Federal Register / Vol. 86, No. 139 / Friday, July 23, 2021 / Rules and Regulations 38909 

(3) If, during the maintenance records 

review required by paragraph (g)(1) of the 

this AD or during the inspection required by 

paragraph (g)(2) of this AD, you can 

positively determine that a disc assembly P/ 

N 101584–1 or –2 is not installed, before 

further flight, make an entry in the log book 

showing compliance with this AD. 

(4) If, during the maintenance records 

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

AD or during the inspection required by 

paragraph (g)(2) of this AD, you can 

positively determine that a disc assembly P/ 

N 101584–1 or –2 is installed, within 30 days 

or 100 hours TIS after the effective date of 

this AD, whichever occurs first, replace disc 

assembly P/N 101584–1 or –2 with disc 

assembly P/N 32721–1. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, do not 

install disc assembly P/N 101584–1 or –2. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

Branch, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (j)(1) of this AD. 

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

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

(1) For more information about this AD, 

contact Kathleen Arrigotti, Program Manager, 

Large Aircraft Section, International 

Validation Branch, Compliance & 

Airworthiness Division, FAA, 2200 South 

216th St., Des Moines, WA 98198; phone and 

fax: (206) 231–3218; email: 

kathleen.arrigotti@faa.gov. 

(2) The subject of this AD is addressed in 

Transport Canada Civil Aviation (TCCA) 

Canadian AD CF–2010–07, dated February 

24, 2010. You may view the TCCA AD at 

https://www.regulations.gov in Docket No. 

FAA–2010–0865. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Bell Helicopter Alert Service Bulletin 

206–09–123, Revision A, dated June 10, 

2009. 

(ii) Bell Helicopter Alert Service Bulletin 

206L–09–157, Revision A, dated June 10, 

2009. 

(3) For service information identified in 

this AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4; phone: 450–437– 

2862 or 800–363–8023; fax: (450) 433–0272; 

internet: https://www.bellcustomer.com. 

(4) You may view this service information 

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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email: fedreg.legal@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on July 9, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–15478 Filed 7–22–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0188; Project 

Identifier MCAI–2020–00642–R; Amendment 

39–21572; AD 2021–11–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Helicopters Model SA–365N, 

SA–365N1, AS–365N2, and AS 365 N3 

helicopters. This AD was prompted by 

a report that damage (scorch marks) was 

found on an internal life raft installation 

that contained a half rescue kit. This AD 

requires identifying the part number 

and serial number of each half rescue kit 

located in the internal life raft 

installation and, depending on the 

findings, inspecting the life raft for 

damage, inspecting the condition of the 

flashlight battery, testing the flashlight 

battery, and replacing the life raft or 

flashlight battery (including the leak 

test) as applicable, as specified in a 

European Aviation Safety Agency (now 

European Union Aviation Safety 

Agency) (EASA) AD, which is 

incorporated by reference. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective August 27, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 27, 2021. 

ADDRESSES: For EASA material 

incorporated by reference (IBR) in this 

AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +49 221 8999 000; 

email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

material on the EASA website at https:// 

ad.easa.europa.eu. For Zodiac 

Aerospace service information 

identified in this final rule, contact 

Safran Aerosystems—Plaisir, 61 rue 

Pierre Curie CS20001, 78373 Plaisir 

Cedex, France; telephone (33) 1 61 34 23 

23; fax (33) 1 61 34 24 41; or at https:// 

www.safran-aerosystems.com. You may 

view this material at the FAA, Office of 

the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 

6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call 817–222–5110. 

It is also available in the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0188. 

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–2021– 

0188; 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 final rule, 

any comments received, and other 

information. The address for Docket 

Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Kathleen Arrigotti, Program Manager, 

Large Aircraft Section, International 

Validation Branch, Compliance & 

Airworthiness Division, FAA, 2200 

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

telephone and fax 206–231–3218; email 

kathleen.arrigotti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2016–0028, dated February 15, 2016 

(EASA AD 2016–0028) (also referred to 

as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI), to correct an unsafe condition 

for certain Airbus Helicopters Model 


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SA–365N, SA–365N1, AS–365N2, and 

AS 365 N3 helicopters. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters. The NPRM published in the 

Federal Register on March 23, 2021 (86 

FR 15431). The NPRM was prompted by 

a report that damage (scorch marks) was 

found on an internal life raft installation 

that contained a half rescue kit. 

Investigation revealed that the damage 

was caused by an unsuitable folding 

process for the life raft, which led to 

compression of the flashlight battery in 

the half rescue kit. This compression 

caused an electrolyte leakage, followed 

by a short-circuit that damaged the 

internal life raft. The NPRM proposed to 

require identifying the part number and 

serial number of each half rescue kit 

located in the internal life raft 

installation and, depending on the 

findings, inspecting the life raft for 

damage, inspecting the condition of the 

flashlight battery, testing the flashlight 

battery, and replacing the life raft or 

flashlight battery (including the leak 

test) as applicable, as specified in an 

EASA AD. 

The FAA is issuing this AD to address 

leakage of the flashlight battery in a half 

rescue kit, which could result in damage 

to the internal life raft, and subsequent 

failure of the internal life raft to deploy 

(for example after a ditching), which 

could impede or prevent safe evacuation 

of the occupants from the helicopter. 

See the MCAI for additional background 

information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Costs of Compliance Update 

The NPRM did not include the kit 

cost for the on-condition action 

specified in paragraph (2) of EASA AD 

2016–0028. The FAA has received this 

cost data and has updated the costs of 

compliance accordingly. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

changes. In the NPRM, the FAA 

proposed to require actions specified in 

EASA AD 2016–0028 through 

incorporation by reference, except for 

certain differences. The FAA has 

obtained approval to use this process 

from certain manufacturers, including 

Airbus Helicopters; however, the FAA 

has not worked with Zodiac Aerospace 

(which has been merged into Safran 

Aerosystems) for approval of this 

process. EASA AD 2016–0028 specifies 

using Zodiac Aerospace Service Bulletin 

SB 025–64–13, Revision 0, dated 

November 23, 2015 (SB 025–64–13 Rev 

0) or Revision 1, dated January 19, 2016 

(SB 025–64–13 Rev 1), to accomplish a 

certain action. In light of this, an 

exception has been added into this final 

rule to directly use SB 025–64–13 Rev 

0 or SB 025–64–13 Rev 1, instead of 

using SB 025–64–13 Rev 0 or SB 025– 

64–13 Rev 1 through incorporation by 

reference of EASA AD 2016–0028. 

The FAA has determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2016–0028 specifies 

identifying the part number and serial 

number of each half rescue kit located 

in the internal life raft installation, 

inspecting the life raft for damage 

(scorch marks), inspecting the condition 

of the flashlight battery (including 

cracks, impacts, swelling, damage, 

distorted case, and the connecting wire), 

testing the flashlight battery (turning on 

the flashlight), and replacing the life raft 

or flashlight battery (including the leak 

test). 

The FAA reviewed SB 025–64–13 Rev 

0, which specifies procedures to 

visually inspect the condition of the life 

raft and battery, and test the battery. The 

FAA also reviewed SB 025–64–13 Rev 

1, which specifies the same procedures 

as SB 025–64–13 Rev 0, except SB 025– 

64–13 Rev 1 corrects the serial numbers 

identified in the effectivity. 

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. 

Differences Between This AD and the 

MCAI 

Although the service information 

referenced in EASA AD 2016–0028 

specifies to return damaged life rafts to 

the manufacturer, this AD does not 

include that requirement. 

Where EASA AD 2016–0028 refers to 

its effective date or to January 7, 2016 

(the effective date of EASA AD 2015– 

0242), this AD requires compliance 

within 3 months after the effective date 

of this AD. 

Although the service information 

referenced in EASA AD 2016–0028 

specifies that trained and authorized 

Zodiac Aerospace personnel must do 

the inspection of the half rescue kit, this 

AD does not require that Zodiac 

Aerospace personnel do the inspection. 

Costs of Compliance 

The FAA estimates that this AD 

affects 30 helicopters of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

1 work-hour × $85 per hour = $85 .............................................................................................. $3,000 $3,085 $92,550 

The FAA estimates the following 

costs to do any necessary on-condition 

actions that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of helicopters that might need 

these on-condition actions: 


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Federal Register / Vol. 86, No. 139 / Friday, July 23, 2021 / Rules and Regulations 38911 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per product 

7.5 work-hours × $85 per hour = $637.50 .............................................................................................. Up to $78,154 ........ Up to $78,791.50. 

According to Zodiac Aerospace, some 

or all of the costs of this 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 the 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 that this AD: 

(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 Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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: 

2021–11–10 Airbus Helicopters:

Amendment 39–21572; Docket No. 

FAA–2021–0188; Project Identifier 

MCAI–2020–00642–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 27, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model SA–365N, SA–365N1, AS–365N2, and 

AS 365 N3 helicopters, certificated in any 

category, as identified in European Aviation 

Safety Agency (now European Union 

Aviation Safety Agency) (EASA) AD 2016– 

0028, dated February 15, 2016 (EASA AD 

2016–0028). 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2564, Life Raft. 

(e) Reason 

This AD was prompted by a report that 

damage (scorch marks) was found on an 

internal life raft installation that contained a 

half rescue kit. Investigation revealed that the 

damage was caused by an unsuitable folding 

process for the life raft, which led to 

compression of the flashlight battery in the 

half rescue kit. The FAA is issuing this AD 

to address leakage of the flashlight battery in 

a half rescue kit, which could result in 

damage to the internal life raft, and 

subsequent failure of the internal life raft to 

deploy (for example after a ditching), which 

could impede or prevent safe evacuation of 

the occupants from the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, EASA AD 2016–0028. 

(h) Exceptions to EASA AD 2016–0028 

(1) Where EASA AD 2016–0028 refers to its 

effective date or to January 7, 2016 (the 

effective date of EASA AD 2015–0242), this 

AD requires compliance within 3 months 

after the effective date of this AD. 

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

2016–0028 does not apply to this AD. 

(3) Where paragraph (2) of EASA AD 2016– 

0028 specifies accomplishing corrective 

actions in accordance with the instructions of 

Zodiac Aerospace SB No. 025–64–13 referred 

to in paragraph 3.B of Airbus Helicopters 

ASB AS365–25.01.63, this AD requires using 

Zodiac Aerospace Service Bulletin SB 025– 

64–13, Revision 0, dated November 23, 2015 

or Revision 1, dated January 19, 2016. 

(4) Although the service information 

referenced in EASA AD 2016–0028 specifies 

to return certain parts, this AD does not 

include that requirement. 

(5) Although the service information 

referenced in EASA AD 2016–0028 specifies 

that trained and authorized Zodiac 

Aerospace personnel must do the inspection 

of the half rescue kit, this AD does not 

require that Zodiac Aerospace personnel do 

the inspection. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

Branch, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (j) of this AD. 

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

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

For more information about this AD, 

contact Kathleen Arrigotti, Program Manager, 

Large Aircraft Section, International 

Validation Branch, Compliance & 

Airworthiness Division, FAA, 2200 South 

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

and fax (206) 231–3218; email 

kathleen.arrigotti@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 


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38912 Federal Register / Vol. 86, No. 139 / Friday, July 23, 2021 / Rules and Regulations 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) European Aviation Safety Agency 

(EASA) AD 2016–0028, dated February 15, 

2016. 

(ii) Zodiac Aerospace Service Bulletin SB 

025–64–13, Revision 0, dated November 23, 

2015. 

(iii) Zodiac Aerospace Service Bulletin SB 

025–64–13, Revision 1, dated January 19, 

2016. 

(3) For EASA AD 2016–0028, 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 

EASA AD on the EASA website at https://

ad.easa.europa.eu. For Zodiac Aerospace 

service information, contact Safran 

Aerosystems—Plaisir, 61 rue Pierre Curie 

CS20001, 78373 Plaisir Cedex, France; 

telephone (33) 1 61 34 23 23; fax (33) 1 61 

34 24 41; or at https://www.safranaerosystems.com. 

(4) You may view this service information 

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–2021–0188. 

(5) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, email fedreg.legal@

nara.gov, or go to https://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued on June 10, 2021. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–15480 Filed 7–22–21; 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; Amendment 

39–21638; AD 2021–14–11] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

General Electric Company (GE) CF6– 

80A and CF6–80C2 model turbofan 

engines. This AD was prompted by an 

inspection by the manufacturer that 

revealed cracking of the high-pressure 

turbine (HPT) rotor stage 1 disk. This 

AD requires 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 issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective August 27, 

2021. 

ADDRESSES: For service information 

identified in this final rule, 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. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

1179. 

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 

final rule, any comments received, and 

other information. The address for 

Docket Operations is U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

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: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply 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. The 

NPRM published in the Federal 

Register on February 22, 2021 (86 FR 

10496). The NPRM was prompted by an 

inspection by the manufacturer that 

revealed cracking of the HPT rotor stage 

1 disk caused by increased stress on the 

HPT rotor stage 1 disk as a result of 

flange-to-flange cracking on the HPT 

thermal shield. In the NPRM, the FAA 

proposed to require visual inspection 

and 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 issuing this AD to 

address the unsafe condition on these 

products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

five commenters. The commenters were 

Atlas Air, Boeing Commercial Airplanes 

(Boeing), Delta Air Lines (Delta), United 

Airlines (United) and the Air Line Pilots 

Association, International (ALPA). The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Update Shop Manual 

Atlas Air requested that the FAA 

revise GE CF6–80C2, ESM 72–53–05, 

High Pressure Turbine (HPT) Rotor 

Thermal Shield—Inspection to add the 

proposed requirement to remove from 

service the HPT thermal shield, the HPT 

rotor stage 1 disk, and the HPT rotor 

stage 2 disk from service if a crack is 

found, since the thermal shield can be 

sent to different vendors outside the 

engine shop. Delta also suggested that 

the technical data within the Engine 

Shop Manual (ESM) should be updated 

to ensure inspection requirements are 

equivalent across all tasks within the 

ESM. 

The FAA disagrees. Requiring updates 

to the ESM is unnecessary to correct the 

unsafe condition identified in this AD. 

The visual and FPI inspections in the 

required actions of this AD are the 

necessary actions to correct the unsafe 

condition. Operators, at their discretion, 

may work with the original equipment 

manufacturer to suggest changes to the 

ESM to include the inspections required 

by this AD. 


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