Airworthiness Directives; General Electric Company Turbofan Engines, 81378-81381 [2020-27628]
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81378
Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations
(i) Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(1) The Manager, Strategic Policy
Rotorcraft Section, FAA, may approve
AMOCs for this AD. Send your proposal to:
Manager, Strategic Policy Rotorcraft Section,
FAA, 10101 Hillwood Pkwy, Fort Worth, TX
76177; telephone 817–222–5110; email 9/
ASW/FTW/AMOC-Requests@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.
Federal Aviation Administration
(j) Related Information
For more information about this AD,
contact Kathleen Arrigotti, Aerospace
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA; telephone
206–231–3218; email kathleen.arrigotti@
faa.gov.
(k) Material Incorporated by Reference
khammond on DSKJM1Z7X2PROD with RULES
(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 this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0095, dated April 29, 2020.
(ii) [Reserved]
(3) For EASA AD 2020–0095, contact the
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
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(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. This
material may be found in the AD docket on
the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–3343.
(5) You may view this material 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 December 3, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2020–27659 Filed 12–15–20; 8:45 am]
BILLING CODE 4910–13–P
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14 CFR Part 39
[Docket No. FAA–2020–0592; Project
Identifier AD–2020–00251–E; Amendment
39–21352; AD 2020–25–10]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
General Electric Company (GE) GEnx1B64/P2, GEnx-1B67/P2, GEnx-1B70/
75/P2, GEnx-1B70/P2, GEnx-1B70C/P2,
GEnx-1B74/75/P2, GEnx-1B76/P2,
GEnx-1B76A/P2, and GEnx-2B67/P
model turbofan engines with a certain
high-pressure turbine (HPT) rotor stage
2 disk installed. This AD was prompted
by a report of the potential for
undetected subsurface anomalies
formed during the manufacturing
process that could result in uncontained
failure of the HPT rotor stage 2 disk.
This AD requires an immersion
ultrasonic inspection (USI) of the HPT
rotor stage 2 disk and, depending on the
results of the inspection, replacement of
the HPT rotor stage 2 disk with a part
eligible for installation. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective January 21,
2021.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 21, 2021.
ADDRESSES: For service information
identified in this final rule, contact
General Electric Company, GE Aviation,
Room 285, 1 Neumann Way, Cincinnati,
OH 45215; phone: (513) 552–3272;
email: aviation.fleetsupport@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–2020–0592.
SUMMARY:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0592; or in person at Docket
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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: Mehdi.Lamnyi@faa.gov.
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 all GE GEnx-1B64/P2, GEnx1B67/P2, GEnx-1B70/75/P2, GEnx1B70/P2, GEnx-1B70C/P2, GEnx-1B74/
75/P2, GEnx-1B76/P2, GEnx-1B76A/P2,
and GEnx-2B67/P model turbofan
engines with a certain HPT rotor stage
2 disk installed. The NPRM published
in the Federal Register on June 12, 2020
(85 FR 35816). The NPRM was
prompted by a report of the potential for
undetected subsurface anomalies
formed during the manufacturing
process that could result in uncontained
failure of the HPT rotor stage 2 disk. In
the NPRM, the FAA proposed to require
an immersion USI of the HPT rotor stage
2 disk and, depending on the results of
the inspection, replacement of the HPT
rotor stage 2 disk 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 six
commenters. The commenters were Air
Line Pilots Association, International
(ALPA); The Boeing Company (Boeing);
Cargolux Airlines International S.A.
(Cargolux); GE Aviation; United Airlines
(UAL) Engineering; and Qantas Airways
Limited (Qantas). One commenter
requested that the FAA update the
Affected ADs paragraph of this AD. One
commenter requested that the HPT rotor
stage 2 disks be replaced instead of
inspected. One commenter requested
that the FAA update the Definitions
paragraph of this AD. Two commenters
requested adding credit for previous
action. Three commenters supported the
AD. The following presents the
comments received on the NPRM and
the FAA’s response to each comment.
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Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations
Request To Update Affected ADs
UAL Engineering requested that the
FAA update paragraph (b), Affected
ADs, of this AD to note the impact of the
reduced life limits imposed by AD
2020–20–11 (85 FR 60898, September
29, 2020) (AD 2020–20–11) when
complying with this AD. UAL
Engineering reasoned that multiple HPT
rotor stage 2 disks are affected by both
rules, and leaving paragraph (b) blank
creates ambiguity for operators
generating compliance documentation
for the dual-affected disks and engines.
The FAA disagrees. Paragraph (b) of
this AD identifies superseded or revised
ADs, or other ADs if the requirements of
those ADs are affected (i.e., terminating
actions). This AD does not meet any of
those conditions. Although this AD
affects certain HPT rotor stage 2 disks
that also affected AD 2020–20–11, the
ADs address separate root causes and
have different compliance actions and
times. To comply with this AD, the
affected HPT rotor stage 2 disks must be
inspected and replaced if a rejectable
indication is found. If, in accordance
with AD 2020–20–11, an affected HPT
rotor stage 2 disk has already been
removed from service, then no further
action is necessary to comply with the
requirements of this AD.
Request To Replace Certain HPT Rotor
Stage 2 Disks
GE Aviation requested that HPT rotor
stage 2 disks with serial numbers
TMT3UA34, TMT3UA55, TMT4CT46,
or TMT4CT47, be replaced instead of
inspected. GE reasoned that AD 2020–
20–11 supersedes this AD, and the disks
should be replaced in accordance with
AD 2020–20–11.
The FAA disagrees. AD 2020–20–11
does not supersede this AD. Both ADs
address separate root causes and have
different compliance actions and times.
AD 2020–20–11 requires replacement of
certain HPT rotor stage 2 disks before
accumulating a specified number of
cycles since new. This AD requires a
USI of certain HPT rotor stage 2 disks
and, depending on the results of the
inspection, replacement of the HPT
rotor stage 2 disk. This AD may require
replacement of an HPT rotor stage 2 disk
prior to the required compliance time
specified in AD 2020–20–11. If,
however, an HPT rotor stage 2 disk is
removed from service per AD 2020–20–
11, then the affected turbofan engine
would no longer have an affected HPT
rotor stage 2 disk installed and would
fall outside of the applicability of this
AD.
Request To Update Definition of Engine
Shop Visit
Qantas requested that the FAA update
the definition of an ‘‘engine shop visit’’
to exclude engines with 2,000 or fewer
cycles since new (CSN) that install the
new retaining clips for the HPT stage 2
nozzle assembly (retaining clips)
introduced in GEnx-1B Service Bulletin
(SB) 72–0398 during a ‘‘Quick Turn’’
shop visit. Qantas reasoned that the
definition of an ‘‘engine shop visit’’ in
the NPRM would require the removal
and inspection of an affected HPT rotor
stage 2 disk during their planned lowtime engine elective ‘‘Quick Turn’’ shop
visit for installation of the new retaining
clips. Qantas concluded that additional
disassembly, cost, and engine shop turn
time will significantly affect the
viability of the GE retaining clip ‘‘Quick
Turn’’ program.
The FAA disagrees with excluding
low-time engines that install the new
retaining clips for the HPT Stage 2
Nozzle Assembly during a ‘‘Quick
Turn’’ shop visit. Changing the
definition to exclude the ‘‘Quick Turn’’
shop visit would possibly postpone the
immersion USI of the HPT rotor stage 2
disk required by this AD until a
subsequent shop visit. As a result, the
risk of failure of the HPT rotor stage 2
disk would increase. Qantas did not
provide documentation to show that
excluding the ‘‘Quick Turn’’ shop visit
from the definition of an engine shop
visit offers an acceptable level of safety.
The FAA, however, will consider
requests for alternative methods of
compliance if submitted documentation
supports an acceptable level of safety.
Request To Add Credit for Previous
Action
Cargolux and GE Aviation requested
credit for previous performance of the
immersion USI of the HPT rotor stage 2
disk using GE GEnx-1B Cleaning,
Inspection and Repair Manual (CIR) 72–
53–41, Special Procedure 001, or GE
81379
GEnx-2B CIR 72–53–41, Special
Procedure 001. Cargolux reasoned that
GE GEnx-2B SB 72–0402 R00, dated
November 20, 2019, refers to GEnx-2B
CIR 72–53–41, Special Procedure 001.
The FAA disagrees. This AD does not
require the use of GE GEnx-1B CIR
GEK112862, CIR 72–53–41, Special
Procedure 001, Rev 31, dated January
31, 2020, or GE GEnx-2B CIR
GEK114120, CIR 72–53–41, Special
Procedure 001, Rev 24, dated January
31, 2020, to perform the immersion USI
of the HPT rotor stage 2 disk. The CIR
are referred to in the service information
referenced in paragraph (i), Credit for
Previous Action. Therefore, if an
operator performs the actions using the
CIR, the operator is performing the
action using the service information and
has complied with this AD. The FAA
did not change this AD.
Support for the AD
ALPA, Boeing, and UAL Engineering
expressed support for the AD as written.
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.
Related Service Information Under 1
CFR Part 51
The FAA reviewed GE GEnx-1B SB
72–0463 R01, dated January 6, 2020,
and GE GEnx-2B SB 72–0402 R01, dated
January 8, 2020. This service
information describes procedures for
performing an immersion USI of the
affected HPT rotor stage 2 disks on
GEnx-1B and GEnx-2B model turbofan
engines, respectively. 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.
Costs of Compliance
The FAA estimates that this AD
affects 276 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
USI of HPT rotor stage 2 disk ........................
8 work-hours × $85 per hour = $680 .............
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Cost per
product
Parts cost
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$0
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$680
Cost on U.S.
operators
$187,680
81380
Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations
The FAA estimates the following
costs to do any necessary replacements
that would be required based on the
results of the required inspection. The
agency has no way of determining the
number of aircraft that might need this
replacement:
ON-CONDITION COSTS
Action
Labor cost
Remove and replace the HPT rotor stage 2 disk ........
2 work-hours x $85 per hour = $170 ...........................
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,
(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.
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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:
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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
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2020–25–10 General Electric Company:
Amendment 39–21352; Docket No.
FAA–2020–0592; Project Identifier AD–
2020–00251–E.
(a) Effective Date
This airworthiness directive (AD) is
effective January 21, 2021.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all General Electric
Company (GE) GEnx-1B64/P2, GEnx-1B67/
P2, GEnx-1B70/75/P2, GEnx-1B70/P2, GEnx1B70C/P2, GEnx-1B74/75/P2, GEnx-1B76/P2,
and GEnx-1B76A/P2 model turbofan engines
that have a high-pressure turbine (HPT) rotor
stage 2 disk, part number (P/N) 2383M86P02,
and a serial number (S/N) listed in paragraph
4, Appendix—A, Table 1, Table 2, or Table
3, of GE GEnx-1B Service Bulletin (SB) 72–
0463 R01, dated January 6, 2020, installed.
(2) This AD applies to all GE GEnx-2B67/
P model turbofan engines that have a HPT
rotor stage 2 disk, P/N 2383M86P02, and a
S/N listed in paragraph 4, Appendix—A,
Table 1, Table 2, or Table 3, of GE GEnx-2B
SB 72–0402 R01, dated January 8, 2020,
installed.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7250, Turbine Section.
(e) Unsafe Condition
This AD was prompted by a report of the
potential for undetected subsurface
anomalies formed during the manufacturing
process that could result in uncontained
failure of the HPT rotor stage 2 disk. The
FAA is issuing this AD to prevent failure of
the HPT rotor stage 2 disk. The unsafe
condition, if not addressed, could result in
uncontained HPT rotor stage 2 disk release,
damage to the engine, and damage to the
airplane.
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Parts cost
$458,900
Cost per
product
$459,070
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) For affected GE GEnx-1B engines, at the
next engine shop visit after the effective date
of this AD, or before the HPT rotor stage 2
disk has accumulated 6,500 cycles since new
(CSN), whichever occurs first, perform an
immersion ultrasonic inspection (USI) of the
HPT rotor stage 2 disk using paragraph
3.B.(1) of GE GEnx–1B SB 72–0463 R01,
dated January 6, 2020.
(2) If, during the USI required by paragraph
(g)(1) of this AD, a rejectable indication is
found, before further flight, remove the HPT
rotor stage 2 disk from service and replace it
with a part eligible for installation.
(3) For affected GE GEnx-2B engines, at the
next engine shop visit after the effective date
of this AD, or before the HPT rotor stage 2
disk has accumulated 6,500 CSN, whichever
occurs first, perform an immersion USI of the
HPT rotor stage 2 disk using paragraph
3.B.(1) of GE GEnx-2B SB 72–0402 R01, dated
January 8, 2020.
(4) If, during the USI required by paragraph
(g)(3) of this AD, a rejectable indication is
found, before further flight, remove the HPT
rotor stage 2 disk 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 when a major engine flange is
separated for purposes other than the
removal of the fan for transportation.
(2) For the purposes of this AD, a ‘‘part
eligible for installation’’ is:
(i) An HPT rotor stage 2 disk that does not
have an S/N listed in paragraph 4,
Appendix—A, Table 1, Table 2, or Table 3,
of GE GEnx-1B SB 72–0463 R01, dated
January 6, 2020, or GE GEnx-2B SB 72–0402
R01, dated January 8, 2020; or,
(ii) An HPT rotor stage 2 disk that has
successfully passed the immersion USI
required by paragraph (g)(1) or (3) of this AD,
or passed the immersion USI using GE GEnx1B SB 72–0463 R00, dated November 20,
2019, or GE GEnx-2B SB 72–0402 R00, dated
November 20, 2019, before the effective date
of this AD.
(i) Credit for Previous Action
You may take credit for the immersion USI
of the HPT rotor stage 2 disk required by
paragraph (g)(1) or (3) of this AD if you
performed this inspection before the effective
date of this AD using GE GEnx-1B SB 72–
0463 R00, dated November 20, 2019, or GE
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Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations
GEnx-2B SB 72–0402 R00, dated November
20, 2019.
Federal Aviation Administration
(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: ANE-AD-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.
(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:
Mehdi.Lamnyi@faa.gov.
(l) Material Incorporated by Reference
khammond on DSKJM1Z7X2PROD with RULES
(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) General Electric Company (GE) GEnx-1B
Service Bulletin (SB) 72–0463 R01, dated
January 6, 2020, and
(ii) GE GEnx-2B SB 72–0402 R01, dated
January 8, 2020.
(3) For GE service information identified in
this AD, contact General Electric Company,
GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: (513) 552–
3272; email: aviation.fleetsupport@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 fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on December 3, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2020–27628 Filed 12–15–20; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Yabora˜
Indu´stria Aerona´utica S.A. (Type
Certificate Previously Held by Embraer
S.A.) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Yabora˜ Indu´stria Aerona´utica S.A.
Model ERJ 170 airplanes and Model ERJ
190–100 STD, –100 LR, –100 ECJ, –100
IGW, –200 STD, –200 LR, and –200 IGW
airplanes. This AD was prompted by
reports of installation of inverted poles
of the horizontal stabilizer pitch trim
switches on the control yokes, which
causes opposite commands for the
horizontal stabilizer. This AD requires
installing supports for the horizontal
stabilizer control yoke pitch trim
switches and re-identifying the control
yokes, as specified in two Ageˆncia
Nacional de Aviac
¸a˜o Civil (ANAC) ADs,
which are incorporated by reference.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective January 21,
2021.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 21, 2021.
ADDRESSES: For material incorporated
by reference (IBR) in this AD, contact
National Civil Aviation Agency (ANAC),
Aeronautical Products Certification
Branch (GGCP), Rua Dr. Orlando
Feirabend Filho, 230—Centro
Empresarial Aquarius—Torre B—
Andares 14 a 18, Parque Residencial
Aquarius, CEP 12.246–190—Sa˜o Jose´
dos Campos—SP, BRAZIL, Tel: 55 (12)
3203–6600; Email: pac@anac.gov.br;
internet www.anac.gov.br/en/. You may
find this IBR material on the ANAC
website at https://sistemas.anac.gov.br/
certificacao/DA/DAE.asp. 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
SUMMARY:
Frm 00043
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the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0842.
Examining the AD Docket
[Docket No. FAA–2020–0842; Product
Identifier 2020–NM–101–AD; Amendment
39–21350; AD 2020–25–08]
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81381
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You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0842; 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:
Krista Greer, Aerospace Engineer, Large
Aircraft Section, International
Validation Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3221;
Krista.Greer@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The ANAC, which is the aviation
authority for Brazil, has issued ANAC
AD 2020–05–01, effective May 26, 2020;
and ANAC AD 2020–05–02, effective
May 26, 2020 (ANAC AD 2020–05–01
and ANAC AD 2020–05–02) (also
referred to as the Mandatory Continuing
Airworthiness Information, or the
MCAI); to correct an unsafe condition
for certain Yabora˜ Indu´stria Aerona´utica
S.A. Model ERJ 170 airplanes and
Model ERJ 190–100 STD, –100 LR, –100
ECJ, –100 IGW, –100 SR, –200 STD,
–200 LR, and –200 IGW airplanes.
Model ERJ 190–100 SR 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.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Yabora˜ Indu´stria
Aerona´utica S.A. Model ERJ 170
airplanes and Model ERJ 190–100 STD,
–100 LR, –100 ECJ, –100 IGW, –200
STD, –200 LR, and –200 IGW airplanes.
The NPRM published in the Federal
Register on September 17, 2020 (85 FR
58004). The NPRM was prompted by
reports of installation of inverted poles
of the horizontal stabilizer pitch trim
switches on the control yokes, which
causes opposite commands for the
horizontal stabilizer. The NPRM
proposed to require installing supports
E:\FR\FM\16DER1.SGM
16DER1
]]>Agencies
[Federal Register Volume 85, Number 242 (Wednesday, December 16, 2020)]
[Rules and Regulations]
[Pages 81378-81381]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-27628]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0592; Project Identifier AD-2020-00251-E;
Amendment 39-21352; AD 2020-25-10]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
General Electric Company (GE) GEnx-1B64/P2, GEnx-1B67/P2, GEnx-1B70/75/
P2, GEnx-1B70/P2, GEnx-1B70C/P2, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx-
1B76A/P2, and GEnx-2B67/P model turbofan engines with a certain high-
pressure turbine (HPT) rotor stage 2 disk installed. This AD was
prompted by a report of the potential for undetected subsurface
anomalies formed during the manufacturing process that could result in
uncontained failure of the HPT rotor stage 2 disk. This AD requires an
immersion ultrasonic inspection (USI) of the HPT rotor stage 2 disk
and, depending on the results of the inspection, replacement of the HPT
rotor stage 2 disk with a part eligible for installation. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective January 21, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 21,
2021.
ADDRESSES: For service information identified in this final rule,
contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: (513) 552-3272; email:
[email protected]. You may view this service information at
the FAA, Airworthiness Products Section, Operational Safety Branch,
1200 District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call (781) 238-7759. It is
also available at https://www.regulations.gov by searching for and
locating Docket No. FAA-2020-0592.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0592; 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 all GE GEnx-1B64/P2,
GEnx-1B67/P2, GEnx-1B70/75/P2, GEnx-1B70/P2, GEnx-1B70C/P2, GEnx-1B74/
75/P2, GEnx-1B76/P2, GEnx-1B76A/P2, and GEnx-2B67/P model turbofan
engines with a certain HPT rotor stage 2 disk installed. The NPRM
published in the Federal Register on June 12, 2020 (85 FR 35816). The
NPRM was prompted by a report of the potential for undetected
subsurface anomalies formed during the manufacturing process that could
result in uncontained failure of the HPT rotor stage 2 disk. In the
NPRM, the FAA proposed to require an immersion USI of the HPT rotor
stage 2 disk and, depending on the results of the inspection,
replacement of the HPT rotor stage 2 disk 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 six commenters. The commenters were
Air Line Pilots Association, International (ALPA); The Boeing Company
(Boeing); Cargolux Airlines International S.A. (Cargolux); GE Aviation;
United Airlines (UAL) Engineering; and Qantas Airways Limited (Qantas).
One commenter requested that the FAA update the Affected ADs paragraph
of this AD. One commenter requested that the HPT rotor stage 2 disks be
replaced instead of inspected. One commenter requested that the FAA
update the Definitions paragraph of this AD. Two commenters requested
adding credit for previous action. Three commenters supported the AD.
The following presents the comments received on the NPRM and the FAA's
response to each comment.
[[Page 81379]]
Request To Update Affected ADs
UAL Engineering requested that the FAA update paragraph (b),
Affected ADs, of this AD to note the impact of the reduced life limits
imposed by AD 2020-20-11 (85 FR 60898, September 29, 2020) (AD 2020-20-
11) when complying with this AD. UAL Engineering reasoned that multiple
HPT rotor stage 2 disks are affected by both rules, and leaving
paragraph (b) blank creates ambiguity for operators generating
compliance documentation for the dual-affected disks and engines.
The FAA disagrees. Paragraph (b) of this AD identifies superseded
or revised ADs, or other ADs if the requirements of those ADs are
affected (i.e., terminating actions). This AD does not meet any of
those conditions. Although this AD affects certain HPT rotor stage 2
disks that also affected AD 2020-20-11, the ADs address separate root
causes and have different compliance actions and times. To comply with
this AD, the affected HPT rotor stage 2 disks must be inspected and
replaced if a rejectable indication is found. If, in accordance with AD
2020-20-11, an affected HPT rotor stage 2 disk has already been removed
from service, then no further action is necessary to comply with the
requirements of this AD.
Request To Replace Certain HPT Rotor Stage 2 Disks
GE Aviation requested that HPT rotor stage 2 disks with serial
numbers TMT3UA34, TMT3UA55, TMT4CT46, or TMT4CT47, be replaced instead
of inspected. GE reasoned that AD 2020-20-11 supersedes this AD, and
the disks should be replaced in accordance with AD 2020-20-11.
The FAA disagrees. AD 2020-20-11 does not supersede this AD. Both
ADs address separate root causes and have different compliance actions
and times. AD 2020-20-11 requires replacement of certain HPT rotor
stage 2 disks before accumulating a specified number of cycles since
new. This AD requires a USI of certain HPT rotor stage 2 disks and,
depending on the results of the inspection, replacement of the HPT
rotor stage 2 disk. This AD may require replacement of an HPT rotor
stage 2 disk prior to the required compliance time specified in AD
2020-20-11. If, however, an HPT rotor stage 2 disk is removed from
service per AD 2020-20-11, then the affected turbofan engine would no
longer have an affected HPT rotor stage 2 disk installed and would fall
outside of the applicability of this AD.
Request To Update Definition of Engine Shop Visit
Qantas requested that the FAA update the definition of an ``engine
shop visit'' to exclude engines with 2,000 or fewer cycles since new
(CSN) that install the new retaining clips for the HPT stage 2 nozzle
assembly (retaining clips) introduced in GEnx-1B Service Bulletin (SB)
72-0398 during a ``Quick Turn'' shop visit. Qantas reasoned that the
definition of an ``engine shop visit'' in the NPRM would require the
removal and inspection of an affected HPT rotor stage 2 disk during
their planned low-time engine elective ``Quick Turn'' shop visit for
installation of the new retaining clips. Qantas concluded that
additional disassembly, cost, and engine shop turn time will
significantly affect the viability of the GE retaining clip ``Quick
Turn'' program.
The FAA disagrees with excluding low-time engines that install the
new retaining clips for the HPT Stage 2 Nozzle Assembly during a
``Quick Turn'' shop visit. Changing the definition to exclude the
``Quick Turn'' shop visit would possibly postpone the immersion USI of
the HPT rotor stage 2 disk required by this AD until a subsequent shop
visit. As a result, the risk of failure of the HPT rotor stage 2 disk
would increase. Qantas did not provide documentation to show that
excluding the ``Quick Turn'' shop visit from the definition of an
engine shop visit offers an acceptable level of safety. The FAA,
however, will consider requests for alternative methods of compliance
if submitted documentation supports an acceptable level of safety.
Request To Add Credit for Previous Action
Cargolux and GE Aviation requested credit for previous performance
of the immersion USI of the HPT rotor stage 2 disk using GE GEnx-1B
Cleaning, Inspection and Repair Manual (CIR) 72-53-41, Special
Procedure 001, or GE GEnx-2B CIR 72-53-41, Special Procedure 001.
Cargolux reasoned that GE GEnx-2B SB 72-0402 R00, dated November 20,
2019, refers to GEnx-2B CIR 72-53-41, Special Procedure 001.
The FAA disagrees. This AD does not require the use of GE GEnx-1B
CIR GEK112862, CIR 72-53-41, Special Procedure 001, Rev 31, dated
January 31, 2020, or GE GEnx-2B CIR GEK114120, CIR 72-53-41, Special
Procedure 001, Rev 24, dated January 31, 2020, to perform the immersion
USI of the HPT rotor stage 2 disk. The CIR are referred to in the
service information referenced in paragraph (i), Credit for Previous
Action. Therefore, if an operator performs the actions using the CIR,
the operator is performing the action using the service information and
has complied with this AD. The FAA did not change this AD.
Support for the AD
ALPA, Boeing, and UAL Engineering expressed support for the AD as
written.
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.
Related Service Information Under 1 CFR Part 51
The FAA reviewed GE GEnx-1B SB 72-0463 R01, dated January 6, 2020,
and GE GEnx-2B SB 72-0402 R01, dated January 8, 2020. This service
information describes procedures for performing an immersion USI of the
affected HPT rotor stage 2 disks on GEnx-1B and GEnx-2B model turbofan
engines, respectively. 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.
Costs of Compliance
The FAA estimates that this AD affects 276 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
----------------------------------------------------------------------------------------------------------------
USI of HPT rotor stage 2 disk......... 8 work-hours x $85 per $0 $680 $187,680
hour = $680.
----------------------------------------------------------------------------------------------------------------
[[Page 81380]]
The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
required inspection. The agency has no way of determining the number of
aircraft that might need this replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Remove and replace the HPT rotor stage 2 disk. 2 work-hours x $85 per hour = $458,900 $459,070
$170.
----------------------------------------------------------------------------------------------------------------
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,
(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:
2020-25-10 General Electric Company: Amendment 39-21352; Docket No.
FAA-2020-0592; Project Identifier AD-2020-00251-E.
(a) Effective Date
This airworthiness directive (AD) is effective January 21, 2021.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all General Electric Company (GE) GEnx-
1B64/P2, GEnx-1B67/P2, GEnx-1B70/75/P2, GEnx-1B70/P2, GEnx-1B70C/P2,
GEnx-1B74/75/P2, GEnx-1B76/P2, and GEnx-1B76A/P2 model turbofan
engines that have a high-pressure turbine (HPT) rotor stage 2 disk,
part number (P/N) 2383M86P02, and a serial number (S/N) listed in
paragraph 4, Appendix--A, Table 1, Table 2, or Table 3, of GE GEnx-
1B Service Bulletin (SB) 72-0463 R01, dated January 6, 2020,
installed.
(2) This AD applies to all GE GEnx-2B67/P model turbofan engines
that have a HPT rotor stage 2 disk, P/N 2383M86P02, and a S/N listed
in paragraph 4, Appendix--A, Table 1, Table 2, or Table 3, of GE
GEnx-2B SB 72-0402 R01, dated January 8, 2020, installed.
(d) Subject
Joint Aircraft System Component (JASC) Code 7250, Turbine
Section.
(e) Unsafe Condition
This AD was prompted by a report of the potential for undetected
subsurface anomalies formed during the manufacturing process that
could result in uncontained failure of the HPT rotor stage 2 disk.
The FAA is issuing this AD to prevent failure of the HPT rotor stage
2 disk. The unsafe condition, if not addressed, could result in
uncontained HPT rotor stage 2 disk 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) For affected GE GEnx-1B engines, at the next engine shop
visit after the effective date of this AD, or before the HPT rotor
stage 2 disk has accumulated 6,500 cycles since new (CSN), whichever
occurs first, perform an immersion ultrasonic inspection (USI) of
the HPT rotor stage 2 disk using paragraph 3.B.(1) of GE GEnx-1B SB
72-0463 R01, dated January 6, 2020.
(2) If, during the USI required by paragraph (g)(1) of this AD,
a rejectable indication is found, before further flight, remove the
HPT rotor stage 2 disk from service and replace it with a part
eligible for installation.
(3) For affected GE GEnx-2B engines, at the next engine shop
visit after the effective date of this AD, or before the HPT rotor
stage 2 disk has accumulated 6,500 CSN, whichever occurs first,
perform an immersion USI of the HPT rotor stage 2 disk using
paragraph 3.B.(1) of GE GEnx-2B SB 72-0402 R01, dated January 8,
2020.
(4) If, during the USI required by paragraph (g)(3) of this AD,
a rejectable indication is found, before further flight, remove the
HPT rotor stage 2 disk 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 when
a major engine flange is separated for purposes other than the
removal of the fan for transportation.
(2) For the purposes of this AD, a ``part eligible for
installation'' is:
(i) An HPT rotor stage 2 disk that does not have an S/N listed
in paragraph 4, Appendix--A, Table 1, Table 2, or Table 3, of GE
GEnx-1B SB 72-0463 R01, dated January 6, 2020, or GE GEnx-2B SB 72-
0402 R01, dated January 8, 2020; or,
(ii) An HPT rotor stage 2 disk that has successfully passed the
immersion USI required by paragraph (g)(1) or (3) of this AD, or
passed the immersion USI using GE GEnx-1B SB 72-0463 R00, dated
November 20, 2019, or GE GEnx-2B SB 72-0402 R00, dated November 20,
2019, before the effective date of this AD.
(i) Credit for Previous Action
You may take credit for the immersion USI of the HPT rotor stage
2 disk required by paragraph (g)(1) or (3) of this AD if you
performed this inspection before the effective date of this AD using
GE GEnx-1B SB 72-0463 R00, dated November 20, 2019, or GE
[[Page 81381]]
GEnx-2B SB 72-0402 R00, dated November 20, 2019.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, ECO Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
certification office, send it to the attention of the person
identified in 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) General Electric Company (GE) GEnx-1B Service Bulletin (SB)
72-0463 R01, dated January 6, 2020, and
(ii) GE GEnx-2B SB 72-0402 R01, dated January 8, 2020.
(3) For GE service information identified in this AD, contact
General Electric Company, GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: (513) 552-3272; email:
[email protected].
(4) You may view this service information at FAA, Airworthiness
Products Section, Operational Safety Branch, 1200 District Avenue,
Burlington, MA 01803. For information on the availability of this
material at the FAA, call (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 December 3, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020-27628 Filed 12-15-20; 8:45 am]
BILLING CODE 4910-13-P
