paragraph 3.B.2.e.3 of the 

applicable modification ASB referenced in 

EASA AD 2019–0008 refers to paragraph 

3.B.e.3, this AD requires referring to 

paragraph 3.B.3 of ASB AS365–53.00.62 or 

ASB EC155–53A038, as applicable to your 

model helicopter. 

(i) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, are not allowed. 

(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) 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. 

(k) Related Information 

For more information about this AD, 

contact Blaine Williams, Aerospace Engineer, 

Los Angeles ACO Branch, Compliance & 

Airworthiness Division, 3960 Paramount 

Blvd., Lakewood, California 90712; telephone 

(562) 627–5227; email blaine.williams@

faa.gov. 

(l) 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 Aviation Safety Agency 

(EASA) AD 2019–0008, dated January 22, 

2019. 

(ii) Airbus Helicopters Alert Service 

Bulletin ASB No. AS365–53.00.62, Revision 

0, dated December 20, 2018. 

(iii) Airbus Helicopters Alert Service 

Bulletin ASB No. EC155–53A038, Revision 0, 

dated December 20, 2018. 

(3) For EASA AD 2019–0008, 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. For Airbus Helicopters 

service information, contact Airbus 

Helicopters, 2701 N Forum Drive, Grand 

Prairie, TX 75052; telephone (972) 641–0000 

or (800) 232–0323; fax (972) 641–3775; or at 

https://www.airbus.com/helicopters/services/ 

technical-support.html. 

(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. 

This material may be found in the AD docket 

on the internet at https://

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–1183. 

(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 May 11, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–12037 Filed 6–9–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1074; Project 

Identifier MCAI–2020–01257–A; Amendment 

39–21574; AD 2021–11–12] 

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 the 

engine attachment hardware not 


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30762 Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 

conforming to the approved design, 

which could affect the structural 

integrity of the airplane. This AD 

requires inspecting the engine 

attachment hardware for missing 

washers and loose nuts and taking 

corrective actions as necessary. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective July 15, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 15, 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: 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 (816) 329–4148. It is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2020–1074. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–1074; 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 by adding an AD that would 

apply to certain serial-numbered Pilatus 

Model PC–24 airplanes. The NPRM 

published in the Federal Register on 

March 26, 2021 (86 FR 16124). 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 2020–0194, dated 

September 8, 2020 (referred to after this 

as ‘‘the MCAI’’), to address an unsafe 

condition on certain serial-numbered 

Pilatus Model PC–24 airplanes. The 

MCAI states: 

During a scheduled maintenance 

inspection, the engine attachment hardware 

of a PC–24 airplane was found not to 

conform to the approved design. A washer 

was missing beneath each of the four mating 

bolt heads on the rear engine beam. In 

addition, some of the keeper fitting 

attachment bolts on the LH/RH middle inner 

nacelle were found with loose nuts. It was 

also determined that other aeroplanes may 

have the same non-conformities. 

This condition, if not detected and 

corrected, could damage the engine 

attachment hardware, possibly affecting the 

structural integrity of the aeroplane. 

To address this potential unsafe condition, 

Pilatus issued the [service bulletin] SB, 

providing instructions for inspection and 

corrective action. 

For the reason described above, this 

[EASA] AD requires a one-time inspection for 

missing washers and loose nuts on the engine 

attachment hardware and, depending on 

findings, the accomplishment of applicable 

corrective action(s). 

You may examine the MCAI in the 

AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

1074. 

In the NPRM, the FAA proposed to 

require inspecting the engine 

attachment hardware for missing 

washers and loose nuts and taking 

corrective actions as necessary. The 

FAA is issuing this AD to address the 

unsafe condition on this product. 

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. 71–001, dated June 

30, 2020. This service information 

specifies procedures for inspecting the 

engine attachment hardware for loose 

nuts and missing washers and taking 

corrective actions depending on 

findings. 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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 34 airplanes of U.S. registry. 

The FAA estimates that it would take 

2.5 work-hours to do the one-time 

inspections. The average labor rate is 

$85 per work-hour. 

Based on these figures, the FAA 

estimates the cost of this AD on U.S. 

operators would be $7,225 or $212.50 

per airplane. 

The FAA also estimates that, as oncondition costs, installing missing 

washers, replacing bolts, and doing an 

eddy current inspection of the bolt holes 

would take 4.5 work-hours and require 

parts costing $200 for a cost of $582.50 

per airplane. This estimate assumes 

replacing all of the rear engine beam 

attachment bolts and washers and doing 

an eddy current inspection of all the 

attachment bolt holes. If the bolt holes 

are found damaged during the eddy 

current inspection, the damage will vary 

considerably from airplane to airplane, 

and the FAA has no way of estimating 

a repair cost. In addition, the FAA has 

no way of determining the number of 

airplanes that might need these actions. 

The FAA has included all known 

costs in this cost estimate. According to 

the manufacturer, however, some of the 

costs of this AD may be covered under 

warranty, thereby reducing the cost 

impact on affected operators. 

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 


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Federal Register / Vol. 86, No. 110 / Thursday, June 10, 2021 / Rules and Regulations 30763 

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. 

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: 

2021–11–12 Pilatus Aircraft Ltd.: 

Amendment 39–21574; Docket No. 

FAA–2020–1074; Project Identifier 

MCAI–2020–01257–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 15, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pilatus Aircraft Ltd. 

Model PC–24 airplanes, serial numbers (S/ 

Ns) 101 through 162, S/N 164, S/N 165, S/ 

N 167, and S/N 168, certificated in any 

category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7120, Engine Mount Section. 

(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 

identifies the unsafe condition as engine 

attachment hardware not conforming to the 

approved design. The FAA is issuing this AD 

to detect and address incorrectly installed 

attachment hardware in the engine and 

nacelle area. The unsafe condition, if not 

addressed, could result in damage to the 

engine attachment hardware, which may 

affect the structural integrity of the airplane. 

(f) Actions and Compliance 

Unless already done, do the actions in 

paragraphs (f)(1) and (2) of this AD at the 

next annual inspection after the effective date 

of this AD or within 11 months after the 

effective date of this AD, whichever occurs 

later. 

(1) Inspect the left hand (LH) and right 

hand (RH) middle inner nacelles for loose 

nuts and correctly install any loose nut 

before further flight by following section 

3.B(1) of the Accomplishment Instructions in 

Pilatus PC–24 Service Bulletin No. 71–001, 

dated June 30, 2020 (Pilatus SB 71–001). 

(2) Inspect the LH and RH front and rear 

engine beams for missing washers by 

following section 3.B(2)(a) through (b) of the 

Accomplishment Instructions in Pilatus SB 

71–001. If there are any missing washers, 

before further flight, do an eddy current 

inspection of the bolt holes for damage by 

following section 3.C of the Accomplishment 

Instructions in Pilatus SB 71–001. Where 

Pilatus SB 71–001 specifies obtaining repair 

instructions from Pilatus, the instructions 

must be accomplished using a method 

approved by the Manager, International 

Validation Branch, FAA; or the European 

Union Aviation Safety Agency (EASA); or 

Pilatus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(g) 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. If sending 

information directly to the manager of the 

International Validation Branch, send it to 

the attention of the person identified in 

Related Information. 

(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. 

(h) Related Information 

(1) 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; 

phone: (816) 329–4059; fax: (816) 329–4090; 

email: doug.rudolph@faa.gov. 

(2) Refer to EASA AD 2020–0194, dated 

September 8, 2020, for more information. 

You may examine the EASA AD at https:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–1074. 

(i) 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–24 Service Bulletin No. 71– 

001, dated June 30, 2020. 

(ii) [Reserved] 

(3) For Pilatus Aircraft Ltd. service 

information identified in this AD, contact 

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 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 17, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–12044 Filed 6–9–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0812; Project 

Identifier MCAI–2020–01317–A; Amendment 

39–21561; AD 2021–10–28] 

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 all 

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 


khammond on DSKJM1Z7X2PROD with RULES