Airworthiness Directives; CFM International, S.A. Turbofan Engines

[Federal Register Volume 87, Number 138 (Wednesday, July 20, 2022)]
[Rules and Regulations]
[Pages 43209-43211]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-15391]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 87, No. 138 / Wednesday, July 20, 2022 / 
Rules and Regulations

[[Page 43209]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0877; Project Identifier AD-2022-00506-E; 
Amendment 39-22123; AD 2022-15-04]
RIN 2120-AA64


Airworthiness Directives; CFM International, S.A. Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain CFM International, S.A. (CFM) LEAP-1A model turbofan engines. 
This AD was prompted by reports of non-synchronous vibrations resulting 
in more open clearances and potential hot gas ingestion into the high-
pressure turbine (HPT) rotor cavity, which may result in thermal 
degradation of the HPT rotor interstage seal and HPT rotor stage 2 
disk. This AD requires inspection of the stage 2 HPT nozzle assembly 
honeycomb and HPT stator stationary seal honeycomb. Depending on the 
results of the inspection, this AD requires replacement of the stage 2 
HPT nozzle assembly honeycomb, HPT stator stationary seal, HPT rotor 
interstage seal, and HPT rotor stage 2 disk. The FAA is issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective August 4, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 4, 
2022.
    The FAA must receive comments on this AD by September 6, 2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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.
    <bullet> 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 final rule, contact CFM 
International, S.A., Aviation Operations Center, 1 Neumann Way, M/D 
Room 285, Cincinnati, OH 45125; phone: (877) 432-3272; email: 
[email protected]">aviation.[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 (817) 222-5110. It is 
also available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2022-0877.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-0877; 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 street address for the 
Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Mehdi Lamnyi, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: (781) 238-7743; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    On January 26, 2020, an Airbus Model A319NEO airplane, powered by 
CFM LEAP-1A model turbofan engines, experienced high vibrations. A 
subsequent engine disassembly by the manufacturer revealed three areas 
of missing material on the HPT rotor interstage seal and multiple 
radial and circumferential cracks on the forward arm. The 
manufacturer's investigation determined that the degraded HPT rotor 
interstage seal failure locations were initiated by creep rupture, 
related to hot gas ingestion due to reduced effectiveness of the stage 
2 HPT nozzle honeycomb seals, a condition that could impact the HPT 
rotor stage 2 disk low-cycle fatigue life. This condition, if not 
addressed, could result in an uncontained release of the HPT rotor 
interstage seal and HPT rotor stage 2 disk, damage to the engine, and 
damage to the airplane. The FAA is issuing this AD to address the 
unsafe condition on these products.

FAA's Determination

    The FAA is issuing this AD because the agency has determined the 
unsafe condition described previously is likely to exist or develop in 
other products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed CFM Service Bulletin (SB) LEAP-1A-72-00-0460-01A-
930A-D, Issue 002-00, dated June 10, 2022. This service information 
specifies procedures for inspecting the stage 2 HPT nozzle assembly 
honeycomb and HPT stator stationary seal honeycomb. This service 
information also specifies procedures for replacing the stage 2 HPT 
nozzle assembly honeycomb, HPT stator stationary seal, HPT rotor 
interstage seal, and 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 ADDRESSES.

AD Requirements

    This AD requires inspection of the stage 2 HPT nozzle assembly 
honeycomb and HPT stator stationary seal honeycomb. Depending on the 
results of the inspection, this AD requires replacement of the stage 2 
HPT nozzle assembly honeycomb, HPT stator stationary seal, HPT rotor 
interstage seal, and HPT rotor stage 2 disk.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public

[[Page 43210]]

interest.'' Under this section, an agency, upon finding good cause, may 
issue a final rule without providing notice and seeking comment prior 
to issuance. Further, section 553(d) of the APA authorizes agencies to 
make rules effective in less than thirty days, upon a finding of good 
cause.
    The FAA has found the risk to the flying public justifies waiving 
notice and comment prior to adoption of this rule because no domestic 
operators use this product. It is unlikely that the FAA will receive 
any adverse comments or useful information about this AD from any U.S. 
operator. Accordingly, notice and opportunity for prior public comment 
are unnecessary, pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for 
the foregoing reason, the FAA finds that good cause exists pursuant to 
5 U.S.C. 553(d) for making this amendment effective in less than 30 
days.

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2022-0877 and Project Identifier 
AD-2022-00506-E'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the final rule, 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 final rule 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 final rule.

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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to Mehdi 
Lamnyi, 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.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 0 engines installed on 
airplanes of U.S. registry.
    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
----------------------------------------------------------------------------------------------------------------
Inspect stage 2 HPT nozzle assembly     3 work-hours x $85 per                $0            $255              $0
 honeycomb.                              hour = $255.
Inspect HPT stator stationary seal      3 work-hours x $85 per                 0             255               0
 honeycomb.                              hour = $255.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that would be required based on the results of the 
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 rotor interstage seal.............  8 work-hours x $85 per hour =           $168,000        $168,680
                                                 $680.
Replace HPT rotor stage 2 disk................  8 work-hours x $85 per hour =            324,400         325,080
                                                 $680.
Replace stage 2 HPT nozzle assembly honeycomb.  24 work-hours x $85 per hour =           951,840         953,880
                                                 $2,040.
Replace HPT stator stationary seal............  8 work-hours x $85 per hour =             98,000          98,680
                                                 $680.
----------------------------------------------------------------------------------------------------------------

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:

[[Page 43211]]

    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866, and
    (2) Will not affect intrastate aviation in Alaska.

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:

2022-15-04 CFM International, S.A.: Amendment 39-22123; Docket No. 
FAA-2022-0877; Project Identifier AD-2022-00506-E.

(a) Effective Date

    This airworthiness directive (AD) is effective August 4, 2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to CFM International, S.A. (CFM) LEAP-1A23, 
LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-
1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, 
LEAP-1A35A model turbofan engines with engine serial number (ESN) 
598-280, 598-283, 598-284, 598-291, 598-300, 598-302, 598-327, 598-
572, 598-629, 598-646, 598-648, 598-659, 598-667, 598-812, 598-862, 
598-909, and 599-192.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of non-synchronous vibrations 
resulting in more open clearances and potential hot gas ingestion 
into the high-pressure turbine (HPT) rotor cavity, which may result 
in thermal degradation of the HPT rotor interstage seal and HPT 
rotor stage 2 disk. The FAA is issuing this AD to prevent creep 
rupture and low-cycle fatigue of the HPT rotor interstage seal and 
HPT rotor stage 2 disk. The unsafe condition, if not addressed, 
could result in an uncontained release of the HPT rotor interstage 
seal and HPT rotor stage 2 disk, 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) Before reaching the lowest applicable inspection threshold 
in Accomplishment Instructions, paragraph 5.A.(1), Table 1 or Table 
2 of CFM Service Bulletin LEAP-1A-72-00-0460-01A-930A-D, Issue 002-
00, dated June 10, 2022 (the SB), as applicable to each ESN and 
engine rating, or within 100 cycles after the effective date of this 
AD, whichever occurs later, perform an inspection of the stage 2 HPT 
nozzle assembly honeycomb in accordance with the Accomplishment 
Instructions, paragraph 5.B.(3)(a) of the SB.
    (2) If, during the inspection required by paragraph (g)(1) of 
this AD, the stage 2 HPT nozzle assembly honeycomb fails to meet the 
criteria in the Accomplishment Instructions, paragraphs 5.B.(3)(a)1 
to 5.B.(3)(a)4 of the SB, perform the following:
    (i) Before further flight, remove and replace the stage 2 HPT 
nozzle assembly honeycomb in accordance with the Accomplishment 
Instructions, paragraph 5.B.(3)(c)1 of the SB.
    (ii) For engines with an installed HPT rotor interstage seal, 
identified by serial number in Accomplishment Instructions, 
paragraph 5.A.(1), Table 1 of the SB, before further flight, remove 
the HPT rotor interstage seal and replace with a part eligible for 
installation.
    (iii) For engines with ESN 598-646 and ESN 598-812, before 
further flight, remove the HPT rotor stage 2 disk and replace with a 
part eligible for installation.
    (iv) For Group 1 engines, or an engine that has previously 
operated as a Group 1 engine, before further flight, remove the HPT 
rotor stage 2 disk and replace with a part eligible for 
installation.
    (3) Before reaching the lowest applicable inspection threshold 
in Accomplishment Instructions, paragraph 5.A.(1), Table 1 or Table 
2 of the SB, as applicable to each ESN and engine rating, or within 
100 cycles after the effective date of this AD, whichever occurs 
later, perform an inspection of the HPT stator stationary seal 
honeycomb in accordance with the Accomplishment Instructions, 
paragraph 5.B.(4)(a) of the SB.
    (4) If, during the inspection required by paragraph (g)(3) of 
this AD, the HPT stator stationary seal honeycomb fails to meet the 
criteria in the Accomplishment Instructions, paragraph 5.B.(4)(a)1 
to 5.B.(4)(a)3 of the SB, before further flight, replace the HPT 
stator stationary seal in accordance with the Accomplishment 
Instructions, paragraph 5.B.(4)(c)1, of the SB.

(h) Definition

    For the purpose of this AD, Group 1 engines are affected LEAP-
1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A model 
turbofan engines.

(i) No Reporting Requirement

    The reporting requirements in the Accomplishment Instructions, 
paragraphs 5.B.(3)(a)5 and 5.B.(4)(a)4, of the SB, are not required 
by this AD.

(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 
certification office, send it to the attention of the person 
identified in paragraph (k) of this AD and email 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

    For more information about this AD, contact Mehdi Lamnyi, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7743; email: 
[email protected].

(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 the AD specifies otherwise.
    (i) CFM Service Bulletin LEAP-1A-72-00-0460-01A-930A-D, Issue 
002-00, dated June 10, 2022.
    (ii) [Reserved]
    (3) For CFM service information identified in this AD, contact 
CFM International, S.A., Aviation Operations Center, 1 Neumann Way, 
M/D Room 285, Cincinnati, OH 45125; phone: (877) 432-3272; 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 (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on July 8, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-15391 Filed 7-19-22; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T01:41:11.316095+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

5c213fa47e829f1b056a07dd9c2419e1c7022789a4465cab709b9d52e9579e09

Text SHA-256

c202215a827c2650f848a013fe748e7fb7b3a52530e2001fccc9dcf11848eb2d