[Federal Register Volume 85, Number 111 (Tuesday, June 9, 2020)]
[Rules and Regulations]
[Pages 35177-35181]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-12379]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0099; Product Identifier 2019-NM-169-AD; Amendment
39-19917; AD 2020-11-13]
RIN 2120-AA64
July 14, 2020 Airworthiness Directives; De Havilland Aircraft of
Canada Limited (Type Certificate Previously Held by Bombardier, Inc.)
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2010-23-
04, which applied to all De Havilland Aircraft of Canada Limited Model
DHC-8-400 series airplanes. AD 2010-23-04 required repetitive detailed
inspections of the nacelle attachment fittings for cracks, a
conductivity inspection of the nacelle attachment fittings, and
replacement if necessary. This AD continues to require these
inspections and replacement if necessary, removes a certain inspection
requirement for certain airplanes, and adds a new requirement to
replace the rear spar fitting and nacelle attaching structure with a
new nacelle attachment fitting. This AD was prompted by a determination
that it is necessary to do a replacement with new nacelle attachment
fittings. The FAA is issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective July 14, 2020.
The Director of the Federal Register approved the incorporation by
reference
[[Page 35178]]
of certain publications listed in this AD as of July 14, 2020.
ADDRESSES: For service information identified in this final rule,
contact De Havilland Aircraft of Canada Limited, Q-Series Technical
Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada;
telephone 416-375-4000; fax 416-375-4539; email [email protected];
internet https://dehavilland.com. You may view this referenced service
information 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 on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0099.
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-
0099; 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: Andrea Jimenez, Aerospace Engineer,
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7330; fax 516-
794-5531; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2010-30R2, dated July
30, 2019, (also referred to as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for all
De Havilland Aircraft of Canada Limited (Type Certificate previously
held by Bombardier, Inc.) Model DHC-8-400, -401, and -402 airplanes.
You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0099.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2010-23-04, Amendment 39-16493 (75 FR
68174, November 5, 2010) (``AD 2010-23-04''). AD 2010-23-04 applied to
all De Havilland Aircraft of Canada Limited Model DHC-8-400 series
airplanes. The NPRM published in the Federal Register on March 12, 2020
(85 FR 14423). The NPRM was prompted by reports of cracked nacelle
attachment fittings, which a preliminary investigation determined to be
caused by stress corrosion, and a determination that it is necessary to
install new nacelle attachment fittings in order to address the unsafe
condition. The NPRM proposed to continue to require repetitive detailed
inspections of the nacelle attachment fittings for cracks, a
conductivity inspection of the nacelle attachment fittings, and
replacement if necessary. The NPRM also proposed to remove a certain
inspection requirement for certain airplanes, and add a new requirement
to replace the rear spar fitting and nacelle attaching structure with a
new nacelle attachment fitting. The FAA is issuing this AD to address
reports of cracked nacelle attachment fittings, which, if not detected
and corrected, could compromise the structural integrity of the nacelle
attachment fitting and possibly result in collapse of the landing gear.
See the MCAI for additional background information.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the NPRM or
on the determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
except for minor editorial changes. The FAA has determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Bombardier, Inc. has issued Service Bulletin 84-54-14, Revision K,
dated August 7, 2018. This service bulletin describes procedures for a
conductivity inspection of the nacelle attachment fittings, repetitive
detailed inspections of the nacelle attachment fittings for cracks, and
replacement of the fitting.
Bombardier, Inc. has also issued Service Bulletin 84-54-16,
Revision D, dated August 7, 2018. This service information describes
procedures for replacing the rear spar nacelle attachment fitting and
associated structure with a new nacelle attachment fitting, part number
(P/N) 8Z9305. The replacement includes applicable related investigative
and corrective actions. The related investigative actions include an
inspection of the internal bore and external surface of the main
landing gear yoke pins, the drag strut pins, and the stabilizer brace
pins for signs of corrosion and damage; and an inspection of the inner
bore and outer surface of the coat hangar pins for signs of corrosion
and damage. The corrective actions include repair, rework, or
replacement.
Bombardier, Inc. has also issued Modification Summary Package
IS4Q5400012, Revision B, dated July 11, 2012. This service information
describes procedures for applying a fay sealant gasket to the rear spar
access fitting access panel.
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.
Costs of Compliance
The FAA estimates that this AD affects 54 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Retained actions from AD 2010-23- 3 work-hours x $85 $0................ $255.............. $13,770.
04. per hour = $255.
New actions..................... 320 work-hours x Up to $104,739.... Up to $131,939.... Up to $7,124,706.
$85 per hour =
$27,200.
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[[Page 35179]]
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
The FAA 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)
2010-23-04, Amendment 39-16493 (75 FR 68174, November 5, 2010), and
adding the following new AD:
2020-11-13 De Havilland Aircraft of Canada Limited (Type Certificate
previously held by Bombardier, Inc.): Amendment 39-19917; Docket No.
FAA-2020-0099; Product Identifier 2019-NM-169-AD.
(a) Effective Date
This AD is effective July 14, 2020.
(b) Affected ADs
This AD replaces AD 2010-23-04, Amendment 39-16493 (75 FR 68174,
November 5, 2010) (``AD 2010-23-04'').
(c) Applicability
This AD applies to De Havilland Aircraft of Canada Limited (Type
Certificate previously held by Bombardier, Inc.) Model DHC-8-400, -
401, and -402 airplanes, certificated in any category, serial
numbers 4001 and subsequent.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.
(e) Reason
This AD was prompted by reports of cracked nacelle attachment
fittings, which a preliminary investigation determined to be caused
by stress corrosion. The FAA is issuing this AD to address this
condition, which, if not detected and corrected, could compromise
the structural integrity of the nacelle attachment fitting and
possibly result in collapse of the landing gear.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Detailed and Conductivity Inspections and Replacement,
With Revised Service Information and Revised Replacement Instructions
This paragraph restates the requirements of paragraph (g) of AD
2010-23-04, with revised service information and revised replacement
instructions. For airplanes having serial numbers 4001 through 4304
inclusive, 4314, and 4315: Within 100 flight hours after November
22, 2010 (the effective date of AD 2010-23-04), do a detailed
inspection for cracking, and a conductivity inspection on each of
the 4 nacelle attachment fittings, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14,
Revision K, dated August 7, 2018. Repeat the detailed inspection at
intervals not to exceed 300 flight hours, except as provided by
paragraph (i) of this AD. Accomplishing the replacement specified in
paragraph (g)(1)(ii) or (g)(2)(ii)(B) of this AD terminates the
inspections required by this paragraph.
(1) If any nacelle attachment fitting is found cracked, before
further flight, do the action specified in paragraph (g)(1)(i) or
(ii) of this AD. As of the effective date of this AD, only the
action specified in paragraph (g)(1)(ii) of this AD may be done.
(i) Replace the fitting with a new fitting in accordance with
paragraph (2) of Part A of the Accomplishment Instructions of
Bombardier Service Bulletin 84-54-14, Revision K, dated August 7,
2018.
(ii) Replace the rear spar nacelle attachment fitting and
associated structure with a new nacelle attachment fitting, part
number (P/N) 8Z9305, and do all applicable related investigative and
corrective actions, in accordance with Part B of the Accomplishment
Instructions of Bombardier Service Bulletin 84-54-16 Revision D,
dated August 7, 2018. Do all applicable related investigative and
corrective actions before further flight.
(2) If the conductivity of any test points on any fitting is
found to be greater than 45.0 percent International Annealed Copper
Standard (IACS) or if the conductivity of any test points on any
fitting is found to be less than 38.0 percent IACS, do the actions
required by paragraphs (g)(2)(i) and (ii) of this AD.
(i) Within 24 hours after accomplishing the conductivity
inspection specified in paragraph (g) of this AD, do a detailed
inspection of the nacelle attachment fitting for cracking, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 84-54-14, Revision K, dated August 7, 2018, and
repeat thereafter at intervals not to exceed 24 hours. If cracking
is found, before further flight, replace the fitting with a new
fitting in accordance with the requirements of paragraph (g)(2)(ii)
of this AD. Replacement of the fitting terminates the daily detailed
inspection requirements of this paragraph.
(ii) Except as required by paragraph (g)(2)(i) of this AD:
Within 300 flight hours after accomplishing the conductivity
inspection specified in paragraph (g) of this AD, do the action
specified in paragraph (g)(2)(ii)(A) or (B) of this AD. As of the
effective date of this AD, only the action specified in paragraph
(g)(2)(ii)(B) of this AD may be done.
(A) Replace the fitting with a new fitting in accordance with
paragraph (2) of Part A of the Accomplishment Instructions of
Bombardier Service Bulletin 84-54-14, Revision K, dated August 7,
2018.
(B) Replace the rear spar nacelle attachment fitting and
associated structure with a new nacelle attachment fitting, P/N
8Z9305, and do all applicable related investigative and corrective
actions, in accordance with Part B of the Accomplishment
Instructions of Bombardier Service Bulletin 84-54-16 Revision D,
dated August 7, 2018. Do all applicable related investigative and
corrective actions before further flight.
(h) Retained Inspections and Replacement, With Revised Service
Information, Revised Affected Airplanes, and Revised Replacement
Instructions
This paragraph restates the requirements of paragraph (i) of AD
2010-23-04, with revised service information, revised affected
airplanes, and revised replacement instructions. For airplanes
having serial numbers 4305 through 4313 inclusive, and 4316 through
4380 inclusive, and airplanes that have replaced nacelle attachment
fitting(s) with P/N 854146663: Within 1,200
[[Page 35180]]
flight hours after November 22, 2010 (the effective date of AD 2010-
23-04), do a detailed inspection for cracking on each of the 4
nacelle attachment fittings, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 84-54-14, Revision K,
dated August 7, 2018. If any nacelle attachment fitting is found
cracked, before further flight, do the action specified in paragraph
(h)(1) or (2) of this AD. As of the effective date of this AD, only
the action specified in paragraph (h)(2) of this AD may be done.
Thereafter, repeat the detailed inspection at intervals not to
exceed 300 flight hours, except as provided by paragraph (i) of this
AD. Accomplishing the replacement specified in paragraph (h)(2) of
this AD terminates the inspections required by this paragraph.
(1) Replace the fitting with a new fitting in accordance with
paragraph (2) of Part A of the Accomplishment Instructions of
Bombardier Service Bulletin 84-54-14, Revision K, dated August 7,
2018.
(2) Replace the rear spar nacelle attachment fitting and
associated structure with a new nacelle attachment fitting, P/N
8Z9305, and do all applicable related investigative and corrective
actions, in accordance with Part B of the Accomplishment
Instructions of Bombardier Service Bulletin 84-54-16 Revision D,
dated August 7, 2018. Do all applicable related investigative and
corrective actions before further flight.
(i) Retained Inspection Compliance Time, With Revised Service
Information
This paragraph restates the requirements of paragraph (j) of AD
2010-23-04, with revised service information. For any fitting that
is replaced in accordance with paragraph (3) of Part A of the
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14,
Revision J, dated September 17, 2010; or paragraph (2) of Part A of
the Accomplishment Instructions of Bombardier Service Bulletin 84-
54-14, Revision K, dated August 7, 2018, as specified in paragraph
(g) or (h) of this AD: Within 1,200 flight hours after replacing the
fitting, do a detailed inspection of that replaced fitting as
specified in paragraph (g) or (h) of this AD, and repeat the
detailed inspection thereafter at intervals not to exceed 300 flight
hours. Accomplishing the replacement specified in paragraph
(g)(1)(ii), (g)(2)(ii)(B), or (h)(2) of this AD terminates the
inspections required by this paragraph.
(j) Retained Credit for Previous Actions (Replacing the Fitting), With
Revised Paragraph References
This paragraph restates the credit provided in paragraph (k) of
AD 2010-23-04, with revised paragraph references. Accomplishing the
replacement of the nacelle fittings in accordance with any
Bombardier service bulletin identified in figure 1 to paragraphs (j)
and (k) of this AD before November 22, 2010 (the effective date of
AD 2010-23-04) is also acceptable for compliance with the fitting
replacements specified in paragraphs (g)(1)(i), (g)(2)(ii)(A), and
(h)(1) of this AD.
[GRAPHIC] [TIFF OMITTED] TR09JN20.001
(k) Retained Credit for Previous Actions (Inspections), With No Changes
This paragraph restates the credit provided in paragraph (l) of
AD 2010-23-04, with no changes. Accomplishment of the inspections
required by paragraphs (g) and (h) of this AD before November 22,
2010 (the effective date of AD 2010-23-04) in accordance with any
Bombardier service bulletin identified in figure 1 to paragraphs (j)
and (k) of this AD is acceptable for compliance with the
corresponding actions required by paragraphs (g) and (h) of this AD.
(l) New Requirements of This AD: Modification of the Rear Spar Fitting
and Nacelle Attaching Structure
For airplanes with nacelle attachment fitting P/N 85414663:
Unless already done as specified in paragraph (g)(1)(ii),
(g)(2)(ii)(B), or (h)(2) of this AD: Within 8,000 flight hours or 48
months, whichever occurs first, from the effective date of this AD,
replace the rear spar nacelle attachment fitting and associated
structure with a new nacelle attachment fitting, P/N 8Z9305, and do
all applicable related investigative and corrective actions, in
accordance with Part B of the Accomplishment Instructions of
Bombardier Service Bulletin 84-54-16, Revision D, dated August 7,
2018. Do all applicable related investigative and corrective actions
before further flight.
[[Page 35181]]
(m) New Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD that are identified in Bombardier
Service Bulletin 84-54-14, Revision K, dated August 7, 2018, if
those actions were performed before the effective date of this AD
using Bombardier Service Bulletin 84-54-14, Revision J, dated
September 17, 2010, which was incorporated by reference in AD 2010-
23-04; except as provided by paragraph (p) of this AD.
(2) This paragraph provides credit for accomplishing the
replacement of the rear spar fitting and nacelle attaching structure
required by paragraph (l) of this AD, if those actions were
performed before the effective date of this AD using the service
information specified in paragraphs (m)(2)(i) through (iii) of this
AD.
(i) Bombardier Service Bulletin 84-54-16, dated April 29, 2011.
(ii) Bombardier Service Bulletin 84-54-16, Revision A, dated
August 1, 2011.
(iii) Bombardier Service Bulletin 84-54-16, Revision C, dated
January 31, 2017.
(3) This paragraph provides credit for accomplishing the
replacement of the rear spar fitting and nacelle attaching structure
required by paragraph (l) of this AD, if those actions were
performed before the effective date of this AD using Bombardier
Service Bulletin 84-54-16, Revision B, dated October 6, 2016.
Although Bombardier Service
Bulletin 84-54-16, Revision B, dated October 6, 2016,
incorrectly stated that airworthiness limitations (AWLs) or damage
tolerance inspections (DTIs) are not affected, they are affected.
Refer to the applicable AWLs for Post/Pre-Modification Summary
(ModSum) 4-113697 and Bombardier Service Bulletin 84-54-16 in the
existing maintenance requirements manual.
(4) This paragraph provides credit for accomplishing the action
identified in Bombardier Service Bulletin 84-54-14, Revision K,
dated August 7, 2018, that are required by paragraphs (g) and (h) of
this AD, if those actions were performed before the effective date
of this AD using the service information specified in paragraphs
(m)(4)(i) through (iv) of this AD.
(i) Bombardier Service Bulletin 84-54-15, dated August 20, 2010.
(ii) Bombardier Service Bulletin 84-54-15, Revision A, dated
October 25, 2010. (iii) Bombardier Service Bulletin 84-54-15,
Revision B, dated February 2, 2017. (iv) Bombardier Service Bulletin
84-54-15, Revision C, dated August 7, 2018.
(n) Terminating Action for Certain Actions in Paragraphs (g), (h), and
(i) of This AD
Accomplishing the modification of the rear spar fitting and
nacelle attaching structure required by paragraph (l) of this AD
terminates the repetitive inspection required by paragraphs (g),
(h), and (i) of this AD for that airplane.
(o) Parts Installation Limitations
As of the effective date of this AD, no person may install a
rear spar nacelle attachment fitting P/N 85414663 on any airplane.
(p) Credit for Alternative to Certain Credit Actions
For airplanes on which Bombardier Service Bulletin 84-54-14,
Revision J, dated September 17, 2010, was accomplished before the
effective date of this AD: As an alternative to applying sealant to
each fitting and access panel as specified in paragraph C.(1) of the
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14,
Revision J, dated September 17, 2010, the use of the instructions of
Bombardier Modification Summary Package IS4Q5400012, Revision B,
dated July 11, 2012, to apply sealant is also acceptable if
accomplished before the effective date of this AD.
(q) Other FAA AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York ACO 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 ATTN: Program Manager, Continuing Operational
Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531.
(i) 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.
(ii) AMOCs approved previously for AD 2010-23-04, are approved
as AMOCs for the corresponding provisions of this AD.
(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, New York ACO
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or De
Havilland Aircraft of Canada Limited's TCCA Design Approval
Organization (DAO). If approved by the DAO, the approval must
include the DAO-authorized signature.
(r) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian AD CF-2010-30R2, dated July 30, 2019, for related
information. This MCAI may be found in the AD docket on the internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2020-0099.
(2) For more information about this AD, contact Andrea Jimenez,
Aerospace Engineer, Airframe and Propulsion Section, FAA, New York
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 516-228-7330; fax 516-794-5531; email [email protected].
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (s)(3) and (4) of this AD.
(s) 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.
(i) Bombardier Service Bulletin 84-54-14, Revision K, dated
August 7, 2018.
(ii) Bombardier Service Bulletin 84-54-16, Revision D, dated
August 7, 2018.
(iii) Bombardier Modification Summary Package IS4Q5400012,
Revision B, dated July 11, 2012.
(3) For service information identified in this AD, contact De
Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk,
123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone
416-375-4000; fax 416-375-4539; email [email protected]; internet
https://dehavilland.com.
(4) You may view this service information 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on May 29, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-12379 Filed 6-8-20; 8:45 am]
BILLING CODE 4910-13-P