10496 Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Proposed Rules 

(5) For airplanes with Mod 116010: This 

AD does not require the actions specified in 

paragraph (1), (3), and (4) of EASA AD 2020– 

0203, as specified in paragraph (g) of this AD. 

(6) ‘‘Note 1’’ of EASA AD 2020–0203 does 

not apply to this AD. However, after the 

actions required by EASA AD 2020–0203, 

paragraphs (3) to (5), as required by 

paragraph (g) of this AD, have been 

accomplished on an airplane, that airplane 

may be operated with a damaged or missing 

ICP removable cover, provided provisions 

that address the ICP removable cover are 

included in the operator’s approved 

minimum equipment list (MEL). After the 

actions required by EASA AD 2020–0203, 

paragraph (6), as required by paragraph (g) of 

this AD, have been accomplished on an 

airplane, that airplane may be operated 

without an ICP removable cover, provided 

provisions that address the ICP removable 

cover are removed from the operator’s 

approved MEL. 

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

2020–0203 does not apply to this AD. 

(i) Special Flight Permit 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the airplane to a location where 

the actions specified in this AD can be 

accomplished (if the operator elects to do so), 

provided a removable ICP cover is installed 

on the flight deck. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, 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 responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (k)(2) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): For any 

service information referenced in EASA AD 

2020–0203 that contains RC procedures and 

tests: RC procedures and tests must be done 

to comply with this AD; any procedures or 

tests that are not identified as RC are 

recommended. Those procedures and tests 

that are not identified as RC may be deviated 

from using accepted methods in accordance 

with the operator’s maintenance or 

inspection program without obtaining 

approval of an AMOC, provided the 

procedures and tests identified as RC can be 

done and the airplane can be put back in an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Related Information 

(1) For information about EASA AD 2020– 

0203, 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, Airworthiness Products 

Section, Operational Safety Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 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–2020–1178. 

(2) For more information about this AD, 

contact Kathleen Arrigotti, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

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

telephone and fax 206–231–3218. 

Issued on January 19, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–01609 Filed 2–19–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1179; Project 

Identifier AD–2020–00818–E] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company 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 all 

General Electric Company (GE) CF6– 

80A, CF6–80A1, CF6–80A2, CF6–80A3, 

CF6–80C2A1, CF6–80C2A2, CF6– 

80C2A3, CF6–80C2A5, CF6–80C2A5F, 

CF6–80C2A8, CF6–80C2B1, CF6– 

80C2B1F, CF6–80C2B1F1, CF6– 

80C2B1F2, CF6–80C2B2, CF6–80C2B2F, 

CF6–80C2B3F, CF6–80C2B4, CF6– 

80C2B4F, CF6–80C2B5F, CF6–80C2B6, 

CF6–80C2B6F, CF6–80C2B6FA, CF6– 

80C2B7F, CF6–80C2B8F, CF6– 

80C2D1F, CF6–80C2K1F and CF6– 

80C2L1F model turbofan engines. This 

proposed AD was prompted by an 

inspection by the manufacturer that 

revealed cracking of the high-pressure 

turbine (HPT) rotor stage 1 disk. This 

proposed AD would require visual 

inspection and fluorescent penetrant 

inspection (FPI) of the HPT thermal 

shield and, if cracking is detected, 

removal from service of the HPT 

thermal shield, HPT rotor stage 1 disk 

and HPT rotor stage 2 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 8, 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 General Electric 

Company, 1 Neumann Way, Cincinnati, 

OH 45215; phone: (513) 552–3272; 

email: aviation.fleetsupport@ae.ge.com; 

website: www.ge.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–2020–1179; 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: 

Kevin M. Clark, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7088; fax: (781) 238– 

7199; email: Kevin.M.Clark@faa.gov. 

SUPPLEMENTARY INFORMATION: 


tkelley on DSKBCP9HB2PROD with PROPOSALS
Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Proposed Rules 10497 

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–2020–1179; Project Identifier AD– 

2020–00818–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 this proposal 

because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this NPRM. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this NPRM 

contain commercial or financial 

information that is customarily treated 

as private, that you actually treat as 

private, and that is relevant or 

responsive to this NPRM, it is important 

that you clearly designate the submitted 

comments as CBI. Please mark each 

page of your submission containing CBI 

as ‘‘PROPIN.’’ The FAA will treat such 

marked submissions as confidential 

under the FOIA, and they will not be 

placed in the public docket of this 

NPRM. Submissions containing CBI 

should be sent to Kevin M. Clark, 

Aviation Safety Engineer, ECO Branch, 

FAA, 1200 District Avenue, Burlington, 

MA 01803. 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 was notified by the 

manufacturer that a crack on the HPT 

rotor stage 1 disk was found during an 

inspection. Subsequent investigation by 

the manufacturer determined that the 

crack on the HPT rotor stage 1 disk was 

caused by increased stress on the HPT 

rotor stage 1 disk as a result of flangeto-flange cracking on the HPT thermal 

shield. This condition, if not addressed, 

could result in failure of the HPT rotor 

stage 1 disk, failure of the HPT rotor 

stage 2 disk, uncontained release of the 

HPT rotor stage 1 and stage 2 disks, 

damage to the engine, and damage to the 

airplane. 

FAA’s Determination 

The FAA is issuing this NPRM after 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information 

The FAA reviewed ESM 72–53–00 

High Pressure Turbine Rotor 

Assembly—Disassembly (ESM 72–53– 

00) from the GE CF6–80A Engine 

Manual GEK72501—Rev 89, dated 

February 15, 2020. ESM 72–53–00 

describes procedures for the removal of 

the HPT thermal shield, the HPT rotor 

stage 1 disk, and the HPT rotor stage 2 

disk. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

repetitive visual inspection and FPI of 

the HPT thermal shield at every piece 

part opportunity of the HPT rotor stage 

1 disk, HPT rotor stage 2 disk, or the 

HPT thermal shield. Depending on the 

results of the inspections, this proposed 

AD requires the removal from service of 

the HPT thermal shield, HPT rotor stage 

1 disk, and the HPT rotor stage 2 disk. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 1,084 

engines installed on 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 

product 

Cost on U.S. 

operators 

Perform FPI and visual inspection of HPT 

thermal shield.

2 work-hours × $85 per hour = $170 ............. $0 $170 $184,280 

The FAA estimates the following 

costs to do any necessary replacements 

that would be required based on the 

results of the proposed inspection. The 

agency has no way of determining the 

number of aircraft that might need these 

replacements. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace HPT thermal shield ........................................ 2 work-hours × $85 per hour = $170 ........................... $209,600 $209,770 

Replace HPT rotor stage 1 disk ................................... 2 work-hours × $85 per hour = $170 ........................... 799,700 799,870 

Replace HPT rotor stage 2 disk ................................... 2 work-hours × $85 per hour = $170 ........................... 364,600 364,770 

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 


tkelley on DSKBCP9HB2PROD with PROPOSALS
10498 Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Proposed Rules 

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 adding 

the following new airworthiness 

directive: 

General Electric Company: Docket No. FAA– 

2020–1179; Project Identifier AD–2020– 

00818–E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by April 8, 

2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all General Electric 

Company (GE) CF6–80A, CF6–80A1, CF6– 

80A2, CF6–80A3, CF6–80C2A1, CF6– 

80C2A2, CF6–80C2A3, CF6–80C2A5, CF6– 

80C2A5F, CF6–80C2A8, CF6–80C2B1, CF6– 

80C2B1F, CF6–80C2B1F1, CF6–80C2B1F2, 

CF6–80C2B2, CF6–80C2B2F, CF6–80C2B3F, 

CF6–80C2B4, CF6–80C2B4F, CF6–80C2B5F, 

CF6–80C2B6, CF6–80C2B6F, CF6– 

80C2B6FA, CF6–80C2B7F, CF6–80C2B8F, 

CF6–80C2D1F, CF6–80C2K1F and CF6– 

80C2L1F model turbofan engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by an inspection by 

the manufacturer that revealed cracking of 

the high-pressure turbine (HPT) rotor stage 1 

disk, caused by initial flange-to-flange 

cracking on the HPT thermal shield between 

the HPT rotor stage 1 disk and the HPT rotor 

stage 2 disk. The FAA is issuing this AD to 

prevent failure of the HPT rotor stage 1 disk 

and the HPT rotor stage 2 disk. The unsafe 

condition, if not addressed, could result in 

uncontained release of the HPT rotor stage 1 

and stage 2 disks, damage to the engine, and 

damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) After the effective date of this AD, at 

every piece-part exposure of the HPT rotor 

stage 1 disk, HPT rotor stage 2 disk, or the 

HPT thermal shield, perform a visual 

inspection and a fluorescent penetrant 

inspection (FPI) of the HPT thermal shield. 

(2) During any inspection required by 

paragraph (g)(1) of this AD, if a crack 

extending through either the forward or aft 

flange of the HPT thermal shield is detected, 

remove the HPT thermal shield, the HPT 

rotor stage 1 disk, and the HPT rotor stage 2 

disk from service. 

(h) Installation Prohibition 

Do not install onto any engine an HPT 

rotor stage 1 disk or HPT rotor stage 2 disk 

that was removed from service due to the 

requirements of paragraph (g)(2) of this AD. 

(i) Definition 

For the purpose of this AD, ‘‘piece-part 

exposure’’ is when the HPT rotor stage 1 

disk, HPT rotor stage 2 disk, or HPT thermal 

shield is separated from their mating rotor 

parts within the HPT rotor module. 

(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 Kevin M. Clark, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7088; fax: (781) 238–7199; email: 

Kevin.M.Clark@faa.gov. 

(2) For service information identified in 

this AD, contact General Electric Company, 

1 Neumann Way, Cincinnati, OH 45215; 

phone: (513) 552–3272; email: 

aviation.fleetsupport@ae.ge.com; website: 

www.ge.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 January 20, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–01814 Filed 2–19–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0014; Project 

Identifier MCAI–2020–01457–T] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

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 Airbus SAS Model A330–200 

Freighter series airplanes. This 

proposed AD was prompted by a report 

indicating occurrences of broken 

brackets of the support structure of the 

halon fire extinguishing bottle 4005WX; 

investigation showed that fatigue cracks 

initiated in the attachment brackets at 

the cross beams due to dynamic loading, 

and in some cases propagated in the 

struts. This proposed AD would require 

replacing the support brackets of the 

4005WX fire extinguisher bottle with 

reinforced support brackets, and 

replacing the strut assembly at the 

affected location, as specified in a 

European Union Aviation Safety Agency 

(EASA) AD, which is proposed for 

incorporation 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 April 8, 2021. 


tkelley on DSKBCP9HB2PROD with PROPOSALS