This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

51022 

Vol. 86, No. 175 

Tuesday, September 14, 2021 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0283; Project 

Identifier 2018–SW–045–AD] 

RIN 2120–AA64 

Airworthiness Directives; Leonardo 

S.p.a. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: The FAA is revising an earlier 

proposal for certain Leonardo S.p.a. 

Model AB139 and AW139 helicopters. 

This action revises the notice of 

proposed rulemaking (NPRM) by 

expanding the required actions. This 

proposed AD would require various 

inspections of certain main rotor (MR) 

dampers, as specified in a European 

Aviation Safety Agency (now European 

Union Aviation Safety Agency) (EASA) 

AD, which is proposed for incorporation 

by reference (IBR). This proposed AD 

would also require reducing the torque 

of the MR damper hub attachment bolts, 

installing a special washer, installing a 

certain part-numbered MR damper, and 

prohibit installing other part-numbered 

MR dampers. The FAA is proposing this 

airworthiness directive (AD) to address 

the unsafe condition on these products. 

Since these actions would impose an 

additional burden over those in the 

NPRM, the FAA is requesting comments 

on this SNPRM. 

DATES: The comment period for the 

NPRM published in the Federal 

Register on March 31, 2020 (85 FR 

17788), is reopened. 

The FAA must receive comments on 

this SNPRM by October 29, 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 

p.m., Monday through Friday, except 

Federal holidays. 

For material that is proposed for IBR 

in this AD, contact the EASA, KonradAdenauer-Ufer 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 in the AD docket on the 

internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2020–0283. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0283; 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 SNPRM, 

any comments received, and other 

information. The street address for 

Docket Operations is listed above. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, AD Program Manager, General 

Aviation & Rotorcraft Unit, 

Airworthiness Products Section, 

Operational Safety Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

matthew.fuller@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–2020–0283; Project Identifier 

2018–SW–045–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 proposal. 

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 SNPRM 

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 SNPRM, 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 SNPRM. Submissions containing 

CBI should be sent to Matt Fuller, AD 

Program Manager, General Aviation & 

Rotorcraft Unit, Airworthiness Products 

Section, Operational Safety Branch, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222– 

5110; email matthew.fuller@faa.gov. 

Any commentary that the FAA receives 

that is not specifically designated as CBI 

will be placed in the public docket for 

this rulemaking. 

Background 

The FAA issued an NPRM to amend 

14 CFR part 39 by adding an AD that 

would apply to certain serial-numbered 

Leonardo S.p.A. Model AB139 and 

AW139 helicopters with an MR damper 

part number (P/N) 3G6220V01351, 

3G6220V01352, or 3G6220V01353 


tkelley on DSK125TN23PROD with PROPOSALS
Federal Register / Vol. 86, No. 175 / Tuesday, September 14, 2021 / Proposed Rules 51023 

installed. The NPRM published in the 

Federal Register on March 31, 2020 (85 

FR 17788). In the NPRM, the FAA 

proposed to require, for an affected 

helicopter with MR damper P/N 

3G6220V01351, 3G6220V01352, or 

3G6220V01353 installed, reducing the 

installation torque of each hub 

attachment bolt for each MR damper. 

For an affected helicopter with MR 

damper P/N 3G6220V01351 or 

3G6220V01352 installed, the NPRM 

proposed to require: Repetitively 

inspecting the MR damper rod end (rod 

end) and MR damper body end (body 

end) for a crack; dye penetrant 

inspecting or eddy current inspecting 

certain rod and body ends for a crack; 

repetitively inspecting the rod and body 

end bearings for rotation in the damper 

seat and for misaligned slippage marks; 

repetitively inspecting the rod end 

broached ring nut; and repetitively 

inspecting the bearing friction torque 

value of the body and rod ends, and the 

MR damper anti-rotation block. 

Depending on the results of the various 

inspections, the NPRM proposed to 

require removing a part from service or 

replacing a part. For an affected 

helicopter with MR damper P/N 

3G6220V01351 or 3G6220V01352 

installed, the NPRM also proposed to 

require inspecting each rod end to 

determine if special washer P/N 

3G6220A05052 is installed, and 

depending on the results, aligning the 

rod ends and broached rings, replacing 

any broached ring that cannot be 

aligned, inspecting the broached rings 

for wear and damage, and replacing the 

broached ring and installing a special 

washer. Lastly, the NPRM proposed to 

require installing MR damper P/N 

3G220V01353, prohibit installing MR 

damper P/N 3G6220V01351 and P/N 

3G6220V01352 on any helicopter, and 

allow the installation of MR damper 

P/N 3G220V01353 to constitute 

terminating action for all of the 

proposed repetitive required actions. 

The NPRM was prompted by EASA 

AD 2018–0112R1, dated June 4, 2018 

(EASA AD 2018–0112R1), which is the 

most recent of a series of ADs issued by 

EASA, the Technical Agent for the 

Member States of the European Union, 

to correct an unsafe condition for 

certain Leonardo S.p.A. Helicopters 

(formerly Finmeccanica S.p.A., 

Helicopter Division (FHD), 

AgustaWestland S.p.A., Agusta S.p.A.), 

AgustaWestland Philadelphia 

Corporation (formerly Agusta Aerospace 

Corporation) Model AB139 and AW139 

helicopters. EASA advises of multiple 

failures of MR damper P/Ns 

3G6220V01351 and 3G6220V01352. 

EASA states that in some cases these 

failures occurred at the eye end and 

body lugs resulting in disconnection of 

the MR damper in-flight. EASA further 

states that a combination of factors, 

including cracks on the MR damper rod 

end and body end and in-service failure 

of the eye end and body lugs may have 

contributed to the MR damper 

disconnections. Information issued by 

Leonardo Helicopters advises of MR 

damper cracking, loose rod ends, 

bearing rotation in the damper seat, and 

damage, incorrect engagement, and 

misalignment of the lag damper 

broached ring nut, particularly the 

broached ring teeth and the damper 

piston slots. 

EASA states that this condition could 

result in loss of the lead-lag damping 

function of the MR blade, damage to 

adjacent critical rotor components, and 

subsequent reduced control of the 

helicopter. Accordingly, EASA AD 

2018–0112R1 requires various one-time 

and repetitive inspections of the MR 

damper, a torque check of the damper 

body end, and replacing any MR 

damper with a crack or that fails the 

torque check. EASA AD 2018–0112R1 

also requires replacing MR damper P/N 

3G6220V01351 and 3G6220V01352 with 

P/N 3G220V01353, as additional tests 

determined that MR damper P/N 

3G220V01353 does not need to be 

subject to inspections for cracks, 

provided it is removed from service 

before it reaches its retirement life. 

Actions Since the NPRM Was Issued 

Since the NPRM was issued, the FAA 

identified an action required by EASA 

AD 2018–0112R1 that was inadvertently 

omitted in the NPRM and incorrect 

thresholds for different actions 

proposed in the NPRM. The NPRM 

omitted the one-time dye penetrant 

inspection for any MR dampers that 

have accumulated 300 or more total 

hours time-in-service (TIS). The NPRM 

also stated incorrect thresholds to 

inspect each rod end bearing and body 

end bearing for rotation. The NPRM 

proposed to require those inspections 

based on the total hours TIS 

accumulated by the MR damper, when 

the thresholds for those inspections 

should have been based on the total 

hours TIS accumulated by the rod end 

and body end, independently. This 

SNPRM makes those updates. 

The NPRM also inadvertently omitted 

the option to accomplish an eddy 

current inspection for some inspections. 

This SNPRM adds that alternative for 

those inspections. 

Lastly, this SNPRM utilizes the FAA’s 

new practice of proposing to incorporate 

EASA AD 2018–0112R1 by reference. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this proposed AD. The FAA has 

considered the comment received. 

Request To Reduce the Applicability 

One commenter requested removing 

MR damper P/N 3G6220V01353 from 

the applicability. The commenter stated 

that the only requirement in this AD for 

that P/N is to reduce the torque on the 

body end of the MR damper and that 

procedures for this are available in the 

Interactive Electronic Technical 

Publications (IETP). The commenter 

asked if the intent is to capture any MR 

damper P/N 3G6220V01353 installed 

prior to the current IETP revisions with 

an incorrect torque. The commenter 

further stated that part II of Leonardo 

Helicopters Alert Service Bulletin No. 

139–452, Revision B, dated April 10, 

2018 (ASB 139–452 Rev B), is not 

applicable to MR damper P/N 

3G6220V01353. 

The FAA disagrees. The commenter is 

correct that part II of ASB 139–452 Rev 

B is not applicable to MR damper P/N 

3G6220V01353; however, part I of ASB 

139–452 Rev B, which specifies 

procedures to reduce the torque of the 

nut on the bolt attaching each MR 

damper to the MR hub, is applicable to 

MR damper P/N 3G6220V01353. 

Additionally, the FAA appreciates that 

while the procedures to reduce that 

torque may now be available in the 

IETP, not all operators are required to 

accomplish manufacturer’s maintenance 

procedures. Where the FAA has 

determined that procedures, including 

manufacturer’s maintenance 

procedures, are necessary to correct an 

unsafe condition, the FAA must issue 

an AD. 

FAA’s Determination 

These products have been approved 

by the aviation authority of another 

country, and are approved for operation 

in the United States. Pursuant to the 

bilateral agreement with the State of 

Design Authority, the FAA has been 

notified of the unsafe condition 

described in EASA AD 2018–0112R1 

referenced above. The FAA is proposing 

this AD after evaluating all the relevant 

information and determining the unsafe 

condition described previously is likely 

to exist or develop in other products of 

these same type designs. 

Certain changes described above 

expand the scope of the NPRM. As a 

result, the FAA has determined that it 

is necessary to reopen the comment 

period to provide additional 

opportunity for the public to comment 

on this SNPRM. 


tkelley on DSK125TN23PROD with PROPOSALS
51024 Federal Register / Vol. 86, No. 175 / Tuesday, September 14, 2021 / Proposed Rules 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2018–0112R1 requires 

reducing the installation torque of the 

bolts affixing each affected MR damper 

to the MR hub. For certain affected MR 

dampers, EASA AD 2018–0112R1 

requires a one-time dye penetrant 

inspection of the rod and body ends, 

and a repetitive detailed visual 

inspection of the rod and body ends. 

EASA AD 2018–0112R1 allows an eddy 

current inspection as an alternative to 

those inspections. For certain affected 

MR dampers, EASA AD 2018–0112R1 

also requires repetitively inspecting the 

rod and body end bearings for rotation, 

visually inspecting the rod end 

broached ring nut, accomplishing a 

bearing friction inspection of the body 

and rod end bearings, and a detailed 

inspection of the anti-rotation block. 

EASA AD 2018–0112R1 also requires a 

one-time visual inspection of certain 

affected MR damper rod end 

installations and a torque check of the 

MR damper broached ring nut. For 

certain affected MR dampers, EASA AD 

2018–0112R1 requires replacing any 

special washer P/N 3G6220A05051 with 

a new washer P/N 3G6220A05052. If 

there is a crack or damage detected in 

any inspection, EASA AD 2018–0112R1 

requires contacting Leonardo and, if the 

discrepancy is confirmed, replacing the 

MR damper. EASA AD 2018–0112R1 

also requires corrective actions if any 

discrepancy is detected in the 

inspections for rotation, friction, and 

torque. EASA AD 2018–0112R1 allows 

installing MR damper P/N 

3G6220V01353 on a helicopter, 

provided that it is installed using the 

correct torque values. Lastly, EASA AD 

2018–0112R1 prohibits installing MR 

damper P/N 3G6220V01351 and P/N 

3G6220V01352 on any helicopter. 

This material is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

Proposed AD Requirements of This 

SNPRM 

This proposed AD would require 

accomplishing the actions specified in 

EASA AD 2018–0112R1, described 

previously, as incorporated by 

reference, except for any differences 

identified as exceptions in the 

regulatory text of this AD and except as 

discussed under ‘‘Differences Between 

this Proposed AD and the EASA AD.’’ 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA developed a process to 

use some civil aviation authority (CAA) 

ADs as the primary source of 

information for compliance with 

requirements for corresponding FAA 

ADs. The FAA has been coordinating 

this process with manufacturers and 

CAAs. As a result, the FAA proposes to 

incorporate EASA AD 2018–0112R1 by 

reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with EASA AD 2018– 

0112R1 in its entirety through that 

incorporation, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

Using common terms that are the same 

as the heading of a particular section in 

EASA AD 2018–0112R1 does not mean 

that operators need comply only with 

that section. For example, where the AD 

requirement refers to ‘‘all required 

actions and compliance times,’’ 

compliance with this AD requirement is 

not limited to the section titled 

‘‘Required Action(s) and Compliance 

Time(s)’’ in EASA AD 2018–0112R1. 

Service information referenced in EASA 

AD 2018–0112R1 for compliance will be 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2020–0283 after the FAA final 

rule is published. 

Differences Between This Proposed AD 

and the EASA AD 

Where EASA AD 2018–0112R1 

requires the compliance time of after the 

last flight (ALF) of the day inspection, 

this proposed AD would require the 

compliance time of before the first flight 

of the day. Some compliance times in 

EASA AD 2018–0112R1 are on 

condition of part removal or 

replacement, whereas this proposed AD 

would not include those compliance 

times. EASA AD 2018–0112R1 requires 

a torque check of the MR damper 

broached ring nut, whereas this 

proposed AD would require a torque 

inspection instead to clarify that the 

action must be accomplished by a 

mechanic that meets the requirements of 

14 CFR part 65 subpart D. EASA AD 

2018–0112R1 requires making sure that 

there are no scratches or dents on the 

rod end, however it does not state 

corrective action for this requirement; 

this proposed AD would require 

removing the rod end from service if 

there is a scratch or dent on the rod end. 

Where EASA AD 2018–0112R1 requires 

contacting Leonardo and replacing the 

MR damper with a serviceable part, this 

proposed would require replacing or 

removing parts from service instead. 

Where EASA AD 2018–0112R1 requires 

accomplishing applicable corrective 

action(s) as specified in, and in 

accordance with, the instructions in 

service information, this proposed AD 

would require removing parts from 

service for some of the corrective 

actions instead. Where EASA AD 2018– 

0112R1 requires a one-time dye 

penetrant inspection of certain rod ends 

when installed, this proposed AD would 

not. Instead, this proposed AD would 

prohibit installing certain rod ends that 

are not marked with a black dot and 

therefore have not been inspected. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 126 

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. 

Performing the MR damper 

inspections would take about 24 workhours, for an estimated cost of $2,040 

per helicopter and $257,040 for the U.S. 

fleet, per inspection cycle. 

Replacing a rod end would take about 

3 work-hours and parts would cost 

about $500, for an estimated cost of 

$755 per rod end. Replacing a broached 

ring and broached ring nut would take 

about 3 work-hours and parts would 

cost about $125, for an estimated cost of 

$380 per broached ring and broached 

ring nut. Replacing an anti-rotation 

block would take about 3 work-hours 

and parts would cost about $50, for an 

estimated cost of $305 per anti-rotation 

block. Replacing an MR damper would 

take about 2 work-hours and parts 

would cost about $18,000, for an 

estimated cost of $18,170 per MR 

damper. 

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 


tkelley on DSK125TN23PROD with PROPOSALS
Federal Register / Vol. 86, No. 175 / Tuesday, September 14, 2021 / Proposed Rules 51025 

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 above, 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: 

Leonardo S.p.a.: Docket No. FAA–2020– 

0283; Project Identifier 2018–SW–045–AD. 

(a) Comments Due Date 

The FAA must receive comments by 

October 29, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

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

AB139 and AW139 helicopters, certificated 

in any category, as identified in European 

Aviation Safety Agency (now European 

Union Aviation Safety Agency) (EASA) AD 

2018–0112R1, dated June 4, 2018 (EASA AD 

2018–0112R1). 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200, Main Rotor System. 

(e) Unsafe Condition 

This AD was prompted by reports of failed 

main rotor (MR) dampers. The FAA is issuing 

this AD to address a crack in an MR damper. 

The unsafe condition, if not addressed, could 

result in seizure of the MR damper, 

detachment of the MR damper in-flight, and 

subsequent loss of control of the helicopter. 

(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 2018–0112R1. 

(h) Exceptions to EASA AD 2018–0112R1 

(1) Where EASA AD 2018–0112R1 requires 

compliance in terms of flight hours (FH), this 

AD requires using hours time-in-service 

(TIS). 

(2) Where EASA AD 2018–0112R1 refers to 

FH accumulated by a part since new (first 

installation on a helicopter) or since 

overhaul, this AD requires using total hours 

TIS. 

(3) Where EASA AD 2018–0112R1 refers to 

its effective date; May 10, 2016 (the effective 

date of EASA AD 2016–0087, dated May 3, 

2016); July 28, 2016 (the effective date of 

EASA AD 2016–0140, dated July 14, 2016); 

or September 11, 2017 (the effective date of 

EASA AD 2017–0160, dated August 28, 

2017), this AD requires using the effective 

date of this AD. 

(4) Where EASA AD 2018–0112R1 requires 

the compliance time of during an ‘‘after the 

last flight (ALF) of the day inspection,’’ this 

AD requires the compliance time of before 

the first flight of the day. 

(5) Where the service information 

referenced in EASA AD 2018–0112R1 

specifies using a magnifying glass, this AD 

requires using a 5X or higher power 

magnifying glass. 

(6) Where the service information 

referenced in EASA AD 2018–0112R1 

specifies discarding parts, this AD requires 

removing those parts from service. 

(7) Where paragraph (2) of EASA AD 2018– 

0112R1 requires compliance within 30 FH 

after 10 May 2016 (the effective date of EASA 

AD 2016–0087, dated May 3, 2016), or at the 

first MR damper removal, whichever occurs 

first, for a MR damper that has accumulated 

300 or more FH, this AD requires compliance 

within 30 hours TIS after the effective date 

of this AD for a MR damper that has 

accumulated 300 or more total hours TIS. 

(8) This AD does not require the actions 

required by paragraph (3) of EASA AD 2018– 

0112R1. 

(9) Where paragraph (8) of EASA AD 2018– 

0112R1 refers to having a serial number (S/ 

N) specified in Part V of FHD BT 139–450, 

this AD requires the actions of that paragraph 

for helicopters with an MR damper part 

number (P/N) 3G6220V01351 or 

3G6220V01352 with an S/N up to MCR8086 

inclusive, installed, that has accumulated 

less than 600 total hours TIS. 

(10) Where paragraph (10) of EASA AD 

2018–0112R1 refers to having an S/N 

specified in in Part VII of FHD BT 139–450, 

this AD requires the actions of that paragraph 

for helicopters with: 

(i) MR damper P/N 3G6220V01351 or 

3G6220V01352 with an S/N up to MCR8764 

inclusive, and with rod end P/N M006– 

01H004–041, –045, or –053, installed, except 

MR dampers confirmed of having 60–80 Nm 

applied and MR dampers marked with ‘‘BT 

139–446 Part II’’ or ‘‘BT 139–446 Part III’’ on 

the logcard; or 

(ii) MR damper P/N 3G6220V01351 or 

3G6220V01352 that has had the damper rod 

end assembly removed before the issuance of 

‘‘BT 139–446’’ installed, even if it has an S/ 

N higher than MCR8764 or it has been 

confirmed of having 60–80 Nm applied. 

Note 1 to paragraph (h)(10): MR dampers 

confirmed of having 60–80 Nm applied are 

listed in Table 1 (two pages) of Annex A, of 

Leonardo Helicopters Alert Service Bulletin 

No. 139–450, Revision D, dated May 28, 

2019. 

(11) Where paragraph (10) of EASA AD 

2018–0112R1 requires a torque check, this 

AD requires a torque inspection. 

(12) Where the service information 

referenced in paragraph (10) of EASA AD 

2018–0112R1 specifies making sure that 

there are not scratches or dents on the rod 

end, this AD requires, before further flight, 

removing the rod end from service if there is 

a scratch or dent on the rod end. 

(13) Where paragraph (12) of EASA AD 

2018–0112R1 requires contacting Leonardo 

and replacing the MR damper with a 

serviceable part, this AD does not. This AD 

requires the following: 

(i) If there is a crack in an MR damper body 

end, before further flight, replace the MR 

damper. 

(ii) If there is a crack in an MR damper rod 

end, before further flight, remove the MR 

damper rod end from service. 

(iii) If there is damage in any teeth of a rod 

end broached ring nut or damper piston slot, 

or if the engagement or alignment is not 

correct, before further flight, remove the rod 

end broached ring nut from service. 

(14) Paragraph (13) of EASA AD 2018– 

0112R1 requires accomplishing the 

applicable corrective action(s) as specified in, 

and in accordance with, the instructions of 

FHD BT 139–450 or FHD BT 139–452, as 

applicable, except where: 

(i) If there is any bearing seat rotation or 

misaligned slippage mark in the MR damper 

rod end, this AD requires, before further 

flight, removing the MR damper rod end from 

service. 

(ii) If the MR damper rod end torque value 

is more than 30.0 Nm (265.5 in lb), this AD 

requires, before further flight, removing the 

MR damper rod end from service. 

(iii) If any MR damper anti-rotation block 

dimension measurement exceeds allowable 

limits, this AD requires, before further flight, 

removing the anti-rotation block from 

service. 

(15) This AD does not mandate compliance 

with the ‘‘Remarks’’ section of EASA AD 

2018–0112R1. 

(i) Parts Prohibition 

As of the effective date of this AD, do not 

install an MR damper rod end P/N M006– 


tkelley on DSK125TN23PROD with PROPOSALS
51026 Federal Register / Vol. 86, No. 175 / Tuesday, September 14, 2021 / Proposed Rules 

01H004–041, M006–01H004–045, or M006– 

01H004–053 on any helicopter, unless it is 

marked with a black dot indicating that it has 

passed inspections specified by Leonardo 

Helicopters BT 139–450. 

(j) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2018–0112R1 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(k) 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 (l)(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. 

(l) Related Information 

(1) For EASA AD 2018–0112R1, 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–2020–0283. 

(2) For more information about this AD, 

contact Matt Fuller, AD Program Manager, 

General Aviation & Rotorcraft Unit, 

Airworthiness Products Section, Operational 

Safety Branch, FAA, 10101 Hillwood Pkwy., 

Fort Worth, TX 76177; telephone (817) 222– 

5110; email matthew.fuller@faa.gov. 

Issued on September 7, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–19607 Filed 9–13–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0781; Project 

Identifier AD–2021–00775–E] 

RIN 2120–AA64 

Airworthiness Directives; Austro 

Engine GmbH Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2021–09–04, which applies to all Austro 

Engine GmbH E4 and E4P model diesel 

piston engines. AD 2021–09–04 requires 

replacing a certain oil pump as well as 

the oil filter and engine oil. Since the 

FAA issued AD 2021–09–04, the FAA 

determined that the requirement to 

replace the oil pump should be limited 

to only Austro Engine E4 and E4P 

model diesel piston engines with a 

certain oil pump, identified by part 

number (P/N) and serial number (S/N), 

installed. This proposed AD would 

require replacing a certain oil pump, the 

oil filter, and the engine oil installed on 

Austro Engine GmbH E4 and E4P model 

diesel piston engines. 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 October 14, 

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 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Austro Engine 

GmbH, Rudolf-Diesel-Strasse 11, 2700 

Weiner Neustadt, Austria; phone: +43 

2622 23000; website: 

www.austroengine.at. You may view 

this service information at the 

Airworthiness Products Section, 

Operational Safety Branch, FAA, 1200 

District Avenue, Burlington, MA 01803. 

For information on the availability of 

this material at the FAA, call (781) 238– 

7759. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0781; 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, any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Wego Wang, Aviation Safety Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

(781) 238–7134; fax: (781) 238–7199; 

email: wego.wang@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–2021–0781; Project Identifier AD– 

2021–00775–E’’ 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 the 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 we receive about this proposed 

AD. 

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 


tkelley on DSK125TN23PROD with PROPOSALS