35692 Federal Register / Vol. 86, No. 127 / Wednesday, July 7, 2021 / Proposed Rules 

FAA is issuing this AD to address spurious 

degradation or unavailability of the full 

AFCS. The unsafe condition, if not 

addressed, could result in temporary 

impairment of the automated flight aid for 

control of the helicopter and increase the 

flightcrew’s workload. 

(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 Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD 2018–0002, dated 

January 4, 2018 (EASA AD 2018–0002). 

(h) Exceptions to EASA AD 2018–0002 

(1) Where EASA AD 2018–0002 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(2) Where EASA AD 2018–0002 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

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

2018–0002 does not apply to this AD. 

(4) Where the service information 

referenced in EASA AD 2018–0002 specifies 

to download an option file from a certain 

website, that method of installation is not 

required by this AD. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2018–0002 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(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)(2) 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 

(1) For EASA AD 2018–0002, contact 

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 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. 

This material may be found in the AD docket 

at https://www.regulations.gov by searching 

for and locating Docket No. FAA–2021–0505. 

(2) For more information about this AD, 

contact Hal Jensen, Aerospace Engineer, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 L’Enfant 

Plaza N SW, Washington, DC 20024; 

telephone (202) 267–9167; email hal.jensen@

faa.gov. 

Issued on June 15, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–14401 Filed 7–6–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0497; Project 

Identifier 2019–SW–043–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Canada Limited Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Bell Textron Canada Limited 

Model 429 helicopters. This proposed 

AD was prompted by three reports of 

unexpected forces or uncommanded 

inputs to the directional (yaw) control 

system. This proposed AD would 

require revising the existing Rotorcraft 

Flight Manual (RFM) for your 

helicopter. The FAA is proposing this 

AD to address the unsafe condition on 

these products. 

DATES: The FAA must receive comments 

on this proposed AD by August 23, 

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

Monday through Friday, except Federal 

holidays. 

For service information identified in 

this NPRM, contact Bell Textron Canada 

Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4, Canada; 

telephone (450) 437–2862 or (800) 363– 

8023; fax (450) 433–0272; or at https:// 

www.bellcustomer.com. 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0497; 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 

NPRM, the Transport Canada AD, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Mitch Soth, Flight Test Engineer, 

Southwest Section, Flight Test Branch, 

Compliance & Airworthiness Division, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222– 

5110; email mitch.soth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2021–0497; Project Identifier 

2019–SW–043–AD’’ at the beginning of 

your comments. The most helpful 

comments reference a specific portion of 

the proposal, 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 proposal 

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 

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 NPRM. 

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 


khammond on DSKJM1Z7X2PROD with PROPOSALS
Federal Register / Vol. 86, No. 127 / Wednesday, July 7, 2021 / Proposed Rules 35693 

comments responsive to this NPRM 

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 NPRM, 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 

NPRM. Submissions containing CBI 

should be sent to Mitch Soth, Flight 

Test Engineer, Southwest Section, Flight 

Test Branch, Compliance & 

Airworthiness Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

mitch.soth@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. 

Background 

Transport Canada, which is the 

aviation authority for Canada, has 

issued Transport Canada Emergency AD 

CF–2019–16, dated May 6, 2019 

(Transport Canada AD CF–2019–16), to 

correct an unsafe condition for Bell 

Helicopter Textron Canada Limited 

(now Bell Textron Canada Limited) 

Model 429 helicopters, serial numbers 

57001 and subsequent. Transport 

Canada advises of three reports of 

unexpected forces or uncommanded 

inputs to the directional (yaw) control 

system during ground operations. 

Investigation revealed that a yaw trim 

runaway can occur while the automatic 

pedal trim function is operating. This 

condition, if not addressed, could result 

in loss of control of the helicopter. 

Accordingly, Transport Canada AD CF– 

2019–16 requires revising Bell RFM 

BHT–429–FM–1 by incorporating 

revision 14, dated April 18, 2019. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to the FAA’s bilateral 

agreement with Canada, Transport 

Canada, its technical representative, has 

notified the FAA of the unsafe condition 

described in its AD. The FAA is 

proposing this AD after evaluating all 

known relevant information and 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other helicopters of the same 

type design. 

Related Service Information 

The FAA reviewed Section 2—Normal 

Procedures, Section 3—Emergency and 

Malfunction Procedures, and Section 

4—Performance, of Bell RFM BHT–429– 

FM–1, Revision 14, dated April 18, 

2019. This revision of the service 

information adds a procedure to reduce 

the risk of trim runaway during start 

sequence, cautions to reduce the risk of 

uncommanded control movement 

during engine start and takeoff and resetting force trim detent instructions 

during engine start and takeoff, and an 

emergency procedure to assist flight 

crew to recognize trim runaway and 

response instructions. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

revising the existing RFM for your 

helicopter by adding procedures in 

Section 2, Normal Procedures, under 2– 

4. INTERIOR AND PRESTART CHECK, 

2–5. ENGINE START, and 2–8. 

TAKEOFF; Section 3, Emergency and 

Malfunction Procedures, under 3–9. 

AUTOMATIC FLIGHT CONTROL 

SYSTEM; and Section 4, Performance, 

under 4–2. POWER ASSURANCE 

CHECK. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 120 

helicopters of U.S. Registry. Labor rates 

are estimated at $85 per work-hour. 

Based on these numbers, the FAA 

estimates the following costs to comply 

with this proposed AD. 

Revising the existing RFM for your 

helicopter would take about 0.50 workhour for an estimated cost of $43 per 

helicopter and $5,160 for the U.S. fleet. 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 

this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would 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 Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Bell Textron Canada Limited: Docket No. 

FAA–2021–0497; Project Identifier 

2019–SW–043–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by August 23, 

2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bell Textron Canada 

Limited Model 429 helicopters, certificated 

in any category, serial numbers 57001 and 

subsequent. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720, Tail Rotor Control System. 


khammond on DSKJM1Z7X2PROD with PROPOSALS
35694 Federal Register / Vol. 86, No. 127 / Wednesday, July 7, 2021 / Proposed Rules 

(e) Unsafe Condition 

This AD was prompted by three reports of 

unexpected forces or uncommanded inputs 

to the directional (yaw) control system. The 

FAA is issuing this AD to prevent yaw trim 

runaway. The unsafe condition, if not 

addressed, could result in loss of control of 

the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 30 days after the effective date 

of this AD, revise the existing Rotorcraft 

Flight Manual for your helicopter as follows: 

(i) In Section 2, Normal Procedures, under 

2–4. INTERIOR AND PRESTART CHECK, 

add the following as item 25: ‘‘25. Depress 

the cyclic force TRIM REL button and 

collective FORCE REL button (4-axis only) to 

center actuators and extinguish any active 

out of detent indications.’’ 

(ii) In Section 2, Normal Procedures, under 

2–5. ENGINE START and under 2–8. 

TAKEOFF, add the following above item 1: 

‘‘CAUTION: WHEN MANIPULATING 

FLIGHT CONTROLS WITH FORCE TRIM 

SELECTED ON, DO NOT RELEASE 

AFFECTED FLIGHT CONTROL UNTIL THE 

OUT OF DETENT INDICATION 

EXTINGUISHES. THE FLIGHT CONTROLS 

MAY BE RESET BY DEPRESSING THE 

CYCLIC FORCE TRIM REL BUTTON AND 

COLLECTIVE FORCE REL BUTTON (4–AXIS 

ONLY) UNTIL THE OUT OF DETENT 

INDICATION EXTINGUISHES.’’ 

(iii) In Section 3, Emergency and 

Malfunction Procedures, under 3–9. 

AUTOMATIC FLIGHT CONTROL SYSTEM, 

add the information in Figure 1 to paragraph 

(g)(1)(iii) of this AD as item 3–9–D: 

(iv) In Section 4, Performance, under 4–2. 

POWER ASSURANCE CHECK, add the 

following above the instructions for 

performing a power assurance check: 

‘‘CAUTION: WHEN MANIPULATING 

FLIGHT CONTROLS WITH FORCE TRIM 

SELECTED ON, DO NOT RELEASE 

AFFECTED FLIGHT CONTROL UNTIL THE 

OUT OF DETENT INDICATION 

EXTINGUISHES. THE FLIGHT CONTROLS 

MAY BE RESET BY DEPRESSING THE 

CYCLIC FORCE TRIM REL BUTTON AND 

COLLECTIVE FORCE REL BUTTON (4–AXIS 

ONLY) UNTIL THE OUT OF DETENT 

INDICATION EXTINGUISHES.’’ 

(2) Using a document with information 

identical to the information in paragraph 

(g)(1) of this AD is acceptable for compliance 

with the actions required by paragraph (g)(1) 

of this AD. 

(3) The actions required by paragraphs 

(g)(1) and (2) of this AD may be performed 

by the owner/operator (pilot) holding at least 

a private pilot certificate and must be entered 

into the aircraft records showing compliance 

with this AD in accordance with § 43.9(a)(1) 

through (4) and § 91.417(a)(2)(v). The record 

must be maintained as required by § 91.417, 

§ 121.380, or § 135.439. 

(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 Mitch Soth, Flight Test Engineer, 


khammond on DSKJM1Z7X2PROD with PROPOSALSEP07JY21.070</GPH>

3-9-D. TRIM RUNAWAY 

• INDICATIONS: 

Flight controls - Uncommanded movement. 

Flight control forces - High in axis of uncommanded movement, 

normal in other axes. 

Out of detent indication for affected axis 

• PROCEDURE: 

1. Cyclic force TRIM REL and/or collective FORCE REL button 

(4-axis only)-Depress until the out of detent indication extinguishes. 

2. Flight controls - Do not release flight control if out of detent 

indication is present. 

3. Force TRIM switch-OFF; check TRM OFF illuminates on PFD. 

4. IfIMC, land as soon as practical. IfVMC, continue flight in SCAS. 

Figure 1 to paragraph (g)(l)(iii) 
Federal Register / Vol. 86, No. 127 / Wednesday, July 7, 2021 / Proposed Rules 35695 

Southwest Section, Flight Test Branch, 

Compliance & Airworthiness Division, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

mitch.soth@faa.gov. 

(2) The subject of this AD is addressed in 

Transport Canada Emergency AD CF–2019– 

16, dated May 6, 2019. You may view the 

Transport Canada AD on the internet at 

https://www.regulations.gov in Docket No. 

FAA–2021–0497. 

Issued on June 10, 2021. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–14400 Filed 7–6–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–500; Project 

Identifier 2017–SW–069–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

Airbus Helicopters Model EC130B4 and 

EC130T2 helicopters. This proposed AD 

was prompted by a report of a jammed 

pilot collective pitch lever (collective). 

This proposed AD would require 

inspecting the collective for proper 

engagement of the locking pin. The FAA 

is proposing this AD to address the 

unsafe condition on these products. 

DATES: The FAA must receive comments 

on this proposed AD by August 23, 

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

Monday through Friday, except Federal 

holidays. 

For service information identified in 

this NPRM, contact Airbus Helicopters, 

2701 North 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. You 

may view the 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–500; 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 

NPRM, 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, Aviation Safety 

Engineer, Fort Worth ACO Branch, 

Compliance & Airworthiness Division, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222– 

5152; email anthony.kenward@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2021–500; Project Identifier 2017– 

SW–069–AD’’ at the beginning of your 

comments. The most helpful comments 

reference a specific portion of the 

proposal, 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 proposal 

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 

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 NPRM. 

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 NPRM 

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 NPRM, 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 

NPRM. Submissions containing CBI 

should be sent to Anthony Kenward, 

Aviation Safety Engineer, Fort Worth 

ACO Branch, Compliance & 

Airworthiness Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

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. 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0062, 

dated April 11, 2017 (EASA AD 2017– 

0062), to correct an unsafe condition for 

Airbus Helicopters Model EC130B4 and 

EC130T2 helicopters. EASA states that 

during an autorotation test conducted 

during an acceptance flight, the pilot 

felt a jamming sensation when pushing 

the collective to the low pitch position, 

and he subsequently was able to free the 

collective by pulling on it. According to 

EASA, an analysis determined that the 

locking tab hook (hook) and the low 

pitch locking pin (pin) were extremely 

close, and that a fold in the control lever 

boot may have become caught between 

the two components. EASA states that 

this condition, if not detected and 

corrected, could result in an untimely 

locking of the collective and subsequent 

reduced control of the helicopter. 

Accordingly, EASA AD 2017–0062 

requires inspecting and adjusting, if 

necessary, the clearance between the 

hook and the pin while in the low pitch 

position. 

FAA’s Determination 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA about the unsafe condition 

described in its AD. The FAA is 

proposing this AD after evaluating all 


khammond on DSKJM1Z7X2PROD with PROPOSALS