Federal Register / Vol. 85, No. 240 / Monday, December 14, 2020 / Proposed Rules 80689 

Note 1 to paragraph (g)(1): In ‘‘TA/RA’’ 

mode, the TA stands for traffic advisory and 

RA stands for resolution advisory. 

(2) In addition to the provisions of 14 CFR 

43.3 and 43.7, the actions required by 

paragraphs (g)(1)(i) through (iii) 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 14 CFR 43.9(a)(1) 

through (4) and 14 CFR 91.417(a)(2)(v). The 

record must be maintained as required by 14 

CFR 91.417. This authority is not applicable 

to aircraft being operated under 14 CFR part 

119. 

(3) Within 12 months after the effective 

date of this AD, upgrade the FDSA–6500 

field loadable software for your airplane as 

listed in the table in Section C and by 

following the instructions in Section F of 

Rockwell Collins Service Information Letter 

FDSA–6500–19–1, Revision No. 2, dated June 

12, 2019. 

(4) The airplane flight manual revision and 

placards required by paragraph (g)(1) of this 

AD may be removed after completing the 

software upgrade required by paragraph (g)(3) 

of this AD. 

(5) As of the effective date of this AD, do 

not install a Rockwell Collins Flight Display 

System Application FDSA–6500 P/N 810– 

0234–1H0001, 810–0234–1H0002, 810– 

0234–1H0003, 810–0234–2H0001, 810– 

0234–2C0001, 810–0234–2C0002, or 810– 

0234–4B0001 on any airplane. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita ACO 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 Related Information. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(i) Related Information 

(1) For more information about this AD, 

contact Nhien Hoang, Aviation Safety 

Engineer, Wichita ACO Branch, FAA, 1801 

Airport Road, Room 100, Wichita, Kansas 

67209; phone: (316) 946–4157; fax: (316) 

946–4107; email: nhien.hoang@faa.gov or 

Wichita-COS@faa.gov. 

(2) For service information identified in 

this AD, contact Rockwell Collins, Inc. at 

Collins Aviation Services, 400 Collins Road 

NE, M/S 164–100, Cedar Rapids, IA 52498– 

0001; phone: (319) 295–9258; fax: (319) 295– 

4351; email: techmanuals@

rockwellcollins.com; website: https://

www.rockwellcollins.com/Services_and_

Support/Publications.aspx. You may view 

this referenced service information at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. For information on 

the availability of this material at the FAA, 

call (816) 329–4148. 

Issued on December 8, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–27281 Filed 12–11–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1123; Project 

Identifier MCAI–2020–01294–R] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2016–23–05, which applies to certain 

Airbus Helicopters Model SA–365N1, 

AS–365N2, AS 365 N3, SA–366G1, EC 

155B, and EC155B1 helicopters. AD 

2016–23–05 requires repetitive checks 

of the oil level of the tail rotor gearbox 

and, if necessary, filling the oil to the 


jbell on DSKJLSW7X2PROD with PROPOSALSEP14DE20.087</GPH>
80690 Federal Register / Vol. 85, No. 240 / Monday, December 14, 2020 / Proposed Rules 

maximum level; and replacement of a 

certain control rod double bearing 

(bearing) with a new bearing. Since 

issuing AD 2016–23–05, the FAA has 

determined additional inspections, 

replacements, and modifications are 

necessary to address the unsafe 

condition. This proposed AD would 

retain the requirements of AD 2016–23– 

05 and would add helicopters to the 

applicability. This proposed AD would 

also require modifying the helicopter by 

replacing the tail gearbox (TGB) control 

shaft guide bushes; repetitive 

inspections of the TGB magnetic plug 

and corrective actions if necessary; 

repetitive replacements of the bearing; 

and modifying the helicopter by 

replacing the TGB; as specified in a 

European Union Aviation Safety Agency 

(EASA) AD, which will be incorporated 

by reference. 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 January 28, 

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 incorporated by reference 

(IBR) in this AD, contact the EASA, 

Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 

8999 000; email ADs@easa.europa.eu; 

internet www.easa.europa.eu. You may 

find this IBR material on the EASA 

website at https://ad.easa.europa.eu. 

You may view this IBR 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– 

1123. 

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– 

1123; 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. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Kathleen Arrigotti, Aviation Safety 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 

2200 South 216th St., Des Moines, WA 

98198; telephone and fax 206–231– 

3218; email kathleen.arrigotti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to participate in 

this rulemaking by submitting written 

comments, data, or views about this 

proposal. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should submit only one 

copy of the comments. Send your 

comments to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA 20_2020–1123; Project Identifier 

MCAI–2020–01294–R’’ at the beginning 

of your 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, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, the FAA 

will consider all comments received by 

the closing date for comments. The FAA 

will consider comments filed after the 

comment period has closed if it is 

possible to do so without incurring 

expense or delay. The FAA may change 

this NPRM because of those comments. 

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 Kathleen Arrigotti, 

Aviation Safety Engineer, Large Aircraft 

Section, International Validation 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 

206–231–3218; email 

kathleen.arrigotti@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. 

Discussion 

The FAA issued AD 2016–23–05, 

Amendment 39–18712 (81 FR 85126, 

November 25, 2016) (‘‘AD 2016–23– 

05’’), which applies to certain Airbus 

Helicopters Model SA–365N1, AS– 

365N2, AS 365 N3, SA–366G1, EC 155B, 

and EC155B1 helicopters. AD 2016–23– 

05 requires repetitive checks of the oil 

level of the tail rotor gearbox and, if 

necessary, filling the oil to the 

maximum level; and replacement of a 

certain bearing with a new partnumbered bearing. The FAA issued AD 

2016–23–05 to address damage to the 

bearing, which could result in end play, 

loss of tail rotor pitch control, and 

subsequent loss of control of the 

helicopter. 

Actions Since AD 2016–23–05 Was 

Issued 

Since the FAA issued AD 2016–23– 

05, the FAA has determined additional 

repetitive inspections of the TGB 

magnetic plug for the presence of 

particles (and corrective actions if 

necessary), repetitive replacements of 

the bearing, and modifications 

(replacing TGB control shaft guide 

bushes and replacing the TGB) are 

necessary to address the unsafe 

condition. 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2017–0125, dated July 21, 2017 (‘‘EASA 

AD 2017–0125’’) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Helicopters Model SA 365 N1, AS 365 

N2, AS 365 N3, SA 366 G1, EC 155 B, 

and EC 155 B1 helicopters. EASA AD 

2017–0125 supersedes EASA AD 2017– 

0007, dated January 13, 2017, which 

superseded EASA AD 2016–0097R1, 

dated May 25, 2016 (which corresponds 

to FAA AD 2016–23–05). EASA AD 

2017–0125 adds helicopters to the 


jbell on DSKJLSW7X2PROD with PROPOSALS
Federal Register / Vol. 85, No. 240 / Monday, December 14, 2020 / Proposed Rules 80691 

applicability, adds repetitive 

inspections of the magnetic plug after 

bearing replacement, requires the use of 

the revised Airbus Helicopters Alert 

Service Bulletin (ASB) instructions, and 

requires replacement of the TGB with a 

modified unit, which terminates the 

repetitive inspections. 

This proposed AD was prompted by 

a determination that additional 

inspections, replacements, and 

modifications are necessary to address 

the unsafe condition. The FAA is 

proposing this AD to address damage to 

the bearing, which could result in end 

play, loss of tail rotor pitch control, and 

subsequent loss of control of the 

helicopter. See the MCAI for additional 

background information. 

Comments on AD 2016–23–05 

The FAA gave the public the 

opportunity to comment on AD 2016– 

23–05. The following presents the 

comments received on AD 2016–23–05 

and the FAA’s response to each 

comment. 

Request To Revise the Applicability To 

Exclude Certain TGBs 

A commenter requested that the FAA 

revise the applicability of AD 2016–23– 

05 to exclude TGBs that are post-Airbus 

Helicopters mod 07 65B63 having part 

number (P/N) 365A33–6005–09. The 

commenter stated that the referenced 

service information clarifies that only 

TGBs that are pre-Airbus Helicopters 

mod 07 65B63 are affected. 

The FAA disagrees. In developing AD 

2016–23–05, the FAA differed with 

EASA AD 2016–0097R1, dated May 25, 

2016, and the referenced service 

information. The FAA determined that 

TGBs that are post-Airbus Helicopters 

mod 07 65B63 having P/N 365A33– 

6005–09 should not be excluded from 

the requirements of that AD. However, 

the FAA notes that the new MCAI 

addresses TGBs that are pre-Airbus 

Helicopters mod 07 65B63 and TGBs 

that are post-Airbus Helicopters mod 07 

65B63 separately, as does this proposed 

AD. 

Request To Revise the Applicability To 

Include All TGBs 

A commenter requested that the FAA 

revise the applicability of AD 2016–23– 

05 to include all TGBs. The commenter 

stated the applicability for AD 2016–23– 

05 should be the same as AD 2007–25– 

08, Amendment 39–15290 (72 FR 

69604, December 10, 2007), which 

included all bearings, regardless of the 

part number of the TGB. 

The FAA disagrees. In developing AD 

2016–23–05, the FAA determined the 

requirement to check the oil level is 

only necessary for helicopters with a 

TGB bearing having P/N 704A33–651– 

093 or P/N 704A33–651–104. However, 

the FAA notes that the new MCAI 

requires the oil level check for all TGBs, 

as does this proposed AD. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2017–0125 describes 

procedures for modifying the helicopter 

by replacing TGB control shaft guide 

bushes, repetitive inspections (checks) 

of the oil level of the tail rotor gearbox 

and, if necessary, filling the oil to the 

maximum level, repetitive inspections 

of the TGB magnetic plug for the 

presence of particles and corrective 

actions if necessary (corrective actions 

include removing the TGB, complying 

with certain work cards to address 

particles and other conditions such as 

abrasions, scales, flakes, and splinters, 

and replacing the bearing), repetitive 

replacements of the bearing; and 

modifying the helicopter by replacing 

the TGB. 

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. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is 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 the MCAI referenced 

above. The FAA is proposing this AD 

because the FAA evaluated all the 

relevant information and determined 

the unsafe condition described 

previously is likely to exist or develop 

in other products of the same type 

design. 

Proposed AD Requirements 

This proposed AD would retain the 

actions required by AD 2016–23–05 and 

would require accomplishing the 

actions specified in EASA AD 2017– 

0125 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 

MCAI.’’ 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA initially worked with 

Airbus and EASA to develop a process 

to use certain EASA ADs as the primary 

source of information for compliance 

with requirements for corresponding 

FAA ADs. The FAA has since 

coordinated with other manufacturers 

and civil aviation authorities (CAAs) to 

use this process. As a result, EASA AD 

2017–0125 will be incorporated by 

reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with EASA AD 2017–0125 

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 

the EASA AD 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 the EASA AD. Service 

information specified in EASA AD 

2017–0125 that is required for 

compliance with EASA AD 2017–0125 

will be available on the internet at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–1123 after the FAA final 

rule is published. 

Explanation of Retained Requirements 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2016–23–05, this proposed AD would 

retain certain requirements of AD 2016– 

23–05. Those requirements are 

referenced in paragraphs (2) and (5) of 

EASA AD 2017–0125, which, in turn, is 

referenced in paragraph (g) of this 

proposed AD. 

Costs of Compliance 

The FAA estimates that this proposed 

AD affects 52 helicopters of U.S. 

registry. The FAA estimates the 

following costs to comply with this 

proposed AD: 


jbell on DSKJLSW7X2PROD with PROPOSALS
80692 Federal Register / Vol. 85, No. 240 / Monday, December 14, 2020 / Proposed Rules 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Retained actions from AD 2016–23–05 ......... 17 work-hours × $85 per hour = $1,445 ........ $1,125 $2,570 $133,640 

New proposed actions .................................... 63 work-hours × 85 per hour = 5,355 ............ 1,395 6,750 351,000 

ESTIMATED COSTS FOR OPTIONAL ACTIONS

Labor cost Parts cost Cost per 

product 

8 work-hours × $85 per hour = $680 ...................................................................................................................... $0 $680 

The FAA has received no definitive 

data that would enable the agency to 

provide cost estimates for the oncondition actions specified in this 

proposed AD. 

According to the manufacturer, some 

or all of the costs of this proposed 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 this 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 

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) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The 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 

removing Airworthiness Directive (AD) 

2016–23–05, Amendment 39–18712 (81 

FR 85126, November 25, 2016), and 

adding the following new AD: 

Airbus Helicopters: Docket No. FAA–2020– 

1123; Project Identifier MCAI–2020– 

01294–R. 

(a) Comments Due Date 

The FAA must receive comments by 

January 28, 2021. 

(b) Affected Airworthiness Directives (ADs) 

This AD replaces AD 2016–23–05, 

Amendment 39–18712 (81 FR 85126, 

November 25, 2016) (‘‘AD 2016–23–05’’). 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model SA–365N1, AS–365N2, AS 365 N3, 

SA–366G1, EC 155B, and EC155B1 

helicopters, certificated in any category, all 

serial numbers. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 65, Tail Rotor. 

(e) Reason 

This AD was prompted by reports of 

occurrences of loss of yaw control due to 

failure of the tail gearbox (TGB) control rod 

double bearing (bearing). This AD was also 

prompted by the determination that 

additional inspections, replacements, and 

modifications are necessary to address the 

unsafe condition. The FAA is issuing this AD 

to address damage to the bearing, which 

could result in end play, loss of tail rotor 

pitch control, 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, European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD 2017–0125, dated 

July 21, 2017 (‘‘EASA AD 2017–0125’’). 

(h) Exceptions to EASA AD 2017–0125 

(1) Where EASA AD 2017–0125 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where EASA AD 2017–0125 refers to 

June 4, 2011 (the effective date of EASA AD 

2011–0105), this AD requires using the 

effective date of this AD. 

(3) Where EASA AD 2017–0125 refers to 

May 25, 2016 (the effective date of EASA AD 

2016–0197R1), this AD requires using the 

effective date of this AD. 

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

2017–0125 does not apply to this AD. 

(5) Where paragraph (2) of EASA AD 2017– 

0125 requires inspections (checks) to be done 

‘‘in accordance with the instructions of 

Paragraph 3.B.1 of the applicable inspection 

ASB,’’ for this AD, those instructions are for 

reference only and are not required for the 

actions in paragraph (2) of EASA AD 2017– 

0125. The inspections (checks) required by 

paragraph (2) of EASA AD 2017–0125 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 


jbell on DSKJLSW7X2PROD with PROPOSALS
Federal Register / Vol. 85, No. 240 / Monday, December 14, 2020 / Proposed Rules 80693 

accordance with 14 CFR 43.9 (a)(1) through 

(4) and 14 CFR 91.417(a)(2)(v). The record 

must be maintained as required by 14 CFR 

91.417, 121.380, or 135.439. 

(6) Where paragraph (5) of EASA AD 2017– 

0125 specifies to ‘‘accomplish the applicable 

corrective action(s) in accordance with the 

instructions of Paragraph 3.B.1 of the 

applicable inspection ASB,’’ for this AD, a 

qualified mechanic must add oil to the TGB 

to the ‘‘max’’ level if the oil level is not at 

maximum. The instructions are for reference 

only and are not required for the actions in 

paragraph (5) of EASA AD 2017–0125. 

(7) Where EASA AD 2017–0125 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(8) Where EASA AD 2017–0125 requires 

action after the last flight of the day or 

‘‘ALF,’’ this AD requires those actions before 

the first flight of the day. 

(9) Where the service information referred 

to in EASA AD 2017–0125 specifies to 

perform a metallurgical analysis and contact 

the manufacturer if collected particles are not 

clearly characterized, this AD does not 

require contacting the manufacturer to 

determine the characterization of the 

particles collected. 

(10) Although service information 

referenced in EASA AD 2017–0125 specifies 

to scrap parts, this AD does not include that 

requirement. 

(11) Although service information 

referenced in EASA AD 2017–0125 specifies 

reporting information to Airbus Helicopters 

and filling in a ‘‘particle dectection’’ followup sheet, this AD does not include those 

requirements. 

(12) Although service information 

referenced in EASA AD 2017–0125 specifies 

returning certain parts to an approved 

workshop, this AD does not include that 

requirement. 

(13) Where paragraph (6) of EASA AD 

2017–0125 refers to ‘‘any discrepancy,’’ for 

this AD, discrepancies include the presence 

of particles and other conditions such as 

abrasions, scales, flakes, and splinters. 

(i) 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. 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 International Validation Branch, send 

it to the attention of the person identified in 

paragraph (j)(2) of this AD. Information may 

be emailed to: 9-AVS-AIR-730-AMOC@

faa.gov. 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. 

(j) Related Information 

(1) For information about EASA AD 2017– 

0125, contact the 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 

EASA AD 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. This 

material may be found in the AD docket on 

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

by searching for and locating Docket No. 

FAA–2020–1123. 

(2) For more information about this AD, 

contact Kathleen Arrigotti, Aviation Safety 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3218; email 

kathleen.arrigotti@faa.gov. 

Issued on December 8, 2020. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2020–27416 Filed 12–11–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0819; Project 

Identifier 2019–CE–027–AD] 

RIN 2120–AA64 

Airworthiness Directives; Textron 

Aviation Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

97–06–10, which applies to certain 

Raytheon Aircraft Company (type 

certificate now held by Textron 

Aviation Inc. (Textron)) Model 76 

airplanes. AD 97–06–10 requires 

repetitively inspecting the main landing 

gear (MLG) ‘‘A’’ frame assemblies for 

cracks and replacing any cracked 

assembly. Since the FAA issued AD 97– 

06–10, the replacement parts have also 

experienced failure due to cracking. 

This proposed AD would require 

magnetic particle inspections of the 

MLG ‘‘A’’ frame assemblies for cracks 

and replacement of the affected parts if 

necessary. 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 January 28, 

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 Textron Aviation 

Customer Service, P.O. Box 7706, 

Wichita, Kansas 67277; phone: (316) 

517–5800; email: customercare@

txtav.com; website: https://txtav.com. 

You may view this service information 

at the FAA, Airworthiness Products 

Section, Operational Safety Branch, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0819; 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: 

Brian Adamson, Aviation Safety 

Engineer, Wichita ACO Branch, FAA, 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; phone: (316) 946–4193; 

fax: (316) 946–4107; email: 

brian.adamson@faa.gov or WichitaCOS@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 the ADDRESSES section. Include 

‘‘Docket No. FAA–2020–0819; Project 

Identifier 2019–CE–027–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 

proposal because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 


jbell on DSKJLSW7X2PROD with PROPOSALS