Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 45066-45069 [2020-16166]
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Federal Register / Vol. 85, No. 144 / Monday, July 27, 2020 / Rules and Regulations
BILLING CODE 4910–13–C
(2) [Reserved]
(h) Installation Prohibition
(1) Do not install any part with a P/N listed
in Tables 2 through 5 to paragraph (g) of this
AD on any engine after that engine has been
modified as required by paragraph (g)(1) of
this AD.
(2) After the effective date of this AD, do
not install a part with a P/N listed in Tables
2 through 5 of this AD on any engine
manufactured on or after September 1, 2017.
(i) Definition
For the purpose of this AD, an engine shop
visit is when the engine is overhauled or
rebuilt, or the PT is disassembled.
(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 ECO Branch, send it to
the attention of the person identified in
paragraph (k)(1) of this AD. 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.
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(k) Related Information
(1) For more information about this AD,
contact Barbara Caufield, Aerospace
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: 781–
238–7146; fax: 781–238–7199; email:
barbara.caufield@faa.gov.
(2) Refer to European Union Aviation
Safety Agency (EASA) AD 2017–0151R1,
dated December 5, 2018, for more
information. You may examine the EASA AD
in the AD docket on the internet at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2017–0967.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) GE Aviation Alert Service Bulletin
ASB–M601E–72–00–00–0070[03], ASB–
M601D–72–00–00–0053[03], ASB–M601F–
72–00–00–0036[03], ASB–M601T–72–00–
00–0029[03], ASB–M601Z–72–00–00–
0039[03], ASB–H75–72–00–00–0011[03],
ASB–H80–72–00–00–0025[03], and ASB–
H85–72–00–00–0007[03] (single document;
formatted as service bulletin
identifier[revision number]), dated July 24,
2018.
(ii) [Reserved]
(3) For GE Aviation Czech service
information identified in this AD, contact GE
Aviation Czech s.r.o., Beranovy´ch 65, 199 02
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Praha 9—Letnˇany, Czech Republic; phone:
+420 222 538 111; fax: +420 222 538 222.
(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.
Airbus Helicopters, 2701 N Forum
Drive, Grand Prairie, TX 75052;
telephone 972–641–0000 or 800–232–
0323; fax 972–641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html. You may view
this referenced service information at
the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2017–1123.
Issued on July 10, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
Examining the AD Docket
[FR Doc. 2020–16122 Filed 7–24–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–1123; Product
Identifier 2017–SW–013–AD; Amendment
39–21176; AD 2020–15–13]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2017–02–
07 for Airbus Helicopters Deutschland
GmbH (Airbus Helicopters) Model
MBB–BK 117 C–2 and Model MBB–BK
117 D–2 helicopters. AD 2017–02–07
required a repetitive inspection and a
one-time torque of each hydraulic
module plate assembly attachment point
(attachment point). This new AD retains
the initial inspection and torque
requirements of AD 2017–02–07 and
requires replacing the attachment point
hardware. This AD was prompted by a
terminating action has been developed
to address the unsafe condition. The
actions of this AD are intended to
address an unsafe condition on these
products.
SUMMARY:
This AD is effective August 31,
2020.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 31, 2020.
ADDRESSES: For service information
identified in this final rule, contact
DATES:
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You may examine the AD docket on
the internet at https://
www.regulations.gov in Docket No.
FAA–2017–1123; 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
AD, the European Aviation Safety
Agency (now European Union Aviation
Safety Agency) (EASA) AD, any service
information that is incorporated by
reference, any comments received, and
other information. The street 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: Matt
Fuller, AD Program Manager, Continued
Operational Safety Branch,
Airworthiness Products Section,
General Aviation and Rotorcraft Unit,
FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone 817–222–
5110; email matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 to supersede
AD 2017–02–07, Amendment 39–18786
(82 FR 10267, February 10, 2017) (‘‘AD
2017–02–07’’). AD 2017–02–07 applied
to Airbus Helicopters Model MBB–BK
117 C–2 helicopters, serial numbers up
to and including 9750, and Model
MBB–BK 117 D–2 helicopters, serial
numbers up to and including 20110,
with a hydraulic module plate assembly
part number B291M0003103 with a
single locking attachment point
installed. The SNPRM published in the
Federal Register on February 27, 2020
(85 FR 11315). The FAA preceded the
SNPRM with a notice of proposed
rulemaking (NPRM) that published in
the Federal Register on December 5,
2017 (82 FR 57390). The NPRM
proposed to retain the initial inspection
and torque requirements of AD 2017–
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Federal Register / Vol. 85, No. 144 / Monday, July 27, 2020 / Rules and Regulations
02–07 and require replacing each single
locking attachment point mechanism
with a double locking attachment point
mechanism. The SNPRM proposed to
add a requirement to reposition the aft
grounding straps and inspect the
clamping effect of the aft attachment
points when the double locking
attachment hardware is installed, and
for helicopters that have previously
installed the double locking attachment
hardware, the SNPRM proposed to add
an alternative clamp effect inspection
requirement. The SNPRM also corrected
the torque application requirement
proposed in the NPRM to just each
forward (not aft) attachment point.
The NPRM was prompted by EASA
AD No. 2017–0047, dated March 13,
2017, issued by EASA, which is the
Technical Agent for the Member States
of the European Union, to correct an
unsafe condition on Airbus Helicopters
Deutschland GmbH (formerly
Eurocopter Deutschland GmbH) Model
MBB–BK117 C–2, MBB–BK117 C–2e,
MBB–BK117 D–2 and MBB–BK117 D–
2m helicopters. EASA advises that the
hydraulic plate assembly on certain
MBB–BK117 models has four
attachment points on the fuselage
secured by a single locking mechanism.
According to EASA, a design
reassessment revealed stiffness of the
hydraulic plate may be insufficient to
withstand the in-service loads in the
event one of the four single locking
attachment points fails. The EASA AD
requires a repetitive inspection and onetime torque tightening of the attachment
points until replacement of the single
locking attachment hardware with
double locking attachment hardware.
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA has considered
the comment received. One commenter
commented in support of the SNPRM.
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FAA’s Determination
The FAA has reviewed the relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
Differences Between this AD and the
EASA AD
The EASA AD specifies performing
the visual inspection of each attachment
point at intervals not exceeding 400
flight hours. This AD does not require
a repetitive inspection. This AD requires
the replacement of each single locking
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attachment point mechanism with a
double locking attachment point
mechanism within 300 hours TIS
instead, which makes subsequent
inspections unnecessary. Since EASA
has not revised or superseded its AD to
incorporate Revision 3 of the service
information, the EASA AD does not
require inspecting the clamping effect of
the aft joints, torque tightening the bolts,
and corrective action if necessary for
helicopters with a hydraulic module
plate assembly with double locking
attachment hardware installed in
accordance with Airbus Helicopters
Alert Service Bulletin (ASB) No. ASB
MBB–BK117 C–2–29A–003 or ASB No.
ASB MBB–BK117 D–2–29A–001, both
Revision 2 and dated February 1, 2017.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters
ASB No. ASB MBB–BK117 C–2–29A–
003 for Model MBB–BK 117 C–2
helicopters and ASB No. ASB MBB–
BK117 D–2–29A–001 for Model MBB–
BK 117 D–2 helicopters, both Revision
3 and dated December 19, 2017. Until
the attachment points are modified with
double locking attachment mechanisms,
this service information specifies a
repetitive visual inspection for
condition and correct installation of the
attachment points and replacing the
affected parts if there is a crack. This
service information also specifies a
tightening torque check of the forward
attachment points after the initial
inspection and replacing the affected
parts if torque cannot be applied. This
service information specifies procedures
to replace the single locking attachment
hardware with double locking
attachment hardware.
For certain helicopters with a
hydraulic module plate assembly with
the double locking attachment hardware
installed, this revision of the service
information contains procedures to
inspect the clamping effect of the aft
attachment points and torque tightening
the screw joints (bolts). If a bolt can be
turned while applying this torque, the
service information specifies
instructions to replace the split pin,
washer, and self-locking castellated nut,
check the bolt for wear and replace it if
necessary, change the position of the aft
grounding strap, check the electrical
bonding, and apply PU-Lacquer to the
grounding connection.
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 the ADDRESSES section.
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45067
Other Related Service Information
The FAA also reviewed Airbus
Helicopters ASB No. ASB MBB–BK117
C–2–29A–003 for Model MBB–BK 117
C–2 helicopters and ASB No. ASB
MBB–BK117 D–2–29A–001 for Model
MBB–BK 117 D–2 helicopters, both
Revision 1 and dated October 14, 2016,
and both Revision 2 and dated February
1, 2017. Revisions 1 and 2 of this service
information contain the same visual
inspection and torque tightening check
procedures as Revision 3. Revision 2 of
this service information adds the
procedures to replace the single locking
attachment hardware with double
locking attachment hardware and
contains the same forward locking
attachment hardware replacement
procedures as Revision 3.
Costs of Compliance
The FAA estimates that this AD
affects 167 helicopters of U.S. Registry.
The FAA estimates that operators may
incur the following costs in order to
comply with this AD. The FAA
estimates the cost of labor at $85 per
work-hour.
Visually inspecting the four
attachment points takes about 0.75
work-hour for an estimated cost of $64
per helicopter and $10,688 for the U.S.
fleet. Inspecting the torque of the
attachment points takes about 0.25
work-hour for an estimated cost of $21
per helicopter and $3,507 for the U.S.
fleet. Replacing any of the attachment
point parts takes a minimal amount of
time and parts cost about $48 per
attachment point. Installing four double
locking attachment point mechanisms
takes a minimal amount of time and
parts cost about $400 per helicopter and
$66,800 for the U.S. fleet.
For certain double locking attachment
hardware aft joints, inspecting the
clamping effect and applying torque
takes about 1 work-hour for an
estimated cost of $85 per helicopter. If
required, inspecting and replacing parts,
repositioning the aft grounding strap,
inspecting the electrical bonding, and
applying lacquer to the grounding
connection takes about 0.5 work-hour
and parts cost about $15 for an
estimated cost of $58 per helicopter.
According to Airbus Helicopters’
service information, some of the costs of
this AD may be covered under warranty,
thereby reducing the cost impact on
affected individuals. The FAA does not
control warranty coverage by Airbus
Helicopters. Accordingly, the FAA has
included all costs in this cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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Federal Register / Vol. 85, No. 144 / Monday, July 27, 2020 / Rules and Regulations
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
The FAA has determined that 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.
Adoption of 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:
■
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2017–02–07, Amendment 39–18786 (82
FR 10267, February 10, 2017), and
adding the following new AD:
■
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2020–15–13 Airbus Helicopters
Deutschland GmbH: Amendment 39–
21176; Docket No. FAA–2017–1123;
Product Identifier 2017–SW–013–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Deutschland GmbH Model MBB–BK 117 C–
2 helicopters, serial numbers up to and
including 9750, and Airbus Helicopters
Deutschland GmbH Model MBB–BK 117 D–
2 helicopters, serial numbers up to and
including 20110, certificated in any category,
with a hydraulic module plate assembly part
number B291M0003103 with a single locking
attachment point installed or with a double
locking attachment point installed before the
effective date of this AD in accordance with
Airbus Helicopters Alert Service Bulletin
(ASB) No. ASB MBB–BK117 C–2–29A–003
(ASB MBB–BK117 C–2–29A–003 Rev 2) or
ASB No. ASB MBB–BK117 D–2–29A–001
(ASB MBB–BK117 D–2–29A–001 Rev 2),
both Revision 2 and dated February 1, 2017,
as applicable to your model helicopter.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of a hydraulic module plate assembly
attachment point (attachment point). This
condition could result in loss of the
hydraulic module plate and subsequent loss
of control of the helicopter.
(c) Affected ADs
This AD replaces AD 2017–02–07,
Amendment 39–18786 (82 FR 10267,
February 10, 2017).
(d) Effective Date
This AD becomes effective August 31,
2020.
(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
Comply with either paragraphs (f)(1) and
(2) of this AD, or paragraph (f)(3) of this AD,
as applicable to your helicopter.
(1) For helicopters with a hydraulic
module plate assembly with a single locking
attachment hardware installed, within 100
hours time-in-service (TIS):
(i) Visually inspect the split pins,
castellated nuts, plugs, nuts, and hexagon
bolts of each attachment point for a crack and
for proper installation by following the
Accomplishment Instructions, paragraphs
3.B.1.3.a. through 3.B.1.3.d., of Airbus
Helicopters ASB No. ASB MBB–BK117 C–2–
29A–003 (ASB MBB–BK117 C–2–29A–003
Rev 3) or Airbus Helicopters ASB No. ASB
MBB–BK117 D–2–29A–001 (ASB MBB–
BK117 D–2–29A–001 Rev 3), both Revision 3
and dated December 19, 2017, as applicable
to your model helicopter. Replace any part
that has a crack before further flight. If the
split pins, castellated nuts, or hexagon bolts
are not as depicted in Figures 1 and 2 of ASB
MBB–BK117 C–2–29A–003 Rev 3 or ASB
MBB–BK117 D–2–29A–001 Rev 3, before
further flight, properly install them.
(ii) Apply a torque of 9 to 10 Nm to the
left-hand (LH) and right-hand (RH) nuts of
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each forward attachment point. If a torque of
9 to 10 Nm cannot be applied, replace the
affected nut before further flight.
(2) For helicopters with a hydraulic
module plate assembly with a single locking
attachment hardware installed, within 300
hours TIS:
(i) Replace each forward single locking
attachment hardware with double locking
attachment hardware by following the
Accomplishment Instructions, paragraphs
3.B.3.3. through 3.B.3.6. on page 11 of ASB
MBB–BK117 C–2–29A–003 Rev 3 or ASB
MBB–BK117 D–2–29A–001 Rev 3, as
applicable to your model helicopter, except
you are not required to discard old parts.
(ii) Replace each aft single locking
attachment hardware with double locking
attachment hardware and reposition the LH
and RH aft grounding straps by following the
Accomplishment Instructions, paragraphs
3.B.3.1. through 3.B.3.7. on page 13 of ASB
MBB–BK117 C–2–29A–003 Rev 3 or ASB
MBB–BK117 D–2–29A–001 Rev 3, as
applicable to your model helicopter, except
you are not required to discard old parts.
(3) If you have replaced the attachment
hardware with double locking attachment
hardware before the effective date of this AD
in accordance with ASB MBB–BK117 C–2–
29A–003 Rev 2 or ASB MBB–BK117 D–2–
29A–001 Rev 2, as applicable to your model
helicopter: Within 300 hours TIS, inspect the
clamping effect of the LH and RH aft screw
joints (bolts) of the hydraulic module plate
by following the Accomplishment
Instructions, paragraph 3.B.5., of ASB MBB–
BK117 C–2–29A–003 Rev 3 or ASB MBB–
BK117 D–2–29A–001 Rev 3, as applicable to
your model helicopter, except you are not
required to discard old parts.
Note 1 to paragraph (f)(3) of this AD:
Airbus Helicopters refers to bolts as ‘‘screw
joints.’’
(g) Credit for Previous Actions
Actions accomplished before the effective
date of this AD in accordance with the
procedures specified in the following are
considered acceptable for compliance with
the corresponding actions in paragraph (f)(1)
of this AD:
(1) AD 2017–02–07, Amendment 39–18786
(82 FR 10267, February 10, 2017).
(2) Airbus Helicopters ASB No. ASB MBB–
BK117 C–2–29A–003, Revision 1, dated
October 14, 2016.
(3) Airbus Helicopters ASB No. ASB MBB–
BK117 C–2–29A–003, Revision 2, dated
February 1, 2017.
(4) Airbus Helicopters ASB No. ASB MBB–
BK117 D–2–29A–001, Revision 1, dated
October 14, 2016.
(5) Airbus Helicopters ASB No. ASB MBB–
BK117 D–2–29A–001, Revision 2, dated
February 1, 2017.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Fuller, AD
Program Manager, Continued Operational
Safety Branch, Airworthiness Products
Section, General Aviation and Rotorcraft
Unit, FAA, 10101 Hillwood Pkwy., Fort
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Worth, TX 76177; telephone 817–222–5110;
email 9-ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(i) Additional Information
(1) Airbus Helicopters ASB No. ASB MBB–
BK117 C–2–29A–003 and ASB No. ASB
MBB–BK117 D–2–29A–001, both Revision 1
and dated October 14, 2016, and both
Revision 2 and dated February 1, 2017,
which are not incorporated by reference,
contain additional information about the
subject of this AD. For service information
identified in this AD, contact Airbus
Helicopters, 2701 N Forum Drive, Grand
Prairie, TX 75052; telephone 972–641–0000
or 800–232–0323; fax 972–641–3775; or at
https://www.airbus.com/helicopters/services/
technical-support.html. You may view a copy
of the service information at the FAA, Office
of the Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321, Fort
Worth, TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (now
European Union Aviation Safety Agency) AD
No. 2017–0047, dated March 13, 2017. You
may view the EASA AD on the internet at
https://www.regulations.gov in Docket No.
FAA–2017–1123.
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(j) Subject
Joint Aircraft Service Component (JASC)
Code: 2900, Hydraulic Power System.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Alert Service
Bulletin (ASB) No. ASB MBB–BK117 C–2–
29A–003, Revision 3, dated December 19,
2017.
(ii) Airbus Helicopters ASB No. ASB MBB–
BK117 D–2–29A–001, Revision 3, dated
December 19, 2017.
(3) For Airbus Helicopters service
information identified in this AD, contact
Airbus Helicopters, 2701 N Forum Drive,
Grand Prairie, TX 75052; telephone 972–641–
0000 or 800–232–0323; fax 972–641–3775; or
at https://www.airbus.com/helicopters/
services/technical-support.html.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call 817–222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
VerDate Sep<11>2014
16:16 Jul 24, 2020
Jkt 250001
email fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on July 15, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–16166 Filed 7–24–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–1021; Project
Identifier MCAI–2019–00120–E; Amendment
39–21166; AD 2020–15–03]
RIN 2120–AA64
Airworthiness Directives; GE Aviation
Czech s.r.o. Turboprop Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2016–07–
13 and AD 2018–03–22 which apply to
certain GE Aviation Czech s.r.o.
M601D–11, M601E–11, M601E–11A,
M601E–11AS, M601E–11S, and M601F
model turboprop engines. AD 2016–07–
13 required inspection of the engine
power turbine (PT) disk and, if found
damaged, its replacement with a part
eligible for installation. AD 2018–03–22
required the removal of certain engine
PT disks identified by part number (P/
N) installed on the affected engines.
This AD requires an inspection of the
engine PT disk and, if found damaged,
its replacement with a part eligible for
installation. This AD also requires the
removal of certain engine PT disks
identified by P/N installed on the
affected engines. This AD was prompted
by the discovery of damage to certain
engine PT disks and a review by the
manufacturer that determined that
certain engine PT rotors have less
overspeed margin than originally
declared during product certification.
This AD was also prompted by the
manufacturer identifying additional P/
Ns and serial numbers (S/Ns) of engine
PT disks affected by damage or nonconformity since publishing AD 2016–
07–13 and AD 2018–03–22. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 31,
2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 31, 2020.
SUMMARY:
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
45069
For service information
identified in this final rule, contact GE
Aviation Czech s.r.o., Beranovy´ch 65,
199 02 Praha 9—Letnˇany, Czech
Republic; phone: +420 222 538 111; fax
+420 222 538 222; email: tp.ops@
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 on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
1021.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
1021; 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,
the mandatory continuing airworthiness
information (MCAI), 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, Aerospace 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:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016–07–13,
Amendment 39–18458 (81 FR 20222,
April 7, 2016) (‘‘AD 2016–07–13’’), and
AD 2018–03–22, Amendment 39–19195
(83 FR 6455, February 14, 2018) (‘‘AD
2018–03–22’’). AD 2016–07–13 and AD
2018–03–22 applied to certain GE
Aviation Czech s.r.o. M601D–11,
M601E–11, M601E–11A, M601E–11AS,
M601E–11S, and M601F model
turboprop engines. The NPRM
published in the Federal Register on
February 21, 2020 (85 FR 10099). The
NPRM was prompted by the discovery
of damage to certain engine PT disks
and a review by the manufacturer that
determined that certain engine PT rotors
have less overspeed margin than
originally declared during product
certification. The NPRM was also
prompted by the manufacturer
E:\FR\FM\27JYR1.SGM
27JYR1
]]>Agencies
[Federal Register Volume 85, Number 144 (Monday, July 27, 2020)]
[Rules and Regulations]
[Pages 45066-45069]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-16166]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1123; Product Identifier 2017-SW-013-AD; Amendment
39-21176; AD 2020-15-13]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2017-02-07
for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-
BK 117 C-2 and Model MBB-BK 117 D-2 helicopters. AD 2017-02-07 required
a repetitive inspection and a one-time torque of each hydraulic module
plate assembly attachment point (attachment point). This new AD retains
the initial inspection and torque requirements of AD 2017-02-07 and
requires replacing the attachment point hardware. This AD was prompted
by a terminating action has been developed to address the unsafe
condition. The actions of this AD are intended to address an unsafe
condition on these products.
DATES: This AD is effective August 31, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 31,
2020.
ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX
75052; telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at
https://www.airbus.com/helicopters/services/technical-support.html. You
may view this referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321,
Fort Worth, TX 76177. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1123.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2017-1123; 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 AD, the European Aviation
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD,
any service information that is incorporated by reference, any comments
received, and other information. The street 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: Matt Fuller, AD Program Manager,
Continued Operational Safety Branch, Airworthiness Products Section,
General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone 817-222-5110; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 to supersede AD 2017-02-07, Amendment 39-18786
(82 FR 10267, February 10, 2017) (``AD 2017-02-07''). AD 2017-02-07
applied to Airbus Helicopters Model MBB-BK 117 C-2 helicopters, serial
numbers up to and including 9750, and Model MBB-BK 117 D-2 helicopters,
serial numbers up to and including 20110, with a hydraulic module plate
assembly part number B291M0003103 with a single locking attachment
point installed. The SNPRM published in the Federal Register on
February 27, 2020 (85 FR 11315). The FAA preceded the SNPRM with a
notice of proposed rulemaking (NPRM) that published in the Federal
Register on December 5, 2017 (82 FR 57390). The NPRM proposed to retain
the initial inspection and torque requirements of AD 2017-
[[Page 45067]]
02-07 and require replacing each single locking attachment point
mechanism with a double locking attachment point mechanism. The SNPRM
proposed to add a requirement to reposition the aft grounding straps
and inspect the clamping effect of the aft attachment points when the
double locking attachment hardware is installed, and for helicopters
that have previously installed the double locking attachment hardware,
the SNPRM proposed to add an alternative clamp effect inspection
requirement. The SNPRM also corrected the torque application
requirement proposed in the NPRM to just each forward (not aft)
attachment point.
The NPRM was prompted by EASA AD No. 2017-0047, dated March 13,
2017, issued by EASA, which is the Technical Agent for the Member
States of the European Union, to correct an unsafe condition on Airbus
Helicopters Deutschland GmbH (formerly Eurocopter Deutschland GmbH)
Model MBB-BK117 C-2, MBB-BK117 C-2e, MBB-BK117 D-2 and MBB-BK117 D-2m
helicopters. EASA advises that the hydraulic plate assembly on certain
MBB-BK117 models has four attachment points on the fuselage secured by
a single locking mechanism. According to EASA, a design reassessment
revealed stiffness of the hydraulic plate may be insufficient to
withstand the in-service loads in the event one of the four single
locking attachment points fails. The EASA AD requires a repetitive
inspection and one-time torque tightening of the attachment points
until replacement of the single locking attachment hardware with double
locking attachment hardware.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA has considered the comment
received. One commenter commented in support of the SNPRM.
FAA's Determination
The FAA has reviewed the relevant information and determined that
an unsafe condition exists and is likely to exist or develop on other
helicopters of these same type designs and that air safety and the
public interest require adopting the AD requirements as proposed.
Differences Between this AD and the EASA AD
The EASA AD specifies performing the visual inspection of each
attachment point at intervals not exceeding 400 flight hours. This AD
does not require a repetitive inspection. This AD requires the
replacement of each single locking attachment point mechanism with a
double locking attachment point mechanism within 300 hours TIS instead,
which makes subsequent inspections unnecessary. Since EASA has not
revised or superseded its AD to incorporate Revision 3 of the service
information, the EASA AD does not require inspecting the clamping
effect of the aft joints, torque tightening the bolts, and corrective
action if necessary for helicopters with a hydraulic module plate
assembly with double locking attachment hardware installed in
accordance with Airbus Helicopters Alert Service Bulletin (ASB) No. ASB
MBB-BK117 C-2-29A-003 or ASB No. ASB MBB-BK117 D-2-29A-001, both
Revision 2 and dated February 1, 2017.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-
003 for Model MBB-BK 117 C-2 helicopters and ASB No. ASB MBB-BK117 D-2-
29A-001 for Model MBB-BK 117 D-2 helicopters, both Revision 3 and dated
December 19, 2017. Until the attachment points are modified with double
locking attachment mechanisms, this service information specifies a
repetitive visual inspection for condition and correct installation of
the attachment points and replacing the affected parts if there is a
crack. This service information also specifies a tightening torque
check of the forward attachment points after the initial inspection and
replacing the affected parts if torque cannot be applied. This service
information specifies procedures to replace the single locking
attachment hardware with double locking attachment hardware.
For certain helicopters with a hydraulic module plate assembly with
the double locking attachment hardware installed, this revision of the
service information contains procedures to inspect the clamping effect
of the aft attachment points and torque tightening the screw joints
(bolts). If a bolt can be turned while applying this torque, the
service information specifies instructions to replace the split pin,
washer, and self-locking castellated nut, check the bolt for wear and
replace it if necessary, change the position of the aft grounding
strap, check the electrical bonding, and apply PU-Lacquer to the
grounding connection.
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 the ADDRESSES section.
Other Related Service Information
The FAA also reviewed Airbus Helicopters ASB No. ASB MBB-BK117 C-2-
29A-003 for Model MBB-BK 117 C-2 helicopters and ASB No. ASB MBB-BK117
D-2-29A-001 for Model MBB-BK 117 D-2 helicopters, both Revision 1 and
dated October 14, 2016, and both Revision 2 and dated February 1, 2017.
Revisions 1 and 2 of this service information contain the same visual
inspection and torque tightening check procedures as Revision 3.
Revision 2 of this service information adds the procedures to replace
the single locking attachment hardware with double locking attachment
hardware and contains the same forward locking attachment hardware
replacement procedures as Revision 3.
Costs of Compliance
The FAA estimates that this AD affects 167 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. The FAA estimates the cost of
labor at $85 per work-hour.
Visually inspecting the four attachment points takes about 0.75
work-hour for an estimated cost of $64 per helicopter and $10,688 for
the U.S. fleet. Inspecting the torque of the attachment points takes
about 0.25 work-hour for an estimated cost of $21 per helicopter and
$3,507 for the U.S. fleet. Replacing any of the attachment point parts
takes a minimal amount of time and parts cost about $48 per attachment
point. Installing four double locking attachment point mechanisms takes
a minimal amount of time and parts cost about $400 per helicopter and
$66,800 for the U.S. fleet.
For certain double locking attachment hardware aft joints,
inspecting the clamping effect and applying torque takes about 1 work-
hour for an estimated cost of $85 per helicopter. If required,
inspecting and replacing parts, repositioning the aft grounding strap,
inspecting the electrical bonding, and applying lacquer to the
grounding connection takes about 0.5 work-hour and parts cost about $15
for an estimated cost of $58 per helicopter.
According to Airbus Helicopters' service information, some of the
costs of this AD may be covered under warranty, thereby reducing the
cost impact on affected individuals. The FAA does not control warranty
coverage by Airbus Helicopters. Accordingly, the FAA has included all
costs in this cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue
[[Page 45068]]
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
The FAA has determined that 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.
Adoption of 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 removing Airworthiness Directive (AD)
2017-02-07, Amendment 39-18786 (82 FR 10267, February 10, 2017), and
adding the following new AD:
2020-15-13 Airbus Helicopters Deutschland GmbH: Amendment 39-21176;
Docket No. FAA-2017-1123; Product Identifier 2017-SW-013-AD.
(a) Applicability
This AD applies to Airbus Helicopters Deutschland GmbH Model
MBB-BK 117 C-2 helicopters, serial numbers up to and including 9750,
and Airbus Helicopters Deutschland GmbH Model MBB-BK 117 D-2
helicopters, serial numbers up to and including 20110, certificated
in any category, with a hydraulic module plate assembly part number
B291M0003103 with a single locking attachment point installed or
with a double locking attachment point installed before the
effective date of this AD in accordance with Airbus Helicopters
Alert Service Bulletin (ASB) No. ASB MBB-BK117 C-2-29A-003 (ASB MBB-
BK117 C-2-29A-003 Rev 2) or ASB No. ASB MBB-BK117 D-2-29A-001 (ASB
MBB-BK117 D-2-29A-001 Rev 2), both Revision 2 and dated February 1,
2017, as applicable to your model helicopter.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of a hydraulic
module plate assembly attachment point (attachment point). This
condition could result in loss of the hydraulic module plate and
subsequent loss of control of the helicopter.
(c) Affected ADs
This AD replaces AD 2017-02-07, Amendment 39-18786 (82 FR 10267,
February 10, 2017).
(d) Effective Date
This AD becomes effective August 31, 2020.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
Comply with either paragraphs (f)(1) and (2) of this AD, or
paragraph (f)(3) of this AD, as applicable to your helicopter.
(1) For helicopters with a hydraulic module plate assembly with
a single locking attachment hardware installed, within 100 hours
time-in-service (TIS):
(i) Visually inspect the split pins, castellated nuts, plugs,
nuts, and hexagon bolts of each attachment point for a crack and for
proper installation by following the Accomplishment Instructions,
paragraphs 3.B.1.3.a. through 3.B.1.3.d., of Airbus Helicopters ASB
No. ASB MBB-BK117 C-2-29A-003 (ASB MBB-BK117 C-2-29A-003 Rev 3) or
Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001 (ASB MBB-BK117
D-2-29A-001 Rev 3), both Revision 3 and dated December 19, 2017, as
applicable to your model helicopter. Replace any part that has a
crack before further flight. If the split pins, castellated nuts, or
hexagon bolts are not as depicted in Figures 1 and 2 of ASB MBB-
BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, before
further flight, properly install them.
(ii) Apply a torque of 9 to 10 Nm to the left-hand (LH) and
right-hand (RH) nuts of each forward attachment point. If a torque
of 9 to 10 Nm cannot be applied, replace the affected nut before
further flight.
(2) For helicopters with a hydraulic module plate assembly with
a single locking attachment hardware installed, within 300 hours
TIS:
(i) Replace each forward single locking attachment hardware with
double locking attachment hardware by following the Accomplishment
Instructions, paragraphs 3.B.3.3. through 3.B.3.6. on page 11 of ASB
MBB-BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as
applicable to your model helicopter, except you are not required to
discard old parts.
(ii) Replace each aft single locking attachment hardware with
double locking attachment hardware and reposition the LH and RH aft
grounding straps by following the Accomplishment Instructions,
paragraphs 3.B.3.1. through 3.B.3.7. on page 13 of ASB MBB-BK117 C-
2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to
your model helicopter, except you are not required to discard old
parts.
(3) If you have replaced the attachment hardware with double
locking attachment hardware before the effective date of this AD in
accordance with ASB MBB-BK117 C-2-29A-003 Rev 2 or ASB MBB-BK117 D-
2-29A-001 Rev 2, as applicable to your model helicopter: Within 300
hours TIS, inspect the clamping effect of the LH and RH aft screw
joints (bolts) of the hydraulic module plate by following the
Accomplishment Instructions, paragraph 3.B.5., of ASB MBB-BK117 C-2-
29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to
your model helicopter, except you are not required to discard old
parts.
Note 1 to paragraph (f)(3) of this AD: Airbus Helicopters
refers to bolts as ``screw joints.''
(g) Credit for Previous Actions
Actions accomplished before the effective date of this AD in
accordance with the procedures specified in the following are
considered acceptable for compliance with the corresponding actions
in paragraph (f)(1) of this AD:
(1) AD 2017-02-07, Amendment 39-18786 (82 FR 10267, February 10,
2017).
(2) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003,
Revision 1, dated October 14, 2016.
(3) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003,
Revision 2, dated February 1, 2017.
(4) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001,
Revision 1, dated October 14, 2016.
(5) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001,
Revision 2, dated February 1, 2017.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Standards Branch, FAA, may approve
AMOCs for this AD. Send your proposal to: Matt Fuller, AD Program
Manager, Continued Operational Safety Branch, Airworthiness Products
Section, General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood
Pkwy., Fort
[[Page 45069]]
Worth, TX 76177; telephone 817-222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or lacking a principal
inspector, the manager of the local flight standards district office
or certificate holding district office, before operating any
aircraft complying with this AD through an AMOC.
(i) Additional Information
(1) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003 and ASB
No. ASB MBB-BK117 D-2-29A-001, both Revision 1 and dated October 14,
2016, and both Revision 2 and dated February 1, 2017, which are not
incorporated by reference, contain additional information about the
subject of this AD. For service information identified in this AD,
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX
75052; telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or
at https://www.airbus.com/helicopters/services/technical-support.html. You may view a copy of the service information at the
FAA, Office of the Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (now European Union Aviation Safety Agency) AD No.
2017-0047, dated March 13, 2017. You may view the EASA AD on the
internet at https://www.regulations.gov in Docket No. FAA-2017-1123.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 2900, Hydraulic
Power System.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Alert Service Bulletin (ASB) No. ASB MBB-
BK117 C-2-29A-003, Revision 3, dated December 19, 2017.
(ii) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001,
Revision 3, dated December 19, 2017.
(3) For Airbus Helicopters service information identified in
this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand
Prairie, TX 75052; telephone 972-641-0000 or 800-232-0323; fax 972-
641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call 817-222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on July 15, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-16166 Filed 7-24-20; 8:45 am]
BILLING CODE 4910-13-P
