Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes, 58058-58061 [2024-15656]
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Federal Register / Vol. 89, No. 137 / Wednesday, July 17, 2024 / Rules and Regulations
paragraph (a) of this section, the code of
record interval is two consecutive
inservice inspection or inservice
examination and test intervals.
Inservice examination and test (IST)
code of record means the specific
edition(s) and addenda of the ASME
OM Code required by (f)(4)(i) or (ii) of
this section, subject to the conditions
listed in paragraph (b) of this section,
and applicable NRC endorsed code
cases, for inservice test to verify
operational readiness of pumps, valves,
and dynamic restraints, whose function
is required for safety.
Inservice examination and test (IST)
interval means the inservice
examination and test interval described
by the licensee’s code of record
(paragraph ISTA–3120 of the ASME OM
Code, 2001 Edition through 2009
Edition, or paragraph ISTA–3120 of the
ASME OM Code, 2012 Edition and
later).
Inservice examination and testing
(IST) program means the requirements
for preservice and inservice
examination and testing of pumps,
valves, and dynamic restraints within
the scope of this section to assess their
operational readiness in nuclear power
plants, including but not limited to:
(1) The requirements specified in the
ASME OM Code, as incorporated by
reference in this section, such as for test
or examination, responsibilities,
methods, intervals, parameters to be
measured and evaluated, criteria for
evaluating the results, corrective action,
personnel qualification, and
recordkeeping.
(2) Relief requested under paragraph
(f)(5)(iii) of this section and granted
under paragraph (f)(6)(i) of this section.
(3) Augmented IST requirements as
applied by the Commission under
paragraph (f)(6)(ii) of this section.
(4) Alternatives authorized under
paragraph (z) of this section.
Inservice inspection (ISI) code of
record means the specific edition(s) and
addenda of the ASME BPV Code,
Section XI, required by paragraphs
(g)(4)(i) or (ii) of this section, subject to
the conditions listed in paragraph (b) of
this section, and applicable NRC
endorsed code cases, for the inservice
examination of components and system
pressure tests.
Inservice inspection (ISI) interval
means the inservice inspection interval
described in Article IWA–2432 of ASME
BPV Code, Section XI, 1989 Edition
with 1991 Addenda through the 2008
Addenda, or Article IWA–2431 of
ASME BPV Code, Section XI, 2009
Addenda and later.
Inservice inspection (ISI) program
means the set of all administrative and
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technical requirements pertaining to
periodic examination of nuclear
components, as specified in ASME BPV
Code, Section XI, and this section,
including but not limited to:
(1) The requirements of IWA–2400 of
ASME BPV Code, Section XI, 1991
Addenda and later.
(2) Relief requested under paragraph
(g)(5)(iii) of this section and granted
under paragraph (g)(6)(i) of this section.
(3) The augmented inspection
program described in paragraph (g)(6)(ii)
of this section.
(4) Alternatives authorized under
paragraph (z) of this section.
*
*
*
*
*
■ 3. In appendix J to part 50, in section
III of option A:
■ a. Remove footnote 2;
■ b. Redesignate footnote 3 as new
footnote 2; and
■ c. Revise paragraph D.1.(a).
The revision reads as follows:
Appendix J to Part 50—Primary
Reactor Containment Leakage Testing
for Water-Cooled Power Reactors
*
*
*
*
*
Option A—Prescriptive Requirements
*
*
*
*
*
III. * * *
D. * * * 1. * * *
(a) After the preoperational leakage rate
tests, a set of three Type A tests shall be
performed, at approximately equal intervals
during each inservice inspection interval, as
defined in § 50.55a(y). The third test of each
set shall be conducted when the plant is shut
down for the final plant inservice inspections
of the inservice inspection interval.
*
*
*
*
*
Dated: July 5, 2024.
Nuclear Regulatory Commission.
Andrea Veil,
Director, Office of Nuclear Reactor
Regulation.
[FR Doc. 2024–15288 Filed 7–16–24; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–0756; Project
Identifier MCAI–2023–00549–T; Amendment
39–22769; AD 2024–12–05]
RIN 2120–AA64
Airworthiness Directives; De Havilland
Aircraft of Canada Limited (Type
Certificate Previously Held by
Bombardier, Inc.) Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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ACTION:
Final rule.
The FAA is superseding
Airworthiness Directive (AD) 2021–25–
12 and AD 2022–11–11, which applied
to certain De Havilland Aircraft of
Canada Limited Model DHC–8–401 and
–402 airplanes. AD 2021–25–12
required repetitive lubrications of the
trailing arm of the nose landing gear
(NLG). AD 2021–25–12 also required
revising the existing maintenance or
inspection program to include new and
revised airworthiness limitations. AD
2022–11–11 required a modification to
the NLG shock strut assembly. This AD
continues to require the actions
specified in AD 2021–25–12 and AD
2022–11–11 and requires replacement of
the pivot pin and tow fitting assembly
with a new, improved pivot pin and tow
fitting assembly and prohibits the
installation of affected parts. This AD
was prompted by a determination that
the pivot pin and tow fitting assembly
of the NLG must be replaced. The FAA
is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 21,
2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 21, 2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of July 8, 2022 (87 FR 33627,
June 3, 2022).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of January 5, 2022 (86 FR
72174, December 21, 2021).
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2024–0756; 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.
Material Incorporated by Reference:
• For De Havilland material
identified in this AD, contact De
Havilland Aircraft of Canada Limited,
Dash 8 Series Customer Response
Centre, 5800 Explorer Drive,
Mississauga, Ontario, L4W 5K9, Canada;
telephone North America (toll-free):
855–310–1013, Direct: 647–277–5820;
SUMMARY:
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email thd@dehavilland.com; website
dehavilland.com.
• 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.
It is also available at regulations.gov
under Docket No. FAA–2024–0756.
FOR FURTHER INFORMATION CONTACT:
Deep Gaurav, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516–
228–7300; email 9-avs-nyaco-cos@
faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2021–25–12,
Amendment 39–21856 (86 FR 72174,
December 21, 2021) (AD 2021–25–12);
and AD 2022–11–11, Amendment 39–
22061 (87 FR 33627, June 3, 2022) (AD
2022–11–11). AD 2021–25–12 and AD
2022–11–11 applied to certain
DeHavilland Aircraft of Canada Limited
Model DHC–8–401 and –402 airplanes.
AD 2021–25–12 required repetitive
lubrications of the trailing arm of the
NLG. AD 2021–25–12 also required
revising the existing maintenance or
inspection program to include new and
revised airworthiness limitations (life
limits for certain bolts). AD 2022–11–11
required modification to the NLG shock
strut assembly. The FAA issued AD
2021–25–12 and AD 2022–11–11 to
address failure of the pivot pin retention
bolt, which could result in a loss of
directional control or loss of an NLG tire
during takeoff or landing, which could
lead to runway excursions.
The NPRM published in the Federal
Register on March 22, 2024 (89 FR
20367). The NPRM was prompted by
AD CF–2023–22, dated March 30, 2023
(Transport Canada AD CF–2023–22)
(also referred to as the MCAI), issued by
Transport Canada, which is the aviation
authority for Canada. Transport Canada
AD CF–2023–22 superseded Transport
Canada AD CF–2009–29R4, October 1,
2021 (Transport Canada AD CF–2009–
29R4). The MCAI states that it requires
the removal of pivot pin part number (P/
N) 47127–1 or P/N 47127–3 and tow
fitting assembly P/N 47160–1, and their
replacement with pivot pin P/N 47127–
5 and tow fitting assembly P/N 47160–
3, as terminating action to the
requirements of Transport Canada AD
CF–2009–29R4. The pivot pin P/N
47127–5 is now attached directly to the
new tow fitting lug and no longer
requires the use of a retention bolt.
Transport Canada AD CF–2023–22 also
prohibits the installation of certain
parts.
In the NPRM, the FAA proposed to
continue to require the actions specified
in AD 2021–25–12 and AD 2022–11–11
and to require replacement of the pivot
pin and tow fitting assembly with a
new, improved pivot pin and tow fitting
assembly and prohibit the installation of
affected parts. In the NPRM, the FAA
also proposed to remove airplanes from
the applicability of AD 2021–25–12 and
AD 2022–11–11. The FAA is issuing
this AD to address the unsafe condition
on these products.
You may examine the MCAI in the
AD docket at regulations.gov under
Docket No. FAA–2024–0756.
Discussion of Final Airworthiness
Directive
Comments
The FAA received no comments on
the NPRM or on the determination of
the cost to the public.
Conclusion
This product has been approved by
the aviation authority of another
country and is approved for operation in
the United States. Pursuant to the FAA’s
bilateral agreement with this State of
Design Authority, it has notified the
FAA of the unsafe condition described
in the MCAI referenced above. The FAA
reviewed the relevant data and
determined that air safety requires
adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on this
product. Except for minor editorial
58059
changes, this AD is adopted as proposed
in the NPRM. None of the changes will
increase the economic burden on any
operator.
Material Incorporated by Reference
Under 1 CFR Part 51
The FAA reviewed De Havilland
Aircraft of Canada Limited Service
Bulletin 84–32–173, dated November
15, 2022, including Collins Aerospace
Service Bulletin 47100–32–153, dated
November 10, 2022. This material
specifies procedures for replacing the
pivot pin retention mechanism and tow
fitting assembly with a new, improved
pivot pin and tow fitting assembly,
which consists of removing pivot pin
linkage components and replacing pivot
pin P/N 47127–1 or P/N 47127–3 and
tow fitting assembly P/N 47160–1 with
pivot pin P/N 47127–5 and tow fitting
assembly P/N 47160–3.
This AD also requires De Havilland
Aircraft of Canada Limited Service
Bulletin 84–32–161, Revision B, dated
March 31, 2021, including UTC
Aerospace Systems Service Bulletin
47100–32–145, Revision 3, dated March
26, 2021, which the Director of the
Federal Register approved for
incorporation by reference as of July 8,
2022 (87 FR 33627, June 3, 2022).
This AD also requires De Havilland
Aircraft of Canada Limited Service
Bulletin 84–32–167, dated August 12,
2021; and De Havilland Aircraft of
Canada Limited Temporary Revision
ALI–0223, dated October 15, 2020,
which the Director of the Federal
Register approved for incorporation by
reference as of January 5, 2022 (86 FR
72174, December 21, 2021).
This material 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 will
affect 41 airplanes of U.S. registry.
The FAA estimates the following
costs to comply with this AD:
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ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Parts cost
Retained actions from AD 2021–25–12 * .......
Retained actions from AD 2022–11–11 .........
New actions ....................................................
1 work-hour × $85 per hour = $85 .................
4 work-hours × $85 per hour = $340 .............
4 work-hours × $85 per hour = $340 .............
Negligible
$8
25,804
Cost per
product
$85
348
26,144
Cost on U.S.
operators
$3,485
14,268
1,071,904
* Table does not include estimated costs for revising the maintenance or inspection program.
The FAA has determined that revising
the maintenance or inspection program
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takes an average of 90 work-hours per
operator, although the FAA recognizes
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that this number may vary from operator
to operator. In the past, the FAA has
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Federal Register / Vol. 89, No. 137 / Wednesday, July 17, 2024 / Rules and Regulations
estimated that this action takes 1 workhour per airplane. Since operators
incorporate maintenance or inspection
program changes for their affected
fleet(s), the FAA has determined that a
per-operator estimate is more accurate
than a per-airplane estimate. Therefore,
the FAA estimates the total cost per
operator to be $7,650 (90 work-hours ×
$85 per work-hour).
The FAA estimates the following
costs to do any necessary on-condition
actions that would be required based on
the results of any required actions. The
FAA has no way of determining the
number of aircraft that might need these
on-condition actions:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Cost per
product
2 work-hours × $85 per hour = $170 ......................................................................................................................
$8
$178
Authority for This Rulemaking
The Amendment
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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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.
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PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
(AD) 2021–25–12, Amendment 39–
21856 (86 FR 72174, December 21,
2021); and AD 2022–11–11,
Amendment 39–22061 (87 FR 33627,
June 3, 2022); and
■ b. Adding the following new AD:
■
■
2024–12–05 De Havilland Aircraft of
Canada (Type Certificate Previously
Held by Bombardier, Inc.): Amendment
39–22769; Docket No. FAA–2024–0756;
Project Identifier MCAI–2023–00549–T.
(a) Effective Date
This airworthiness directive (AD) is
effective August 21, 2024.
(b) Affected ADs
This AD replaces AD 2021–25–12,
Amendment 39–21856 (86 FR 72174,
December 21, 2021) (AD 2021–25–12); and
AD 2022–11–11, Amendment 39–22061 (87
FR 33627, June 3, 2022) (AD 2022–11–11).
(c) Applicability
This AD applies to De Havilland Aircraft
of Canada Limited (Type Certificate
previously held by Bombardier, Inc.) Model
DHC–8–401 and –402 airplanes, certificated
in any category, having serial numbers 4001,
and 4003 through 4633 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Reason
This AD was prompted by reports of a
certain bolt at the pivot pin link being found
missing or having stress corrosion cracking
and a determination that the pivot pin and
tow fitting assembly of the nose landing gear
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(NLG) must be replaced. The FAA is issuing
this AD to address failure of the pivot pin
retention bolt. The unsafe condition, if not
addressed, could result in a loss of
directional control or loss of an NLG tire
during takeoff or landing, which could lead
to runway excursions.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Maintenance or Inspection
Program Revision, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2021–25–12, with no
changes. For airplanes with pivot pin
retention bolt part number (P/N) NAS6204–
14D installed on the NLG assembly: Within
30 days after January 5, 2022 (the effective
date of AD 2021–25–12), or within 30 days
after installation of pivot pin retention bolt
part number P/N NAS6204–14D, whichever
occurs later, revise the existing maintenance
or inspection program, as applicable, to
incorporate the information for Structures
Safe Life Task 32–21–01–701 and Task 32–
21–01–702, as specified in De Havilland
Aircraft of Canada Limited Temporary
Revision ALI–0223, dated October 15, 2020.
The initial compliance time for doing the
tasks is at the applicable time specified in De
Havilland Aircraft of Canada Limited
Temporary Revision ALI–0223, dated
October 15, 2020, or within 30 days after
January 5, 2022, whichever occurs later;
except, if replacement of bolt P/N NAS6204–
14D was performed before January 5, 2022,
as specified in De Havilland Aircraft of
Canada Service Bulletin 84–32–161, the
initial compliance time for Task 32–21–01–
702 (bolt P/N NAS6204–14D replacement) is
within 3 months after January 5, 2022, or
within 800 flight cycles after performing the
replacement, whichever occurs later.
(h) Retained No Alternative Actions or
Intervals, With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2021–25–12, with no
changes. After the existing maintenance or
inspection program has been revised as
required by paragraph (g) of this AD, no
alternative actions (e.g., replacements) or
intervals may be used unless the actions and
intervals are approved as an alternative
method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (n)(1) of this AD.
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(i) Retained Repetitive Lubrications, With
No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2021–25–12, with no
changes. For airplanes with pivot pin
retention bolt P/N NAS6204–14D installed
on the NLG assembly: Within 30 days or 400
flight cycles, whichever occurs first after
January 5, 2022 (the effective date of AD
2021–25–12), and thereafter at intervals not
exceeding 400 flight cycles, lubricate the
trailing arm of the NLG, including doing a
general visual inspection of the NLG pivot
pin mechanism for discrepancies (i.e., bolt P/
N NAS602–14D is missing or has damage
(e.g., stress corrosion or stress corrosion
cracking)) and, as applicable, replacing the
bolt before further flight, in accordance with
paragraph 3.B. of the Accomplishment
Instructions of De Havilland Aircraft of
Canada Limited Service Bulletin 84–32–167,
dated August 12, 2021.
(j) Retained Modification, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2022–11–11, with no
changes. For any airplane having an NLG
shock strut assembly, P/N 47100–XX (where
XX represents any number), that has special
bolt P/N 47205–1 or 47205–3: Within 1,600
flight cycles or 9 months after July 8, 2022
(the effective date of AD 2022–11–11),
whichever occurs first, modify the NLG
shock strut assembly, in accordance with
paragraph 3.B., ‘‘Procedure,’’ of the
Accomplishment Instructions of De
Havilland Aircraft of Canada Limited Service
Bulletin 84–32–161, Revision B, dated March
31, 2021, including UTC Aerospace Systems
Service Bulletin 47100–32–145, Revision 3,
dated March 26, 2021.
Note 1 to paragraph (j): After installing
pivot pin retention bolt part number
NAS6204–14D, paragraphs (g), (h), and (i) of
this AD apply to pivot pin retention bolt part
number NAS6204–14D.
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(k) New Replacement
Within 8,000 flight hours or 48 months,
whichever occurs first, after the effective date
of this AD, remove pivot pin linkage
components and replace pivot pin P/N
47127–1 or P/N 47127–3 and tow fitting
assembly P/N 47160–1 with pivot pin P/N
47127–5 and tow fitting assembly P/N
47160–3, in accordance with Section 3.B. of
the Accomplishment Instructions of De
Havilland Aircraft of Canada Limited Service
Bulletin 84–32–173, dated November 15,
2022, including Collins Aerospace Service
Bulletin 47100–32–153, dated November 10,
2022. Accomplishing the replacement
required by this paragraph terminates the
requirements of paragraphs (g), (h), (i), and (j)
of this AD.
(l) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (j) of this AD, if those
actions were performed before July 8, 2022
(the effective date of AD 2022–11–11), using
De Havilland Aircraft of Canada Limited
Service Bulletin 84–32–161, dated April 7,
2020, including UTC Aerospace Systems
Service Bulletin 47100–32–145, dated April
3, 2020; or De Havilland Aircraft of Canada
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Limited Service Bulletin 84–32–161,
Revision A, dated January 27, 2021,
including UTC Aerospace Systems Service
Bulletin 47100–32–145, Revision 2, dated
January 4, 2021.
(m) Parts Installation Prohibition
As of the effective date of this AD, no
person may install pivot pin P/N 47127–1 or
P/N 47127–3 as a replacement part for pivot
pin P/N 47127–5 on De Havilland Aircraft of
Canada Limited Model DHC–8–401 and
DHC–8–402 airplanes.
(n) Additional AD Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Validation 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
responsible Flight Standards Office, as
appropriate. If sending information directly
to the manager of the International Validation
Branch, mail it to the address identified in
paragraph (o)(2) of this AD. Information may
be emailed to: 9-AVS-NYACO-COS@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, International Validation
Branch, FAA; or Transport Canada; or De
Havilland Aircraft of Canada Limited’s
Transport Canada Design Approval
Organization (DAO). If approved by the DAO,
the approval must include the DAOauthorized signature.
(o) Additional Information
(1) For more information about this AD,
contact Deep Gaurav, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone 518–
228–7300; email 9-avs-nyaco-cos@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the address specified in
paragraph (p)(6) of this AD.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the material listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as
applicable to do the actions required by this
AD, unless this AD specifies otherwise.
(3) The following material was approved
for IBR on August 21, 2024.
(i) De Havilland Aircraft of Canada Limited
Service Bulletin 84–32–173, dated November
15, 2022, including Collins Aerospace
Service Bulletin 47100–32–153, dated
November 10, 2022.
Note 2 to paragraph (p)(3)(i): De Havilland
issued De Havilland Aircraft of Canada
Limited Service Bulletin 84–32–173, dated
November 15, 2022, with Collins Aerospace
Service Bulletin 47100–32–153, dated
November 10, 2022, attached as one
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58061
‘‘merged’’ file for the convenience of affected
operators.
(ii) [Reserved]
(4) The following material was approved
for IBR on July 8, 2022 (87 FR 33627, June
3, 2022).
(i) De Havilland Aircraft of Canada Limited
Service Bulletin 84–32–161, Revision B,
dated March 31, 2021, including UTC
Aerospace Systems Service Bulletin 47100–
32–145, Revision 3, dated March 26, 2021.
Note 3 to paragraph (p)(4)(i): De Havilland
issued De Havilland Service Bulletin 84–32–
161, Revision B, dated March 31, 2021, with
UTC Aerospace Systems Service Bulletin
47100–32–145, Revision 3, dated March 26,
2021, attached as one ‘‘merged’’ file for the
convenience of affected operators.
(ii) [Reserved]
(5) The following material was approved
for IBR on January 5, 2022 (86 FR 72174,
December 21, 2021).
(i) De Havilland Aircraft of Canada Limited
Service Bulletin 84–32–167, dated August 12,
2021.
(ii) De Havilland Aircraft of Canada
Limited Temporary Revision ALI–0223,
dated October 15, 2020.
(6) For De Havilland material identified in
this AD, contact De Havilland Aircraft of
Canada Limited, Dash 8 Series Customer
Response Centre, 5800 Explorer Drive,
Mississauga, Ontario, L4W 5K9, Canada;
telephone North America (toll-free): 855–
310–1013, Direct: 647–277–5820; email thd@
dehavilland.com; website dehavilland.com.
(7) 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.
(8) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locations, or email fr.inspection@
nara.gov.
Issued on July 10, 2024.
James D. Foltz,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–15656 Filed 7–16–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–1885; Project
Identifier MCAI–2022–01484–T; Amendment
39–22770; AD 2024–12–06]
RIN 2120–AA64
Airworthiness Directives; De Havilland
Aircraft of Canada Limited (Type
Certificate Previously Held by
Bombardier, Inc.) Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
E:\FR\FM\17JYR1.SGM
17JYR1
]]>Agencies
[Federal Register Volume 89, Number 137 (Wednesday, July 17, 2024)]
[Rules and Regulations]
[Pages 58058-58061]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-15656]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-0756; Project Identifier MCAI-2023-00549-T;
Amendment 39-22769; AD 2024-12-05]
RIN 2120-AA64
Airworthiness Directives; De Havilland Aircraft of Canada Limited
(Type Certificate Previously Held by Bombardier, Inc.) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2021-25-12
and AD 2022-11-11, which applied to certain De Havilland Aircraft of
Canada Limited Model DHC-8-401 and -402 airplanes. AD 2021-25-12
required repetitive lubrications of the trailing arm of the nose
landing gear (NLG). AD 2021-25-12 also required revising the existing
maintenance or inspection program to include new and revised
airworthiness limitations. AD 2022-11-11 required a modification to the
NLG shock strut assembly. This AD continues to require the actions
specified in AD 2021-25-12 and AD 2022-11-11 and requires replacement
of the pivot pin and tow fitting assembly with a new, improved pivot
pin and tow fitting assembly and prohibits the installation of affected
parts. This AD was prompted by a determination that the pivot pin and
tow fitting assembly of the NLG must be replaced. The FAA is issuing
this AD to address the unsafe condition on these products.
DATES: This AD is effective August 21, 2024.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 21,
2024.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of July
8, 2022 (87 FR 33627, June 3, 2022).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of January
5, 2022 (86 FR 72174, December 21, 2021).
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2024-0756; 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.
Material Incorporated by Reference:
For De Havilland material identified in this AD, contact
De Havilland Aircraft of Canada Limited, Dash 8 Series Customer
Response Centre, 5800 Explorer Drive, Mississauga, Ontario, L4W 5K9,
Canada; telephone North America (toll-free): 855-310-1013, Direct: 647-
277-5820;
[[Page 58059]]
email dehavilland.com">thd@dehavilland.com; website dehavilland.com.
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. It is also available at regulations.gov under
Docket No. FAA-2024-0756.
FOR FURTHER INFORMATION CONTACT: Deep Gaurav, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-
228-7300; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2021-25-12, Amendment 39-21856 (86 FR
72174, December 21, 2021) (AD 2021-25-12); and AD 2022-11-11, Amendment
39-22061 (87 FR 33627, June 3, 2022) (AD 2022-11-11). AD 2021-25-12 and
AD 2022-11-11 applied to certain DeHavilland Aircraft of Canada Limited
Model DHC-8-401 and -402 airplanes. AD 2021-25-12 required repetitive
lubrications of the trailing arm of the NLG. AD 2021-25-12 also
required revising the existing maintenance or inspection program to
include new and revised airworthiness limitations (life limits for
certain bolts). AD 2022-11-11 required modification to the NLG shock
strut assembly. The FAA issued AD 2021-25-12 and AD 2022-11-11 to
address failure of the pivot pin retention bolt, which could result in
a loss of directional control or loss of an NLG tire during takeoff or
landing, which could lead to runway excursions.
The NPRM published in the Federal Register on March 22, 2024 (89 FR
20367). The NPRM was prompted by AD CF-2023-22, dated March 30, 2023
(Transport Canada AD CF-2023-22) (also referred to as the MCAI), issued
by Transport Canada, which is the aviation authority for Canada.
Transport Canada AD CF-2023-22 superseded Transport Canada AD CF-2009-
29R4, October 1, 2021 (Transport Canada AD CF-2009-29R4). The MCAI
states that it requires the removal of pivot pin part number (P/N)
47127-1 or P/N 47127-3 and tow fitting assembly P/N 47160-1, and their
replacement with pivot pin P/N 47127-5 and tow fitting assembly P/N
47160-3, as terminating action to the requirements of Transport Canada
AD CF-2009-29R4. The pivot pin P/N 47127-5 is now attached directly to
the new tow fitting lug and no longer requires the use of a retention
bolt. Transport Canada AD CF-2023-22 also prohibits the installation of
certain parts.
In the NPRM, the FAA proposed to continue to require the actions
specified in AD 2021-25-12 and AD 2022-11-11 and to require replacement
of the pivot pin and tow fitting assembly with a new, improved pivot
pin and tow fitting assembly and prohibit the installation of affected
parts. In the NPRM, the FAA also proposed to remove airplanes from the
applicability of AD 2021-25-12 and AD 2022-11-11. The FAA is issuing
this AD to address the unsafe condition on these products.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2024-0756.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
This product has been approved by the aviation authority of another
country and is approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with this State of Design Authority, it
has notified the FAA of the unsafe condition described in the MCAI
referenced above. The FAA reviewed the relevant data and determined
that air safety requires adopting this AD as proposed. Accordingly, the
FAA is issuing this AD to address the unsafe condition on this product.
Except for minor editorial changes, this AD is adopted as proposed in
the NPRM. None of the changes will increase the economic burden on any
operator.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed De Havilland Aircraft of Canada Limited Service
Bulletin 84-32-173, dated November 15, 2022, including Collins
Aerospace Service Bulletin 47100-32-153, dated November 10, 2022. This
material specifies procedures for replacing the pivot pin retention
mechanism and tow fitting assembly with a new, improved pivot pin and
tow fitting assembly, which consists of removing pivot pin linkage
components and replacing pivot pin P/N 47127-1 or P/N 47127-3 and tow
fitting assembly P/N 47160-1 with pivot pin P/N 47127-5 and tow fitting
assembly P/N 47160-3.
This AD also requires De Havilland Aircraft of Canada Limited
Service Bulletin 84-32-161, Revision B, dated March 31, 2021, including
UTC Aerospace Systems Service Bulletin 47100-32-145, Revision 3, dated
March 26, 2021, which the Director of the Federal Register approved for
incorporation by reference as of July 8, 2022 (87 FR 33627, June 3,
2022).
This AD also requires De Havilland Aircraft of Canada Limited
Service Bulletin 84-32-167, dated August 12, 2021; and De Havilland
Aircraft of Canada Limited Temporary Revision ALI-0223, dated October
15, 2020, which the Director of the Federal Register approved for
incorporation by reference as of January 5, 2022 (86 FR 72174, December
21, 2021).
This material 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 will affect 41 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2021-25-12 *. 1 work-hour x $85 per Negligible $85 $3,485
hour = $85.
Retained actions from AD 2022-11-11... 4 work-hours x $85 per $8 348 14,268
hour = $340.
New actions........................... 4 work-hours x $85 per 25,804 26,144 1,071,904
hour = $340.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for revising the maintenance or inspection program.
The FAA has determined that revising the maintenance or inspection
program takes an average of 90 work-hours per operator, although the
FAA recognizes that this number may vary from operator to operator. In
the past, the FAA has
[[Page 58060]]
estimated that this action takes 1 work-hour per airplane. Since
operators incorporate maintenance or inspection program changes for
their affected fleet(s), the FAA has determined that a per-operator
estimate is more accurate than a per-airplane estimate. Therefore, the
FAA estimates the total cost per operator to be $7,650 (90 work-hours x
$85 per work-hour).
The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required actions. The FAA has no way of determining the number of
aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
2 work-hours x $85 per hour = $170.... $8 $178
------------------------------------------------------------------------
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.
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:
0
a. Removing Airworthiness Directive (AD) 2021-25-12, Amendment 39-21856
(86 FR 72174, December 21, 2021); and AD 2022-11-11, Amendment 39-22061
(87 FR 33627, June 3, 2022); and
0
b. Adding the following new AD:
2024-12-05 De Havilland Aircraft of Canada (Type Certificate
Previously Held by Bombardier, Inc.): Amendment 39-22769; Docket No.
FAA-2024-0756; Project Identifier MCAI-2023-00549-T.
(a) Effective Date
This airworthiness directive (AD) is effective August 21, 2024.
(b) Affected ADs
This AD replaces AD 2021-25-12, Amendment 39-21856 (86 FR 72174,
December 21, 2021) (AD 2021-25-12); and AD 2022-11-11, Amendment 39-
22061 (87 FR 33627, June 3, 2022) (AD 2022-11-11).
(c) Applicability
This AD applies to De Havilland Aircraft of Canada Limited (Type
Certificate previously held by Bombardier, Inc.) Model DHC-8-401 and
-402 airplanes, certificated in any category, having serial numbers
4001, and 4003 through 4633 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports of a certain bolt at the pivot
pin link being found missing or having stress corrosion cracking and
a determination that the pivot pin and tow fitting assembly of the
nose landing gear (NLG) must be replaced. The FAA is issuing this AD
to address failure of the pivot pin retention bolt. The unsafe
condition, if not addressed, could result in a loss of directional
control or loss of an NLG tire during takeoff or landing, which
could lead to runway excursions.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Maintenance or Inspection Program Revision, With No
Changes
This paragraph restates the requirements of paragraph (g) of AD
2021-25-12, with no changes. For airplanes with pivot pin retention
bolt part number (P/N) NAS6204-14D installed on the NLG assembly:
Within 30 days after January 5, 2022 (the effective date of AD 2021-
25-12), or within 30 days after installation of pivot pin retention
bolt part number P/N NAS6204-14D, whichever occurs later, revise the
existing maintenance or inspection program, as applicable, to
incorporate the information for Structures Safe Life Task 32-21-01-
701 and Task 32-21-01-702, as specified in De Havilland Aircraft of
Canada Limited Temporary Revision ALI-0223, dated October 15, 2020.
The initial compliance time for doing the tasks is at the applicable
time specified in De Havilland Aircraft of Canada Limited Temporary
Revision ALI-0223, dated October 15, 2020, or within 30 days after
January 5, 2022, whichever occurs later; except, if replacement of
bolt P/N NAS6204-14D was performed before January 5, 2022, as
specified in De Havilland Aircraft of Canada Service Bulletin 84-32-
161, the initial compliance time for Task 32-21-01-702 (bolt P/N
NAS6204-14D replacement) is within 3 months after January 5, 2022,
or within 800 flight cycles after performing the replacement,
whichever occurs later.
(h) Retained No Alternative Actions or Intervals, With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2021-25-12, with no changes. After the existing maintenance or
inspection program has been revised as required by paragraph (g) of
this AD, no alternative actions (e.g., replacements) or intervals
may be used unless the actions and intervals are approved as an
alternative method of compliance (AMOC) in accordance with the
procedures specified in paragraph (n)(1) of this AD.
[[Page 58061]]
(i) Retained Repetitive Lubrications, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2021-25-12, with no changes. For airplanes with pivot pin retention
bolt P/N NAS6204-14D installed on the NLG assembly: Within 30 days
or 400 flight cycles, whichever occurs first after January 5, 2022
(the effective date of AD 2021-25-12), and thereafter at intervals
not exceeding 400 flight cycles, lubricate the trailing arm of the
NLG, including doing a general visual inspection of the NLG pivot
pin mechanism for discrepancies (i.e., bolt P/N NAS602-14D is
missing or has damage (e.g., stress corrosion or stress corrosion
cracking)) and, as applicable, replacing the bolt before further
flight, in accordance with paragraph 3.B. of the Accomplishment
Instructions of De Havilland Aircraft of Canada Limited Service
Bulletin 84-32-167, dated August 12, 2021.
(j) Retained Modification, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2022-11-11, with no changes. For any airplane having an NLG shock
strut assembly, P/N 47100-XX (where XX represents any number), that
has special bolt P/N 47205-1 or 47205-3: Within 1,600 flight cycles
or 9 months after July 8, 2022 (the effective date of AD 2022-11-
11), whichever occurs first, modify the NLG shock strut assembly, in
accordance with paragraph 3.B., ``Procedure,'' of the Accomplishment
Instructions of De Havilland Aircraft of Canada Limited Service
Bulletin 84-32-161, Revision B, dated March 31, 2021, including UTC
Aerospace Systems Service Bulletin 47100-32-145, Revision 3, dated
March 26, 2021.
Note 1 to paragraph (j): After installing pivot pin retention
bolt part number NAS6204-14D, paragraphs (g), (h), and (i) of this
AD apply to pivot pin retention bolt part number NAS6204-14D.
(k) New Replacement
Within 8,000 flight hours or 48 months, whichever occurs first,
after the effective date of this AD, remove pivot pin linkage
components and replace pivot pin P/N 47127-1 or P/N 47127-3 and tow
fitting assembly P/N 47160-1 with pivot pin P/N 47127-5 and tow
fitting assembly P/N 47160-3, in accordance with Section 3.B. of the
Accomplishment Instructions of De Havilland Aircraft of Canada
Limited Service Bulletin 84-32-173, dated November 15, 2022,
including Collins Aerospace Service Bulletin 47100-32-153, dated
November 10, 2022. Accomplishing the replacement required by this
paragraph terminates the requirements of paragraphs (g), (h), (i),
and (j) of this AD.
(l) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(j) of this AD, if those actions were performed before July 8, 2022
(the effective date of AD 2022-11-11), using De Havilland Aircraft
of Canada Limited Service Bulletin 84-32-161, dated April 7, 2020,
including UTC Aerospace Systems Service Bulletin 47100-32-145, dated
April 3, 2020; or De Havilland Aircraft of Canada Limited Service
Bulletin 84-32-161, Revision A, dated January 27, 2021, including
UTC Aerospace Systems Service Bulletin 47100-32-145, Revision 2,
dated January 4, 2021.
(m) Parts Installation Prohibition
As of the effective date of this AD, no person may install pivot
pin P/N 47127-1 or P/N 47127-3 as a replacement part for pivot pin
P/N 47127-5 on De Havilland Aircraft of Canada Limited Model DHC-8-
401 and DHC-8-402 airplanes.
(n) Additional AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Validation 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 responsible Flight Standards Office, as
appropriate. If sending information directly to the manager of the
International Validation Branch, mail it to the address identified
in paragraph (o)(2) of this AD. Information may be emailed to: 9-
[email protected]. 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, International
Validation Branch, FAA; or Transport Canada; or De Havilland
Aircraft of Canada Limited's Transport Canada Design Approval
Organization (DAO). If approved by the DAO, the approval must
include the DAO-authorized signature.
(o) Additional Information
(1) For more information about this AD, contact Deep Gaurav,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 518-228-7300; email [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the address specified in
paragraph (p)(6) of this AD.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the material listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless this AD specifies otherwise.
(3) The following material was approved for IBR on August 21,
2024.
(i) De Havilland Aircraft of Canada Limited Service Bulletin 84-
32-173, dated November 15, 2022, including Collins Aerospace Service
Bulletin 47100-32-153, dated November 10, 2022.
Note 2 to paragraph (p)(3)(i): De Havilland issued De Havilland
Aircraft of Canada Limited Service Bulletin 84-32-173, dated
November 15, 2022, with Collins Aerospace Service Bulletin 47100-32-
153, dated November 10, 2022, attached as one ``merged'' file for
the convenience of affected operators.
(ii) [Reserved]
(4) The following material was approved for IBR on July 8, 2022
(87 FR 33627, June 3, 2022).
(i) De Havilland Aircraft of Canada Limited Service Bulletin 84-
32-161, Revision B, dated March 31, 2021, including UTC Aerospace
Systems Service Bulletin 47100-32-145, Revision 3, dated March 26,
2021.
Note 3 to paragraph (p)(4)(i): De Havilland issued De Havilland
Service Bulletin 84-32-161, Revision B, dated March 31, 2021, with
UTC Aerospace Systems Service Bulletin 47100-32-145, Revision 3,
dated March 26, 2021, attached as one ``merged'' file for the
convenience of affected operators.
(ii) [Reserved]
(5) The following material was approved for IBR on January 5,
2022 (86 FR 72174, December 21, 2021).
(i) De Havilland Aircraft of Canada Limited Service Bulletin 84-
32-167, dated August 12, 2021.
(ii) De Havilland Aircraft of Canada Limited Temporary Revision
ALI-0223, dated October 15, 2020.
(6) For De Havilland material identified in this AD, contact De
Havilland Aircraft of Canada Limited, Dash 8 Series Customer
Response Centre, 5800 Explorer Drive, Mississauga, Ontario, L4W 5K9,
Canada; telephone North America (toll-free): 855-310-1013, Direct:
647-277-5820; email dehavilland.com">thd@dehavilland.com; website dehavilland.com.
(7) 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.
(8) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations, or email [email protected].
Issued on July 10, 2024.
James D. Foltz,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-15656 Filed 7-16-24; 8:45 am]
BILLING CODE 4910-13-P
