Federal Register / Vol. 86, No. 164 / Friday, August 27, 2021 / Proposed Rules 48083 

compliance times in Part 1, paragraph 1, or 

Part 2, paragraph 1, of the ASB. 

(i) If the results of the torque inspection 

required by paragraph (g)(6) of this AD meet 

the criteria for engine removal specified in 

Table 1, 2 or 3, of the ASB, as applicable, 

perform piece-part inspections in accordance 

with the ICA on all 3rd-stage and 4th-stage 

LPT blades before exceeding 20 hours TIS 

since the last torque inspection. 

(ii) [Reserved] 

(7) The initial inspection or the 

reinspection interval should not be reset 

unless the blades are refurbished. Whenever 

a used blade is reinstalled in a rotor, the 

previous used time should be subtracted 

from the initial inspection threshold. 

(8) Whenever a refurbished or used blade 

is intermixed with zero hours time-since-new 

(TSN) blades in a rotor, use the lowest initial 

inspection threshold that is applicable. 

(9) At the next accessibility to the LPT-toexhaust case bolts and nuts after the effective 

date of this AD, do the following: 

(i) Replace the bolts with part number (P/ 

N) MS9557–26 bolts; 

(ii) Replace the nuts with P/N 375095 nuts 

or P/N 490270 nuts; and 

(iii) Install crushable sleeve spacers, P/N 

822903, under the head of the bolts. 

Note 1 to paragraph (g): Guidance on 

replacing the 3rd-stage and 4th-stage LPT 

blades can be found in P&W ASB JT8D 

A6507, dated November 2, 2020. 

Note 2 to paragraph (g): Guidance on 

replacing the LPT-to-exhaust case bolts and 

nuts and installing the crushable sleeve 

spacers can be found in P&W ASB No. JT8D 

A6494, Revision No. 1, dated January 26, 

2010. 

(h) Definitions 

For the purpose of this AD: 

(1) An ‘‘engine shop visit’’ is the induction 

of an engine into the shop for maintenance 

involving the separation of pairs of major 

mating engine flanges, except that the 

separation of engine flanges solely for the 

purposes of transportation without 

subsequent engine maintenance does not 

constitute an engine shop visit. 

(2) Accessibility to the LPT-to-exhaust case 

bolts refers to maintenance involving the 

inner turbine fan ducts being removed from 

the engine. 

(3) Parts eligible for installation are 3rdstage or 4th-stage LPT blades with less than 

5,000 hours TIS. 

(4) A ‘‘piece-part inspection’’ is when the 

blades are removed from the rotor. 

(5) A ‘‘used blade’’ refers to a 3rd-stage or 

4th-stage LPT blade that has more than zero 

hours TSN. 

(i) Credit for Previous Actions 

You may take credit for any initial torque 

inspection for shroud notch wear required by 

paragraphs (g)(1) through (3) of this AD if you 

performed the initial inspection before the 

effective date of this AD using P&W ASB No. 

JT8D A6224, Revision No. 5, dated June 11, 

2004, or Revision No. 6, dated May 3, 2007. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO 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 ECO Branch, send it to 

the attention of the person identified in 

Related Information. You may email your 

request to: ANE-AD-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 more information about this AD, 

contact Nicholas Paine, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: (781) 

238–7116; fax: (781) 238–7199; email: 

nicholas.j.paine@faa.gov. 

(2) For service information identified in 

this AD, contact Pratt & Whitney, 400 Main 

Street, East Hartford, CT 06118; phone: (800) 

565–0140; email: help24@prattwhitney.com; 

website: https://fleetcare.prattwhitney.com. 

You may view this referenced service 

information at the FAA, Airworthiness 

Products Section, Operational Safety Branch, 

1200 District Avenue, Burlington, MA 01803. 

For information on the availability of this 

material at the FAA, call (781) 238–7759. 

Issued on August 5, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–18489 Filed 8–26–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0712; Project 

Identifier 2019–CE–018–AD] 

RIN 2120–AA64 

Airworthiness Directives; ASI Aviation 

(Type Certificate Previously Held by 

Reims Aviation S.A.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2015–16–07 R1, which applies to 

certain Reims Aviation S.A. (type 

certificate now held by ASI Aviation) 

Model F406 airplanes. AD 2015–16–07 

R1 requires inspecting the left-hand and 

right-hand rudder control pedal torque 

tubes and replacing with a serviceable 

part as necessary. Since the FAA issued 

AD 2015–16–07 R1, the European 

Aviation Safety Agency (EASA) 

superseded its mandatory continuing 

airworthiness information (MCAI) to 

correct an unsafe condition on these 

products. This proposed AD would 

retain the requirements of AD 2015–16– 

07 R1, expand the applicability, and 

require repeating the inspections using 

updated procedures. 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 12, 

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 ASI Aviation, 

Ae ́rodrome de Reims Prunay, 51360 

Prunay, France; telephone: +33 3 26 48 

46 84; fax: +33 3 26 49 18 57; email: 

contact@asi-aviation.fr; website: https:// 

asi-aviation.fr/page-Accueil.html. You 

may view this service information at the 

Airworthiness Products Section, 

Operational Safety Branch, FAA, 901 

Locust, Kansas City, MO 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–2021–0712; 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 MCAI, any comments 

received, and other information. The 

street address for Docket Operations is 

listed above. 

FOR FURTHER INFORMATION CONTACT: 

Gregory Johnson, Aviation Safety 

Engineer, FAA, General Aviation & 

Rotorcraft Section, International 

Validation Branch, 901 Locust, Room 

301, Kansas City, MO 64106; phone: 

(720) 626–5462; fax: (816) 329–4090; 

email: gregory.johnson@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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48084 Federal Register / Vol. 86, No. 164 / Friday, August 27, 2021 / Proposed Rules 

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–2021–0712; Project Identifier 

2019–CE–018–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 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 received 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 

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 Gregory Johnson, 

Aviation Safety Engineer, FAA, General 

Aviation & Rotorcraft Section, 

International Validation Branch, 901 

Locust, Room 301, Kansas City, MO 

64106. Any commentary that the FAA 

receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

The FAA issued AD 2015–16–07 R1, 

Amendment 39–18328 (80 FR 72563, 

November 20, 2015) (AD 2015–16–07 

R1), for certain serial-numbered Reims 

Aviation S.A. (type certificate now held 

by ASI Aviation) Model F406 airplanes. 

AD 2015–16–07 R1 was prompted by 

MCAI originated by EASA, which is the 

Technical Agent for the Member States 

of the European Union. EASA issued 

EASA AD 2015–0159R1, dated August 

24, 2015, to identify and correct an 

unsafe condition identified as 

detachment of the pilot’s rudder control 

pedal in flight. 

AD 2015–16–07 R1 requires 

inspecting the left-hand and right-hand 

rudder control pedal torque tubes and 

replacing with a serviceable part as 

necessary. The FAA issued AD 2015– 

16–07 R1 to detect and correct cracking 

of the pilot rudder control pedal which, 

if not corrected, could result in 

detachment of the pedal with possible 

loss of airplane directional control. AD 

2015–16–07 R1 revised AD 2015–16–07, 

Amendment 39–18232 (80 FR 49127, 

August 17, 2015) (AD 2015–16–07), by 

adding an option for acceptable 

serviceable replacement parts. AD 

2015–16–07 R1 retained the compliance 

times required by AD 2015–16–07. 

Actions Since AD 2015–16–07 R1 Was 

Issued 

Since the FAA issued AD 2015–16–07 

R1, EASA superseded EASA AD 2015– 

0159R1, dated August 24, 2015, and 

issued EASA AD 2019–0016, dated 

January 29, 2019 (referred to after this 

as ‘‘the MCAI’’). The MCAI states: 

An occurrence was reported where one 

pilot rudder control pedal of an F 406 

aeroplane detached in flight. No change in 

aeroplane attitude occurred. The rudder was 

controlled using the co-pilot rudder pedals, 

and an uneventful landing was made. 

Investigation results determined that the 

affected rudder pedal torque tube had failed 

due to a crack. 

This condition, if not detected and 

corrected, could lead to further cases of 

rudder pedal torque tube failure, possibly 

resulting in reduced control of the aeroplane. 

To address this potential unsafe condition, 

ASI Aviation issued SB [service bulletin] 

F406–104 to provide inspection instructions. 

Consequently, EASA issued Emergency AD 

2015–0159–E (later revised) to require a onetime inspection of the rudder control pedal 

torque tubes, both left-hand (LH) and righthand (RH), and, depending on findings, 

replacement with a serviceable part. That 

[EASA] AD also required inspection of 

replacement rudder control pedal torque 

tubes before installation. 

Since EASA AD 2015–0159R1 was issued, 

further occurrences were reported of finding 

cracks on rudder pedal torque tubes. 

Consequently, ASI Aviation issued the SB (as 

defined in this [EASA] AD) to provide 

instructions for repetitive visual, dye- or 

fluorescent-penetrant, and magnetic particle 

inspections. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2015–0159R1, which is superseded, and 

requires implementation of repetitive 

inspections of the affected parts and, 

depending on findings, replacement. 

You may examine the MCAI in the 

AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0712. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed ASI Aviation 

Service Bulletin No. F406–104, Revision 

1, dated December 14, 2018. The service 

information specifies procedures for 

repetitively inspecting the left-hand and 

right-hand rudder control pedal torque 

tubes for cracks and replacing with a 

serviceable part. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

FAA’s Determination 

This product has been approved by 

the aviation authority of another 

country and is approved for operation in 

the United States. Pursuant to the FAA’s 

bilateral agreement with this State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI and service information 

referenced above. The FAA is issuing 

this NPRM after determining the unsafe 

condition described previously is likely 

to exist or develop on other products of 

the same type design. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would retain the 

requirements of AD 2015–16–07 R1, 

expand the applicability, and require 

repetitive inspections (using improved 

procedures) of the left-hand and righthand rudder control pedal torque tubes, 

and, depending on findings, 

replacement with a serviceable part. 

Differences Between This Proposed AD 

and the MCAI 

The MCAI specifies an initial 

compliance time of during the next 600 

flight hour (FH) maintenance check for 

a visual and a dye or fluorescent 

penetrant inspection. This proposed AD 

would require those initial inspections 

before further flight. 

The MCAI specifies an initial 

compliance time of during the next 

2,400 FH maintenance check for a 

magnetic particle inspection. This 

proposed AD would require that initial 

inspection within 100 hours time-inservice after the effective date of this 

AD. 

If a crack is detected during any 

inspection, the MCAI specifies 

contacting ASI Aviation for further 

information. This proposed AD would 


lotter on DSK11XQN23PROD with PROPOSALS1
Federal Register / Vol. 86, No. 164 / Friday, August 27, 2021 / Proposed Rules 48085 

require replacing the rudder control 

pedal torque tube with a serviceable 

part. 

Costs of Compliance 

The FAA estimates that this proposed 

AD, if adopted as proposed, would 

affect 4 airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per airplane Cost on U.S. 

operators 

Inspections ............. 5 work-hours × $85 per hour = 

$425 per inspection cycle.

$0 $425 per inspection cycle ........... $1,700 per inspection cycle. 

The FAA estimates the following 

costs to replace a rudder control pedal 

torque tube if required by the results of 

the proposed inspections. The FAA has 

no way of determining the number of 

airplanes that might need these 

replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

airplane 

Replacement .......... 20 work-hours × $85 per hour = $1,700 ............................................................................. $9,100 $10,800 

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) 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: 

■ a. Removing Airworthiness Directive 

2015–16–07 R1, Amendment 39–18328 

(80 FR 72563, November 20, 2015); and 

■ b. Adding the following new 

airworthiness directive: 

ASI Aviation (Type Certificate Previously 

Held by Reims Aviation S.A.): Docket 

No. FAA–2021–0712; Project Identifier 

2019–CE–018–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by October 12, 

2021. 

(b) Affected ADs 

This AD replaces AD 2015–16–07 R1, 

Amendment 39–18328 (80 FR 72563, 

November 20, 2015) (AD 2015–16–07 R1). 

(c) Applicability 

This AD applies to ASI Aviation (type 

certificate previously held by Reims Aviation 

S.A.) Model F406 airplanes, all serial 

numbers, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2700, Flight Control System. 

(e) Unsafe Condition 

This AD was prompted by reports of 

detachment of the pilot’s rudder control 

pedal in flight. The FAA is issuing this AD 

to detect and correct cracking of the pilot’s 

rudder control pedal. The unsafe condition, 

if not addressed, could result in detachment 

of the pedal with possible loss of airplane 

directional control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition 

For the purpose of this AD, a serviceable 

part is: 

(1) A rudder control pedal torque tube (lefthand (LH) part number (P/N) 5115260–1 or 

right hand (RH) P/N 5115260–2) that has had 

a magnetic particle inspection by following 

the instructions of Part B of ASI Aviation 

Service Bulletin No. F406–104, Revision 1, 

dated December 14, 2018, and no cracks were 

found; or 

(2) A new rudder control pedal torque tube 

(LH P/N 5115260–1 or RH P/N 5115260–2) 

that has never been installed on an airplane. 

(h) Repetitive Inspections and Corrective 

Actions 

(1) Before further flight after the effective 

date of this AD, and thereafter at intervals not 

to exceed 600 hours time-in-service (TIS), do 

a visual inspection and a dye or fluorescent 

penetrant inspection for cracks of the LH and 

RH rudder control pedal torque tubes by 


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48086 Federal Register / Vol. 86, No. 164 / Friday, August 27, 2021 / Proposed Rules 

following the Accomplishment Instructions, 

Part A or Part AA, in ASI Aviation Service 

Bulletin No. F406–104, Revision 1, dated 

December 14, 2018. 

(2) Within 100 hours TIS after the effective 

date of this AD, and thereafter at intervals not 

to exceed 2,400 hours TIS, do a magnetic 

particle inspection for cracks of the LH and 

RH rudder control pedal torque tubes by 

following the Accomplishment Instructions, 

Part B, in ASI Aviation Service Bulletin No. 

F406–104, Revision 1, dated December 14, 

2018. 

(3) If, during any inspection required by 

paragraph (h)(1) or (2) of this AD, any crack 

is detected on a rudder control pedal torque 

tube, you are not required to contact ASI 

Aviation as specified in steps A.16, AA.5, 

and B.4 of ASI Aviation Service Bulletin No. 

F406–104, Revision 1, dated December 14, 

2018. Instead, before further flight, replace 

the rudder control pedal torque tube with a 

serviceable part as defined by this AD. 

(i) Installation Limitation 

As of the effective date of this AD, do not 

install a rudder control pedal torque tube P/ 

N 5115260–1 (LH) or P/N 5115260–2 (RH) on 

any airplane unless it is a serviceable part as 

defined by this AD. 

(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 certification office, 

send it to the attention of the person 

identified in Related Information or email: 9- 

AVS-AIR-730-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 more information about this AD, 

contact Gregory Johnson, Aviation Safety 

Engineer, FAA, General Aviation & Rotorcraft 

Section, International Validation Branch, 901 

Locust, Room 301, Kansas City, MO 64106; 

phone: (720) 626–5462; fax: (816) 329–4090; 

email: gregory.johnson@faa.gov. 

(2) Refer to European Aviation Safety 

Agency (EASA) AD 2019–0016, dated 

January 29, 2019, for more information. You 

may examine the EASA AD in the AD docket 

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

for and locating it in Docket No. FAA–2021– 

0712. 

(3) For service information identified in 

this AD, contact ASI Aviation, Ae ́rodrome de 

Reims Prunay, 51360 Prunay, France; 

telephone: +33 3 26 48 46 84; fax: +33 3 26 

49 18 57; email: contact@asi-aviation.fr; 

website: https://asi-aviation.fr/pageAccueil.html. You may view this service 

information at the Airworthiness Products 

Section, Operational Safety Branch, FAA, 

901 Locust, Kansas City, MO 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

Issued on August 20, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–18384 Filed 8–26–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0711; Project 

Identifier 2019–CE–024–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Aerospace Limited Airplanes 

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 Pacific Aerospace Limited 

Model 750XL airplanes. This proposed 

AD was prompted by mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as chafing of the 

engine fuel feed line hoses. This 

proposed AD would require inspecting 

the engine fuel feed line hoses and the 

electrical wiring and rerouting all fuel 

lines. 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 12, 

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 the Civil Aviation 

Authority of New Zealand, Level 15, 

Asteron Centre, 55 Featherston Street, 

Wellington 6011; phone: + 64 4 560 

9400; fax: + 64 4 569 2024; email: info@

caa.govt.nz. You may view this service 

information at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 901 Locust, Kansas City, MO 

64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0711; 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 MCAI, any comments 

received, and other information. The 

street address for Docket Operations is 

listed above. 

FOR FURTHER INFORMATION CONTACT: 

Mike Kiesov, Aviation Safety Engineer, 

General Aviation & Rotorcraft Section, 

International Validation Branch, FAA, 

901 Locust, Room 301, Kansas City, MO 

64106; phone: (816) 329–4144; fax: (816) 

329–4090; email: mike.kiesov@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–2021–0711; Project Identifier 

2019–CE–024–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 


lotter on DSK11XQN23PROD with PROPOSALS1