Airworthiness Directives; Bombardier, Inc., Airplanes, 11722-11726 [2024-03047]
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11722
Federal Register / Vol. 89, No. 32 / Thursday, February 15, 2024 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
2019–16–11, Amendment 39–19714 (84
FR 45061, August 28, 2019); and
■ b. Adding the following new
Airworthiness Directive:
■
■
2024–01–08 Airbus SAS: Amendment 39–
22659; Docket No. FAA–2023–2136;
Project Identifier MCAI–2023–00759–T.
(a) Effective Date
This airworthiness directive (AD) is
effective March 21, 2024.
(b) Affected ADs
This AD replaces AD 2019–16–11,
Amendment 39–19714 (84 FR 45061, August
28, 2019) (AD 2019–16–11).
(c) Applicability
This AD applies to Airbus SAS Model
A300 F4–605R and F4–622R airplanes,
certificated in any category, as identified in
European Union Aviation Safety Agency
(EASA) AD 2023–0117, dated June 13, 2023
(EASA AD 2023–0117).
(d) Subject
Air Transport Association (ATA) of
America Code: 52, Doors.
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(e) Unsafe Condition
This AD was prompted by a report of two
adjacent frame forks that were found cracked
on the aft lower deck cargo door (LDCD) of
two airplanes during scheduled maintenance,
and a determination that certain compliance
times need to be revised. The FAA is also
issuing this AD to address the susceptibility
of the frame forks of affected LDCDs to
develop cracks, which could lead to
additional rupture of one or more LDCD
frame forks, compromising the structural
integrity of the LDCD and therefore of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2023–0117.
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(h) Exceptions to EASA AD 2023–0117
(1) Where EASA AD 2023–0117 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) Where Table 2 of EASA AD 2023–0117
refers to the effective date of EASA AD 2015–
0152R1, dated May 23, 2017, this AD
requires using November 5, 2018 (the
effective date of AD 2018–20–06,
Amendment 39–19440 (83 FR 49265, October
1, 2018)).
(3) Where Table 2 of EASA AD 2023–0117
refers to the effective date of EASA AD 2015–
0152, dated July 24, 2015, this AD requires
using January 26, 2017 (the effective date of
AD 2016–25–03, Amendment 39–18729 (81
FR 93801, December 22, 2016)).
(4) Where paragraph (6) of EASA AD 2023–
0117 uses the phrase ‘‘before next flight,
contact Airbus for approved corrective action
instructions, and within the compliance time
specified therein, accomplish those
instructions accordingly,’’ this AD requires
replacing those words with ‘‘repair cracking
before further flight using a method approved
by the Manager, International Validation
Branch, FAA; or EASA; or Airbus SAS’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.’’
(5) This AD does not adopt the ‘‘Remarks’’
section of EASA AD 2023–0117.
(i) No Reporting Requirement
Although the service information
referenced in EASA AD 2023–0117 specifies
to submit certain information to the
manufacturer, this AD does not include that
requirement.
(j) Additional AD Provisions
The following provisions also apply to this
AD:
(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 International Validation Branch, send
it to the attention of the person identified in
paragraph (k) of this AD. Information may be
emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, International Validation
Branch, FAA; or EASA; or Airbus SAS’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraphs (h)(4) and (j)(2) of
this AD, if any service information contains
procedures or tests that are identified as RC,
those procedures and tests must be done to
comply with this AD; any procedures or tests
that are not identified as RC are
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Sfmt 4700
recommended. Those procedures and tests
that are not identified as RC may be deviated
from using accepted methods in accordance
with the operator’s maintenance or
inspection program without obtaining
approval of an AMOC, provided the
procedures and tests identified as RC can be
done and the airplane can be put back in an
airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(k) Additional Information
For more information about this AD,
contact Dan Rodina, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone 206–
231–3225; email dan.rodina@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2023–0117, dated June 13, 2023.
(ii) [Reserved]
(3) For EASA AD 2023–0117, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; website
easa.europa.eu. You may find this EASA AD
on the EASA website ad.easa.europa.eu.
(4) You may view this service information
at the FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South 216th
Street, Des Moines, WA. For information on
the availability of this material at the FAA,
call 206–231–3195.
(5) 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 January 9, 2024.
Caitlin Locke,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–03080 Filed 2–14–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–2145; Project
Identifier MCAI–2023–00358–T; Amendment
39–22660; AD 2024–01–09]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Federal Register / Vol. 89, No. 32 / Thursday, February 15, 2024 / Rules and Regulations
ACTION:
Final rule.
The FAA is adopting a new
airworthiness directive (AD) for all
Bombardier, Inc., Model BD–100–1A10
airplanes. This AD was prompted by a
report of a steering control unit (SCU)
filter plate connector that does not meet
the certification requirements for
exposure of electronic components to
high intensity radiated field
environments, which could result in
malfunction of the nose wheel steering
(NWS) system. This AD requires
determining if the SCU is an affected
SCU, replacing all affected SCUs, and
rigging and testing the NWS control.
This AD also prohibits installing an
affected SCU on any airplane. The FAA
is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective March 21,
2024.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 21, 2024.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–2145; 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 service information identified
in this final rule, contact Bombardier
Business Aircraft Customer Response
Center, 400 Coˆte-Vertu Road West,
Dorval, Que´bec H4S 1Y9, Canada;
telephone 514–855–2999; email ac.yul@
aero.bombardier.com; website
bombardier.com.
• You may view this service
information at the FAA, Airworthiness
SUMMARY:
11723
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–
2023–2145.
Discussion of Final Airworthiness
Directive
FOR FURTHER INFORMATION CONTACT:
Conclusion
William Reisenauer, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590;
telephone 516–228–7301; email 9-avsnyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Bombardier, Inc., Model
BD–100–1A10 airplanes. The NPRM
published in the Federal Register on
November 13, 2023 (88 FR 77538). The
NPRM was prompted by AD CF–2023–
13, dated February 24, 2023, issued by
Transport Canada, which is the aviation
authority for Canada (referred to after
this as the MCAI). The MCAI states that
the manufacturer of SCU part number
(P/N) 46000–01 introduced a new filter
plate connector that does not meet the
certification requirements related to the
susceptibility of electronic components
to high intensity radiated field.
According to the MCAI, this noncompliant filter plate connector, if not
replaced, could result in a malfunction
of the NWS system and cause uncommanded steering or lateral
excursion from the runway.
In the NPRM, the FAA proposed to
require determining if the SCU is an
affected SCU, replacing all affected
SCUs, and rigging and testing the NWS
control. In the NPRM, the FAA also
proposed to prohibit installing an
affected SCU on any airplane. 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–2023–2145.
Comments
The FAA received no comments on
the NPRM or on the determination of
the cost to the public.
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.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Bombardier
Service Bulletin 100–32–34, dated
October 18, 2021, and Bombardier
Service Bulletin 350–32–010, dated
October 18, 2021. This service
information specifies procedures for
determining the serial number of SCU
P/N 46000–01, replacing any affected
SCU, and rigging and testing the NWS
control. These documents are distinct
since they apply to different airplane
serial numbers. 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 725 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
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
9 work-hours × $85 per hour = $765 ..........................................................................................
$44,950
$45,715
$33,143,375
The FAA has included all known
costs in its cost estimate. According to
the manufacturer, however, some of the
costs of this AD may be covered under
warranty, thereby reducing the cost
impact on affected operators.
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
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
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Federal Register / Vol. 89, No. 32 / Thursday, February 15, 2024 / Rules and Regulations
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(a) Effective Date
(2) Will not affect intrastate aviation
in Alaska, and
This airworthiness directive (AD) is
effective March 21, 2024.
(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.
(b) Affected ADs
VerDate Sep<11>2014
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None.
(c) Applicability
This AD applies to all Bombardier, Inc.,
Model BD–100–1A10 airplanes, certificated
in any category.
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Fmt 4700
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing gear.
(e) Unsafe Condition
This AD was prompted by a report of a
steering control unit (SCU) filter plate
connector that does not meet the certification
requirements for exposure of electronic
components to high intensity radiated field
environments. The FAA is issuing this AD to
prevent malfunction of the nose wheel
steering (NWS) system. The unsafe condition,
if not addressed, could result in uncommanded steering or lateral runway
excursion.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection or Records Review
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2024–01–09 Bombardier, Inc.: Amendment
39–22660; Docket No. FAA–2023–2145;
Project Identifier MCAI–2023–00358–T.
For the reasons discussed above, I
certify that this AD:
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List of Subjects in 14 CFR Part 39
Sfmt 4700
Within 24 months after the effective date
of this AD: Inspect the SCU to determine if
SCU part number (P/N) 46000–01 with a
serial number listed in Figure 1 to paragraph
(g) of this AD is installed on the airplane. A
review of the airplane maintenance records is
acceptable in lieu of the inspection if the
SCU P/N and serial number can be
conclusively determined from that review. If
an SCU P/N 46000–01 with a serial number
listed in Figure 1 to paragraph (g) of this AD
is not installed on the airplane, or if the SCU
identification plate is marked with SB100–
32–030, then no further action is required by
this AD; however, the installation prohibition
in paragraph (i) of this AD still applies.
Figure 1 to Paragraph (g)—Affected SCU
Serial Numbers
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Federal Register / Vol. 89, No. 32 / Thursday, February 15, 2024 / Rules and Regulations
11725
06-188, 16042190, 16047519, 16047521, 16047522, 17053050, 17053052,
17054845, 17054846, 17054847, 17055273, 17055274, 18057933, 18057934,
18058184, 18058185, 18058599, 18058600, 18058601, 18058602, 18058884,
18058885, 18058886, 18059357, 18059358, 18059359, 18059360, 18059814,
18059815, 18059816, 18059817, 18060201, 18060202, 18060582, 18060789,
18060982, 18060983, 18061292, 18061572, 18061573, 18061770, 18061771,
18061880, 18061881, 18061995, 18061996, 18062731, 18062732, 18062733,
18062734, 18063183, 18063184, 18063520, 18063521, 18064776, 18064777,
18064778, 18064779, 18065323, 18065324, 18065325, 18065326, 18065327,
18065331, 18065332, 19068045, 19068046, 19068047, 19068048, 19068049,
19068050, 19068051, 19068052, 19068053, 19068054, 19068055, 19068056,
19068057, 19068058, 19068059, 19068060, 19068061, 19068062, 19068063,
19068064, 19068065, 19068066, 19068067, 19068068, 19068069, 19068070,
19068071, 19068072, 19068073, 19068074, 19072062, 19072063, 19072067,
19072068, 19072069, 19072070, 19072071, 19072072, 19072073, 19072074,
19072075, 19072076, 19072077, 19072078, 19075712, 19075713, 19075714,
19075715, 19075716, 19075718, 19075719,20077461,20077462,20077463,
20077464,20077465,20077466,20077467,20077470,20077472,20077473,
20077474,20077476,20077477,20077478,20077480.
For airplanes with SCU P/N 46000–01 with
a serial number listed in Figure 1 to
paragraph (g) of this AD installed and not
marked on the SCU identification plate with
SB100–32–030: Within 24 months after the
effective date of this AD, replace the SCU and
rig and test the NWS control, in accordance
with the instructions in paragraph (h)(1), (2),
or (3) of this AD, as applicable.
(1) For airplane serial numbers 20001
through 20500 inclusive: Steps 2.C.(1) and
2.C.(3) of Section 2.C., ‘‘Part B—
Modification,’’ and Section 2.D., ‘‘Testing,’’
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16:35 Feb 14, 2024
Jkt 262001
of the Accomplishment Instructions in
Bombardier Service Bulletin 100–32–34,
dated October 18, 2021.
(2) For airplane serial numbers 20501
through 20893 inclusive: Steps 2.C.(1) and
2.C.(3) of Section 2.C., ‘‘Part B—
Modification,’’ and Section 2.D., ‘‘Testing,’’
of the Accomplishment Instructions in
Bombardier Service Bulletin 350–32–010,
dated October 18, 2021.
(3) For airplane serial numbers 20894 and
larger: A method approved by the Manager,
International Validation Branch, FAA; or
Transport Canada; or Bombardier, Inc.’s
Transport Canada Design Approval
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Organization (DAO). If approved by the DAO,
the approval must include the DAOauthorized signature.
(i) Parts Installation Prohibition
As of the effective date of this AD, do not
install SCU P/N 46000–01 on any airplane if
the serial number of the SCU is listed in
figure 1 to paragraph (g) of this AD, unless
the SCU identification plate has been marked
with SB100–32–030.
(j) Additional AD Provisions
The following provisions also apply to this
AD:
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ER15FE24.018</GPH>
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(h) Replacement
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Federal Register / Vol. 89, No. 32 / Thursday, February 15, 2024 / Rules and Regulations
(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 (k)(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
Bombardier, Inc.’s Transport Canada Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(k) Additional Information
(1) Refer to Transport Canada AD CF–
2023–13, dated February 24, 2023, for related
information. This Transport Canada AD may
be found in the AD docket at regulations.gov
under Docket No. FAA–2023–2145.
(2) For more information about this AD,
contact William Reisenauer, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone 516–
228–7301; email 9-avs-nyaco-cos@faa.gov.
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(l) 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 this AD specifies otherwise.
(i) Bombardier Service Bulletin 100–32–34,
dated October 18, 2021.
(ii) Bombardier Service Bulletin 350–32–
010, dated October 18, 2021.
(3) For service information identified in
this AD, contact Bombardier Business
Aircraft Customer Response Center, 400 CoˆteVertu Road West, Dorval, Que´bec H4S 1Y9,
Canada; telephone 514–855–2999; email
ac.yul@aero.bombardier.com; website
bombardier.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 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.
VerDate Sep<11>2014
16:35 Feb 14, 2024
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Issued on January 9, 2024.
Caitlin Locke,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–03047 Filed 2–14–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 31530; Amdt. No. 4099]
Standard Instrument Approach
Procedures, and Takeoff Minimums
and Obstacle Departure Procedures;
Miscellaneous Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This rule establishes, amends,
suspends, or removes Standard
Instrument Approach Procedures
(SIAPS) and associated Takeoff
Minimums and Obstacle Departure
procedures (ODPs) for operations at
certain airports. These regulatory
actions are needed because of the
adoption of new or revised criteria, or
because of changes occurring in the
National Airspace System, such as the
commissioning of new navigational
facilities, adding new obstacles, or
changing air traffic requirements. These
changes are designed to provide safe
and efficient use of the navigable
airspace and to promote safe flight
operations under instrument flight rules
at the affected airports.
DATES: This rule is effective February
15, 2024. The compliance date for each
SIAP, associated Takeoff Minimums,
and ODP is specified in the amendatory
provisions.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of February
15, 2024.
ADDRESSES: Availability of matters
incorporated by reference in the
amendment is as follows:
SUMMARY:
For Examination
1. U.S. Department of Transportation,
Docket Ops–M30. 1200 New Jersey
Avenue SE, West Bldg., Ground Floor,
Washington, DC 20590–0001.
2. The FAA Air Traffic Organization
Service Area in which the affected
airport is located;
3. The office of Aeronautical
Information Services, 6500 South
MacArthur Blvd., Oklahoma City, OK
73169 or,
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4. 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.
Availability
All SIAPs and Takeoff Minimums and
ODPs are available online free of charge.
Visit the National Flight Data Center at
nfdc.faa.gov to register. Additionally,
individual SIAP and Takeoff Minimums
and ODP copies may be obtained from
the FAA Air Traffic Organization
Service Area in which the affected
airport is located.
FOR FURTHER INFORMATION CONTACT:
Thomas J. Nichols, Flight Procedures
and Airspace Group, Flight
Technologies and Procedures Division,
Flight Standards Service, Federal
Aviation Administration. Mailing
Address: FAA Mike Monroney
Aeronautical Center, Flight Procedures
and Airspace Group, 6500 South
MacArthur Blvd., STB Annex, Bldg. 26,
Room 217, Oklahoma City, OK 73099.
Telephone (405) 954–1139.
This rule
amends 14 CFR part 97 by establishing,
amending, suspending, or removes
SIAPS, Takeoff Minimums and/or
ODPS. The complete regulatory
description of each SIAP and its
associated Takeoff Minimums or ODP
for an identified airport is listed on FAA
form documents which are incorporated
by reference in this amendment under 5
U.S.C. 552(a), 1 CFR part 51, and 14
CFR 97.20. The applicable FAA Forms
8260–3, 8260–4, 8260–5, 8260–15A,
8260–15B, when required by an entry
on 8260–15A, and 8260–15C.
The large number of SIAPs, Takeoff
Minimums and ODPs, their complex
nature, and the need for a special format
make publication in the Federal
Register expensive and impractical.
Further, pilots do not use the regulatory
text of the SIAPs, Takeoff Minimums or
ODPs, but instead refer to their graphic
depiction on charts printed by
publishers or aeronautical materials.
Thus, the advantages of incorporation
by reference are realized and
publication of the complete description
of each SIAP, Takeoff Minimums and
ODP listed on FAA form documents is
unnecessary. This amendment provides
the affected CFR sections and specifies
the types of SIAPS, Takeoff Minimums
and ODPs with their applicable effective
dates. This amendment also identifies
the airport and its location, the
procedure, and the amendment number.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\15FER1.SGM
15FER1
]]>Agencies
[Federal Register Volume 89, Number 32 (Thursday, February 15, 2024)]
[Rules and Regulations]
[Pages 11722-11726]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-03047]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2145; Project Identifier MCAI-2023-00358-T;
Amendment 39-22660; AD 2024-01-09]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 11723]]
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by
a report of a steering control unit (SCU) filter plate connector that
does not meet the certification requirements for exposure of electronic
components to high intensity radiated field environments, which could
result in malfunction of the nose wheel steering (NWS) system. This AD
requires determining if the SCU is an affected SCU, replacing all
affected SCUs, and rigging and testing the NWS control. This AD also
prohibits installing an affected SCU on any airplane. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective March 21, 2024.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 21,
2024.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-2145; 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 service information identified in this final rule,
contact Bombardier Business Aircraft Customer Response Center, 400
C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada;
telephone 514-855-2999; email bombardier.com">ac.yul@aero.bombardier.com; website
bombardier.com.
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. It is also available at
regulations.gov under Docket No. FAA-2023-2145.
FOR FURTHER INFORMATION CONTACT: William Reisenauer, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 516-228-7301; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all Bombardier, Inc.,
Model BD-100-1A10 airplanes. The NPRM published in the Federal Register
on November 13, 2023 (88 FR 77538). The NPRM was prompted by AD CF-
2023-13, dated February 24, 2023, issued by Transport Canada, which is
the aviation authority for Canada (referred to after this as the MCAI).
The MCAI states that the manufacturer of SCU part number (P/N) 46000-01
introduced a new filter plate connector that does not meet the
certification requirements related to the susceptibility of electronic
components to high intensity radiated field. According to the MCAI,
this non-compliant filter plate connector, if not replaced, could
result in a malfunction of the NWS system and cause un-commanded
steering or lateral excursion from the runway.
In the NPRM, the FAA proposed to require determining if the SCU is
an affected SCU, replacing all affected SCUs, and rigging and testing
the NWS control. In the NPRM, the FAA also proposed to prohibit
installing an affected SCU on any airplane. 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-2023-2145.
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.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Bombardier Service Bulletin 100-32-34, dated
October 18, 2021, and Bombardier Service Bulletin 350-32-010, dated
October 18, 2021. This service information specifies procedures for
determining the serial number of SCU P/N 46000-01, replacing any
affected SCU, and rigging and testing the NWS control. These documents
are distinct since they apply to different airplane serial numbers.
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 725 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.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
9 work-hours x $85 per hour = $765........................... $44,950 $45,715 $33,143,375
----------------------------------------------------------------------------------------------------------------
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators.
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
[[Page 11724]]
44701: General requirements. Under that section, Congress charges the
FAA with promoting safe flight of civil aircraft in air commerce by
prescribing regulations for practices, methods, and procedures the
Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses
an unsafe condition that is likely to exist or develop on products
identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2024-01-09 Bombardier, Inc.: Amendment 39-22660; Docket No. FAA-
2023-2145; Project Identifier MCAI-2023-00358-T.
(a) Effective Date
This airworthiness directive (AD) is effective March 21, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Bombardier, Inc., Model BD-100-1A10
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
gear.
(e) Unsafe Condition
This AD was prompted by a report of a steering control unit
(SCU) filter plate connector that does not meet the certification
requirements for exposure of electronic components to high intensity
radiated field environments. The FAA is issuing this AD to prevent
malfunction of the nose wheel steering (NWS) system. The unsafe
condition, if not addressed, could result in un-commanded steering
or lateral runway excursion.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection or Records Review
Within 24 months after the effective date of this AD: Inspect
the SCU to determine if SCU part number (P/N) 46000-01 with a serial
number listed in Figure 1 to paragraph (g) of this AD is installed
on the airplane. A review of the airplane maintenance records is
acceptable in lieu of the inspection if the SCU P/N and serial
number can be conclusively determined from that review. If an SCU P/
N 46000-01 with a serial number listed in Figure 1 to paragraph (g)
of this AD is not installed on the airplane, or if the SCU
identification plate is marked with SB100-32-030, then no further
action is required by this AD; however, the installation prohibition
in paragraph (i) of this AD still applies.
Figure 1 to Paragraph (g)--Affected SCU Serial Numbers
[[Page 11725]]
[GRAPHIC] [TIFF OMITTED] TR15FE24.018
(h) Replacement
For airplanes with SCU P/N 46000-01 with a serial number listed
in Figure 1 to paragraph (g) of this AD installed and not marked on
the SCU identification plate with SB100-32-030: Within 24 months
after the effective date of this AD, replace the SCU and rig and
test the NWS control, in accordance with the instructions in
paragraph (h)(1), (2), or (3) of this AD, as applicable.
(1) For airplane serial numbers 20001 through 20500 inclusive:
Steps 2.C.(1) and 2.C.(3) of Section 2.C., ``Part B--Modification,''
and Section 2.D., ``Testing,'' of the Accomplishment Instructions in
Bombardier Service Bulletin 100-32-34, dated October 18, 2021.
(2) For airplane serial numbers 20501 through 20893 inclusive:
Steps 2.C.(1) and 2.C.(3) of Section 2.C., ``Part B--Modification,''
and Section 2.D., ``Testing,'' of the Accomplishment Instructions in
Bombardier Service Bulletin 350-32-010, dated October 18, 2021.
(3) For airplane serial numbers 20894 and larger: A method
approved by the Manager, International Validation Branch, FAA; or
Transport Canada; or Bombardier, Inc.'s Transport Canada Design
Approval Organization (DAO). If approved by the DAO, the approval
must include the DAO-authorized signature.
(i) Parts Installation Prohibition
As of the effective date of this AD, do not install SCU P/N
46000-01 on any airplane if the serial number of the SCU is listed
in figure 1 to paragraph (g) of this AD, unless the SCU
identification plate has been marked with SB100-32-030.
(j) Additional AD Provisions
The following provisions also apply to this AD:
[[Page 11726]]
(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 (k)(2) of this AD. Information may be emailed to: [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 Bombardier, Inc.'s
Transport Canada Design Approval Organization (DAO). If approved by
the DAO, the approval must include the DAO-authorized signature.
(k) Additional Information
(1) Refer to Transport Canada AD CF-2023-13, dated February 24,
2023, for related information. This Transport Canada AD may be found
in the AD docket at regulations.gov under Docket No. FAA-2023-2145.
(2) For more information about this AD, contact William
Reisenauer, Aviation Safety Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone 516-228-7301; email [email protected].
(l) 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 this AD specifies otherwise.
(i) Bombardier Service Bulletin 100-32-34, dated October 18,
2021.
(ii) Bombardier Service Bulletin 350-32-010, dated October 18,
2021.
(3) For service information identified in this AD, contact
Bombardier Business Aircraft Customer Response Center, 400
C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada;
telephone 514-855-2999; email bombardier.com">ac.yul@aero.bombardier.com; website
bombardier.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 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 January 9, 2024.
Caitlin Locke,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2024-03047 Filed 2-14-24; 8:45 am]
BILLING CODE 4910-13-P
