Airworthiness Directives; General Electric Company Turbofan Engines, 72178-72181 [2021-27480]

Download as PDF 72178 Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531; email 9-avs-nyaco-cos@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (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) De Havilland Aircraft of Canada Limited Service Bulletin 84–32–167, dated August 12, 2021. (ii) De Havilland Aircraft of Canada Limited Temporary Revision ALI–0223, dated October 15, 2020. (3) For service information identified in this AD, contact De Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416– 375–4000; fax 416–375–4539; email thd@ dehavilland.com; internet https:// dehavilland.com. (4) You may view this service information 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. (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 fr.inspection@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on December 3, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–27709 Filed 12–17–21; 11:15 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0869; Project Identifier AD–2021–00176–E; Amendment 39–21878; AD 2021–26–19] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. jspears on DSK121TN23PROD with RULES1 AGENCY: VerDate Sep<11>2014 17:14 Dec 20, 2021 Jkt 256001 The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34– 8C and CF34–8E model turbofan engines. This AD was prompted by a report of a quality escape during the manufacturing of a high-pressure turbine (HPT) rotor stage 1 disk. This AD requires removing the HPT rotor stage 1 disk from service and replacing the HPT rotor stage 1 disk with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 25, 2022. 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@ge.com; website: https://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 (817) 222– 5110. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0869. 8C5B1, CF34–8E2, CF34–8E2A1, CF34– 8E5, CF34–8E5A1, CF34–8E5A2, CF34– 8E6, and CF34–8E6A1 model turbofan engines. The NPRM published in the Federal Register on October 8, 2021 (86 FR 56217). The NPRM was prompted by GE notifying the FAA of a quality escape that occurred during the manufacturing of an HPT rotor stage 1 disk. The quality escape occurred at a supplier that began production in August 2019. On November 25, 2019, the supplier discovered tool gouges at the forward chamfer on the air holes of an HPT rotor stage 1 disk. These gouges may reduce the life of the HPT rotor stage 1 disk. In the NPRM, the FAA proposed to require removing a certain HPT rotor stage 1 disk from service and replacing the HPT rotor stage 1 disk with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0869; 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 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: Scott Stevenson, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7132; fax: (781) 238– 7199; email: Scott.M.Stevenson@faa.gov. SUPPLEMENTARY INFORMATION: The FAA reviewed the relevant data, considered the comment received, and determined that air safety requires adopting the AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. This AD is adopted as proposed in the NPRM. Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain GE CF34–8C5, CF34– The FAA estimates that this AD affects 23 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: SUMMARY: PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 Discussion of Final Airworthiness Directive Comments The FAA received a comment from one commenter, the Air Line Pilots Association (ALPA). ALPA supported the NPRM without change. Conclusion Related Service Information The FAA reviewed GE CF34–8C Alert Service Bulletin (ASB) 72–A0344 R01 and GE CF34–8E ASB 72–A0228 R01, both dated December 19, 2019. The ASBs describe procedures for removing the HPT rotor stage 1 disk. The FAA also reviewed GE Repair Document RD #150–1811–P1, dated March 17, 2020. This document describes procedures for repairing the HPT rotor stage 1 disk. Costs of Compliance E:\FR\FM\21DER1.SGM 21DER1 Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations 72179 ESTIMATED COSTS Action Labor cost Remove and replace HPT rotor stage 1 disk 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. jspears on DSK121TN23PROD with RULES1 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 VerDate Sep<11>2014 17:14 Dec 20, 2021 Jkt 256001 Parts cost 812 work-hours × $85 per hour = $69,020 .... 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 $258,100 Cost per product $327,120 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2021–26–19 General Electric Company: Amendment 39–21878; Docket No. FAA–2021–0869; Project Identifier AD– 2021–00176–E. (a) Effective Date This airworthiness directive (AD) is effective January 25, 2022. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) CF34–8C5, CF34–8C5B1, CF34–8E2, CF34–8E2A1, CF34–8E5, CF34– 8E5A1, CF34–8E5A2, CF34–8E6, and CF34– 8E6A1 model turbofan engines with an installed high-pressure turbine (HPT) rotor stage 1 disk, part number (P/N) 4125T22P04, and a serial number (S/N) listed in Figure 1 or Figure 2 to paragraph (c) of this AD. BILLING CODE 4910–13–P 1. The authority citation for part 39 continues to read as follows: Frm 00035 Fmt 4700 Sfmt 4700 $7,523,760 Authority: 49 U.S.C. 106(g), 40113, 44701. ■ PO 00000 Cost on U.S. operators E:\FR\FM\21DER1.SGM 21DER1 Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations release, damage to the engine, and damage to the airplane. (d) Subject jspears on DSK121TN23PROD with RULES1 Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (f) Compliance (e) Unsafe Condition This AD was prompted by a report of a quality escape during the manufacturing of an HPT rotor stage 1 disk. The FAA is issuing this AD to prevent failure of the HPT rotor stage 1 disk. The unsafe condition, if not addressed, could result in uncontained disk VerDate Sep<11>2014 17:14 Dec 20, 2021 Jkt 256001 Comply with this AD within the compliance times specified, unless already done. (g) Required Actions For all affected engines, at the next engine shop visit or before the HPT rotor stage 1 disk accumulates 7,600 cycles since new, PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 whichever occurs first after the effective date of this AD, remove the HPT rotor stage 1 disk from service and replace with a part eligible for installation. (h) Definitions For the purpose of this AD: (1) An ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the E:\FR\FM\21DER1.SGM 21DER1 ER21DE21.008</GPH> 72180 Federal Register / Vol. 86, No. 242 / Tuesday, December 21, 2021 / Rules and Regulations purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (2) A ‘‘part eligible for installation’’ is an HPT rotor stage 1 disk that is not listed in Figure 1 or Figure 2 to paragraph (c) of this AD or an HPT rotor stage 1 disk that has been repaired using an FAA-approved repair. Note 1 to paragraph (h)(2): Guidance for repairing the HPT rotor stage 1 disk can be found in GE Repair Document RD #150– 1811–P1, dated March 17, 2020. (i) 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 certification office, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: ANE-ADAMOC@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 Scott Stevenson, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7132; fax: (781) 238–7199; email: Scott.M.Stevenson@faa.gov. (k) Material Incorporated by Reference None. Issued on December 15, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. BILLING CODE 4910–13–C DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0786; Project Identifier MCAI–2021–00429–A; Amendment 39–21843; AD 2021–24–22] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes jspears on DSK121TN23PROD with RULES1 For service information identified in this final rule, contact Pilatus Aircraft Ltd., Customer Support General Aviation, CH–6371 Stans, Switzerland; phone: +41 848 247 365; email: techsupport.ch@pilatusaircraft.com; website: https:// www.pilatus-aircraft.com. 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. ADDRESSES: You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0786; 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, the MCAI, 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: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2012–06– 16, which applied to all Pilatus Aircraft Ltd. (Pilatus) Model PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC– SUMMARY: 17:14 Dec 20, 2021 This AD is effective January 25, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 25, 2022. DATES: Examining the AD Docket [FR Doc. 2021–27480 Filed 12–20–21; 8:45 am] VerDate Sep<11>2014 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. AD 2012–06–16 required installing a new rudder and elevator locking screw and modifying the installation of the rudder and elevator hinge bolt. Since the FAA issued AD 2012–06–16, the European Union Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on these products. This AD does not retain any actions required by AD 2012–06–16 and requires inspecting and modifying the rudder, elevator, and right-hand (RH) aileron hinge bolt installations. The FAA is issuing this AD to address the unsafe condition on these products. Jkt 256001 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: PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 72181 Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2012–06–16, Amendment 39–16997 (77 FR 19061, March 30, 2012) (AD 2012–06–16). AD 2012–06–16 applied 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 required installing a new elevator and rudder locking screw and modifying the installation of the elevator and rudder hinge bolt. The NPRM published in the Federal Register on September 17, 2021 (86 FR 51835). The NPRM was prompted by AD 2021–0098, dated April 9, 2021 (referred to after this as ‘‘the MCAI’’), issued by EASA, which is the Technical Agent for the Member States of the European Union. The MCAI states: Occurrences were reported where, on certain PC–6 aeroplanes, the elevator or the rudders was lost or partially detached during flight. All the occurrences happened on PC– 6 aeroplanes in CONFIG 1. This condition, if not corrected, could lead to in-flight failure of the elevator or rudder attachment, possibly resulting in reduced control of the aeroplane. To address this potential unsafe condition, Pilatus issued SB 55–001 (original issue and Revision 1) to provide rework instructions for the elevator and rudder hinge bolt locking. Consequently, EASA published AD 2011– 0230 to require this rework. Subsequently, Pilatus issued recommended SB 55–003 (later revised) to provide instructions to modify the hinge bolt installation of the elevator and rudder. This [service bulletin] SB, being recommended only, had no impact on the existing EASA AD. Since that [EASA] AD and the recommended Pilatus SB 55–003 were published, the latest risk assessment determined that the modification of the hinge bolt installation of the elevator, rudder and right-hand (RH) aileron installation must be required to reach an acceptable level of safety for the affected aeroplanes. Consequently, Pilatus issued the SB, as defined in this [EASA] AD, to provide instructions to modify the affected aeroplanes into CONFIG 2 standard. For the reasons described above, this [EASA] AD supersedes EASA AD 2011–0230 and requires, for certain aeroplanes, a onetime inspection of the elevator and rudder installation, followed by repetitive inspections of the elevator and rudder, and, depending on findings, accomplishment of applicable corrective action(s). This [EASA] AD also requires modification of the elevator, rudder and RH aileron hinge bolt installations into CONFIG 2, which is the terminating action for the repetitive inspections required by this [EASA] AD. Finally, this [EASA] AD prohibits (re)installation of affected parts. E:\FR\FM\21DER1.SGM 21DER1

Agencies

[Federal Register Volume 86, Number 242 (Tuesday, December 21, 2021)]
[Rules and Regulations]
[Pages 72178-72181]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-27480]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0869; Project Identifier AD-2021-00176-E; 
Amendment 39-21878; AD 2021-26-19]
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) CF34-8C and CF34-8E model 
turbofan engines. This AD was prompted by a report of a quality escape 
during the manufacturing of a high-pressure turbine (HPT) rotor stage 1 
disk. This AD requires removing the HPT rotor stage 1 disk from service 
and replacing the HPT rotor stage 1 disk with a part eligible for 
installation. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective January 25, 2022.

ADDRESSES: For service information identified in this final rule, 
contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; 
phone: (513) 552-3272; email: [email protected]; website: 
https://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 (817) 222-5110. It is 
also available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2021-0869.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0869; 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 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: Scott Stevenson, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: (781) 238-7132; fax: (781) 238-7199; email: 
[email protected].

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 certain GE CF34-8C5, 
CF34-8C5B1, CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, 
CF34-8E6, and CF34-8E6A1 model turbofan engines. The NPRM published in 
the Federal Register on October 8, 2021 (86 FR 56217). The NPRM was 
prompted by GE notifying the FAA of a quality escape that occurred 
during the manufacturing of an HPT rotor stage 1 disk. The quality 
escape occurred at a supplier that began production in August 2019. On 
November 25, 2019, the supplier discovered tool gouges at the forward 
chamfer on the air holes of an HPT rotor stage 1 disk. These gouges may 
reduce the life of the HPT rotor stage 1 disk. In the NPRM, the FAA 
proposed to require removing a certain HPT rotor stage 1 disk from 
service and replacing the HPT rotor stage 1 disk with a part eligible 
for installation. The FAA is issuing this AD to address the unsafe 
condition on these products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from one commenter, the Air Line Pilots 
Association (ALPA). ALPA supported the NPRM without change.

Conclusion

    The FAA reviewed the relevant data, considered the comment 
received, and determined that air safety requires adopting the AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these products. This AD is adopted as proposed in the 
NPRM.

Related Service Information

    The FAA reviewed GE CF34-8C Alert Service Bulletin (ASB) 72-A0344 
R01 and GE CF34-8E ASB 72-A0228 R01, both dated December 19, 2019. The 
ASBs describe procedures for removing the HPT rotor stage 1 disk. The 
FAA also reviewed GE Repair Document RD #150-1811-P1, dated March 17, 
2020. This document describes procedures for repairing the HPT rotor 
stage 1 disk.

Costs of Compliance

    The FAA estimates that this AD affects 23 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

[[Page 72179]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Remove and replace HPT rotor stage 1    812 work-hours x $85 per        $258,100        $327,120      $7,523,760
 disk.                                   hour = $69,020.
----------------------------------------------------------------------------------------------------------------

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

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:

2021-26-19 General Electric Company: Amendment 39-21878; Docket No. 
FAA-2021-0869; Project Identifier AD-2021-00176-E.

(a) Effective Date

    This airworthiness directive (AD) is effective January 25, 2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) CF34-8C5, CF34-
8C5B1, CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-
8E6, and CF34-8E6A1 model turbofan engines with an installed high-
pressure turbine (HPT) rotor stage 1 disk, part number (P/N) 
4125T22P04, and a serial number (S/N) listed in Figure 1 or Figure 2 
to paragraph (c) of this AD.
BILLING CODE 4910-13-P

[[Page 72180]]

[GRAPHIC] [TIFF OMITTED] TR21DE21.008

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by a report of a quality escape during the 
manufacturing of an HPT rotor stage 1 disk. The FAA is issuing this 
AD to prevent failure of the HPT rotor stage 1 disk. The unsafe 
condition, if not addressed, could result in uncontained disk 
release, 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

    For all affected engines, at the next engine shop visit or 
before the HPT rotor stage 1 disk accumulates 7,600 cycles since 
new, whichever occurs first after the effective date of this AD, 
remove the HPT rotor stage 1 disk from service and replace with a 
part eligible for installation.

(h) Definitions

    For the purpose of this AD:
    (1) An ``engine shop visit'' is the induction of an engine into 
the shop for maintenance involving the separation of pairs of major 
mating engine flanges, except that the separation of engine flanges 
solely for the

[[Page 72181]]

purposes of transportation without subsequent engine maintenance 
does not constitute an engine shop visit.
    (2) A ``part eligible for installation'' is an HPT rotor stage 1 
disk that is not listed in Figure 1 or Figure 2 to paragraph (c) of 
this AD or an HPT rotor stage 1 disk that has been repaired using an 
FAA-approved repair.
    Note 1 to paragraph (h)(2): Guidance for repairing the HPT rotor 
stage 1 disk can be found in GE Repair Document RD #150-1811-P1, 
dated March 17, 2020.

(i) 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 
certification office, send it to the attention of the person 
identified in paragraph (j) of this AD. Information may be emailed 
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.

(j) Related Information

    For more information about this AD, contact Scott Stevenson, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7132; fax: (781) 238-7199; 
email: [email protected].

(k) Material Incorporated by Reference

    None.

    Issued on December 15, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-27480 Filed 12-20-21; 8:45 am]
BILLING CODE 4910-13-C

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