Airworthiness Directives; Engine Alliance Turbofan Engines

[Federal Register Volume 84, Number 249 (Monday, December 30, 2019)]
[Rules and Regulations]
[Pages 71770-71772]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-27889]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0912; Product Identifier 2019-NE-33-AD; Amendment 
39-21011; AD 2019-25-13]
RIN 2120-AA64


Airworthiness Directives; Engine Alliance 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 all 
Engine Alliance (EA) GP7270 and GP7277 model turbofan engines with a 
certain low-pressure compressor (LPC) 1st-stage fan blade installed. 
This AD requires an ultrasonic inspection of the affected LPC 1st-stage 
fan blades and replacement of any affected fan blades that fail the 
inspection. This AD was prompted by a report of an in-flight shutdown 
(IFSD) of an engine due to the fracture of multiple fan blades. The FAA 
is issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective January 14, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 14, 
2020.
    The FAA must receive comments on this AD by February 13, 2020.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this final rule, contact 
Engine Alliance, 411 Silver Lane, East Hartford, CT, 06118; phone: 800-
565-0140; email: [email protected]; website: 
www.engineallianceportal.com. You may view this service information at 
the FAA, Engine and Propeller Standards 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-2019-0912.

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-2019-
0912; 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 regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations is 
listed above. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Matthew Smith, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7735; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA received a report of an IFSD that occurred during a revenue 
flight on March 10, 2019. The IFSD resulted from the fracture of two 
LPC 1st-stage fan blades. After an analysis of these fractures, the 
manufacturer determined the fan blades experienced cracks that 
originated on the internal surface of the convex airfoil and propagated 
to the point of failure. The cracks originated in a microtexture area 
that can result in a low-cycle fatigue debit that may allow a crack to 
initiate and propagate to failure. This condition, if not addressed, 
could result in uncontained fan blade release, damage to the engine, 
and damage to the airplane. The FAA is issuing this AD to address the 
unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed EA Service Bulletin (SB) EAGP7-A72-426, dated 
September 30, 2019. The SB describes procedures for performing an 
ultrasonic inspection of the LPC 1st-stage fan blades. 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.

FAA's Determination

    The FAA is issuing this AD because the FAA evaluated all the 
relevant information and determined the unsafe condition described 
previously is likely to exist or develop in other products of the same 
type design.

AD Requirements

    This AD requires an ultrasonic inspection of the affected LPC 1st-
stage fan blades and replacement of any affected fan blades that fail 
the inspection.

Interim Action

    The FAA considers this AD interim action. The root cause of the LPC 
1st-stage fan blade fracture is still undetermined and the FAA will 
consider further rulemaking depending on the results of the 
investigation.

FAA's Justification and Determination of the Effective Date

    Since there are currently no domestic operators of this product, 
notice and opportunity for public comment before issuing this AD are 
unnecessary. In addition, for the reason stated above, the FAA finds 
that good cause exists for making this amendment effective in less than 
30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, the FAA invites you to send any written data, views, 
or arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number FAA-2019-
0912 and Product Identifier 2019-NE-33-AD at the

[[Page 71771]]

beginning of your comments. The FAA specifically invites comments on 
the overall regulatory, economic, environmental, and energy aspects of 
this final rule. The FAA will consider all comments received by the 
closing date and may amend this final rule because of those comments.
    The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this final rule.

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 the FAA has determined 
that it has good cause to adopt this rule without 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
----------------------------------------------------------------------------------------------------------------
Perform ultrasonic inspection for one   8 work-hours x $85 per                $0            $680              $0
 set of blades.                          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 aircraft 
that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace fan blade.............................  4 work-hours x $85 per hour =           $190,000        $190,340
                                                 $340.
----------------------------------------------------------------------------------------------------------------

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

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, 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.

Adoption of 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):

2019-25-13 Engine Alliance: Amendment 39-21011; Docket No. FAA-2019-
0912; Product Identifier 2019-NE-33-AD.

(a) Effective Date

    This AD is effective January 14, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Engine Alliance (EA) GP7270 and GP7277 model 
turbofan engines with low-pressure compressor (LPC) 1st-stage fan 
blades, part number (P/N) 5700531, 5702931, 5702931CL1, or 
5702931CL2, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7230, Turbine Engine 
Compressor Section.

(e) Unsafe Condition

    This AD was prompted by a report of an in-flight shutdown of an 
engine due to the fracture of multiple LPC 1st-stage fan blades. The 
FAA is issuing this AD to prevent failure of the fan blade. The 
unsafe condition, if not addressed, could result in uncontained fan 
blade release, damage to the engine, and damage to the airplane.

[[Page 71772]]

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) For engines with affected LPC 1st-stage fan blades that have 
3,250 or more flight cycles (FCs) since new as of the effective date 
of this AD, within 250 FCs after the effective date of this AD, 
perform an ultrasonic inspection of the LPC 1st-stage fan blades in 
accordance with the Accomplishment Instructions, ``For Fan Blades 
Installed In An Engine,'' paragraph 1, or ``For Fan Blades Not 
Installed In an Engine,'' paragraph 1, as applicable, of EA Service 
Bulletin (SB) EAGP7-A72-426, dated September 30, 2019.
    (2) If the ultrasonic inspection of the affected fan blades 
results in a rejectable ultrasonic indication, remove the fan blade 
from service and replace with a part eligible for installation 
before further flight.
    Note 1 to paragraph (g)(2): Guidance on determining a rejectable 
ultrasonic indication can be found in Non-Destructive Inspection 
Procedure, NDIP-1205, Revision 1--GP7000 1st Stage LPC Rotor (Fan) 
Blade Assembly Airfoil Ultrasonic Inspection for Cracks (Fan Blades 
installed or uninstalled), (``NDIP-1205''), dated September 23, 
2019.

(h) No Reporting Requirement

    No reporting requirement contained within NDIP-1205 is required 
by this AD.

(i) Credit for Previous Actions

    You may take credit for the ultrasonic inspection required by 
paragraph (g)(1) of this AD if you performed the inspection before 
the effective date of this AD using NDIP-1205, Revision 1, dated 
September 23, 2019, or Original Issue, dated August 30, 2019.

(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. You may email your request 
to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(k) Related Information

    For more information about this AD, contact Matthew Smith, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7735; fax: 781-238-7199; 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) Engine Alliance (EA) Service Bulletin EAGP7-A72-426, dated 
September 30, 2019.
    (ii) [Reserved]
    (3) For EA service information identified in this AD, contact 
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 
800-565-0140; email: [email protected]; website: 
www.engineallianceportal.com.
    (4) You may view this service information at the FAA, Engine and 
Propeller Standards 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 in Burlington, Massachusetts, on December 12, 2019.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2019-27889 Filed 12-27-19; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T02:04:49.261540+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

1fa3d7c464e0e71dc3d344e1a5aac430e7b1c049ea31a42b37bd4b8d35eee05c

Text SHA-256

2898b89165586cf2719abd563b6833ab9236f5741612fd9c877e3d678091e0ce