Airworthiness Directives; Engine Alliance Turbofan Engines, 31092-31095 [2021-12302]
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Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations
(iii) If there is a gap that is more than 0.020
inch (0.508 mm), before further flight,
remove the nut, washer, and bolt from
service and repair or replace the truss
assembly clevis lower lug in accordance with
FAA-approved procedures.
(h) Credit for Previous Actions
You may take credit for the first instance
of the actions that are required by paragraphs
(g)(1) through (4) of this AD, except not
paragraphs (g)(4)(i), (g)(4)(ii)(A) through (C),
or (g)(4)(iii) of this AD if you completed the
Accomplishment Instructions, Part I of Bell
ASB 505–19–12, dated June 27, 2019, before
the effective date of this AD.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
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 International Validation
Branch, send it to the attention of the person
identified in paragraph (j)(1) of this AD.
Information may be emailed to: 9-AVS-AIR730-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.
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(j) Related Information
(1) For more information about this AD,
contact Matt Fuller, AD Program Manager,
General Aviation & Rotorcraft Unit,
Airworthiness Products Section, Operational
Safety Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone 817–222–
5110; email matthew.fuller@faa.gov.
(2) Bell Alert Service Bulletin 505–19–12,
dated June 27, 2019, which is not
incorporated by reference, contains
additional information about the subject of
this AD. This service information is available
at the contact information specified in
paragraphs (k)(3) and (4) of this AD.
(3) The subject of this AD is addressed in
Transport Canada AD CF–2019–35, dated
October 2, 2019. You may view the Transport
Canada AD at https://www.regulations.gov in
Docket No. FAA–2021–0185.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference 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) Bell Alert Service Bulletin 505–19–12,
Revision A, dated July 11, 2019.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Bell Textron Canada
Limited, 12,800 Rue de l’Avenir, Mirabel,
Quebec J7J1R4; telephone 450–437–2862 or
800–363–8023; fax 450–433–0272; or at
https://www.bellcustomer.com.
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(4) You may view this service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. 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: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on May 20, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–12229 Filed 6–10–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0445; Project
Identifier AD–2021–00268–E; Amendment
39–21588; AD 2021–12–01]
RIN 2120–AA64
Airworthiness Directives; Engine
Alliance Turbofan Engines
Examining the AD Docket
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2019–25–
13, which applied to all Engine Alliance
(EA) GP7270 and GP7277 model
turbofan engines with a certain lowpressure compressor (LPC) 1st-stage fan
blade installed. AD 2019–25–13
required an ultrasonic inspection of the
affected LPC 1st-stage fan blades and
replacement of any affected LPC 1ststage fan blade that fails the inspection.
This AD lowers the initial inspection
threshold and requires repetitive
ultrasonic inspections on affected LPC
1st-stage fan blades. This AD was
prompted by a report of an in-flight
shutdown (IFSD) of an engine due to the
fracture of multiple LPC 1st-stage fan
blades. The FAA is issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective June 28,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 28, 2021.
The FAA must receive any comments
on this AD by July 26, 2021.
DATES:
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You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• 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.
• 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 Engine Alliance,
411 Silver Lane, East Hartford, CT
06118; phone: (800) 565–0140; email:
help24@pw.utc.com; website:
www.engineallianceportal.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 (781) 238–
7759. It is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0445.
ADDRESSES:
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0445; 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
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Stephen Elwin, Aviation Safety
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 AD 2019–25–13,
Amendment 39–21011 (84 FR 71770,
December 30, 2019), (AD 2019–25–13),
for all EA GP7270 and GP7277 model
turbofan engines with a certain LPC 1ststage fan blade installed. AD 2019–25–
13 required an ultrasonic inspection of
the affected LPC 1st-stage fan blades and
replacement of any affected fan blades
that fail the inspection. AD 2019–25–13
resulted from a report of an IFSD of an
engine due to the fracture of multiple
LPC 1st-stage fan blades. After an
analysis of these fractures, the
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Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations
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. The
FAA issued AD 2019–25–13 to prevent
failure of the fan blade.
Actions Since AD 2019–25–13 Was
Issued
Since the FAA issued AD 2019–25–
13, the manufacturer performed analysis
of a fractured LPC 1st-stage fan blade
and determined the fracture resulted
from a fatigue crack. The manufacturer
determined that repetitive ultrasonic
inspection for cracks on the LPC 1ststage fan blade convex airfoil is
necessary to decrease the risk of fracture
event. As a result of this analysis, the
manufacturer published EA Alert
Service Bulletin (SB) EAGP7–A72–444,
dated November 18, 2020. This service
information specifies lower initial
inspection thresholds for performing
ultrasonic inspections of affected LPC
1st-stage fan blades and contains
procedures for performing repetitive
ultrasonic inspections of affected LPC
1st-stage fan blades. 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 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 EA Alert SB
EAGP7–A72–444, dated November 18,
2020. The Alert SB describes the
inspection thresholds and 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 ADDRESSES.
AD Requirements
This AD requires initial and repetitive
ultrasonic inspections of the affected
LPC 1st-stage fan blades and
replacement of any LPC 1st-stage fan
blade that fails the inspection.
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
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–2021–0445
and Project Identifier AD–2021–00268–
E’’ at the beginning of your comments.
The most helpful comments reference a
specific portion of the proposal, 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.
31093
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 Stephen Elwin,
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:
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ESTIMATED COSTS
Action
Labor cost
Perform ultrasonic inspection for one set of 1st—stage
LPC blades.
8 work-hours × $85 per hour = $680
The FAA estimates the following
costs to do any necessary replacements
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that would be required based on the
results of the inspection. The agency has
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Cost per
product
Parts cost
$0
Cost on U.S.
operators
$680
no way of determining the number of
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$0
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Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations
aircraft that might need these
replacements.
ON-CONDITION COSTS
Action
Labor cost
Replace 1st-stage LPC fan blade ................................
4 work-hours × $85 per hour = $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.
(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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
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:
■
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
2019–25–13, Amendment 39–21011 (84
FR 71770, December 30, 2019); and
■ b. Adding the following new
airworthiness directive:
2021–12–01 Engine Alliance: Amendment
39–21588; Docket No. FAA–2021–0445;
Project Identifier AD–2021–00268–E.
(a) Effective Date
This airworthiness directive (AD) is
effective June 28, 2021.
Parts cost
$190,000
Cost per
product
$190,340
(b) Affected ADs
This AD replaces AD 2019–25–13,
Amendment 39–21011 (84 FR 71770,
December 30, 2019).
(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 LPC 1st-stage fan blades. The unsafe
condition, if not addressed, could result in
uncontained fan blade 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
(1) Within the compliance time specified
in Table 1 to paragraph (g)(1) of this AD,
perform an ultrasonic inspection of the LPC
1st-stage fan blades using 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
Alert Service Bulletin (SB) EAGP7–A72–444,
dated November 18, 2020.
Fan Blade Flie:ht Cvcles
Fewer than 2,250 flight cycles since new
(CSN) on the effective date of this AD.
2,250 flight CSN or greater as of the
effective date of this AD, but fewer than
3,250 CSN on January 14, 2020 (the
effective date of AD 2019-25-13).
3,250 flight CSN or greater on January
14, 2020.
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Compliance Time
Before exceeding 2,500 flight CSN.
Before exceeding 250 flight cycles from
the effective date of this AD.
Within 250 flight cycles since January 14,
2020 or before further flight, whichever
occurs later.
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Table 1 to Paragraph (g)(l)
Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations
(2) Thereafter, at intervals not to exceed
800 flight cycles since last inspection,
perform an ultrasonic inspection of the LPC
1st-stage fan blades using 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
Alert SB EAGP7–A72–444, dated November
18, 2020.
(3) If an ultrasonic inspection of an LPC
1st-stage fan blade results in a rejectable
ultrasonic indication, remove the LPC 1ststage fan blade from service and replace with
a part eligible for installation before further
flight.
Note 1 to paragraph (g)(3): Guidance on
determining a rejectable ultrasonic indication
can be found in GP7000 1st Stage LPC Rotor
(Fan) Blade Assembly Airfoil Ultrasonic
Inspection for Cracks (Fan Blade Installed or
Uninstalled), NDIP–1205, Revision C, dated
September 15, 2020.
(i) Engine Alliance (EA) Alert Service
Bulletin EAGP7–A72–444, dated November
18, 2020.
(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: help24@pw.utc.com;
website: www.engineallianceportal.com.
(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: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
(h) 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
GP7000 1st Stage LPC Rotor (Fan) Blade
Assembly Airfoil Ultrasonic Inspection for
Cracks (Fan Blade installed or uninstalled),
NDIP–1205, Revision B, dated September 27,
2019, or an earlier version.
Issued on May 25, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
(i) No Reporting Requirement
The reporting requirements contained
within NDIP–1205 are not required by this
AD.
Federal Aviation Administration
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(k) Related Information
For more information about this AD,
contact Stephen Elwin, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7236; fax: (781) 238–7199; email:
Stephen.L.Elwin@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 the AD specifies otherwise.
17:30 Jun 10, 2021
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
(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 Related Information.
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.
VerDate Sep<11>2014
[FR Doc. 2021–12302 Filed 6–10–21; 8:45 am]
[Docket No. FAA–2021–0140; Project
Identifier MCAI–2020–01531–T; Amendment
39–21582; AD 2021–11–20]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus SAS Model A330–200, A330–
300, A340–200, A340–300, A340–500,
and A340–600 series airplanes. This AD
was prompted by reports that, for
certain lower deck mobile crew rest
(LDMCR) units, the connection of a
certain halon outlet tube to the outlet of
a certain fire extinguisher bottle may be
incorrect. This AD requires replacing
each affected halon outlet tube with a
flexible hose, as specified in a European
Union Aviation Safety Agency (EASA)
AD, which is incorporated by reference.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective July 16,
2021.
The Director of the Federal Register
approved the incorporation by reference
SUMMARY:
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31095
of a certain publication listed in this AD
as of July 16, 2021.
For material incorporated
by reference (IBR) in this AD, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
8999 000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find this IBR material on the EASA
website at https://ad.easa.europa.eu.
You may view this IBR material 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.
It is also available in the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0140.
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–2021–
0140; 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:
Vladimir Ulyanov, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3229; email
vladimir.ulyanov@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2020–0255,
dated November 13, 2020 (EASA AD
2020–0255) (also referred to as the
Mandatory Continuing Airworthiness
Information, or the MCAI), to correct an
unsafe condition for certain Airbus SAS
Model A330–201, –202, –203, –223,
–243, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes;
and Model A340–211, –212, –213, –311,
–312, –313, –541, –542, –642, and –643
airplanes. Model A340–542 and A340–
643 airplanes are not certificated by the
FAA and are not included on the U.S.
type certificate data sheet; this AD
therefore does not include those
airplanes in the applicability.
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]]>Agencies
[Federal Register Volume 86, Number 111 (Friday, June 11, 2021)]
[Rules and Regulations]
[Pages 31092-31095]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-12302]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0445; Project Identifier AD-2021-00268-E;
Amendment 39-21588; AD 2021-12-01]
RIN 2120-AA64
Airworthiness Directives; Engine Alliance Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-25-
13, which applied to all Engine Alliance (EA) GP7270 and GP7277 model
turbofan engines with a certain low-pressure compressor (LPC) 1st-stage
fan blade installed. AD 2019-25-13 required an ultrasonic inspection of
the affected LPC 1st-stage fan blades and replacement of any affected
LPC 1st-stage fan blade that fails the inspection. This AD lowers the
initial inspection threshold and requires repetitive ultrasonic
inspections on affected LPC 1st-stage fan blades. This AD was prompted
by a report of an in-flight shutdown (IFSD) of an engine due to the
fracture of multiple LPC 1st-stage fan blades. The FAA is issuing this
AD to address the unsafe condition on these products.
DATES: This AD is effective June 28, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 28,
2021.
The FAA must receive any comments on this AD by July 26, 2021.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
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.
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
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, 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 at https://www.regulations.gov by searching for and
locating Docket No. FAA-2021-0445.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0445; 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 Docket
Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Stephen Elwin, Aviation Safety
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 AD 2019-25-13, Amendment 39-21011 (84 FR 71770,
December 30, 2019), (AD 2019-25-13), for all EA GP7270 and GP7277 model
turbofan engines with a certain LPC 1st-stage fan blade installed. AD
2019-25-13 required an ultrasonic inspection of the affected LPC 1st-
stage fan blades and replacement of any affected fan blades that fail
the inspection. AD 2019-25-13 resulted from a report of an IFSD of an
engine due to the fracture of multiple LPC 1st-stage fan blades. After
an analysis of these fractures, the
[[Page 31093]]
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. The FAA issued AD 2019-25-13 to
prevent failure of the fan blade.
Actions Since AD 2019-25-13 Was Issued
Since the FAA issued AD 2019-25-13, the manufacturer performed
analysis of a fractured LPC 1st-stage fan blade and determined the
fracture resulted from a fatigue crack. The manufacturer determined
that repetitive ultrasonic inspection for cracks on the LPC 1st-stage
fan blade convex airfoil is necessary to decrease the risk of fracture
event. As a result of this analysis, the manufacturer published EA
Alert Service Bulletin (SB) EAGP7-A72-444, dated November 18, 2020.
This service information specifies lower initial inspection thresholds
for performing ultrasonic inspections of affected LPC 1st-stage fan
blades and contains procedures for performing repetitive ultrasonic
inspections of affected LPC 1st-stage fan blades. 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 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 EA Alert SB EAGP7-A72-444, dated November 18,
2020. The Alert SB describes the inspection thresholds and 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 ADDRESSES.
AD Requirements
This AD requires initial and repetitive ultrasonic inspections of
the affected LPC 1st-stage fan blades and replacement of any LPC 1st-
stage fan blade that fails the inspection.
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 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-2021-0445 and Project Identifier
AD-2021-00268-E'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, 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 Stephen
Elwin, 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
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Perform ultrasonic inspection for one 8 work-hours x $85 per $0 $680 $0
set of 1st--stage LPC blades. hour = $680.
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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
[[Page 31094]]
aircraft that might need these replacements.
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace 1st-stage LPC fan blade............... 4 work-hours x $85 per hour = $190,000 $190,340
$340.
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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, 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:
0
a. Removing Airworthiness Directive 2019-25-13, Amendment 39-21011 (84
FR 71770, December 30, 2019); and
0
b. Adding the following new airworthiness directive:
2021-12-01 Engine Alliance: Amendment 39-21588; Docket No. FAA-2021-
0445; Project Identifier AD-2021-00268-E.
(a) Effective Date
This airworthiness directive (AD) is effective June 28, 2021.
(b) Affected ADs
This AD replaces AD 2019-25-13, Amendment 39-21011 (84 FR 71770,
December 30, 2019).
(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 LPC 1st-stage fan
blades. The unsafe condition, if not addressed, could result in
uncontained fan blade 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
(1) Within the compliance time specified in Table 1 to paragraph
(g)(1) of this AD, perform an ultrasonic inspection of the LPC 1st-
stage fan blades using 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
Alert Service Bulletin (SB) EAGP7-A72-444, dated November 18, 2020.
[GRAPHIC] [TIFF OMITTED] TR11JN21.000
[[Page 31095]]
(2) Thereafter, at intervals not to exceed 800 flight cycles
since last inspection, perform an ultrasonic inspection of the LPC
1st-stage fan blades using 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 Alert SB EAGP7-A72-444, dated November 18, 2020.
(3) If an ultrasonic inspection of an LPC 1st-stage fan blade
results in a rejectable ultrasonic indication, remove the LPC 1st-
stage fan blade from service and replace with a part eligible for
installation before further flight.
Note 1 to paragraph (g)(3): Guidance on determining a rejectable
ultrasonic indication can be found in GP7000 1st Stage LPC Rotor
(Fan) Blade Assembly Airfoil Ultrasonic Inspection for Cracks (Fan
Blade Installed or Uninstalled), NDIP-1205, Revision C, dated
September 15, 2020.
(h) 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 GP7000 1st Stage LPC Rotor (Fan)
Blade Assembly Airfoil Ultrasonic Inspection for Cracks (Fan Blade
installed or uninstalled), NDIP-1205, Revision B, dated September
27, 2019, or an earlier version.
(i) No Reporting Requirement
The reporting requirements contained within NDIP-1205 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 Related Information. 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.
(k) Related Information
For more information about this AD, contact Stephen Elwin,
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: (781) 238-7236; 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) Alert Service Bulletin EAGP7-A72-444,
dated November 18, 2020.
(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 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 May 25, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-12302 Filed 6-10-21; 8:45 am]
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