Airworthiness Directives; General Electric Company Turbofan Engines, 11113-11116 [2021-03606]
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Federal Register / Vol. 86, No. 35 / Wednesday, February 24, 2021 / Rules and Regulations
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 responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (k) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or Dassault Aviation’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
Issued on January 28, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
(k) Related Information
SUMMARY:
For more information about this AD,
contact Tom Rodriguez, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; phone and fax:
206–231–3226; email: tom.rodriguez@
faa.gov.
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(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 this AD specifies otherwise.
(3) The following service information was
approved for IBR on March 31, 2021.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0127, dated June 4, 2020.
(ii) [Reserved]
(4) For EASA AD 2020–0127, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; phone: +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.
(5) You may view this 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. 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–2020–0977.
(6) 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.
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11113
DEPARTMENT OF TRANSPORTATION
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–
0371.
Federal Aviation Administration
Examining the AD Docket
[FR Doc. 2021–03601 Filed 2–23–21; 8:45 am]
BILLING CODE 4910–13–P
14 CFR Part 39
[Docket No. FAA–2020–0371; Project
Identifier AD–2019–00124–E; Amendment
39–21405; AD 2021–03–02]
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 certain
General Electric Company (GE) CF6–
80C2A1, CF6–80C2A2, CF6–80C2A3,
CF6–80C2A5, CF6–80C2A5F, CF6–
80C2A8, CF6–80C2B1, CF6–80C2B1F,
CF6–80C2B2, CF6–80C2B2F, CF6–
80C2B4, CF6–80C2B4F, CF6–80C2B5F,
CF6–80C2B6, CF6–80C2B6F, CF6–
80C2B6FA, CF6–80C2B7F, CF6–
80C2B8F, and CF6–80C2D1F model
turbofan engines. This AD was
prompted by reports of incidents that
resulted in a significant fuel loss during
flight and an in-flight shutdown (IFSD)
of the engine. This AD requires initial
and repetitive shim checks of the
hydromechanical unit/main engine
control (HMU/MEC) idler adapter on the
accessory gearbox (AGB) assembly and,
depending on the results of the shim
check, possible replacement of the
inserts on the HMU/MEC idler adapter.
As a terminating action, this AD
requires a protrusion check and a pullout test, and the replacement of inserts
on the HMU/MEC idler adapter that fail
either test. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective March 31,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 31, 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:
aviation.fleetsupport@ge.com. You may
view this service information at the
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You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0371; 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:
Kevin M. Clark, Aviation Safety
Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: (781) 238–7088; fax: (781) 238–
7199; email: kevin.m.clark@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 certain GE CF6–80C2A1, CF6–
80C2A2, CF6–80C2A3, CF6–80C2A5,
CF6–80C2A5F, CF6–80C2A8, CF6–
80C2B1, CF6–80C2B1F, CF6–80C2B2,
CF6–80C2B2F, CF6–80C2B4, CF6–
80C2B4F, CF6–80C2B5F, CF6–80C2B6,
CF6–80C2B6F, CF6–80C2B6FA, CF6–
80C2B7F, CF6–80C2B8F, and CF6–
80C2D1F model turbofan engines. The
NPRM published in the Federal
Register on April 10, 2020 (85 FR
20211). The NPRM was prompted by
reports of incidents that resulted in a
significant fuel loss during flight and an
IFSD of the engine. The incidents
resulted from inserts on the HMU/MEC
idler adapter on the AGB assembly
pulling out of the housing. An
investigation by the manufacturer
discovered improperly cut threads on
the inserts and erroneous instructions in
the maintenance manual, which
contributed to poor thread engagement.
In the NPRM, the FAA proposed to
require initial and repetitive shim
checks of the HMU/MEC idler adapter
on the AGB assembly and, depending
on the results of the shim check,
possible replacement of the inserts on
the HMU/MEC idler adapter. As a
terminating action to the repetitive shim
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Federal Register / Vol. 86, No. 35 / Wednesday, February 24, 2021 / Rules and Regulations
checks, the NPRM proposed to require
a protrusion check and a pull-out test,
and the replacement of inserts on the
HMU/MEC idler adapter that fail either
test. 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
four commenters. The commenters were
All Nippon Airways (ANA), Delta Air
Lines, Inc. (DAL), FedEx Express
(FedEx), and Japan Airlines (JAL). All
commenters requested changes, some of
which resulted in changes to this AD.
The following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Update the Applicability
DAL requested that paragraph (c),
Applicability, of this AD be updated to
align with the effectivity in GE CF6–
80C2 Service Bulletin (SB) 72–1577
R01, dated August 16, 2019 (GE CF6–
80C2 SB 72–1577 R01), which includes
the part numbers (P/Ns) of the affected
HMU/MEC idler adapters.
The FAA agrees. The FAA confirmed
with the manufacturer that only the P/
Ns of the HMU/MEC idler adapter listed
in GE CF6–80C2 SB 72–1577 R01 are
affected. The FAA updated the
applicability of this AD to include the
P/Ns of the affected HMU/MEC idler
adapter. The number of engines affected
by this AD is unchanged from the
NPRM.
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Request To Update Terminating Action
DAL requested that paragraph (h),
Terminating Action, of this AD also
terminate the initial shim check of the
HMU/MEC idler adapter inserts
required by paragraph (g)(1) of this AD.
DAL reasoned that since the NPRM
proposed to allow for terminating the
repetitive shim checks of the HMU/MEC
idler adapter inserts, that this AD
should add a terminating action for the
initial shim check of the HMU/MEC
idler adapter inserts if the action was
performed within 1,200 flight hours
(FHs) after the effective date of this AD.
The FAA agrees. The FAA updated
paragraph (h) of this AD to terminate the
actions required by paragraph (g) of this
AD.
Request To Remove the Shim Check
DAL requested that the FAA remove
the shim check of the HMU/MEC idler
adapter inserts in paragraph (g)(3)(ii) of
the NPRM. DAL reasoned that
performing this shim check is not
necessary because the (g)(3)(ii) shim
check is already required by paragraph
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(g)(3)(i) of this AD. Additionally, DAL
stated that referencing paragraph (g)(1)
of this AD to perform the shim check
may confuse operators as paragraph
(g)(1) of this AD includes the
requirement to perform the shim check
within 1,200 FHs after the effective date
of this AD. Therefore, DAL suggested
that paragraph (g)(3)(ii) of this AD
should only address the requirement to
perform the terminating action if the
shim check fails.
The FAA partially agrees. The FAA
disagrees that paragraph (g)(3)(ii) of this
AD should only address the requirement
to perform the terminating action if the
shim check of the HMU/MEC idler
adapter inserts fails. After retorque of
the bolts at each bolt location that failed
the shim check, operators must perform
the shim check again. If that shim check
fails, then the terminating action is
required. The FAA agrees that
referencing paragraph (g)(1) of this AD
may confuse operators whether to
perform the shim check after the aircraft
operated for some time or within 1,200
FHs after the effective date of this AD.
The FAA updated paragraph (g)(3)(ii) of
this AD to reference the service
information when performing the shim
check rather than paragraph (g)(1) of
this AD.
Request To Update Credit for Previous
Actions
ANA, DAL, FedEx, and JAL requested
updates to paragraph (i), Credit for
Previous Actions, of this AD. ANA
requested adding credit for the
repetitive shim checks of the HMU/MEC
idler adapter inserts and terminating
action. DAL and FedEx requested credit
for the terminating action. JAL
requested credit for the repetitive shim
checks of the HMU/MEC idler adapter
inserts, retorque of the bolts that failed
the shim check, and the terminating
action. The commenters reasoned that
GE CF6–80C2 SB 72–1577 R00, dated
October 31, 2018 (GE CF6–80C2 SB 72–
1577 R00), instructs the operator to
perform the same tasks required by GE
CF6–80C2 SB 72–1577 R01. Therefore,
credit should be allowed for initial and
repetitive shim checks of the HMU/MEC
idler adapter inserts and the terminating
action.
The FAA agrees. The FAA reviewed
GE CF6–80C2 SB 72–1577 R00, and
determined that the instructions are
consistent with GE CF6–80C2 SB 72–
1577 R01. The FAA updated this AD to
allow credit for the initial and repetitive
shim checks of the HMU/MEC idler
adapter inserts, retorque of the bolts that
failed the shim check, and the
terminating action, if performed before
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the effective date of this AD using GE
CF6–80C2 SB 72–1577 R00.
Request for an Alternate Marking Area
ANA requested that the FAA approve
an alternate marking area to show
compliance with performing the
terminating action of this AD. ANA
stated that the marking areas indicated
in GE CF6–80C2 SB 72–1577 R01, are
difficult to access because many
components are installed to AGB
assembly.
The FAA disagrees with approving an
alternate marking area. The
manufacturer provided two possible
marking areas in GE CF6–80C2 SB 72–
1577 R01, and confirmed the suitability
of the areas.
Request To Not Mandate the Marking
Requirement
DAL requested that the FAA not
mandate the provision in GE CF6–80C2
SB 72–1577 R01 to mark the HMU/MEC
idler adapter to show compliance with
the terminating actions of this AD. DAL
reasoned that the NPRM did not
propose to apply to all engines and
therefore should not be required.
The FAA disagrees. Marking the
HMU/MEC idler adapter identifies if the
terminating action of this AD has been
completed. As noted in a previous
comment response, the FAA revised the
applicability of this AD to limit
applicability to affected engines with
certain HMU/MEC idler adapter P/Ns
installed. Operators who determine that
their engines are not applicable to this
AD do not need to perform the
terminating action or mark the HMU/
MEC idler adapter.
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.
None of the changes will increase the
economic burden on any operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed GE CF6–80C2 SB
72–1577 R01, dated August 16, 2019.
The SB describes procedures for
performing shim checks of the HMU/
MEC idler adapter and for replacing the
HMU/MEC idler adapter inserts. This
service information is reasonably
available because the interested parties
have access to it through their normal
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Federal Register / Vol. 86, No. 35 / Wednesday, February 24, 2021 / Rules and Regulations
Costs of Compliance
course of business or by the means
identified in ADDRESSES.
The FAA estimates that this AD
affects 555 engines installed on
airplanes of U.S. registry.
11115
The FAA estimates the following
costs to comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Shim check .....................................................
Protrusion check/pull-out test .........................
1 work-hour × $85 per hour = $85 .................
4 work-hours × $85 per hour = $340 .............
The FAA estimates the following
costs to do any necessary replacements
Cost per
product
Parts cost
that are required based on the results of
the shim check. The agency has no way
$0
0
$85
340
Cost on U.S.
operators
$47,175
188,700
of determining the number of aircraft
that might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Replace HMU/MEC idler adapter insert .......................
4 work-hours × $85 per hour = $340 ...........................
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(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
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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
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:
■
2021–03–02 General Electric Company:
Amendment 39–21405; Docket No.
FAA–2020–0371; Project Identifier AD–
2019–00124–E.
(a) Effective Date
This airworthiness directive (AD) is
effective March 31, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric
Company (GE) CF6–80C2A1, CF6–80C2A2,
CF6–80C2A3, CF6–80C2A5, CF6–80C2A5F,
CF6–80C2A8, CF6–80C2B1, CF6–80C2B1F,
CF6–80C2B2, CF6–80C2B2F, CF6–80C2B4,
CF6–80C2B4F, CF6–80C2B5F, CF6–80C2B6,
CF6–80C2B6F, CF6–80C2B6FA, CF6–
80C2B7F, CF6–80C2B8F, and CF6–80C2D1F
model turbofan engines that underwent an
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Parts cost
$50
Cost per
product
$390
engine shop visit before November 1, 2018,
and with accessory gearbox (AGB) adapter
hydromechanical unit (HMU)/main engine
control (MEC) idler adapter with part number
(P/N) 9395M78G01, P/N 9395M78G02, P/N
9395M78G04, P/N 9395M78G05, P/N
9395M78G08, or P/N 9395M78G10, installed.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7321, Fuel Control/Turbine Engines.
(e) Unsafe Condition
This AD was prompted by failure of the
HMU/MEC on the AGB assembly. The FAA
is issuing this AD to prevent failure of the
HMU/MEC. The unsafe condition, if not
addressed, could result in engine fire and
damage to the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Perform a shim check of the HMU/MEC
idler adapter inserts using paragraph 3.B.(1)
of GE CF6–80C2 Service Bulletin (SB) 72–
1577 R01, dated August 16, 2019 (the SB),
within 1,200 flight hours (FHs) after the
effective date of this AD.
(2) Thereafter, perform a repetitive shim
check of the HMU/MEC idler adapter inserts
using paragraph 3.B.(1) of the SB within
every 1,200 FHs since the last shim check.
(3) If any HMU/MEC idler adapter insert
fails the shim check required by paragraph
(g)(1) or (2) of this AD, perform the following
before further flight:
(i) Retorque the bolts at each bolt location
that failed the shim check using paragraph
3.B.(1)(c) of the SB.
(ii) Perform the shim check again using
paragraph 3.B.(1)(b) of the SB. If the shim
check fails, perform the terminating action
required by paragraph (h) of this AD.
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(h) Terminating Action
As a terminating action to the requirements
of paragraph (g) of this AD, perform the
following:
(1) Do a protrusion check at all eight bolt
locations using paragraph 3.C.(3) of the SB.
(2) Do a pull-out test at all eight bolt
locations using paragraph 3.C.(4) of the SB.
(3) If the inserts on the HMU/MEC idler
adapter fail the protrusion check or pull-out
test required by paragraph (h)(1) or (2) of this
AD, replace the inserts using paragraph
3.C.(5) of the SB. After replacement of the
inserts is accomplished, the requirements of
this AD have been met and no further action
is required.
(4) If the inserts on the HMU/MEC idler
adapter pass both the protrusion check and
the pull-out test required by paragraphs (h)(1)
and (2) of this AD, the requirements of this
AD have been met and no further action is
required.
(i) Credit for Previous Actions
(1) You may take credit for any shim check
of the HMU/MEC idler adapter required by
paragraph (g) of this AD if you performed this
shim check before the effective date of this
AD using GE CF6–80C2 SB 72–1577 R00,
dated October 31, 2018.
(2) You may take credit for the terminating
action required by paragraph (h) of this AD
if you performed this action before the
effective date of this AD using GE CF6–80C2
SB 72–1577 R00, dated October 31, 2018.
(j) Definition
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
case flanges, except separation of engine
flanges solely for the purposes of
transportation of the engine without
subsequent maintenance, which does not
constitute an engine shop visit.
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(k) 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.
(l) Related Information
For more information about this AD,
contact Kevin M. Clark, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7088; fax: (781) 238–7199; email:
kevin.m.clark@faa.gov.
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(m) 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) CF6–
80C2 Service Bulletin 72–1577 R01, dated
August 16, 2019.
(ii) [Reserved]
(3) For GE service information identified in
this AD, contact General Electric Company,
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/
ibr-locations.html.
Issued on January 21, 2021.
Ross Landes,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–03606 Filed 2–23–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0980; Product
Identifier 2020–NM–094–AD; Amendment
39–21414; AD 2021–03–11]
RIN 2120–AA64
Airworthiness Directives; Dassault
Aviation Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2020–02–
21, which applied to all Dassault
Aviation Model FALCON 2000
airplanes. AD 2020–02–21 required
revising the existing maintenance or
inspection program, as applicable, to
incorporate new or more restrictive
airworthiness limitations. This AD
requires revising the existing
maintenance or inspection program, as
applicable to incorporate new or more
SUMMARY:
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Fmt 4700
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restrictive airworthiness limitations, as
specified in a European Union Aviation
Safety Agency (EASA) AD, which is
incorporated by reference. This AD was
prompted by a determination that new
or more restrictive airworthiness
limitations are necessary. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective March 31,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 31, 2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of March 18, 2020 (85 FR
7860, February 12, 2020).
ADDRESSES: For EASA material
incorporated by reference (IBR) in this
AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 8999 000;
email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
IBR material on the EASA website at
https://ad.easa.europa.eu. For Dassault
Aviation service information identified
in this final rule, contact Dassault
Falcon Jet Corporation, Teterboro
Airport, P.O. Box 2000, South
Hackensack, NJ 07606; telephone 201–
440–6700; internet https://
www.dassaultfalcon.com. You may
view this IBR material at the FAA,
Airworthiness Products Section,
Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available in the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0980.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0980; 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: Tom
Rodriguez, Aerospace Engineer, Large
Aircraft Section, International
Validation Branch, FAA, 2200 South
E:\FR\FM\24FER1.SGM
24FER1
]]>Agencies
[Federal Register Volume 86, Number 35 (Wednesday, February 24, 2021)]
[Rules and Regulations]
[Pages 11113-11116]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-03606]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0371; Project Identifier AD-2019-00124-E;
Amendment 39-21405; AD 2021-03-02]
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
certain General Electric Company (GE) CF6-80C2A1, CF6-80C2A2, CF6-
80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1, CF6-80C2B1F,
CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B5F, CF6-
80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, CF6-80C2B8F, and CF6-
80C2D1F model turbofan engines. This AD was prompted by reports of
incidents that resulted in a significant fuel loss during flight and an
in-flight shutdown (IFSD) of the engine. This AD requires initial and
repetitive shim checks of the hydromechanical unit/main engine control
(HMU/MEC) idler adapter on the accessory gearbox (AGB) assembly and,
depending on the results of the shim check, possible replacement of the
inserts on the HMU/MEC idler adapter. As a terminating action, this AD
requires a protrusion check and a pull-out test, and the replacement of
inserts on the HMU/MEC idler adapter that fail either test. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective March 31, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 31,
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]. 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-
0371.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0371; 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: Kevin M. Clark, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
phone: (781) 238-7088; 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 CF6-80C2A1,
CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-
80C2B1, CF6-80C2B1F, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F,
CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, CF6-
80C2B8F, and CF6-80C2D1F model turbofan engines. The NPRM published in
the Federal Register on April 10, 2020 (85 FR 20211). The NPRM was
prompted by reports of incidents that resulted in a significant fuel
loss during flight and an IFSD of the engine. The incidents resulted
from inserts on the HMU/MEC idler adapter on the AGB assembly pulling
out of the housing. An investigation by the manufacturer discovered
improperly cut threads on the inserts and erroneous instructions in the
maintenance manual, which contributed to poor thread engagement. In the
NPRM, the FAA proposed to require initial and repetitive shim checks of
the HMU/MEC idler adapter on the AGB assembly and, depending on the
results of the shim check, possible replacement of the inserts on the
HMU/MEC idler adapter. As a terminating action to the repetitive shim
[[Page 11114]]
checks, the NPRM proposed to require a protrusion check and a pull-out
test, and the replacement of inserts on the HMU/MEC idler adapter that
fail either test. 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 four commenters. The commenters were
All Nippon Airways (ANA), Delta Air Lines, Inc. (DAL), FedEx Express
(FedEx), and Japan Airlines (JAL). All commenters requested changes,
some of which resulted in changes to this AD. The following presents
the comments received on the NPRM and the FAA's response to each
comment.
Request To Update the Applicability
DAL requested that paragraph (c), Applicability, of this AD be
updated to align with the effectivity in GE CF6-80C2 Service Bulletin
(SB) 72-1577 R01, dated August 16, 2019 (GE CF6-80C2 SB 72-1577 R01),
which includes the part numbers (P/Ns) of the affected HMU/MEC idler
adapters.
The FAA agrees. The FAA confirmed with the manufacturer that only
the P/Ns of the HMU/MEC idler adapter listed in GE CF6-80C2 SB 72-1577
R01 are affected. The FAA updated the applicability of this AD to
include the P/Ns of the affected HMU/MEC idler adapter. The number of
engines affected by this AD is unchanged from the NPRM.
Request To Update Terminating Action
DAL requested that paragraph (h), Terminating Action, of this AD
also terminate the initial shim check of the HMU/MEC idler adapter
inserts required by paragraph (g)(1) of this AD. DAL reasoned that
since the NPRM proposed to allow for terminating the repetitive shim
checks of the HMU/MEC idler adapter inserts, that this AD should add a
terminating action for the initial shim check of the HMU/MEC idler
adapter inserts if the action was performed within 1,200 flight hours
(FHs) after the effective date of this AD.
The FAA agrees. The FAA updated paragraph (h) of this AD to
terminate the actions required by paragraph (g) of this AD.
Request To Remove the Shim Check
DAL requested that the FAA remove the shim check of the HMU/MEC
idler adapter inserts in paragraph (g)(3)(ii) of the NPRM. DAL reasoned
that performing this shim check is not necessary because the (g)(3)(ii)
shim check is already required by paragraph (g)(3)(i) of this AD.
Additionally, DAL stated that referencing paragraph (g)(1) of this AD
to perform the shim check may confuse operators as paragraph (g)(1) of
this AD includes the requirement to perform the shim check within 1,200
FHs after the effective date of this AD. Therefore, DAL suggested that
paragraph (g)(3)(ii) of this AD should only address the requirement to
perform the terminating action if the shim check fails.
The FAA partially agrees. The FAA disagrees that paragraph
(g)(3)(ii) of this AD should only address the requirement to perform
the terminating action if the shim check of the HMU/MEC idler adapter
inserts fails. After retorque of the bolts at each bolt location that
failed the shim check, operators must perform the shim check again. If
that shim check fails, then the terminating action is required. The FAA
agrees that referencing paragraph (g)(1) of this AD may confuse
operators whether to perform the shim check after the aircraft operated
for some time or within 1,200 FHs after the effective date of this AD.
The FAA updated paragraph (g)(3)(ii) of this AD to reference the
service information when performing the shim check rather than
paragraph (g)(1) of this AD.
Request To Update Credit for Previous Actions
ANA, DAL, FedEx, and JAL requested updates to paragraph (i), Credit
for Previous Actions, of this AD. ANA requested adding credit for the
repetitive shim checks of the HMU/MEC idler adapter inserts and
terminating action. DAL and FedEx requested credit for the terminating
action. JAL requested credit for the repetitive shim checks of the HMU/
MEC idler adapter inserts, retorque of the bolts that failed the shim
check, and the terminating action. The commenters reasoned that GE CF6-
80C2 SB 72-1577 R00, dated October 31, 2018 (GE CF6-80C2 SB 72-1577
R00), instructs the operator to perform the same tasks required by GE
CF6-80C2 SB 72-1577 R01. Therefore, credit should be allowed for
initial and repetitive shim checks of the HMU/MEC idler adapter inserts
and the terminating action.
The FAA agrees. The FAA reviewed GE CF6-80C2 SB 72-1577 R00, and
determined that the instructions are consistent with GE CF6-80C2 SB 72-
1577 R01. The FAA updated this AD to allow credit for the initial and
repetitive shim checks of the HMU/MEC idler adapter inserts, retorque
of the bolts that failed the shim check, and the terminating action, if
performed before the effective date of this AD using GE CF6-80C2 SB 72-
1577 R00.
Request for an Alternate Marking Area
ANA requested that the FAA approve an alternate marking area to
show compliance with performing the terminating action of this AD. ANA
stated that the marking areas indicated in GE CF6-80C2 SB 72-1577 R01,
are difficult to access because many components are installed to AGB
assembly.
The FAA disagrees with approving an alternate marking area. The
manufacturer provided two possible marking areas in GE CF6-80C2 SB 72-
1577 R01, and confirmed the suitability of the areas.
Request To Not Mandate the Marking Requirement
DAL requested that the FAA not mandate the provision in GE CF6-80C2
SB 72-1577 R01 to mark the HMU/MEC idler adapter to show compliance
with the terminating actions of this AD. DAL reasoned that the NPRM did
not propose to apply to all engines and therefore should not be
required.
The FAA disagrees. Marking the HMU/MEC idler adapter identifies if
the terminating action of this AD has been completed. As noted in a
previous comment response, the FAA revised the applicability of this AD
to limit applicability to affected engines with certain HMU/MEC idler
adapter P/Ns installed. Operators who determine that their engines are
not applicable to this AD do not need to perform the terminating action
or mark the HMU/MEC idler adapter.
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. None of the changes will increase the economic burden on any
operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed GE CF6-80C2 SB 72-1577 R01, dated August 16, 2019.
The SB describes procedures for performing shim checks of the HMU/MEC
idler adapter and for replacing the HMU/MEC idler adapter inserts. This
service information is reasonably available because the interested
parties have access to it through their normal
[[Page 11115]]
course of business or by the means identified in ADDRESSES.
Costs of Compliance
The FAA estimates that this AD affects 555 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
----------------------------------------------------------------------------------------------------------------
Shim check............................ 1 work-hour x $85 per $0 $85 $47,175
hour = $85.
Protrusion check/pull-out test........ 4 work-hours x $85 per 0 340 188,700
hour = $340.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary
replacements that are required based on the results of the shim check.
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 HMU/MEC idler adapter insert.......... 4 work-hours x $85 per hour = $50 $390
$340.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
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:
2021-03-02 General Electric Company: Amendment 39-21405; Docket No.
FAA-2020-0371; Project Identifier AD-2019-00124-E.
(a) Effective Date
This airworthiness directive (AD) is effective March 31, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric Company (GE) CF6-80C2A1,
CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-
80C2B1, CF6-80C2B1F, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-
80C2B4F, CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6-
80C2B7F, CF6-80C2B8F, and CF6-80C2D1F model turbofan engines that
underwent an engine shop visit before November 1, 2018, and with
accessory gearbox (AGB) adapter hydromechanical unit (HMU)/main
engine control (MEC) idler adapter with part number (P/N)
9395M78G01, P/N 9395M78G02, P/N 9395M78G04, P/N 9395M78G05, P/N
9395M78G08, or P/N 9395M78G10, installed.
(d) Subject
Joint Aircraft System Component (JASC) Code 7321, Fuel Control/
Turbine Engines.
(e) Unsafe Condition
This AD was prompted by failure of the HMU/MEC on the AGB
assembly. The FAA is issuing this AD to prevent failure of the HMU/
MEC. The unsafe condition, if not addressed, could result in engine
fire and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Perform a shim check of the HMU/MEC idler adapter inserts
using paragraph 3.B.(1) of GE CF6-80C2 Service Bulletin (SB) 72-1577
R01, dated August 16, 2019 (the SB), within 1,200 flight hours (FHs)
after the effective date of this AD.
(2) Thereafter, perform a repetitive shim check of the HMU/MEC
idler adapter inserts using paragraph 3.B.(1) of the SB within every
1,200 FHs since the last shim check.
(3) If any HMU/MEC idler adapter insert fails the shim check
required by paragraph (g)(1) or (2) of this AD, perform the
following before further flight:
(i) Retorque the bolts at each bolt location that failed the
shim check using paragraph 3.B.(1)(c) of the SB.
(ii) Perform the shim check again using paragraph 3.B.(1)(b) of
the SB. If the shim check fails, perform the terminating action
required by paragraph (h) of this AD.
[[Page 11116]]
(h) Terminating Action
As a terminating action to the requirements of paragraph (g) of
this AD, perform the following:
(1) Do a protrusion check at all eight bolt locations using
paragraph 3.C.(3) of the SB.
(2) Do a pull-out test at all eight bolt locations using
paragraph 3.C.(4) of the SB.
(3) If the inserts on the HMU/MEC idler adapter fail the
protrusion check or pull-out test required by paragraph (h)(1) or
(2) of this AD, replace the inserts using paragraph 3.C.(5) of the
SB. After replacement of the inserts is accomplished, the
requirements of this AD have been met and no further action is
required.
(4) If the inserts on the HMU/MEC idler adapter pass both the
protrusion check and the pull-out test required by paragraphs (h)(1)
and (2) of this AD, the requirements of this AD have been met and no
further action is required.
(i) Credit for Previous Actions
(1) You may take credit for any shim check of the HMU/MEC idler
adapter required by paragraph (g) of this AD if you performed this
shim check before the effective date of this AD using GE CF6-80C2 SB
72-1577 R00, dated October 31, 2018.
(2) You may take credit for the terminating action required by
paragraph (h) of this AD if you performed this action before the
effective date of this AD using GE CF6-80C2 SB 72-1577 R00, dated
October 31, 2018.
(j) Definition
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 case flanges, except
separation of engine flanges solely for the purposes of
transportation of the engine without subsequent maintenance, which
does not constitute an engine shop visit.
(k) 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.
(l) Related Information
For more information about this AD, contact Kevin M. Clark,
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: (781) 238-7088; fax: (781) 238-7199;
email: [email protected].
(m) 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) CF6-80C2 Service Bulletin 72-
1577 R01, dated August 16, 2019.
(ii) [Reserved]
(3) For GE service information identified in this AD, contact
General Electric Company, 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 January 21, 2021.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021-03606 Filed 2-23-21; 8:45 am]
BILLING CODE 4910-13-P
