Rule2021-27981
Airworthiness Directives; Engine Alliance Turbofan Engines
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
December 28, 2021
Effective
January 12, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2019-18-08 which applied to all Engine Alliance (EA) GP7270 and GP7277 model turbofan engines. AD 2019-18-08 required a visual inspection of the engine fan hub assembly, initial and repetitive eddy current inspections (ECIs) of the engine fan hub blade slot bottom and blade slot front edge for cracks, and replacement of the engine fan hub blade lock assembly for certain affected engines. This AD continues to require initial and repetitive ECIs and adds an ultrasonic test (UT) inspection. This AD also lowers the repetitive ECI threshold, and requires an independent inspection of the engine fan hub assembly at the next disassembly and the next reassembly of the engine fan hub blade lock assembly and a visual inspection of the engine fan hub assembly for damage. This AD also requires replacement of the engine fan hub assembly with a part eligible for installation if damage is found outside serviceable limits. This AD was prompted by an uncontained failure of the engine fan hub. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 86 Issue 246 (Tuesday, December 28, 2021)</title>
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[Federal Register Volume 86, Number 246 (Tuesday, December 28, 2021)]
[Rules and Regulations]
[Pages 73667-73670]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-27981]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-1069; Project Identifier AD-2021-00308-E;
Amendment 39-21862; AD 2021-26-04]
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) 2019-18-08
which applied to all Engine Alliance (EA) GP7270 and GP7277 model
turbofan engines. AD 2019-18-08 required a visual inspection of the
engine fan hub assembly, initial and repetitive eddy current
inspections (ECIs) of the engine fan hub blade slot bottom and blade
slot front edge for cracks, and replacement of the engine fan hub blade
lock assembly for certain affected engines. This AD continues to
require initial and repetitive ECIs and adds an ultrasonic test (UT)
inspection. This AD also lowers the repetitive ECI threshold, and
requires an independent inspection of the engine fan hub assembly at
the next disassembly and the next reassembly of the engine fan hub
blade lock assembly and a visual inspection of the engine fan hub
assembly for damage. This AD also requires replacement of the engine
fan hub assembly with a part eligible for installation if damage is
found outside serviceable limits. This AD was prompted by an
uncontained failure of the engine fan hub. The FAA is issuing this AD
to address the unsafe condition on these products.
DATES: This AD is effective January 12, 2022.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 12,
2022.
The FAA must receive any comments on this AD by February 11, 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a>. 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
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: (800)
565-0140; email: <a href="/cdn-cgi/l/email-protection#6a020f061a585e2a1a1d441f1e0944090507"><span class="__cf_email__" data-cfemail="deb6bbb2aeecea9eaea9f0abaabdf0bdb1b3">[email protected]</span></a>; website:
<a href="http://www.engineallianceportal.com">www.engineallianceportal.com</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and
locating Docket No. FAA-2021-1069.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2021-1069; 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:
<a href="/cdn-cgi/l/email-protection#72210617021a171c5c3e5c371e051b1c321413135c151d04"><span class="__cf_email__" data-cfemail="3e6d4a5b4e565b501072107b524957507e585f5f10595148">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued AD 2019-18-08, Amendment 39-19735 (84 FR 49944,
September 24, 2019), (AD 2019-18-08), for all EA GP7270 and GP7277
model turbofan engines. AD 2019-18-08 required, for certain GP7270 and
GP7277 model turbofan engines, an initial and repetitive ECI of the
engine fan hub blade slot bottom and blade slot front edge for cracks.
For all GP7270 and GP7277 model turbofan engines, AD 2019-18-08 also
required an independent inspection of the engine fan hub assembly prior
to the reassembly of the engine fan hub blade lock assembly and a
visual inspection of the engine fan hub assembly for damage. For
certain serial numbered GP7270 and GP7277 model turbofan engines, AD
2019-18-08 required replacement of the engine fan hub blade lock
assembly with a part eligible for installation. AD 2019-18-08 resulted
from the manufacturer identifying a fatigue crack originating inboard
of a blade slot after the manufacturer performed a metallurgical
examination of the engine fan hub that was recovered, related to an
uncontained engine hub failure that occurred on September 30, 2017.
After performing a risk assessment, the manufacturer determined the
need to reduce the compliance time for the initial ECI and add a
repetitive ECI. The FAA issued AD 2019-18-08 to detect defects, damage,
and cracks that could result in an uncontained failure of the engine
fan hub assembly.
Actions Since AD 2019-18-08 Was Issued
Since the FAA issued AD 2019-18-08, EA has revised its Alert
Service Bulletin, reducing the repetitive ECI interval from 330 cycles
to 290 cycles, and adding an inner diameter UT inspection of the rim
area for cracks. EA published EA Turbojet Engine Alert Service Bulletin
(ASB) No. EAGP7-A72-389, Revision No. 7, dated October 8, 2021, to
update the repetitive inspection interval for performing the ECIs and
add UT inspections. The FAA
[[Page 73668]]
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 Turbojet Engine ASB No. EAGP7-A72-389, Revision
No. 7, dated October 8, 2021. This ASB describes procedures for
performing an ECI of the engine fan hub blade slot bottom and blade
slot front edge, and performing a UT inspection of the fan hub rim area
for engine fan hub assemblies at the LPC module assembly level, at the
piece part level, and installed in an engine (on-wing or off-wing).
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.
Other Related Service Information
The FAA reviewed EA Turbojet Engine ASB No. EAGP7-A72-418, Revision
No. 1, dated January 11, 2019. This ASB provides guidance on
replacement or modification of the engine fan hub blade lock assembly.
The FAA also reviewed the following service information:
Subtask 72-31-42-210-001-A, of Task 72-31-42-000-802-A, from the
A380 Aircraft Maintenance Manual (AMM). This subtask describes
procedures for performing an on-wing visual inspection after removal of
the engine fan hub blade lock assembly.
Figure 405 of Task 72-00-31-420-004 of the EA GP7000 Series Engine
Manual (EM). This figure and task describe procedures for performing a
visual inspection after removal of the engine fan hub blade lock
assembly when the engine is in the shop.
Subtask 72-00-00-210-012-A, of Task 72-00-00-210-806-A, from the
A380 AMM. This subtask describes procedures for performing an on-wing
visual inspection after reassembly of the engine fan hub blade lock
assembly.
Task 72-00-31-420-004, Paragraph 1.E.(13), of the EA GP7000 Series
EM. This task describes procedures for performing a visual inspection
after reassembly of the engine fan hub blade lock assembly when the
engine is in the shop.
Table 601 in Subtask 72-00-00-210-012-A of Task 72-00-00-210-806,
from the A380 AMM, and Task 72-00-31-220-010 of the EA GP7000 Series
EM. Table 601 and Task 72-00-31-220-010 describe acceptable damage
service limits for the engine fan hub assembly.
AD Requirements
This AD requires, for GP7270 and GP7277 model turbofan engines with
engine fan hub assembly part numbers (P/Ns) 5760221, 5760321, or
5760001, initial and repetitive ECI of the engine fan hub blade slot
bottom and blade slot front edge for cracks. Additionally, this AD
lowers the repetitive ECI threshold, in conjunction with the added
repetitive UT inspection threshold. This AD also requires initial and
repetitive UT inspections of the fan hub rim area. This AD also
requires an independent inspection of the engine fan hub assembly at
the next disassembly and the next reassembly of the engine fan hub
blade lock assembly and a visual inspection of the engine fan hub
assembly for damage. This AD also requires replacement of the engine
fan hub assembly with a part eligible for installation if damage is
found outside serviceable limits.
For certain serial-numbered GP7270 and GP7277 model turbofan
engines, this AD requires replacement of the engine fan hub blade lock
assembly with a part eligible for installation.
Interim Action
The FAA considers this AD to be an interim action. If final action
is later identified, the FAA might consider further rulemaking.
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(s), 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-2021-1069 and Project Identifier
AD-2021-00308-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
<a href="https://www.regulations.gov">https://www.regulations.gov</a>, 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
[[Page 73669]]
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
----------------------------------------------------------------------------------------------------------------
Perform ECI........................... 20 work-hours x $85 per $0 $1,700 $0
hour = $1,700.
Perform UT Inspection................. 7 work-hours x $85 per 0 595 0
hour = $595.
Perform Visual Inspection............. 1 work-hour x $85 per 0 85 0
hour = $85.
Replace fan hub blade lock assembly... 25 work-hours x $85 per 28,000 30,125 0
hour = $2,125.
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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 engine fan hub assembly............... 50 work-hours x $85 per hour = $790,500 $794,750
$4,250.
----------------------------------------------------------------------------------------------------------------
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 2019-18-08, Amendment 39-19735 (84
FR 49944, September 24, 2019); and
0
b. Adding the following new airworthiness directive:
2021-26-04 Engine Alliance: Amendment 39-21862; Docket No. FAA-2021-
1069; Project Identifier AD-2021-00308-E.
(a) Effective Date
This airworthiness directive (AD) is effective January 12, 2022.
(b) Affected ADs
This AD replaces AD 2019-18-08, Amendment 39-19735 (84 FR 49944,
September 24, 2019).
(c) Applicability
This AD applies to all Engine Alliance (EA) GP7270 and GP7277
model turbofan engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by an uncontained failure of the engine fan
hub. The FAA is issuing this AD to detect defects, damage, and
cracks that could result in an uncontained failure of the engine fan
hub assembly. The unsafe condition, if not addressed, could result
in uncontained failure of the engine fan hub assembly, 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) For EA GP7270 and GP7277 model turbofan engines with engine
fan hub assembly part numbers (P/Ns) 5760221, 5760321, or 5760001,
within 1,700 cycles since new, within 150 flight cycles (FCs) after
October 9, 2019 (the effective date of AD 2019-18-08), within 330
FCs since an eddy current inspection (ECI) was performed using the
Accomplishment Instructions of EA Turbojet Engines Alert Service
Bulletin (ASB) EAGP7-A72-389, Revision No. 6, dated November 21,
2019, or earlier versions of that ASB, or before further flight,
whichever occurs later:
(i) For engine fan hub assemblies at the low-pressure compressor
(LPC) module assembly level, perform an ECI of the engine fan hub
blade slot bottom and blade slot front edge, and perform an
ultrasonic test (UT)
[[Page 73670]]
inspection of the fan hub rim area, using the Accomplishment
Instructions, Part A--For Fan Hubs at LPC Module Assembly Level,
paragraphs 1.B., 1.C., and 1.E., of EA Turbojet Engine ASB EAGP7-
A72-389, Revision No. 7, dated October 8, 2021 (EAGP7-A72-389,
Revision No. 7).
(ii) For engine fan hub assemblies at the piece part level,
perform an ECI of the engine fan hub blade slot bottom and blade
slot front edge, and perform a UT inspection of the fan hub rim
area, using the Accomplishment Instructions, Part B--For Fan Hubs at
Piece Part Level, paragraphs 1.B., 1.C., and 1.E., of EAGP7-A72-389,
Revision No. 7.
(iii) For engine fan hub assemblies installed in an engine (on-
wing or off-wing), perform an ECI of the engine fan hub blade slot
bottom and blade slot front edge, and perform a UT inspection of the
fan hub rim area, using the Accomplishment Instructions, Part C--For
Fan Hubs Installed in an Engine, paragraphs 3.B., 3.C., and 3.E., of
EAGP7-A72-389, Revision No. 7.
(2) Thereafter, at intervals not exceeding 290 FCs since the
previous ECI and UT inspection, repeat the ECI of the engine fan hub
blade slot bottom, ECI of the blade slot front edge, and UT
inspection of the fan hub rim area required by paragraphs (g)(1)(i)
through (iii) of this AD.
(3) If, during any ECI or UT inspection required by paragraphs
(g)(1) through (g)(2) of this AD, a rejectable indication is found,
before further flight, remove the engine fan hub assembly from
service and replace with a part that is eligible for installation.
(4) For all GP7270 and GP7277 model turbofan engines, after the
effective date of this AD:
(i) At the next disassembly of the engine fan hub blade lock
assembly, visually inspect the fan hub fan blade lock groove area
(also known as the fan hub lock ring contact area) for damage.
(ii) At the next reassembly of the engine fan hub blade lock
assembly, visually inspect the following areas of the engine fan hub
for damage:
(A) The fan hub scallop areas;
(B) The fan hub bore area behind the balance flange;
(C) The fan hub fan blade lock retention hooks;
(D) The fan hub rim face; and
(E) The clinch nut holes.
(iii) After any reassembly of the fan hub blade lock assembly,
before further flight, perform an independent inspection for damage
of the areas of the engine fan hub identified in paragraph
(g)(4)(ii) of this AD.
(iv) Thereafter, repeat the inspections required by paragraphs
(g)(4)(i) through (iii) of this AD at each disassembly and
reassembly of the engine fan hub blade lock assembly, as applicable.
(v) As an optional terminating action to the inspection and
independent inspection requirements of paragraphs (g)(4)(i) through
(iv) of this AD, insert the requirements for the visual inspections
and independent inspections required by paragraphs (g)(4)(i) through
(iv) as Required Inspection Items in the existing approved
continuous airworthiness maintenance program for the airplane.
(vi) If damage is found that exceeds serviceable limits during
the inspections required by paragraphs (g)(4)(i) through (iv) of
this AD, before further flight, remove the engine fan hub assembly
from service and replace it with a part eligible for installation.
(5) For GP7270 and GP7277 model turbofan engines with engine
serial numbers P550101 through P550706, inclusive, within 200 FCs
from August 1, 2020 or before further flight, whichever occurs
later, remove the engine fan hub blade lock assembly, P/N 5700451,
and replace it with a part eligible for installation.
Note 1 to paragraph (g)(5): EA Turbojet Engines ASB EAGP7-A72-
418, Revision No. 1, dated January 11, 2019, contains guidance on
replacement of the engine fan hub blade lock assembly.
(h) Credit for Previous Actions
You may take credit for the ECI inspections required by
paragraph (g)(1)(i) through (iii) of this AD if you performed the
ECI inspections before the effective date of this AD using EA ASB
EAGP7-A72-389, Revision No. 6, dated November 21, 2019, or an
earlier version.
(i) Definitions
(1) For the purpose of this AD, a ``part eligible for
installation,'' when referring to replacement of the engine fan hub
assembly, is a part that has passed the inspections required by
paragraph (g)(1) of this AD.
(2) For the purpose of this AD, a ``part eligible for
installation,'' when referring to replacement of the engine fan hub
blade lock assembly, is:
(i) A part that is not P/N 5700451, or
(ii) An engine fan hub blade lock assembly that has been
modified in accordance with EA ASB EAGP7-A72-418, Revision No. 1,
dated January 11, 2019, or EA ASB EAGP7-A72-418, Revision No. 0,
dated December 7, 2018.
(3) For the purpose of this AD, an ``independent inspection'' is
a second visual inspection performed by an individual qualified to
perform inspections who was not involved in the original inspection
of the engine fan hub assembly following disassembly and reassembly
of the engine fan hub blade lock assembly.
(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. Information may be emailed
to: <a href="/cdn-cgi/l/email-protection#14555a513955503955595b57547275753a737b62"><span class="__cf_email__" data-cfemail="763738335b37325b373b39353610171758111900">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#9ecdeafbeef6fbf0b0d2b0dbf2e9f7f0def8ffffb0f9f1e8"><span class="__cf_email__" data-cfemail="481b3c2d38202d266604660d243f2126082e2929662f273e">[email protected]</span></a>.
(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) Turbojet Engines Alert Service Bulletin
EAGP7-A72-389, Revision No. 7, dated October 8, 2021.
(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: <a href="/cdn-cgi/l/email-protection#abc3cec7db999febdbdc85dedfc885c8c4c6"><span class="__cf_email__" data-cfemail="ed8588819ddfd9ad9d9ac398998ec38e8280">[email protected]</span></a>; website:
<a href="http://www.engineallianceportal.com">www.engineallianceportal.com</a>.
(4) 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.
(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: <a href="/cdn-cgi/l/email-protection#bddbcf93d4d3cecdd8dec9d4d2d3fdd3dccfdc93dad2cb"><span class="__cf_email__" data-cfemail="294f5b0740475a594c4a5d4046476947485b48074e465f">[email protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on December 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-27981 Filed 12-27-21; 8:45 am]
BILLING CODE 4910-13-P
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