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 


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Federal Register / Vol. 86, No. 107 / Monday, June 7, 2021 / Rules and Regulations 30159 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this final rule, contact Leonardo S.p.A. 

Helicopters, Emanuele Bufano, Head of 

Airworthiness, Viale G.Agusta 520, 

21017 C.Costa di Samarate (Va) Italy; 

telephone +39–0331–225074; fax +39– 

0331–229046; or at https://

www.leonardocompany.com/en/home. 

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. It is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0378. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0378; 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 European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Anthony Kenward, Aerospace Engineer, 

AIR–7F1, Fort Worth ACO Branch, 

FAA, 10101 Hillwood Parkway, Fort 

Worth, TX 78101; telephone (817) 222– 

5152; email Anthony.Kenward@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2017–0164, dated September 4, 2017 

(EASA AD 2017–0164), to correct an 

unsafe condition for certain Leonardo 

S.p.a. Model AW169 helicopters. The 

EASA advises that there were reports of 

failed NLG retraction actuators during 

the acceptance test procedures on the 

ground on the final assembly line. The 

EASA stated the NLG got stuck at 

approximately a 45° angle (half of the 

full stroke) regardless of the selected 

extension mode (normal or emergency). 

Investigation revealed that excessive 

friction inside the NLG retraction 

actuator caused internal damage, 

resulting in mechanical jam of the 

actuator rotary shaft. The EASA advised 

that due to similarity of design, the 

same failure mode can affect the MLG 

retraction actuators. This condition, if 

not addressed, could result in a partially 

locked or unlocked NLG or MLG upon 

landing, possibly resulting in damage to 

the helicopter and injury to the 

occupants. 

Accordingly, the EASA AD requires, 

depending on the helicopter 

configuration, various modifications, 

installation checks, inspections of the 

plungers of the NLG and MLG up down 

lock actuators, and corrective actions if 

necessary. 

FAA’s Determination 

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 referenced 

above. The FAA is issuing this AD after 

evaluating all pertinent information and 

determining that the unsafe condition 

exists and is likely to exist or develop 

on other products of the same type 

design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Leonardo 

Helicopters Alert Service Bulletin 169– 

023, Revision B, dated April 16, 2018 

(ASB 169–023, Revision B). This service 

information specifies procedures for, 

depending on the helicopter 

configuration, various modifications, 

installation checks (which include 

measurements), inspections of the 

plungers of the NLG and MLG up down 

lock actuators, and corrective actions if 

necessary. The modifications include 

replacing the actuators, installing 

enhanced landing gear retracting 

actuators, modifying the landing gear 

actuator control box, improving the 

landing gear proximity switch, and 

doing checks and measurements. 

Corrective actions include replacing the 

NLG and MLG lock support buffer, 

reinstalling the NLG and MLG retracting 

electrical actuator, shimming gaps, 

adjusting the position of the NLG 

retracting lever, applying lubricant, 

installing a pin, replacing washers, and 

reinstalling the NLG assembly. 

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. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information already described, except as 

discussed under ‘‘Differences Between 

this AD and the MCAI.’’ 

Differences Between This AD and the 

MCAI 

EASA AD 2017–0164 requires 

modifications and installation checks 

within 200 hours time-in-service (TIS) 

or 6 months, whichever occurs first; this 

AD requires those actions within 200 

hours TIS. 

EASA AD 2017–0164 requires, for 

certain helicopters, an inspection of the 

plungers of the NLG and MLG up down 

lock actuators within 50 hours TIS or 30 

days, whichever occurs first; this AD 

requires that action within 30 days. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (APA) (5 

U.S.C. 551 et seq.) authorizes agencies 

to dispense with notice and comment 

procedures for rules when the agency, 

for ‘‘good cause,’’ finds that those 

procedures are ‘‘impracticable, 

unnecessary, or contrary to the public 

interest.’’ Under this section, an agency, 

upon finding good cause, may issue a 

final rule without providing notice and 

seeking comment prior to issuance. 

Further, section 553(d) of the APA 

authorizes agencies to make rules 

effective in less than thirty days, upon 

a finding of good cause. 

There is one helicopter with this type 

certificate on the U.S. Register. The FAA 

has confirmed that the identified unsafe 

condition has been addressed on that 

helicopter. Accordingly, notice and 

opportunity for prior public comment 

are unnecessary, pursuant to 5 U.S.C. 

553(b)(3)(B). 

In addition, for the foregoing 

reason(s), the FAA finds that good cause 

exists pursuant to 5 U.S.C. 553(d) for 

making this amendment effective in less 

than 30 days. 

Comments Invited 

The FAA invites you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2021–0378; 

Project Identifier 2017–SW–122–AD’’ at 

the beginning of your comments. The 

most helpful comments reference a 

specific portion of the final rule, explain 

the reason for any recommended 

change, and include supporting data. 

The FAA will consider all comments 

received by the closing date and may 

amend this final rule because of those 

comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 


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30160 Federal Register / Vol. 86, No. 107 / Monday, June 7, 2021 / Rules and Regulations 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this final rule. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this AD contain 

commercial or financial information 

that is customarily treated as private, 

that you actually treat as private, and 

that is relevant or responsive to this AD, 

it is important that you clearly designate 

the submitted comments as CBI. Please 

mark each page of your submission 

containing CBI as ‘‘PROPIN.’’ The FAA 

will treat such marked submissions as 

confidential under the FOIA, and they 

will not be placed in the public docket 

of this AD. Submissions containing CBI 

should be sent to Anthony Kenward, 

Aerospace Engineer, AIR–7F1, Fort 

Worth ACO Branch, FAA, 10101 

Hillwood Parkway, Fort Worth, TX 

78101; telephone (817) 222–5152; email 

Anthony.Kenward@faa.gov. Any 

commentary that the FAA receives 

which is not specifically designated as 

CBI will be placed in the public docket 

for this rulemaking. 

Regulatory Flexibility Act 

The requirements of the Regulatory 

Flexibility Act (RFA) do not apply when 

an agency finds good cause pursuant to 

5 U.S.C. 553 to adopt a rule without 

prior notice and comment. Because the 

FAA has determined that it has good 

cause to adopt this rule without prior 

notice and comment, RFA analysis is 

not required. 

Costs of Compliance 

Currently, there are no affected U.S.- 

registered helicopters. As stated 

previously, there is one helicopter on 

the U.S. Register; however, the required 

actions have already been accomplished 

on that helicopter. If an affected 

helicopter is imported and placed on 

the U.S. Register in the future, the FAA 

provides the following cost estimates to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Up to 147 work-hours × $85 per hour = $12,495 ................................................................................................... (*) $12,495 

* The FAA has received no definitive data that would enable the agency to provide cost estimates for the parts cost of the required actions 

specified in this AD. 

The FAA estimates the following 

costs to do any necessary on-condition 

actions that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of helicopters that might need 

these on-condition actions: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

8 work-hours × $85 per hour = $680 ...................................................................................................................... Negligible ....... $680 

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, 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. 

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: 

2021–11–14 Leonardo S.p.a.: Amendment 

39–21576; Docket No. FAA–2021–0378; 

Project Identifier 2017–SW–122–AD. 


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Federal Register / Vol. 86, No. 107 / Monday, June 7, 2021 / Rules and Regulations 30161 

(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 

AW169 helicopters, certificated in any 

category, identified in paragraphs (c)(1) and 

(2) of this AD. 

(1) Helicopters having serial number 

69007, 69009, 69011, 69013, 69014, 69015, 

69017, 69018, 69020, 69021, 69022, 69023, 

69024, 69025, 69027, 69028, 69031, 69032, 

69041, 69042, 69043, 69044, 69049 and 

69051. 

(2) All helicopters equipped with 

retractable landing gear (LG) system part 

number (P/N) 6F3200F00311 or P/N 

6F3200F00411. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 3233, Landing Gear Actuator. 

(e) Unsafe Condition 

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. The FAA 

is issuing this AD to address failed NLG and 

main landing gear (MLG) retraction actuators. 

The unsafe condition, if not addressed, could 

result in a partially locked or unlocked NLG 

or MLG upon landing, possibly resulting in 

damage to the helicopter and injury to the 

occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modifications 

Within 200 hours time-in-service (TIS) 

after the effective date of this AD, do the 

applicable actions specified in paragraphs 

(g)(1) through (5) of this AD, in accordance 

with the applicable part of the 

Accomplishment Instructions of Leonardo 

Helicopters Alert Service Bulletin 169–023, 

Revision B, dated April 16, 2018 (ASB 169– 

023, Revision B), except as required by 

paragraph (k) of this AD. 

(1) For helicopters having S/N 69011 and 

S/N 69017 that are not equipped with 

retractable LG system P/N 6F3200F00411 

(enhanced NLG retracting actuator P/N 

6F3230V00532 and enhanced MLG retracting 

actuators P/N 6F3230V00832 and P/N 

6F3230V01032): Modify the helicopter 

(which includes replacing the actuators and 

doing checks and measurements), as 

specified in Part I of ASB 169–023, Revision 

B. 

(2) For helicopters having S/N 69007, S/N 

69015, S/N 69018, and S/N 69022 that are 

not equipped with retractable LG system P/ 

N 6F3200F00411 (enhanced NLG retracting 

actuator P/N 6F3230V00532 and enhanced 

MLG retracting actuators P/N 6F3230V00832 

and P/N 6F3230V01032): Modify the 

helicopter (which includes installing 

enhanced landing gear retracting actuators 

and doing checks and measurements), as 

specified in Part II of ASB 169–023, Revision 

B. 

(3) For helicopters having S/N 69032, S/N 

69041, and S/N 69051 that are not equipped 

with retractable LG system P/N 

6F3200F00411 (enhanced NLG retracting 

actuator P/N 6F3230V00532 and enhanced 

MLG retracting actuators P/N F3230V00832 

and P/N 6F3230V01032): Modify the 

helicopter (which includes installing 

enhanced landing gear retracting actuators 

and doing checks and measurements), as 

specified in Part III of ASB 169–023, Revision 

B. 

(4) For helicopters having S/N 69007, S/N 

69009, S/N 69011, S/N 69013, S/N 69014, S/ 

N 69015, S/N 69017, S/N 69018, S/N 69020, 

S/N 69021, S/N 69022, S/N 69023, S/N 

69024, S/N 69027, S/N 69032, S/N 69041, 

and S/N 69051: Modify the helicopter (which 

includes modifying the landing gear actuator 

control box), as specified in Part IV of ASB 

169–023, Revision B. 

(5) For helicopters having S/N 69007, S/N 

69009, S/N 69011, S/N 69013, S/N 69014, S/ 

N 69015, S/N 69017, S/N 69018, S/N 69020, 

S/N 69021, S/N 69022, S/N 69023, S/N 

69024, S/N 69025, S/N 69027, S/N 69028, S/ 

N 69031, S/N 69032, S/N 69041, S/N 69042, 

S/N 69043, S/N 69044, and S/N 69051: 

Modify the helicopter (which includes 

improving the landing gear proximity switch 

and doing checks and measurements), as 

specified in Part V of ASB 169–023, Revision 

B. 

(h) Installation Checks 

For helicopters having S/N 69009, S/N 

69013, S/N 69014, S/N 69020, S/N 69021, S/ 

N 69023, S/N 69024, S/N 69025, S/N 69027, 

S/N 69028, S/N 69031, S/N 69042, S/N 

69043, S/N 69044, and S/N 69049 that are 

equipped with both retractable LG system P/ 

N 6F3200F00311 and P/N 6F3200F00411: 

Within 200 hours TIS after the effective date 

of this AD, accomplish installation checks 

(which include measurements), in 

accordance with Part VI of the 

Accomplishment Instructions of ASB 169– 

023, Revision B, except as required by 

paragraph (k) of this AD. 

(i) NLG and MLG Up Down Lock Actuator 

Inspection 

For helicopters equipped with retractable 

LG system P/N 6F3200F00311 or P/N 

6F3200F00411: At the time specified in 

paragraph (i)(1) or (2) of this AD, whichever 

occurs first, inspect the plungers of the NLG 

and MLG up down lock actuators, in 

accordance with Part VII of the 

Accomplishment Instructions of ASB 169– 

023, Revision B, except as required by 

paragraph (k) of this AD. 

(1) Within 30 days after the effective date 

of this AD. 

(2) Concurrently with the modifications 

required by paragraphs (g)(1), (2), and (3) of 

this AD, as applicable. 

(j) Corrective Actions 

(1) If, during any modification required by 

paragraph (g)(1), (2), (3), or (5) of this AD, or 

during any installation check required by 

paragraph (h) of this AD, any discrepancy is 

detected, before further flight, accomplish the 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

ASB 169–023, Revision B, except as required 

by paragraph (k) of this AD. For this AD, 

discrepancies include gaps between parts 

that are not within tolerances, improperly 

aligned rotational axis of certain parts, nonparallel lever for certain parts, a certain pin 

is not installed on the MLGs, and incorrect 

thickness of certain washers. 

(2) If, during any inspection required by 

paragraph (i) of this AD, corrosion is 

detected, before further flight, accomplish the 

applicable corrective action and apply 

corrosion inhibitor on the plungers of the 

NLG and MLG up down lock actuators, in 

accordance with Part VII of the 

Accomplishment Instructions of ASB 169– 

023, Revision B, except as required by 

paragraph (k) of this AD. 

(3) If, during any inspection required by 

paragraph (i) of this AD, no corrosion is 

detected, before further flight, apply 

corrosion inhibitor on the plungers of the 

NLG and MLG up down lock actuators, in 

accordance with Part VII of the 

Accomplishment Instructions of ASB 169– 

023, Revision B, except as required by 

paragraph (k) of this AD. 

(k) Service Information Exceptions 

(1) Where ASB 169–023, Revision B, 

specifies to discard certain parts, this AD 

requires removing those parts from service. 

(2) Where ASB 169–023, Revision B, 

specifies to contact the manufacturer, before 

further flight, repair using a method 

approved by the Manager, International 

Validation Branch, FAA. For a repair method 

to be approved by the Manager, International 

Validation Branch, as required by this 

paragraph, the Manager’s approval letter 

must specifically refer to this AD. 

(3) Where ASB 169–023, Revision B, 

specifies to return certain parts, this AD does 

not include that requirement. 

(l) No Reporting Requirement 

Although ASB 169–023, Revision B, 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(m) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraphs (g), (h), (i), 

and (j) of this AD, if those actions were 

performed before the effective date of this AD 

using Leonardo Helicopters Alert Service 

Bulletin 169–023, dated May 31, 2017, 

provided that, for helicopters on which Part 

V of that service information was 

accomplished, the adhesive fixing of the NLG 

and MLG support buffers is replaced within 

3 months after the effective date of this AD. 

The replacement must be done in accordance 

with steps 1., 2., 8.3, 8.4, 18., and 20. of Part 

V of the Accomplishment Instructions of 

ASB 169–023, Revision B, except as specified 

in paragraph (k) of this AD. 

(2) This paragraph provides credit for 

actions required by paragraphs (g), (h), (i), 

and (j) of this AD, if those actions were 

performed before the effective date of this AD 

using Leonardo Helicopters Alert Service 

Bulletin 169–023, Revision A, dated 

September 1, 2017. 


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30162 Federal Register / Vol. 86, No. 107 / Monday, June 7, 2021 / Rules and Regulations 

(n) 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 certification office, 

send it to the attention of the person 

identified in paragraph (o)(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. 

(o) Related Information 

(1) For more information about this AD, 

contact Anthony Kenward, Aerospace 

Engineer, AIR–7F1, Fort Worth ACO Branch, 

FAA, 10101 Hillwood Parkway, Fort Worth, 

TX 78101; telephone (817) 222–5152; email 

Anthony.Kenward@faa.gov. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (now 

European Union Aviation Safety Agency) 

(EASA) AD 2017–0164, dated September 4, 

2017. You may view the EASA AD on the 

internet at https://www.regulations.gov in the 

AD Docket. 

(p) 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) Leonardo Helicopters Alert Service 

Bulletin 169–023, Revision B, dated April 16, 

2018. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Leonardo S.p.A. Helicopters, 

Emanuele Bufano, Head of Airworthiness, 

Viale G.Agusta 520, 21017 C.Costa di 

Samarate (Va) Italy; telephone +39–0331– 

225074; fax +39–0331–229046; or at https:// 

www.leonardocompany.com/en/home. 

(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 19, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–11806 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–2021–0196; Project 

Identifier 2018–SW–021–AD; Amendment 

39–21571; AD 2021–11–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Deutschland GmbH Model 

MBB–BK 117 A–1, MBB–BK 117 A–3, 

MBB–BK 117 A–4, MBB–BK 117 B–1, 

MBB–BK 117 B–2, and MBB–BK 117 C– 

1 helicopters. This AD was prompted by 

an analysis of the main rotor (M/R) 

blade loop area. This AD requires 

repetitive inspections of certain M/R 

blade thimble areas and corrective 

actions if necessary, as specified in a 

European Aviation Safety Agency (now 

European Union Aviation Safety 

Agency) (EASA) AD, which is 

incorporated by reference (IBR). 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 a certain publication listed in this AD 

as of July 12, 2021. 

ADDRESSES: For EASA material in this 

AD, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; 

telephone +49 221 8999 000; email 

ADs@easa.europa.eu; internet 

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

material on the EASA website at https:// 

ad.easa.europa.eu. You may view this 

material 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. It is also 

available on the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0196. 

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–2021– 

0196; 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 EASA AD, 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; telephone 

(206) 231–3218; email 

kathleen.arrigotti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2018– 

0061, dated March 20, 2018 (EASA AD 

2018–0061), to correct an unsafe 

condition for Airbus Helicopters 

Deutschland GmbH (AHD) (formerly 

Eurocopter Deutschland GmbH, 

Eurocopter Hubschrauber GmbH, 

Messerschmitt-Bo ̈lkow-Blohm GmbH), 

Airbus Helicopters Inc. (formerly 

American Eurocopter LLC) Model MBB– 

BK117 A–1, MBB–BK117 A–3, MBB– 

BK117 A–4, MBB–BK117 B–1, MBB– 

BK117 B–2, and MBB–BK117 C–1 

helicopters, all serial numbers. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to Airbus Helicopters 

Deutschland GmbH Model MBB–BK 117 

A–1, MBB–BK 117 A–3, MBB–BK 117 

A–4, MBB–BK 117 B–1, MBB–BK 117 

B–2, and MBB–BK 117 C–1 helicopters 

with an ‘‘affected ‘angle 0’ parts’’ or 

‘‘affected ‘angle 1’ parts’’ installed, as 

identified in EASA AD 2018–0061. The 

NPRM published in the Federal 

Register on March 26, 2021 (86 FR 

16121). The NPRM was prompted by 

new test results from an analysis of the 

M/R blade loop area, which revealed 

that certain M/R blade thimbles require 

reduced inspection intervals. The 

NPRM proposed to require repetitive 

inspections of certain M/R blade 

thimble areas and corrective actions if 

necessary, as specified in EASA AD 

2018–0061. The FAA is issuing this AD 

to address composite failure of the M/ 

R blades, resulting in loss of control of 


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