Airworthiness Directives; General Electric Company Turbofan Engines, 57666-57668 [2020-20337]

Download as PDF 57666 Federal Register / Vol. 85, No. 180 / Wednesday, September 16, 2020 / Rules and Regulations PART 1600—EMPLOYEE CONTRIBUTION ELECTIONS, CONTRIBUTION ALLOCATIONS, AND AUTOMATIC ENROLLMENT PROGRAM NATIONAL CREDIT UNION ADMINISTRATION 1. The authority citation continues to read as follows: Chartering and Field of Membership ■ Authority: 5 U.S.C. 8351, 8432(a), 8432(b), 8432(c), 8432(j), 8432d, 8474(b)(5) and (c)(1), and 8440e. § 1600.34 [Amended] 2. In § 1600.34, amend paragraphs (a), (b), and (c) by removing the term ‘‘3%’’ and adding the term ‘‘5%’’ in its place. ■ § 1600.37 [Amended] 12 CFR Part 701 RIN 3133–AF06 Correction In rule document 2020–16988 appearing on pages 56498–56514 in the issue of September 14, 2020, make the following correction: On page 56498, in the third column, in the DATES section, in the second line ‘‘September 14, 2020’’ should read ‘‘October 14, 2020’’. [FR Doc. C1–2020–16988 Filed 9–14–20; 11:15 am] 3. In § 1600.37, amend paragraph (a) by removing the term ‘‘3 percent’’ and adding the term ‘‘5 percent’’ in its place. ■ BILLING CODE 1301–00–D DEPARTMENT OF TRANSPORTATION PART 1650—METHODS OF WITHDRAWING FUNDS FROM THE THRIFT SAVINGS PLAN Federal Aviation Administration 14 CFR Part 39 4. The authority citation continues to read as follows: ■ Authority: 5 U.S.C. 8351, 8432d, 8433, 8434, 8435, 8474(b)(5) and 8474(c)(1). RIN 2120–AA64 5. Amend § 1650.13 by revising paragraph (a)(2) to read as follows: ■ jbell on DSKJLSW7X2PROD with RULES § 1650.13 Airworthiness Directives; General Electric Company Turbofan Engines Installment payments. (a) * * * (2) An installment payment amount calculated based on life expectancy. Payments based on life expectancy are determined using the factors set forth in the Internal Revenue Service life expectancy tables codified at 26 CFR 1.401(a)(9)–9, Q&A 1 and 2. The installment payment amount is calculated by dividing the account balance by the factor from the IRS life expectancy tables based upon the participant’s age as of his or her birthday in the year payments are to begin. This amount is then divided by the number of installment payments to be made per calendar year to yield the installment payment amount. In subsequent years, the installment payment amount is recalculated on the first installment payment date of the year by dividing the prior December 31 account balance by the factor in the IRS life expectancy tables based upon the participant’s age as of his or her birthday in the year payments will be made. There is no minimum amount for an installment payment calculated based on this method. * * * * * [FR Doc. 2020–17811 Filed 9–15–20; 8:45 am] BILLING CODE 6760–01–P VerDate Sep<11>2014 16:31 Sep 15, 2020 Jkt 250001 [Docket No. FAA–2020–0494; Project Identifier AD–2020–00324–E; Amendment 39–21235; AD 2020–18–14] Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90– 110B1 and GE90–115B model turbofan engines with a certain high-pressure turbine (HPT) rotor stage 2 disk installed. This AD was prompted by a report from the manufacturer that a subsurface anomaly was found on a HPT rotor stage 2 disk. This AD requires an ultrasonic inspection (USI) of the HPT rotor stage 2 disk and, depending on the result of the inspection, replacement of the HPT rotor stage 2 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 October 21, 2020. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 21, 2020. 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. You SUMMARY: PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 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 on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0494. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0494; 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: Stephen Elwin, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7236; fax: 781–238–7199; email: stephen.l.elwin@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 GE GE90–110B1 and GE90– 115B model turbofan engines with a certain HPT rotor stage 2 disk installed. The NPRM published in the Federal Register on May 18, 2020 (85 FR 29676). The NPRM was prompted by a report from the manufacturer that a subsurface anomaly was found on a HPT rotor stage 2 disk. The NPRM proposed to require a USI of the HPT rotor stage 2 disk and, depending on the result of the inspection, replacement of the HPT rotor stage 2 disk with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products. Comments The FAA gave the public the opportunity to participate in developing this final rule. The FAA has considered the comments received. The Boeing Company, FedEx Express, United Airlines, and the Air Line Pilots Association, International, supported the NPRM. Conclusion The FAA reviewed the relevant data, considered the comments received, and E:\FR\FM\16SER1.SGM 16SER1 Federal Register / Vol. 85, No. 180 / Wednesday, September 16, 2020 / Rules and Regulations determined that air safety and the public interest require adopting this final rule as proposed except for minor editorial changes. 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. 57667 Costs of Compliance Service Information Incorporated by Reference under 1 CFR part 51 The FAA reviewed GE GE90–100 Service Bulletin (SB) 72–0838, dated January 31, 2020. The SB describes procedures for performing an USI of the HPT rotor stage 2 disk. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. The FAA estimates that this AD affects 28 engines installed on airplanes of U.S. registry. Based on updated information from the manufacturer, the FAA revised the number of engines installed on airplanes of U.S. registry from 12 in the NPRM to 28 in this final rule. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators USI of HPT rotor stage 2 disk ........................ 8 work-hours × $85 per hour = $680 ............. $0 $680 $19,040 The FAA estimates the following costs to do any necessary replacements that would be required based on the results of the inspection. The FAA has no way of determining the number of engines that might need this replacement: ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Remove and replace HPT rotor stage 2 disk .............................................................................. 2 work-hours × $85 per hour = $170 $565,600 $565,770 Authority for this Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds 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. jbell on DSKJLSW7X2PROD with RULES 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 VerDate Sep<11>2014 16:31 Sep 15, 2020 Jkt 250001 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) 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 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. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2020–18–14 General Electric Company: Amendment 39–21235; Docket No. FAA–2020–0494; Project Identifier AD– 2020–00324–E. (a) Effective Date This AD is effective October 21, 2020. (b) Affected ADs None. (c) Applicability This AD applies to all General Electric Company (GE) GE90–110B1 and GE90–115B model turbofan engines with a high-pressure turbine (HPT) rotor stage 2 disk, part number 2505M73P03, and with a serial number listed in Appendix—A, Table 1, of GE GE90–100 Service Bulletin (SB) 72–0838, dated January 31, 2020. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by a report from the manufacturer that a subsurface anomaly was found on a HPT rotor stage 2 disk. The FAA is issuing this AD to prevent failure of the HPT rotor stage 2 disk. The unsafe condition, if not addressed, could result in uncontained HPT rotor stage 2 disk release, E:\FR\FM\16SER1.SGM 16SER1 57668 Federal Register / Vol. 85, No. 180 / Wednesday, September 16, 2020 / Rules and Regulations 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 Action (1) At the next piece-part exposure after the effective date of this AD, perform an ultrasonic inspection (USI) of the HPT rotor stage 2 disk in accordance with the Accomplishment Instructions, paragraph 3.B.(1)(a), of GE GE90–100 SB 72–0838, dated January 31, 2020. (2) If, during the USI required by paragraph (g)(1) of this AD, a rejectable indication is found, remove the HPT rotor stage 2 disk from service before further flight and replace it with a part eligible for installation. (h) Definition For the purpose of this AD, ‘‘piece-part exposure’’ is when the HPT rotor stage 2 disk is removed from the engine and completely disassembled. (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. 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. jbell on DSKJLSW7X2PROD with RULES (j) Related Information For more information about this AD, contact Stephen Elwin, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7236; fax: 781–238–7199; email: stephen.l.elwin@faa.gov. (k) 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 the AD specifies otherwise. (i) General Electric Company (GE) GE90– 100 Service Bulletin 72–0838, dated January 31, 2020. (ii) [Reserved] (3) For GE 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. (4) You may view this service information at FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District VerDate Sep<11>2014 16:31 Sep 15, 2020 Jkt 250001 Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. (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 August 26, 2020. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–20337 Filed 9–15–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0394; Project Identifier AD–2019–00141–E; Amendment 39–21230; AD 2020–18–09] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all Honeywell International Inc. (Honeywell) ALF502L, ALF502L–2, ALF502L–2A, ALF502L–2C, ALF502L– 3, ALF502R–3, ALF502R–3A, ALF502R–4, ALF502R–5, ALF502R–6, LF507–1F, and LF507–1H model turbofan engines. This AD was prompted by a report of an engine experiencing an uncontained release of low-pressure turbine (LPT) blades. This AD requires initial and repetitive visual inspections of the overspeed fuel solenoid valve assembly and the fuel filter outlet. Depending on the results of these inspections, the AD may require inspection of the adjacent fuel system tube assemblies as well as replacement or overhaul of the overspeed fuel solenoid valve assembly. This AD also requires periodic overhaul of the overspeed fuel solenoid valve assembly. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 21, 2020. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 21, 2020. SUMMARY: PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 For service information identified in this final rule, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034–2802; phone: 800–601–3099; website: https:// aerospace.honeywell.com/en#/. 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 on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0394. ADDRESSES: Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0394; 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: Mark Matzke, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5312; fax: 562–627–5210; email: mark.matzke@ 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 Honeywell ALF502L, ALF502L–2, ALF502L–2A, ALF502L– 2C, ALF502L–3, ALF502R–3, ALF502R– 3A, ALF502R–4, ALF502R–5, ALF502R–6, LF507–1F, and LF507–1H model turbofan engines. The NPRM published in the Federal Register on May 4, 2020 (85 FR 26375). The NPRM was prompted by a report of an engine experiencing an uncontained release of LPT blades. The NPRM proposed to require initial and repetitive visual inspections of the overspeed fuel solenoid valve assembly and the fuel filter outlet. Depending on the results of these inspections, the NPRM proposed to require inspection of the adjacent fuel system tube assemblies as well as replacement or overhaul of the overspeed fuel solenoid valve assembly. The NPRM also proposed to require periodic overhaul of the overspeed fuel E:\FR\FM\16SER1.SGM 16SER1

Agencies

[Federal Register Volume 85, Number 180 (Wednesday, September 16, 2020)]
[Rules and Regulations]
[Pages 57666-57668]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-20337]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0494; Project Identifier AD-2020-00324-E; 
Amendment 39-21235; AD 2020-18-14]
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 all 
General Electric Company (GE) GE90-110B1 and GE90-115B model turbofan 
engines with a certain high-pressure turbine (HPT) rotor stage 2 disk 
installed. This AD was prompted by a report from the manufacturer that 
a subsurface anomaly was found on a HPT rotor stage 2 disk. This AD 
requires an ultrasonic inspection (USI) of the HPT rotor stage 2 disk 
and, depending on the result of the inspection, replacement of the HPT 
rotor stage 2 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 October 21, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 21, 
2020.

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]. 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 on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0494.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0494; 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: Stephen Elwin, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7236; 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 all GE GE90-110B1 and 
GE90-115B model turbofan engines with a certain HPT rotor stage 2 disk 
installed. The NPRM published in the Federal Register on May 18, 2020 
(85 FR 29676). The NPRM was prompted by a report from the manufacturer 
that a subsurface anomaly was found on a HPT rotor stage 2 disk. The 
NPRM proposed to require a USI of the HPT rotor stage 2 disk and, 
depending on the result of the inspection, replacement of the HPT rotor 
stage 2 disk with a part eligible for installation. The FAA is issuing 
this AD to address the unsafe condition on these products.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA has considered the comments 
received. The Boeing Company, FedEx Express, United Airlines, and the 
Air Line Pilots Association, International, supported the NPRM.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and

[[Page 57667]]

determined that air safety and the public interest require adopting 
this final rule as proposed except for minor editorial changes. 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.

Service Information Incorporated by Reference under 1 CFR part 51

    The FAA reviewed GE GE90-100 Service Bulletin (SB) 72-0838, dated 
January 31, 2020. The SB describes procedures for performing an USI of 
the HPT rotor stage 2 disk. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD affects 28 engines installed on 
airplanes of U.S. registry. Based on updated information from the 
manufacturer, the FAA revised the number of engines installed on 
airplanes of U.S. registry from 12 in the NPRM to 28 in this final 
rule.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
USI of HPT rotor stage 2 disk.......  8 work-hours x $85 per               $0             $680          $19,040
                                       hour = $680.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that would be required based on the results of the 
inspection. The FAA has no way of determining the number of engines 
that might need this replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                            Action                                Labor cost       Parts cost        product
----------------------------------------------------------------------------------------------------------------
Remove and replace HPT rotor stage 2 disk....................  2 work-hours x         $565,600         $565,770
                                                               $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: 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) 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 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 (AD):

2020-18-14 General Electric Company: Amendment 39-21235; Docket No. 
FAA-2020-0494; Project Identifier AD-2020-00324-E.

(a) Effective Date

    This AD is effective October 21, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all General Electric Company (GE) GE90-110B1 
and GE90-115B model turbofan engines with a high-pressure turbine 
(HPT) rotor stage 2 disk, part number 2505M73P03, and with a serial 
number listed in Appendix--A, Table 1, of GE GE90-100 Service 
Bulletin (SB) 72-0838, dated January 31, 2020.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report from the manufacturer that a 
subsurface anomaly was found on a HPT rotor stage 2 disk. The FAA is 
issuing this AD to prevent failure of the HPT rotor stage 2 disk. 
The unsafe condition, if not addressed, could result in uncontained 
HPT rotor stage 2 disk release,

[[Page 57668]]

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 Action

    (1) At the next piece-part exposure after the effective date of 
this AD, perform an ultrasonic inspection (USI) of the HPT rotor 
stage 2 disk in accordance with the Accomplishment Instructions, 
paragraph 3.B.(1)(a), of GE GE90-100 SB 72-0838, dated January 31, 
2020.
    (2) If, during the USI required by paragraph (g)(1) of this AD, 
a rejectable indication is found, remove the HPT rotor stage 2 disk 
from service before further flight and replace it with a part 
eligible for installation.

(h) Definition

    For the purpose of this AD, ``piece-part exposure'' is when the 
HPT rotor stage 2 disk is removed from the engine and completely 
disassembled.

(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. 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.

(j) Related Information

    For more information about this AD, contact Stephen Elwin, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7236; fax: 781-238-7199; email: 
[email protected].

(k) 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 the AD specifies otherwise.
    (i) General Electric Company (GE) GE90-100 Service Bulletin 72-
0838, dated January 31, 2020.
    (ii) [Reserved]
    (3) For GE service information identified in this AD, contact 
General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; 
phone: 513-552-3272; email: [email protected].
    (4) You may view this service information at 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.
    (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: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on August 26, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-20337 Filed 9-15-20; 8:45 am]
BILLING CODE 4910-13-P