[Federal Register Volume 86, Number 120 (Friday, June 25, 2021)]
[Rules and Regulations]
[Pages 33494-33498]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-13424]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0850; Project Identifier AD-2020-00288-E;
Amendment 39-21569; AD 2021-11-07]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain General Electric Company (GE) GEnx-1B64, 1B64/P1, -1B64/P2, -
1B67, -1B67/P1, -1B67/P2, -1B70, -1B70/75/P1, -1B70/75/P2, -1B70/P1, -
1B70/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -1B74/75/P2, -1B76/P2, -
1B76A/P2, -2B67, -2B67/P, and -2B67B model turbofan engines. This AD
was prompted by a finding during an inspection by the manufacturer that
two stages 6-10 compressor rotor spools in the high-pressure compressor
(HPC) assembly were damaged at similar locations. Additionally, the
manufacturer reported that certain stages 6-10 compressor rotor spool
webs did not undergo a required fluorescent penetrant inspection (FPI)
during production. This AD requires inspection of the stages 6-10
compressor rotor spool and, depending on the results of the inspection,
replacement of the stages 6-10 compressor rotor spool. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective July 30, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 30,
2021.
ADDRESSES: For service information identified in this final rule,
contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552-3272; email: [email protected]; website:
www.ge.com. You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call (781) 238-7759. It is
also available at https://www.regulations.gov by searching for and
locating Docket No. FAA-2020-0850.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0850; 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: Mehdi Lamnyi, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
phone: (781) 238-7743; fax: (781) 238-7199; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain GE GEnx-1B and
GEnx-2B model turbofan engines. The
[[Page 33495]]
NPRM published in the Federal Register on September 24, 2020 (85 FR
60103). The NPRM was prompted by a report from the manufacturer that an
inspection had found two stages 6-10 compressor rotor spools in the HPC
assembly damaged at similar locations on the webs. The subsequent
investigation determined that tool marks were created during the
manufacturing process. In addition, the manufacturer also reported that
certain stages 6-10 compressor rotor spool webs did not undergo a
required FPI during production.
In the NPRM, the FAA proposed to require inspection of the stages
6-10 compressor rotor spool. Operators of certain affected GEnx-1B or
GEnx-2B model turbofan engines have already completed acceptable
inspections of the aft web of stage 6, stage 7, and stage 8 of the
stages 6-10 compressor rotor spool. The FAA proposed to require
operators of those affected engines to complete the inspection of the
stages 6-10 compressor rotor spool no later than the next engine shop
visit. The FAA proposed to require all other remaining affected GEnx-1B
and GEnx-2B model turbofan engines to complete this inspection by the
next engine shop visit, before the stages 6-10 compressor rotor spools
accumulate 6,500 cycles since new, or before further flight if 6,500
cycles since new has already been accumulated as of the effective date
of this AD. Depending on the results of the inspection, the FAA
proposed to require replacement of the stages 6-10 compressor rotor
spool with a part eligible for installation. The FAA is issuing this AD
to address the unsafe condition on these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from seven commenters. The commenters
were American Airlines (American), GE Aviation, Japan Airlines, Nippon
Cargo Airlines (NCA), the Air Line Pilots Association, International,
United Airlines Engineering, and Boeing Commercial Airplanes. Three
commenters supported the proposed rule without change. One commenter
requested that the FAA add a term to the Definitions paragraph of the
proposed rule, and use the latest version of the service information.
Three commenters requested certain clarifications or changes to the
Required Actions and Previous Credit sections. The following presents
the comments received on the NPRM and the FAA's response to each
comment.
Request To Clarify Rejectable Indication
GE Aviation requested that the FAA define the term ``rejectable
indication'' to avoid confusion in the event an indication is found
during inspection. GE Aviation requested that the FAA define rejectable
indication as an indication that does not meet the serviceable or
repairable limits defined in the special procedure referenced in GE
GEnx-1B Service Bulletin (SB) 72-0472 R02, dated November 5, 2020
(GEnx-1B SB 72-0472) and GE GEnx-2B SB 72-0415 R02, dated November 5,
2020 (GEnx-2B SB 72-0415).
The FAA agrees to define a ``rejectable indication'' as used in
paragraph (g)(2) of the Required Actions section of this AD and added
the definition in paragraph (h), Definitions, of this AD.
Request To Clarify Acceptance of Reworked Parts
American requested that the FAA clarify paragraph (g)(2) and
paragraph (i), Credit for Previous Actions, regarding installation of
parts that initially failed inspection with a rejectable indication but
were later reworked and found acceptable. American stated that GE has
been accepting parts that were reworked using GE Subtask 72-00-00-210-
012 in the GEnx-1B EM 72-00-00, Special Procedure 023, in accordance
with approved GE Departure Recommendations.
The FAA disagrees. Paragraph (g)(2) of this AD requires that if
during an inspection, a stages 6-10 compressor rotor spool is found to
have a rejectable indication, as defined in paragraph (h) of this AD,
then the stages 6-10 compressor rotor spool must be removed from
service. If the stages 6-10 compressor rotor spool is subsequently
repaired or reworked, operators would need to submit an alternative
methods of compliance (AMOC) request to the FAA to allow use of the
repaired or reworked stages 6-10 compressor rotor spool.
Request To Revise References to Service Bulletin
GE Aviation requested that the FAA update the specified service
information by referencing Revision 2 of GE GEnx-1B SB 72-0472 and GE
GEnx-2B SB 72-0415. GE noted that Revision 2 of these SBs had not been
issued at the time of publication of the NPRM.
The FAA agrees and has updated this AD to reference GEnx-1B SB 72-
0472 R02 and GEnx-2B SB 72-0415 R02, both dated November 5, 2020. This
change to this AD imposes no additional burden on operators.
Request To Revise Previous Credit
Japan Airlines requested that the FAA grant credit for the
borescope inspection (BSI) or eddy current inspection (ECI) required by
paragraph (g)(1) of this AD if inspections were previously performed in
accordance with GE GEnx-1B SB 72-0472 R01, dated July 24, 2020.
The FAA agrees and has updated paragraph (i), Credit for Previous
Actions, to allow credit for inspections performed using GE GEnx-1B SB
72-0472 R01, dated July 24, 2020 or GE GEnx-2B SB 72-0415 R01, dated
July 24, 2020, as applicable.
Request for Reference Date Clarification
NCA requested that the FAA clarify the meaning of ``previously
undergone'' in paragraph (g)(1)(ii) of this AD. NCA commented that one
of its engines underwent an inspection during an engine shop visit
using GEnx-2B SB 72-0385 R02, dated July 29, 2019 and GE GEnx-2B SB 72-
0398 R00, dated October 30, 2019, before the effective date of this AD
but after publication of GEnx-2B SB 72-0415 R01. NCA noted that the
reference to ``previously undergone'' means that it has been
implemented in accordance with SB in the past without any specific
timeframe, so it is not clear if the NCA's engine can apply the no
cycles since new (CSN) limit.
The FAA clarified paragraph (g)(1)(i) and (ii) of this AD by
removing the phrase ``previously undergone'' and referring instead to
engines that have undergone inspections ``before the effective date of
this AD.''
Change to Compliance Time
The FAA updated Table 1 to paragraph (g)(1) of this AD by allowing
operators 100 flight cycles to perform the inspections required by
paragraph (g)(1) of this AD when an engine has a stages 6-10 compressor
rotor spool with 6,400 CSN or greater as of the effective date of this
AD. This change allows operators a grace period to complete the
required inspections without unnecessary grounding of airplanes and
still meets the safety intent of this AD.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes and any
other changes described previously, this AD is adopted as proposed in
the NPRM.
[[Page 33496]]
None of the changes will increase the economic burden on any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed GE GEnx-1B Service Bulletin (SB) 72-0472 R02,
dated November 5, 2020 (GEnx-1B SB 72-0472) and GE GEnx-2B SB 72-0415
R02, dated November 5, 2020 (GEnx-2B SB 72-0415).
GEnx-1B SB 72-0472 describes procedures for performing a BSI or an
ECI of stage 6, stage 7, and stage 8 webs, web transitions, and bore
faces of the stages 6-10 compressor rotor spool for GEnx-1B model
turbofan engines. GEnx-1B SB 72-0472 also provides the affected part
and serial numbers of the stages 6-10 compressor rotor spools installed
on GEnx-1B model turbofan engines.
GEnx-2B SB 72-0415 describes procedures for performing a BSI or an
ECI of stage 6, stage 7, and stage 8 webs, web transitions, and bore
faces of the stages 6-10 compressor rotor spool for GEnx-2B model
turbofan engines. GEnx-2B SB 72-0415 also provides the affected part
and serial numbers of the stages 6-10 compressor rotor spools installed
on GEnx-2B model turbofan engines.
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 also reviewed Subtask 72-31-45-160-002 of TASK 72-31-45-
200-807 in GE GEnx-1B Engine Manual 05-21-00, Life Limits 001 Mandatory
Inspections, Rev. 31 dated, January 31, 2020; and Subtask 72-31-45-160-
002 of TASK 72-31-45-200-801 in GE GEnx-2B Engine Manual 05-21-00, Life
Limits 001 Mandatory Inspections, Rev. 24 dated, January 31, 2020. The
Subtasks provide guidance on performing the ECI on the stages 6-10
compressor rotor spool on GE GEnx-1B and GEnx-2B model turbofan
engines.
The FAA also reviewed the following GE SBs: GEnx-1B SB 72-0448 R00,
dated July 29, 2019 (GEnx-1B SB 72-0448); GEnx-1B SB 72-0460 R00, dated
October 30, 2019 (GEnx-1B SB 72-0460); GEnx-2B SB 72-0385 R02, dated
July 29, 2019 (GEnx-2B SB 72-0385); and GEnx-2B SB 72-0398 R00, dated
October 30, 2019 (GEnx-2B SB 72-0398).
GEnx-1B SB 72-0448 describes procedures for performing a BSI or an
ECI of the stage 8 aft web of the HPC stages 6-10 rotor spool for GEnx-
1B model turbofan engines. GEnx-1B SB 72-0460 describes procedures for
performing a BSI or an ECI of the stage 6 and stage 7 aft web of the
HPC stages 6-10 rotor spool for GEnx-1B model turbofan engines.
GEnx-2B SB 72-0385 describes procedures for performing a BSI or an
ECI of the stage 8 aft web of the HPC stages 6-10 spool for GEnx-2B
model turbofan engines. GEnx-2B SB 72-0398 describes procedures for
performing a BSI or an ECI of the stage 6 and stage 7 aft web of the
HPC stages 6-10 rotor spool for GEnx-2B model turbofan engines.
Costs of Compliance
The FAA estimates that this AD affects 268 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
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BSI of GEnx-1B stage 6, stage 7, and 6 work-hours x $85 per $0 $510 $89,760
stage 8 webs, web transitions and hour = $510.
bore faces of the stages 6-10
compressor rotor spool.
BSI of GEnx-2B stage 6, stage 7, and 6 work-hours x $85 per 0 510 46,920
stage 8 webs, web transitions and hour = $510.
bore faces of the stages 6-10
compressor rotor spool.
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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 aircraft
that might need these replacements:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Replace the stages 6-10 compressor rotor spool 64 work-hours x $85 per hour = $1,018,600 $1,024,040
$5,440.
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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:
[[Page 33497]]
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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:
2021-11-07 General Electric Company: Amendment 39-21569; Docket No.
FAA-2020-0850; Project Identifier AD-2020-00288-E.
(a) Effective Date
This airworthiness directive (AD) is effective July 30, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to:
(1) General Electric Company (GE) GEnx-1B64, GEnx-1B64/P1, GEnx-
1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx-
1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/
P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2,
GEnx-1B76A/P2 model turbofan engines with stages 6-10 compressor
rotor spools in the high-pressure compressor (HPC) assembly with the
following part numbers (P/N) installed:
(i) P/N 2357M30G01, P/N 2357M30G02, P/N 2439M35G01, P/N
2439M35G02, or P/N 2445M40G02, all serial numbers (S/Ns);
(ii) P/N 2610M90G01 with the S/Ns listed in paragraph 4.,
APPENDIX--A, Table 1 of the GE GEnx-1B Service Bulletin (SB) 72-0472
R02, dated November 5, 2020 (GEnx-1B SB 72-0472); and
(iii) P/N 2628M56G01 with the S/Ns listed in paragraph 4.,
APPENDIX--A, Table 2 or Table 3 of GEnx-1B SB 72-0472.
(2) GEnx-2B67, GEnx-2B67/P, GEnx-2B67B model turbofan engines
with the following stages 6-10 compressor rotor spools P/Ns
installed:
(i) P/N 2357M30G02, P/N 2439M35G02, or P/N 2445M40G02, all S/Ns;
(ii) P/N 2340M36G01 with S/Ns listed in paragraph 4., APPENDIX--
A, Table 1 of GE GEnx-2B SB 72-0415 R02, dated November 5, 2020
(GEnx-2B SB 72-0415); and
(iii) P/N 2628M56G01 with S/Ns listed in paragraph 4.,
APPENDIX--A, Table 2 or Table 3 of GEnx-2B SB 72-0415.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by a finding during an inspection that two
stages 6-10 compressor rotor spools were damaged at similar
locations. In addition, the manufacturer reported that certain
stages 6-10 compressor rotor spool webs did not undergo a required
fluorescent penetrant inspection (FPI) during production. The FAA is
issuing this AD to prevent failure of the compressor rotor spool.
The unsafe condition, if not addressed, could result in uncontained
release of debris, 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 all affected GEnx-1B and GEnx-2B model turbofan engines,
before exceeding the compliance time in Table 1 to paragraph (g)(1)
of this AD, perform a borescope inspection (BSI) or eddy current
inspection (ECI) of the stage 6, stage 7, and stage 8 webs, web
transitions, and bore faces of the stages 6-10 compressor rotor
spool in accordance with the Accomplishment Instructions, paragraph
3, of GEnx-1B SB 72-0472 (for GEnx-1B models) or the Accomplishment
Instructions, paragraph 3, of GEnx-2B SB 72-0415 (for GEnx-2B
models).
Table 1 to Paragraph (g)(1)
------------------------------------------------------------------------
Cycles Since New (CSN) accumulated
on the stages 6-10 compressor Compliance time
rotor spool
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Less than 6,400 CSN............... Next engine shop visit or before the
stages 6-10 compressor rotor spool
accumulates 6,500 CSN, whichever
occurs first after the effective
date of this AD.
6,400 CSN or greater.............. Within 100 flight cycles after the
effective date of this AD.
------------------------------------------------------------------------
(i) For GEnx-1B model turbofan engines, except those identified
in paragraph 4, APPENDIX--A, Table 3 of SB 72-0472, if, before the
effective date of this AD, the engines have undergone inspections of
the aft web of stage 6, stage 7, and stage 8 of the stages 6-10
compressor rotor spool using both GE GEnx-1B SB 72-0448 R00, dated
July 29, 2019, and GE GEnx-1B SB 72-0460 R00, dated October 30,
2019, regardless of the CSN accumulated on the stages 6-10
compressor rotor spool, perform the inspection required by paragraph
(g)(1) of this AD no later than the next engine shop visit after the
effective date of this AD.
(ii) For GEnx-2B model turbofan engines, except those identified
in paragraph 4., APPENDIX--A, Table 3 of SB 72-0415, if, before the
effective date of this AD, the engines have undergone inspections of
the aft web of stage 6, stage 7, and stage 8 of the stages 6-10
compressor rotor spool using both GE GEnx-2B SB 72-385 R02, dated
July 29, 2019, and GE GEnx-2B SB 72-0398 R00, dated October 30,
2019, regardless of the CSN accumulated on the stages 6-10
compressor rotor spool, perform the inspection required by paragraph
(g)(1) of this AD no later than the next engine shop visit after the
effective date of this AD.
(2) For all affected GEnx-1B and GEnx-2B model turbofan engines,
during the inspections required by paragraph (g)(1) of this AD, if a
rejectable indication is found, before further flight, remove the
stages 6-10 compressor rotor spool from service and replace it with
a part eligible for installation.
(h) Definitions
(1) For the purpose of this AD, an ``engine shop visit'' is the
induction of an engine into the shop for maintenance involving the
separation of pairs of major mating engine flanges, except that the
separation of engine flanges solely for the purposes of
transportation of the engine without subsequent engine maintenance
does not constitute an engine shop visit.
(2) For the purpose of this AD, a rejectable indication is:
(i) A BSI indication that does not meet the BSI serviceable or
repairable limits referenced in the Accomplishment Instructions,
paragraph 3.A.(1)(a)2, of GEnx-1B SB 72-0472, or paragraph
3.A.(1)(a)2 of GEnx-2B SB 72-0415, and the affected part has not
undergone a subsequent ECI; or
(ii) A BSI indication that does not meet the BSI serviceable or
repairable limits referenced in the Accomplishment Instructions,
paragraph 3.A.(1)(a)2, of GEnx-1B SB 72-0472, or paragraph
3.A.(1)(a)2 of GEnx-2B SB 72-0415, and the affected part has
undergone a subsequent ECI in which the indication did not meet the
ECI serviceable or repairable limits referenced in the
[[Page 33498]]
Accomplishment Instructions, paragraph 3.A.(1)(b) of GEnx-1B SB 72-
0472, or paragraph 3.A.(1)(b) of GEnx-2B SB 72-0415; or
(iii) An ECI indication that does not meet the serviceable or
repairable limits referenced in the Accomplishment Instructions,
paragraph 3.A.(1)(b) of GEnx-1B SB 72-0472, or paragraph 3.A.(1)(b)
of GEnx-2B SB 72-0415.
(i) Credit for Previous Actions
(1) For affected GEnx-1B model turbofan engines, you may take
credit for the BSI or ECI required by paragraph (g)(1) of this AD,
if you performed an ECI of the stages 6-10 compressor rotor spool
webs, web transitions, and bore faces before the effective date of
this AD using Subtask 72-31-45-160-002 of TASK 72-31-45-200-807 in
GE GEnx-1B Engine Manual 05-21-00, Life Limits 001 Mandatory
Inspections, Rev. 31, dated January 31, 2020, or earlier, and no
rejectable indications were found.
(2) For affected GEnx-2B model turbofan engines, you may take
credit for the BSI or ECI required by paragraph (g)(1) of this AD,
if you performed and ECI of the stages 6-10 compressor rotor spool
webs, web transitions, and bore faces before the effective date of
this AD using Subtask 72-31-45-160-002 of TASK 72-31-45-200-801 in
GE GEnx-2B Engine Manual 05-21-00, Life Limits 001 Mandatory
Inspections, Rev. 24, dated January 31, 2020, or earlier, and no
rejectable indications were found.
(3) For affected GEnx-1B model turbofan engines, you may take
credit for the BSI or ECI required by paragraph (g)(1) of this AD,
if you performed that inspection before the effective date of this
AD using GE GEnx-1B Service Bulletin (SB) 72-0472 R00, dated April
24, 2020, or GE GEnx-1B SB 72-0472 R01, dated July 24, 2020, and no
rejectable indications were found.
(4) For affected GEnx-2B model turbofan engines, you may take
credit for the BSI or ECI required by paragraph (g)(1) of this AD,
if you performed that inspection before the effective date of this
AD using GE GEnx-2B SB 72-0415 R00, dated April 24, 2020, or GE
GEnx-2B SB 72-0415 R01, dated July 24, 2020, and no rejectable
indications were found.
(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. 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 Mehdi Lamnyi,
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: (781) 238-7743; 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) GE GEnx-1B Service Bulletin (SB) 72-0472 R02, dated November
5, 2020.
(ii) GE GEnx-2B SB 72-0415 R02, dated November 5, 2020.
(3) For General Electric Company service information identified
in this AD, contact General Electric Company, 1 Neumann Way,
Cincinnati, OH 45215; phone: (513) 552-3272; email:
[email protected]; website: www.ge.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 19, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-13424 Filed 6-24-21; 8:45 am]
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