13222 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 

Comments on the ANPR were 

required to be received on or before 

February 26, 2021. We are reopening the 

comment period on Docket No. APHIS– 

2020–0079 for an additional 60 days. 

The comment period will now close on 

May 7, 2021. This action will allow 

interested persons additional time to 

prepare and submit comments. 

Authority: 7 U.S.C. 8301–8317; 7 CFR 2.22, 

2.80, and 371.4. 

Done in Washington, DC, this 2nd day of 

March 2021 . 

Heather Pichelman, 

Acting Deputy Under Secretary for Marketing 

and Regulatory Programs. 

Paul Kiecker, 

Acting Deputy Under Secretary, Office for 

Food Safety. 

[FR Doc. 2021–04716 Filed 3–5–21; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0857; Project 

Identifier MCAI–2020–00707–A] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM). 

SUMMARY: The FAA is revising a notice 

of proposed rulemaking (NPRM) to 

supersede Airworthiness Directive (AD) 

2014–25–04, which applies to all Pilatus 

Aircraft Ltd. (Pilatus) Model PC–6, PC– 

6–H1, PC–6–H2, PC–6/350, PC–6/350– 

H1, PC–6/350–H2, PC–6/A, PC–6/A–H1, 

PC–6/A–H2, PC–6/B–H2, PC–6/B1–H2, 

PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2, 

and PC–6/C1–H2 airplanes. This action 

revises the NPRM by adding an eddy 

current inspection of each fuselage wing 

fitting if an earlier version of the service 

information was accomplished. The 

FAA is proposing this 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 FAA must receive comments 

on this SNPRM by April 22, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this SNPRM, contact Pilatus Aircraft 

Ltd., Customer Support General 

Aviation, CH–6371 Stans, Switzerland; 

phone: +41 848 24 7 365; email: 

Techsupport@pilatus-aircraft.com; 

website: https://www.pilatusaircraft.com/en. 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 on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0857; or in person at Docket Operations 

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

through Friday, except Federal holidays. 

The AD docket contains the NPRM, this 

SNPRM, any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aviation Safety 

Engineer, FAA, General Aviation & 

Rotorcraft Section, International 

Validation Branch, 901 Locust, Room 

301, Kansas City, MO 64106; phone: 

(816) 329–4059; fax: (816) 329–4090; 

email: doug.rudolph@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–2020–0857; Project Identifier 

MCAI–2020–00707–A’’ 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 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 Doug Rudolph, 

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 an NPRM to amend 

14 CFR part 39 to supersede AD 2014– 

25–04, Amendment 39–18045 (79 FR 

73803, December 12, 2014) (AD 2014– 

25–04). AD 2014–25–04 applies to all 

Pilatus Model PC–6, PC–6–H1, PC–6– 

H2, PC–6/350, PC–6/350–H1, PC–6/ 

350–H2, PC–6/A, PC–6/A–H1, PC–6/A– 

H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ 

B2–H2, PC–6/B2–H4, PC–6/C–H2, and 

PC–6/C1–H2 airplanes and resulted 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. AD 2014–25–04 requires 

incorporating revised airworthiness 

limitations into the aircraft maintenance 

manual (AMM) for your FAA-approved 

maintenance program. 

The NPRM published in the Federal 

Register on October 2, 2020 (85 FR 

62266). The NPRM was prompted by 


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Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 13223 

MCAI issued by the European Union 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union. EASA 

superseded its previous MCAIs on this 

unsafe condition with EASA AD No. 

2020–0120, dated May 27, 2020 (EASA 

AD 2020–0120). EASA AD 2020–0120 

states that revised airworthiness 

limitations for the subject airplanes 

introduce new data modules that 

require non-destructive visual and eddy 

current inspections instead of a 

previous requirement for the fluorescent 

dye-penetrant method. In the NPRM, the 

FAA proposed to require incorporating 

the new airworthiness limitations 

(revision 29) and performing an eddy 

current inspection of the fuselage wing 

fittings and wing-to-fuselage fittings. 

Actions Since the NPRM Was Issued 

Since the FAA issued the NPRM, 

EASA superseded EASA AD 2020–0120 

and issued EASA AD No. 2020–0278, 

dated December 14, 2020 (EASA AD 

2020–0278) (also referred to after this as 

‘‘the MCAI’’). According to EASA AD 

2020–0278, an installation procedure 

specified in the service information 

identified in the NPRM contained an 

error and, therefore, did not adequately 

address the identified unsafe condition. 

Pilatus has revised the airworthiness 

limitations (revision 30) and issued 

corrected service information, which 

includes installing certain bushes using 

grease instead of a bonding agent and an 

additional one-time eddy current 

inspection of the fuselage wing fittings 

and wing-to-fuselage fittings if the last 

inspection was performed using an 

earlier version of the service 

information. You may examine the 

MCAI in the AD docket on the internet 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0857. 

This SNPRM was prompted by the 

FAA’s determination that the revised 

airworthiness limitations and new 

inspection procedures are necessary, in 

addition to the new life limits proposed 

in the NPRM. The FAA is proposing this 

AD to address reduced airplane 

controllability due to possible loss of 

structural integrity of certain parts. 

Comments 

The FAA received a comment from 

Pilatus. The following presents the 

comment received on the NPRM and the 

FAA’s response to that comment. 

Request to Reference Latest Service 

Information 

Pilatus requested that FAA revise the 

NPRM to require using Pilatus PC–6 

Aircraft Maintenance Manual Document 

Number 01975, Revision 30, dated 

October 30, 2020; and Pilatus PC–6 

Airworthiness Limitations Document 

Number 02334, Revision 10, dated 

October 30, 2020. In support of its 

request, Pilatus stated the installation 

procedure in the service information 

specified in the NPRM is incorrect. 

Pilatus also stated that it has added a 

note to the airworthiness limitations 

section indicating the data module 

procedure has been corrected and 

specifying a repeat of the action if it was 

last done in accordance with the prior 

service information. 

The FAA agrees. After Pilatus 

submitted its comment, EASA issued 

the MCAI to require the revised service 

information, as described previously. In 

this SNPRM, the FAA proposes to 

require the latest service information. 

Related Service Information Under 1 

CFR Part 51 

Pilatus issued PC–6 Airworthiness 

Limitations Document No. 02334, 

Revision 10, dated October 30, 2020; 

and Section 04–00–00, Airworthiness 

Limitations of Chapter 04, 

Airworthiness Limitations, of the 

Pilatus PC–6 Aircraft Maintenance 

Manual Document No. 01975, Revision 

30, dated October 30, 2020. This service 

information contains airworthiness 

limitations for the stabilizer trim 

actuator, fuselage wing fittings, and 

wing-to-fuselage fittings. These 

documents are distinct since they apply 

to different airplane models. 

Pilatus also issued Section 53–00–01, 

Fuselage Wing Fittings—Inspection/ 

Check, of the Pilatus PC–6 Aircraft 

Maintenance Manual Document No. 

01975, Revision 30, dated October 30, 

2020; Section 57–00–03, Wing to 

Fuselage Fittings—Inspection/Check, of 

the PC–6 Aircraft Maintenance Manual 

Document No. 01975, Revision 29, 

dated February 28, 2020; Appendix K, 

Fuselage Wing Fittings—Inspection/ 

Check, of the PC–6 Airworthiness 

Limitations Document No. 02334, 

Revision 10, dated October 30, 2020; 

and Appendix L, Wing to Fuselage 

Fittings—Inspection/Check, of the PC–6 

Airworthiness Limitations Document 

No. 02334, Revision 9, dated March 6, 

2020. This service information specifies 

procedures for repetitive eddy current 

inspections of the fuselage wing fittings 

and wing-to-fuselage fittings and, if 

necessary, installing the bush on the 

fuselage wing fittings using grease. 

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 the State 

of Design Authority, the FAA has been 

notified of the unsafe condition 

described in the MCAI and service 

information referenced above. The FAA 

is proposing this AD because the FAA 

evaluated all pertinent information and 

determined an unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. 

Certain changes described above 

expand the scope of the NPRM. As a 

result, it is necessary to reopen the 

comment period to provide additional 

opportunity for the public to comment 

on this SNPRM. 

Proposed Requirements of This SNPRM 

This proposed AD would retain none 

of the requirements of AD 2014–25–04. 

This proposed AD would require 

revising the airworthiness limitation 

section of the existing AMM or 

instructions for continued airworthiness 

to incorporate new airworthiness 

limitations. The revised limitations 

include an eddy current inspection of 

the fuselage wing fittings and wing-tofuselage fittings. This proposed AD 

would also require, within 50 hours 

time-in-service (TIS) for certain bushes, 

performing an eddy current inspection 

of the fuselage wing fittings and wingto-fuselage fittings and replacing the 

bush on the fuselage wing fittings using 

grease. Lastly, this proposed AD would 

require performing the eddy current 

inspection of the fuselage wing fittings 

and wing-to-fuselage fittings first within 

1,100 hours TIS or 12 months 

(whichever occurs first), and thereafter 

at the intervals specified in the revised 

limitations. 

This proposed AD would require 

revisions to the airworthiness 

limitations section (ALS) of an 

operator’s maintenance documents to 

include new inspections. Compliance 

with the airworthiness limitations 

section is required by 14 CFR 91.403(c). 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 30 

airplanes of U.S. registry. The FAA 

estimates the following costs to comply 

with this proposed AD: 


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13224 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

ALS revision ......................................................... 1 work-hour × $85 per 

hour = $85.

$0 $85 ............................... $2,550. 

Eddy current inspection of the fuselage wing fittings and wing-to-fuselage fittings.7 work-hours × $85 per 

hour = $595.

$1,860 $2,455 per inspection 

cycle.

$73,650 per inspection 

cycle. 

The FAA estimates the following 

costs to do the inspections and 

installation that would be required if an 

earlier version of the service 

information has been accomplished. 

The agency has no way of determining 

the number of aircraft that might need 

these inspections and installation: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Visual and eddy current inspection and installation for 

certain bushes.

7 work-hours × $85 per hour = $595 ........................... $1,860 $2,455 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2014–25–04, Amendment 39– 

18045 (79 FR 73803, December 12, 

2014); and 

■ b. Adding the following new AD: 

Pilatus Aircraft Limited: Docket No. FAA– 

2020–0857; Project Identifier MCAI– 

2020–00707–A. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by April 22, 

2021. 

(b) Affected Airworthiness Directives (ADs) 

This AD replaces AD 2014–25–04, 

Amendment 39–18045 (79 FR 73803, 

December 12, 2014) (AD 2014–25–04). 

(c) Applicability 

This AD applies to Pilatus Aircraft Limited 

Model PC–6, PC–6–H1, PC–6–H2, PC–6/350, 

PC–6/350–H1, PC–6/350–H2, PC–6/A, PC–6/ 

A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1– 

H2, PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2, 

and PC–6/C1–H2 airplanes, all serial 

numbers, certificated in any category. 

Note 1 to paragraph (c): These airplanes 

may also be identified as Fairchild Republic 

Company airplanes, Fairchild Industries 

airplanes, Fairchild Heli Porter airplanes, or 

Fairchild-Hiller Corporation airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by a determination 

that new and more restrictive airworthiness 

limitations, new life limits, and new 

inspection procedures are necessary. The 

FAA is issuing this AD to address reduced 

airplane controllability due to possible loss 

of structural integrity of certain parts. 

(f) Airworthiness Limitations Revision 

Unless already done, before further flight, 

comply with the actions specified in 

paragraphs (f)(1) through (3) of this AD. 

(1) For Models PC–6/B2–H2 and PC–6/B2– 

H4 airplanes, revise the airworthiness 

limitations section (ALS) of the existing 

maintenance manual or instructions for 

continued airworthiness (ICA) for your 

airplane as follows: 

(i) Replace Section 04–00–00 with Section 

04–00–00, Airworthiness Limitations, of 

Chapter 04, Airworthiness Limitations, of the 

Pilatus PC–6 Aircraft Maintenance Manual 

Document No. 01975, Revision 30, dated 

October 30, 2020. 

(ii) Add (or replace, if applicable) Section 

53–00–01, Fuselage Wing Fittings— 

Inspection/Check, of the Pilatus PC–6 

Aircraft Maintenance Manual Document No. 

01975, Revision 30, dated October 30, 2020. 

(iii) Add Section 57–00–03, Wing to 

Fuselage Fittings—Inspection/Check, of the 

Pilatus PC–6 Aircraft Maintenance Manual 

Document No. 01975, Revision 29, dated 

February 28, 2020. 

(2) For all airplanes specified in paragraph 

(c) of this AD except Models PC–6/B2–H2 

and PC–6/B2–H4 airplanes, revise the ALS of 


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Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Proposed Rules 13225 

the existing maintenance manual or ICA for 

your airplane as follows: 

(i) Replace the ALS with the Airworthiness 

Limitations Section of Pilatus PC–6 

Airworthiness Limitations Document No. 

02334, Revision 10, dated October 30, 2020. 

(ii) Add (or replace, if applicable) 

Appendix K, Fuselage Wing Fittings— 

Inspection/Check, of Pilatus PC 6 

Airworthiness Limitations Document No. 

02334, Revision 10, dated October 30, 2020. 

(iii) Add Appendix L, Wing to Fuselage 

Fittings—Inspection/Check, of Pilatus PC 6 

Airworthiness Limitations Document No. 

02334, Revision 9, dated March 6, 2020. 

(3) For all airplanes specified in paragraph 

(c) of this AD, after revising the ALS as 

required by paragraphs (f)(1) and (2) of this 

AD, remove from service each part that has 

reached or exceeded its new life limit. 

(g) Inspections and Replacement 

(1) For airplanes with a bush part number 

(P/N) 6100.0020.01 that has been bonded as 

specified in Section 53–00–01, Fuselage 

Wing Fittings—Inspection/Check, of Pilatus 

PC–6 Aircraft Maintenance Manual 

Document No. 01975, Revision 29, dated 

February 28, 2020; or Appendix K, Fuselage 

Wing Fittings—Inspection/Check, of Pilatus 

PC–6 Airworthiness Limitations Document 

No. 02334, Revision 9, dated March 6, 2020: 

Within 50 hours time-in-service (TIS) after 

the effective date of this AD, perform a visual 

and eddy current inspection of each fuselage 

wing fitting on fuselage Frame 3, remove 

bush P/N 6100.0020.01 from service, and 

install a new (zero hours TIS) bush P/N 

6100.0020.01 into Frame 3 with grease by 

using the procedures specified in paragraph 

(f)(1)(ii) or (f)(2)(ii) of this AD, as applicable 

to your airplane. 

(2) Unless already done, within 1,100 

hours TIS after the effective date of this AD 

or within 12 months after the effective date 

of this AD, whichever occurs first, perform 

an eddy current inspection of each fuselage 

wing fitting and each wing-to-fuselage fitting 

using the procedures specified in paragraphs 

(f)(1)(ii) and (iii) of this AD, or paragraphs 

(f)(2)(ii) and (iii) of this AD, as applicable to 

your airplane. Thereafter, repeat the eddy 

current inspection of each fuselage wing 

fitting and each wing-to-fuselage fitting at the 

intervals specified in the ALS identified in 

paragraph (f)(1)(i) or (f)(2)(i), as applicable to 

your airplane. 

(h) No Alternative Actions or Intervals 

After the ALS has been revised as required 

by paragraph (f) of this AD, no alternative 

inspection intervals or procedures may be 

approved, except as provided in paragraph (i) 

of this AD. 

(i) Other FAA AD Provisions 

Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Validation Branch, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send your request to the person identified in 

Related Information. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspection, the manager of the local Flight 

Standards District Office. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Union Aviation Safety Agency (EASA) AD 

No. 2020–0120, dated May 27, 2020, and 

EASA AD No. 2020–0278, dated December 

14, 2020, for related information. This MCAI 

may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2020–0857. 

(2) For more information about this AD, 

contact Doug Rudolph, Aviation Safety 

Engineer, FAA, General Aviation & Rotorcraft 

Section, International Validation Branch, 901 

Locust, Room 301, Kansas City, MO 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090; email: doug.rudolph@faa.gov. 

(3) For service information identified in 

this AD, contact Pilatus Aircraft Ltd., 

Customer Support General Aviation, CH– 

6371 Stans, Switzerland; telephone: +41 848 

24 7 365; email: Techsupport@

pilatusaircraft.com; internet: https://

www.pilatusaircraft.com/en. 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. 

Issued on February 25, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–04395 Filed 3–5–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0129; Project 

Identifier AD–2020–01597–E] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines AG Turbofan Engines 

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 International Aero Engines AG 

(IAE) V2522–A5, V2524–A5, V2525–D5, 

V2527–A5, V2527E–A5, V2527M–A5, 

V2528–D5, V2530–A5, V2531–E5, and 

V2533–A5 model turbofan engines. This 

proposed AD was prompted by an 

analysis performed by the manufacturer 

after an event involving an uncontained 

failure of a high-pressure turbine (HPT) 

1st-stage disk that resulted in highenergy debris penetrating the engine 

cowling. This proposed AD would 

require the performance of an ultrasonic 

inspection (USI) of the HPT 1st-stage 

disk and HPT 2nd-stage disk and, 

depending on the results of the 

inspections, replacement of the HPT 1ststage disk or HPT 2nd-stage disk. 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 April 7, 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 International Aero 

Engines AG, 400 Main Street, East 

Hartford, CT 06118; phone: (800) 565– 

0140; email: help24@pw.utc.com; 

website: http://fleetcare.pw.utc.com. 

You may view this 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0129; 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: 

Nicholas Paine, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7742; fax: (781) 238– 

7199; email: nicholas.j.paine@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–2021–0129; Project Identifier AD– 

2020–01597–E’’ at the beginning of your 

comments. The most helpful comments 


jbell on DSKJLSW7X2PROD with PROPOSALS