Airworthiness Directives; General Electric Company Turbofan Engines, 10496-10498 [2021-01814]

Download as PDF 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. tkelley on DSKBCP9HB2PROD with PROPOSALS (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 VerDate Sep<11>2014 18:29 Feb 19, 2021 Jkt 253001 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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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– SUMMARY: PO 00000 Frm 00038 Fmt 4702 Sfmt 4702 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. The FAA must receive comments on this proposed AD by April 8, 2021. DATES: 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. ADDRESSES: 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: E:\FR\FM\22FEP1.SGM 22FEP1 10497 Federal Register / Vol. 86, No. 33 / Monday, February 22, 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–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. tkelley on DSKBCP9HB2PROD with PROPOSALS ON-CONDITION COSTS Action Labor cost Replace HPT thermal shield ........................................ Replace HPT rotor stage 1 disk ................................... Replace HPT rotor stage 2 disk ................................... 2 work-hours × $85 per hour = $170 ........................... 2 work-hours × $85 per hour = $170 ........................... 2 work-hours × $85 per hour = $170 ........................... 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: VerDate Sep<11>2014 18:29 Feb 19, 2021 Jkt 253001 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 PO 00000 Frm 00039 Fmt 4702 Sfmt 4702 Parts cost $209,600 799,700 364,600 Cost per product $209,770 799,870 364,770 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 E:\FR\FM\22FEP1.SGM 22FEP1 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: 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [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. tkelley on DSKBCP9HB2PROD with PROPOSALS (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, VerDate Sep<11>2014 18:29 Feb 19, 2021 Jkt 253001 (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. PART 39—AIRWORTHINESS DIRECTIVES § 39.13 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. (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. PO 00000 Frm 00040 Fmt 4702 Sfmt 4702 (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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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. SUMMARY: E:\FR\FM\22FEP1.SGM 22FEP1

Agencies

[Federal Register Volume 86, Number 33 (Monday, February 22, 2021)]
[Proposed Rules]
[Pages 10496-10498]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-01814]


-----------------------------------------------------------------------

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: [email protected]; 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: 
[email protected].

SUPPLEMENTARY INFORMATION:

[[Page 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 flange-to-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
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Perform FPI and visual inspection of  2 work-hours x $85 per               $0             $170         $184,280
 HPT thermal shield.                   hour = $170.
----------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace HPT thermal shield....................  2 work-hours x $85 per hour =           $209,600        $209,770
                                                 $170.
Replace HPT rotor stage 1 disk................  2 work-hours x $85 per hour =            799,700         799,870
                                                 $170.
Replace HPT rotor stage 2 disk................  2 work-hours x $85 per hour =            364,600         364,770
                                                 $170.
----------------------------------------------------------------------------------------------------------------

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

[[Page 10498]]

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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: [email protected].
    (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: [email protected].
    (2) For service information identified in this AD, contact 
General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; 
phone: (513) 552-3272; email: [email protected]; 
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