preamble attached >>>
ADs updated daily at www.Tdata.com
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 tur-
    bine (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.

    FIGURE 1 TO PARAGRAPH (C) –HPT ROTOR STAGE 1 DISK, P/N 4125T22P04, IN-
                               STALLED ON CF34-8C5 AND CF34-8C5B1 ENGINES 
    ______________________________________________________________________
                        HPT ROTOR STAGE 1 DISK S/N
    ______________________________________________________________________
                                  NCU1234C
                                  NCU0180C
                                  NCU0174C
                                  NCU0183C
                                  NCU6175C
                                  NCU6174C
                                  NCU7694C
                                  GATJ8T64
                                  NCU7065C
                                  NCU7068C
                                  NCU6173C
                                  NCU1232C
                                  NCU7698C
                                  GATJ8P5T
    ______________________________________________________________________


    FIGURE 2 TO PARAGRAPH (C) –HPT ROTOR STAGE 1 DISK, P/N 4125T22P04, IN-
                               STALLED ON CF34-8E2,  CF34-8E2A1, CF34-8E5,
                               CF34-8E5A1, CF34-8E5A2, CF34-8E6, AND CF34-
                               8E6A1 ENGINES                              
    ______________________________________________________________________
                        HPT ROTOR STAGE 1 DISK S/N
    ______________________________________________________________________
                                  GATJ8PJF
                                  GATJ8P5R
                                  NCU9014C
                                  NCU9654A
                                  GATJ903T
                                  NCU8314C
                                  GATJ8WK4
                                  NCU9785A
                                  NCU1233C
                                  NCU2151C
                                  NCU7070C
                                  NCU2920C
                                  NCU7692C
                                  NCU6171C
                                  GATJ8TCF
                                  GATJ8T63
                                  NCU8313C
    ______________________________________________________________________

(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 manu-
    facturing 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 al-
    ready 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
    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-AD-AMOC@faa.gov.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector, 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 & Airworth
-iness Division, Aircraft Certification Service.

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.
PREAMBLE 

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: 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.

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:

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:

Estimated Costs

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

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings

This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive: