Airworthiness Directives; Bombardier, Inc., Airplanes, 34961-34982 [2024-09341]
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Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
List of Subjects
Subpart L—Methodology and
Formulas for Allocation of Loan and
Grant Program Funds
7 CFR Part 1780
Community development,
Community facilities, Grant programs—
housing and community development,
Loan programs—housing and
community development, Reporting and
recordkeeping requirements, Rural
areas, Waste treatment and disposal,
Water supply, Watersheds.
7 CFR Part 1940
Administrative practice and
procedure, Agriculture, Environmental
protection, Flood plains, Grant
programs—agriculture, Grant
programs—housing and community
development, Loan programs—
agriculture, Loan programs—housing
and community development, Low and
moderate income housing, Reporting
and recordkeeping requirements, Rural
areas, Truth in lending.
§ 1940.585
Community Facility loans.
*
*
*
*
*
(b) * * *
(2) The data source for the first
criterion is the most recent decennial
Census data. The data source for the
second and third criteria is the 5-year
data from the American Community
Survey (ACS). Each criterion is assigned
a specific weight according to its
relevance in determining need. The
percentage representing each criterion is
multiplied by the weight factor and
summed to arrive at a State factor (SF).
The SF cannot exceed 0.05.
Equation 1 to Paragraph (b)
Accordingly, for the reasons
discussed in the preamble, the Agency
amends 7 CFR parts 1780 and 1940 as
follows:
SF = (criterion (b)(1)(i) × 50 percent) +
(criterion (b)(1)(ii) × 25 percent) +
(criterion (b)(1)(iii) × 25 percent)
*
*
*
*
*
PART 1780—WATER AND WASTE
LOANS AND GRANTS
■
1. The authority citation for part 1780
continues to read as follows:
§ 1940.588 Business and Industry
Guaranteed and Direct Loans, Rural
Business Development Grants, and
Intermediary Relending Program.
5. Amend § 1940.588 by revising
paragraph (a)(2)(ii)(C) to read as follows:
■
Authority: 5 U.S.C. 301; 7 U.S.C. 1989; 16
U.S.C. 1005.
Subpart A—General Policies and
Requirements
2. Amend § 1780.18 by revising
paragraphs (c)(2)(ii)(B) and (C) to read as
follows:
■
§ 1780.18
Allocation of program funds.
*
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4. Amend § 1940.585 by revising
paragraph (b)(2) to read as follows:
■
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*
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*
(c) * * *
(2) * * *
(ii) * * *
(B) For the criterion specified in
paragraph (b)(2)(i)(B) of this section,
5-year income data from the American
Community Survey (ACS).
(C) For the criterion specified in
paragraph (b)(2)(i)(C) of this section, the
5-year data from the ACS.
*
*
*
*
*
PART 1940—GENERAL
3. The authority citation for part 1940
continues to read as follows:
■
Authority: 5 U.S.C. 301; 7 U.S.C. 1989;
and 42 U.S.C. 1480.
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*
*
*
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*
(a) * * *
(2) * * *
(ii) * * *
(C) For the criterion specified in
paragraph (a)(2)(i)(C) of this section, the
5-year data from the ACS.
*
*
*
*
*
6. Amend § 1940.591 by revising
paragraph (b)(2) to read as follows:
■
§ 1940.591 Community Program
Guaranteed loans.
*
*
*
*
*
(b) * * *
(2) The data source for the first
criterion is the most recent decennial
Census data. The data source for the
second and third criteria is the 5-year
data from the American Community
Survey (ACS). Each criterion is assigned
a specific weight according to its
relevance in determining need. The
percentage representing each criterion is
multiplied by the weight factor and
summed to arrive at a State factor (SF).
The SF cannot exceed 0.05.
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34961
Equation 1 to Paragraph (b)
SF = (criterion (b)(1)(i) × 50 percent) +
(criterion (b)(1)(ii) × 25 percent) +
(criterion (b)(1)(iii) × 25 percent)
*
*
*
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Basil I. Gooden,
Under Secretary, USDA, Rural Development.
[FR Doc. 2024–09446 Filed 4–30–24; 8:45 am]
BILLING CODE 3410–15–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–2139; Project
Identifier MCAI–2023–00435–T; Amendment
39–22713; AD 2024–06–08]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model BD–700–2A12
airplanes. This AD was prompted by
reports from the supplier that some
overheat detection sensing elements of
the bleed air leak detection system were
manufactured with insufficient salt fill,
which can result in an inability to detect
hot bleed air leaks. This AD requires
maintenance records verification, and if
an affected part is installed, prohibits
the use of certain Master Minimum
Equipment List (MMEL) items under
certain conditions by requiring revising
the operator’s existing Minimum
Equipment List (MEL). This AD also
requires testing the overheat detection
sensing elements, marking each
serviceable sensing element with a
witness mark, and replacing each
nonserviceable part with a serviceable
part. This AD also prohibits the
installation of affected parts under
certain conditions. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective June 5, 2024.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 5, 2024.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–2139; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
SUMMARY:
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AD CF–2023–18) (also referred to as the
MCAI). The MCAI states that
Bombardier received reports from the
supplier of the overheat detection
sensing elements of a manufacturing
quality escape. Some of the sensing
elements of the bleed air leak detection
system were manufactured with
insufficient salt fill. This condition can
result in an inability to detect hot bleed
air leaks, which can cause damage to
surrounding structures and systems and
prevent continued safe flight and
landing.
In the NPRM, the FAA proposed to
require maintenance records
verification, and if an affected part is
installed, prohibit the use of certain
MMEL items under certain conditions
by requiring revising the operator’s
existing MEL. The NPRM also proposed
to require testing the overheat detection
sensing elements, marking each
serviceable sensing element with a
witness mark, and replacing each
nonserviceable part with a serviceable
part. The NPRM also proposed to
prohibit the installation of affected parts
under certain conditions. 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–2023–2139.
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 Bombardier 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.
• For Liebherr-Aerospace Toulouse
SAS service information identified in
this final rule, contact LiebherrAerospace Toulouse SAS, 408, Avenue
des Etats-Unis—B.P.52010, 31016
Toulouse Cedex, France; telephone +33
(0)5.61.35.28.28; fax +33
(0)5.61.35.29.29; email:
techpub.toulouse@liebherr.com;
website: www.liebherr.aero.
• 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. It is also available in
the AD docket at regulations.gov under
Docket No. FAA–2023–2139.
FOR FURTHER INFORMATION CONTACT:
Steven Dzierzynski, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590;
telephone: 516–228–7300; email: 9-avsnyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion of Final Airworthiness
Directive
Comments
The FAA received a comment from
NetJets. The following presents the
comment received on the NPRM and the
FAA’s response to the comment.
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Bombardier, Inc., Model
BD–700–2A12 airplanes. The NPRM
published in the Federal Register on
November 8, 2023 (88 FR 77044). The
NPRM was prompted by AD CF–2023–
18, dated March 9, 2023, issued by
Transport Canada, which is the aviation
authority for Canada (Transport Canada
Request for Clarification on Location of
Date of Manufacture
NetJets requested a statement be
added to paragraph (h) of the proposed
AD indicating that the date of
manufacture can be found in the aircraft
maintenance logbook, in addition to the
identification plate of the airplane on
certain airplanes. This information is
stated in Transport Canada AD CF–
2023–18, Part II, paragraph A. NetJets
further stated that Bombardier no longer
stamps a date on the airframe data plate.
The FAA agrees the date of
manufacture can be found either on the
identification plate of certain airplanes
or in the aircraft maintenance logbook.
The FAA has amended paragraph (h) of
this AD to specify the two locations
where the date of manufacture can be
found.
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, considered
the comment received, and determined
that air safety requires adopting this AD
as proposed. Accordingly, the FAA is
issuing this AD to address the unsafe
condition on this product. Except for
minor editorial changes, and any other
changes described previously, this AD is
adopted as proposed in the NPRM.
None of the changes will increase the
economic burden on any operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Liebherr Service
Bulletin CFD–F1958–26–01, dated May
6, 2022, which specifies part numbers
for affected sensing elements.
The FAA reviewed Bombardier
Service Bulletin 700–36–7503, dated
December 23, 2022, which specifies
procedures for testing each leak
detection loop (LDL) sensing element
installed on the airplane, marking each
serviceable sensing element with a
witness mark, and replacing each
nonserviceable part with a serviceable
part.
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 19 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
Up to 214 work-hours × $85 per hour = Up to $18,190 ..................................................
$0
Up to $18,190 .....
The FAA has received no definitive
data on which to base the cost estimates
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for the on-condition actions specified in
this AD. The FAA estimates it takes up
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Cost on U.S.
operators
Up to $345,610.
to 1.5 hours to replace a sensing
element.
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Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
The FAA has included all known
costs in its cost estimate. According to
the manufacturer, however, some or all
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected operators.
1. The authority citation for part 39
continues to read as follows:
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Accordingly, under the authority
delegated to me by the Administrator,
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PART 39—AIRWORTHINESS
DIRECTIVES
■
Authority for This Rulemaking
The Amendment
the FAA amends 14 CFR part 39 as
follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2024–06–08 Bombardier, Inc.: Amendment
39–22713; Docket No. FAA–2023–2139;
Project Identifier MCAI–2023–00435–T.
(a) Effective Date
This airworthiness directive (AD) is
effective June 5, 2024.
(b) Affected ADs
None.
This AD applies to Bombardier, Inc.,
Model BD–700–2A12 airplanes, certificated
in any category, having serial numbers 70005
and subsequent.
(d) Subject
Air Transport Association (ATA) of
America Code: 36, Pneumatic.
(e) Unsafe Condition
This AD was prompted by reports that
some overheat detection sensing elements of
the bleed air leak detection system were
manufactured with insufficient salt fill. The
FAA is issuing this AD to address nonconforming sensing elements of the bleed air
leak detection system. The unsafe condition,
if not addressed, could result in an inability
to detect hot bleed air leaks and consequent
damage to surrounding structures and
systems, which could prevent continued safe
flight and landing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Definitions
For the purpose of this AD, the definitions
specified in paragraphs (g)(1) and (2) of this
AD apply.
(1) An affected part is a sensing element
marked with a date code before A2105 and
having an LTS/Kidde part number specified
in Liebherr Service Bulletin CFD–F1958–26–
01, dated May 6, 2022, unless that sensing
element meets the criteria specified in
paragraph (g)(1)(i) or (ii) of this AD.
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(i) The sensing element has been tested as
specified in Section 3 of the Accomplishment
Instructions of Kidde Aerospace and Defense
Service Bulletin CFD–26–1, Revision 6, dated
February 28, 2022, or earlier revisions, and
has been found to be serviceable; and the
sensing element has been marked on one face
of its connector hex nut and packaged as
specified in Section 3.C. of the
Accomplishment Instructions of Kidde
Aerospace and Defense Service Bulletin
CFD–26–1, Revision 6, dated February 28,
2022, or earlier revisions.
(ii) The sensing element has been tested
and found to be serviceable as specified in
paragraph (j) of this AD; and the sensing
element has been marked on one face of one
connector hex nut with one green mark, as
specified in Figure 33 of Bombardier Service
Bulletin 700–36–7503, dated December 23,
2022, as applicable (the figure is
representative for all sensing elements).
(2) A serviceable part is a sensing element
that is not an affected part.
(h) Maintenance Records Verification
(c) Applicability
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For airplane serial numbers 70097 and
subsequent whose airplane date of
manufacture, as identified on the
identification plate of the airplane or in the
aircraft maintenance logbook, is on or before
the effective date of this AD: Within 60 days
after the effective date of this AD, examine
the airplane maintenance records to verify
whether any affected part has been installed
since the airplane date of manufacture, as
identified on the identification plate of the
airplane or in the aircraft maintenance
logbook.
(1) If the maintenance records confirms
that an affected part has been installed, or if
it cannot be confirmed that an affected part
has not been installed, paragraphs (i) and (j)
of this AD must be complied with within the
compliance time specified in paragraphs (i)
and (j) of this AD.
(2) If the maintenance records confirm that
no affected parts have been installed since
airplane date of manufacture, then
paragraphs (i) and (j) of this AD are not
applicable.
(i) Minimum Equipment List (MEL) Revision
For all airplanes: Within 90 days after the
effective date of this AD, revise the operator’s
existing MEL by incorporating the
information specified in figures 1 through 7
to paragraph (i) of this AD, as applicable.
This may be done by inserting a copy of this
information into the operator’s existing MEL.
Figure 1 to Paragraph (i)—MMEL Item 21–
0425
BILLING CODE 4910–13–P
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MMEL Item 21-0425
Crew Alerting System
1. Repair
(CAS) Message
Category
21 AIR COND / PRESS -
2. Dispatch Consideration
(0) May be displayed provided none of the
C
TRIM LOOP ONE
following messages are displayed:
ELEMENT INOP
- 21 AIR COND / PRESS - IASC lB INOP
- 21 AIR COND / PRESS - IASC 2B INOP
-21 AIR COND / PRESS-IASC lB FAULT
-21 AIR COND / PRESS-IASC 2B FAULT
1. OPERATIONS (0)
Before each flight:
(1) Make sure that the airplane is not powered on and that engines and APU are OFF.
a. Connect electrical power to the airplane as follows:
Note: Do not use a Jet Airstart Cart or High Pressure Ground Cart.
1.
Connect external AC power, OR
11.
Start the APU as follows:
switches to ON.
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1. On the ELECTRICAL control panel, set the MAIN BATT and APU BATT
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34965
2. On the BLEED/AIR COND control panel, make sure that the APU
BLEED switch is set to OFF.
3. On the APU control panel, tum the APU switch to START.
b. When external AC power is on or APU is running, wait a minimum of 6 minutes.
c. After 6 minutes, check for the 21 AIR COND / PRESS - TRIM LOOP ONE
ELEMENT INOP info message as follows:
1.
If the 21 AIR COND / PRESS-TRIM LOOP ONE ELEMENT INOP info
message shows - DISPATCH IS PERMITTED.
Note: The INFO message confirms it is not heat related and therefore cannot be
a potential leak in the presence of an affected part.
n. If the 21 AIR COND / PRESS - TRIM LOOP ONE ELEMENT INOP info
message does not show-DISPATCH IS NOT PERMITTED.
Note: No INFO message confirms that it is heat related and therefore could be
a potential leak in the presence of an affected part.
d. If required, remove external AC power from the airplane.
e. If required, set APU BLEED to AUTO.
(2) On the INFO synoptic page, make sure that the messages that follow do not show:
-21 AIR COND / PRESS-IASC lB INOP info
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Note: Confirm the airplane has electrical power to activate the synoptic page.
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- 21 AIR COND / PRESS - IASC 2B INOP info
-21 AIR COND / PRESS-IASC lB FAULT info
-21 AIR COND / PRESS-IASC 2B FAULT info
Figure 2 to Paragraph (ii)—MMEL Item 30–
0055
MMEL Item 30-0055
1. Repair
CAS Message
2. Dispatch Consideration
Category
30 ICE PROT - L WING
C
LOOP ONE ELEMENT
(0) May be displayed provided none of the
following messages are displayed:
INOP
- 21 AIR COND / PRESS -IASC lB INOP
- 21 AIR COND / PRESS - IASC 2B INOP
-21 AIR COND / PRESS-IASC lB FAULT
-21 AIR COND / PRESS-IASC 2B FAULT
1. OPERATIONS (0)
Before each flight:
ER01MY24.022</GPH>
a. Connect electrical power to the airplane as follows:
Note: Do not use a Jet Airstart Cart or High Pressure Ground Cart.
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(1) Make sure that the airplane is not powered on and that engines and APU are OFF.
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1.
Connect external AC power, OR
11.
Start the APU as follows:
34967
1. On the ELECTRICAL control panel, set the MAIN BATT and APU BATT
switches to ON.
2. On the BLEED/AIR COND control panel, make sure that the APU
BLEED switch is set to OFF.
3. On the APU control panel, turn the APU switch to START.
b. When external AC power is on or APU is running, wait a minimum of 6 minutes.
c. After 6 minutes, check for the 30 ICE PROT - L WING LOOP ONE ELEMENT
INOP info message as follows:
i.
If the 30 ICE PROT - L WING LOOP ONE ELEMENT INOP info message
shows - DISPATCH IS PERMITTED.
Note: The INFO message confirms it is not heat related and therefore cannot be
a potential leak in the presence of an affected part.
11.
If the 30 ICE PROT-L WING LOOP ONE ELEMENT INOP info message
does not show - DISPATCH IS NOT PERMITTED.
Note: No INFO message confirms that it is heat related and therefore could be
a potential leak in the presence of an affected part.
e. If required, set APU BLEED to AUTO.
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d. If required, remove external AC power from the airplane.
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(2) On the INFO synoptic page, make sure that the messages that follow do not show:
Note: Confirm the airplane has electrical power to activate the synoptic page.
- 21 AIR COND / PRESS -IASC lB INOP info
- 21 AIR COND / PRESS - IASC 2B INOP info
-21 AIR COND / PRESS-IASC lB FAULT info
- 21 AIR COND / PRESS - IASC 2B FAULT info
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Figure 3 to Paragraph (i)—MMEL Item 30–
0060
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34969
MMEL Item 30-0060
1. Repair
CAS Message
2. Dispatch Consideration
Category
30 ICE PROT - L WIPS
(0) May be displayed provided none of the
C
LOOP ONE ELEMENT
following messages are displayed:
INOP
- 21 AIR COND / PRESS - IASC lB INOP
- 21 AIR COND / PRESS - IASC 2B INOP
-21 AIR COND / PRESS-IASC lB FAULT
-21 AIR COND / PRESS-IASC 2B FAULT
1. OPERATIONS (0)
Before each flight:
(1) Make sure that the airplane is not powered on and that engines and APU are OFF.
a. Connect electrical power to the airplane as follows:
Note: Do not use a Jet Airstart Cart or High Pressure Ground Cart.
1.
Connect external AC power, OR
11.
Start the APU as follows:
1. On the ELECTRICAL control panel, set the MAIN BATT and APU BATT
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01MYR1
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switches to ON.
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2. On the BLEED/AIR COND control panel, make sure that the APU
BLEED switch is set to OFF.
3. On the APU control panel, tum the APU switch to START.
b. When external AC power is on or APU is running, wait a minimum of 6 minutes.
c. After 6 minutes, check for the 30 ICE PROT - L WIPS LOOP ONE ELEMENT INOP
info message as follows:
1.
If the 30 ICE PROT - L WIPS LOOP ONE ELEMENT INOP info message
shows-DISPATCH IS PERMITTED.
Note: The INFO message confirms it is not heat related and therefore cannot be
a potential leak in the presence of an affected part.
n. If the 30 ICE PROT - L WIPS LOOP ONE ELEMENT INOP info message
does not show - DISPATCH IS NOT PERMITTED.
Note: No INFO message confirms that it is heat related and therefore could be
a potential leak in the presence of an affected part.
d. If required, remove external AC power from the airplane.
e. If required, set APU BLEED to AUTO.
(2) On the INFO synoptic page, make sure that the messages that follow do not show:
-21 AIR COND / PRESS-IASC lB INOP info
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ddrumheller on DSK120RN23PROD with RULES1
Note: Confirm the airplane has electrical power to activate the synoptic page.
Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
34971
- 21 AIR COND / PRESS - IASC 2B INOP info
-21 AIR COND / PRESS-IASC lB FAULT info
-21 AIR COND / PRESS-IASC 2B FAULT info
Figure 4 to Paragraph (i)—MMEL Item 30–
0090
MMEL Item 30-0090
1. Repair
CAS Message
2. Dispatch Consideration
Category
30 ICE PROT - R WING
C
LOOP ONE ELEMENT
(0) May be displayed provided none of the
following messages are displayed:
INOP
- 21 AIR COND / PRESS - IASC lB INOP
- 21 AIR COND / PRESS - IASC 2B INOP
-21 AIR COND / PRESS-IASC lB FAULT
-21 AIR COND / PRESS-IASC 2B FAULT
1. OPERATIONS (0)
Before each flight:
ER01MY24.028</GPH>
a. Connect electrical power to the airplane as follows:
Note: Do not use a Jet Airstart Cart or High Pressure Ground Cart.
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ddrumheller on DSK120RN23PROD with RULES1
(1) Make sure that the airplane is not powered on and that engines and APU are OFF.
34972
Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
1.
Connect external AC power, OR
11.
Start the APU as follows:
1. On the ELECTRICAL control panel, set the MAIN BATT and APU BATT
switches to ON.
2. On the BLEED/AIR COND control panel, make sure that the APU
BLEED switch is set to OFF.
3. On the APU control panel, turn the APU switch to START.
b. When external AC power is on or APU is running, wait a minimum of 6 minutes.
c. After 6 minutes, check for the 30 ICE PROT - R WING LOOP ONE ELEMENT
INOP info message as follows:
i.
If the 30 ICE PROT - R WING LOOP ONE ELEMENT INOP info message
shows - DISPATCH IS PERMITTED.
Note: The INFO message confirms it is not heat related and therefore cannot be
a potential leak in the presence of an affected part.
11.
If the 30 ICE PROT-R WING LOOP ONE ELEMENT INOP info message
does not show - DISPATCH IS NOT PERMITTED.
Note: No INFO message confirms that it is heat related and therefore could be
a potential leak in the presence of an affected part.
e. If required, set APU BLEED to AUTO.
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ddrumheller on DSK120RN23PROD with RULES1
d. If required, remove external AC power from the airplane.
Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
34973
(2) On the INFO synoptic page, make sure that the messages that follow do not show:
Note: Confirm the airplane has electrical power to activate the synoptic page.
- 21 AIR COND / PRESS -IASC lB INOP info
- 21 AIR COND / PRESS - IASC 2B INOP info
-21 AIR COND / PRESS-IASC lB FAULT info
- 21 AIR COND / PRESS - IASC 2B FAULT info
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ddrumheller on DSK120RN23PROD with RULES1
Figure 5 to Paragraph (i)—MMEL Item 30–
0095
34974
Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
MMEL Item 30-0095
1. Repair
CAS Message
2. Dispatch Consideration
Category
30 ICE PROT - R WIPS
(0) May be displayed provided none of the
C
LOOP ONE ELEMENT
following messages are displayed:
INOP
- 21 AIR COND / PRESS - IASC lB INOP
- 21 AIR COND / PRESS - IASC 2B INOP
-21 AIR COND / PRESS-IASC lB FAULT
-21 AIR COND / PRESS-IASC 2B FAULT
1. OPERATIONS (0)
Before each flight:
(1) Make sure that the airplane is not powered on and that engines and APU are OFF.
a. Connect electrical power to the airplane as follows:
Note: Do not use a Jet Airstart Cart or High Pressure Ground Cart.
1.
Connect external AC power, OR
11.
Start the APU as follows:
switches to ON.
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15:34 Apr 30, 2024
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ddrumheller on DSK120RN23PROD with RULES1
1. On the ELECTRICAL control panel, set the MAIN BATT and APU BATT
Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
34975
2. On the BLEED/AIR COND control panel, make sure that the APU
BLEED switch is set to OFF.
3. On the APU control panel, tum the APU switch to START.
b. When external AC power is on or APU is running, wait a minimum of 6 minutes.
c. After 6 minutes, check for the 30 ICE PROT - R WIPS LOOP ONE ELEMENT INOP
info message as follows:
1.
If the 30 ICE PROT - R WIPS LOOP ONE ELEMENT INOP info message
shows-DISPATCH IS PERMITTED.
Note: The INFO message confirms it is not heat related and therefore cannot be
a potential leak in the presence of an affected part.
n. If the 30 ICE PROT - R WIPS LOOP ONE ELEMENT INOP info message
does not show - DISPATCH IS NOT PERMITTED.
Note: No INFO message confirms that it is heat related and therefore could be
a potential leak in the presence of an affected part.
d. If required, remove external AC power from the airplane.
e. If required, set APU BLEED to AUTO.
(2) On the INFO synoptic page, make sure that the messages that follow do not show:
-21 AIR COND / PRESS-IASC lB INOP info
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ddrumheller on DSK120RN23PROD with RULES1
Note: Confirm the airplane has electrical power to activate the synoptic page.
34976
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- 21 AIR COND / PRESS - IASC 2B INOP info
-21 AIR COND / PRESS-IASC lB FAULT info
-21 AIR COND / PRESS-IASC 2B FAULT info
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ddrumheller on DSK120RN23PROD with RULES1
Figure 6 to Paragraph (i)—MMEL Item 36–
0050
Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
34977
MMEL Item 36-0050
1. Repair
CAS Message
2. Dispatch Consideration
Category
36 BLEED - L BLEED
C
(0) May be displayed provided none of the
LOOP ONE ELEMENT
following messages are displayed:
INOP
- 21 AIR COND / PRESS - IASC lB INOP
- 21 AIR COND / PRESS - IASC 2B INOP
-21 AIR COND / PRESS -IASC lB FAULT
- 21 AIR COND / PRESS - IASC 2B FAULT
1. OPERATIONS (0)
Before each flight:
(1) Make sure that the airplane is not powered on and that engines and APU are OFF.
a. Connect electrical power to the airplane as follows:
Note: Do not use a Jet Airstart Cart or High Pressure Ground Cart.
VerDate Sep<11>2014
15:34 Apr 30, 2024
Connect external AC power, OR
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ddrumheller on DSK120RN23PROD with RULES1
i.
34978
Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
11.
Start the APU as follows:
1. On the ELECTRICAL control panel, set the MAIN BATT and APU BATT
switches to ON.
2. On the BLEED/AIR COND control panel, make sure that the APU
BLEED switch is set to OFF.
3. On the APU control panel, turn the APU switch to START.
b. When external AC power is on or APU is running, wait a minimum of 6 minutes.
c. After 6 minutes, check for the 36 BLEED - L BLEED LOOP ONE ELEMENT INOP
info message as follows:
i.
If the 36 BLEED - L BLEED LOOP ONE ELEMENT INOP info message
shows - DISPATCH IS PERMITTED.
Note: The INFO message confirms it is not heat related and therefore cannot be
a potential leak in the presence of an affected part.
ii. If the 36 BLEED-L BLEED LOOP ONE ELEMENT INOP info message
does not show - DISPATCH IS NOT PERMITTED.
Note: No INFO message confirms that it is heat related and therefore could be
a potential leak in the presence of an affected part.
d. If required, remove external AC power from the airplane.
(2) On the INFO synoptic page, make sure that the messages that follow do not show:
VerDate Sep<11>2014
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ddrumheller on DSK120RN23PROD with RULES1
e. If required, set APU BLEED to AUTO.
Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
34979
Note: Confirm the airplane has electrical power to activate the synoptic page.
- 21 AIR COND / PRESS -IASC lB INOP info
- 21 AIR COND / PRESS - IASC 2B INOP info
-21 AIR COND / PRESS-IASC IB FAULT info
- 21 AIR COND / PRESS - IASC 2B FAULT info
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01MYR1
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ddrumheller on DSK120RN23PROD with RULES1
Figure 7 to Paragraph (i)—MMEL Item 36–
0105
34980
Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
MMEL Item 36-0105
1. Repair
CAS Message
2. Dispatch Consideration
Category
36 BLEED - R BLEED
(0) May be displayed provided none of the
C
LOOP ONE ELEMENT
following messages are displayed:
INOP
- 21 AIR COND / PRESS - IASC lB INOP
- 21 AIR COND / PRESS - IASC 2B INOP
-21 AIR COND / PRESS-IASC lB FAULT
-21 AIR COND / PRESS-IASC 2B FAULT
1. OPERATIONS (0)
Before each flight:
(1) Make sure that the airplane is not powered on and that engines and APU are OFF.
a. Connect electrical power to the airplane as follows:
Note: Do not use a Jet Airstart Cart or High Pressure Ground Cart.
1.
Connect external AC power, OR
11.
Start the APU as follows:
switches to ON.
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15:34 Apr 30, 2024
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ddrumheller on DSK120RN23PROD with RULES1
1. On the ELECTRICAL control panel, set the MAIN BATT and APU BATT
Federal Register / Vol. 89, No. 85 / Wednesday, May 1, 2024 / Rules and Regulations
34981
2. On the BLEED/AIR COND control panel, make sure that the APU
BLEED switch is set to OFF.
3. On the APU control panel, tum the APU switch to START.
b. When external AC power is on or APU is running, wait a minimum of 6 minutes.
c. After 6 minutes, check for the 36 BLEED - R BLEED LOOP ONE ELEMENT INOP
info message as follows:
1.
If the 36 BLEED-R BLEED LOOP ONE ELEMENT INOP info message
shows-DISPATCH IS PERMITTED.
Note: The INFO message confirms it is not heat related and therefore cannot be
a potential leak in the presence of an affected part.
n. If the 36 BLEED - R BLEED LOOP ONE ELEMENT INOP info message
does not show - DISPATCH IS NOT PERMITTED.
Note: No INFO message confirms that it is heat related and therefore could be
a potential leak in the presence of an affected part.
d. If required, remove external AC power from the airplane.
e. If required, set APU BLEED to AUTO.
(2) On the INFO synoptic page, make sure that the messages that follow do not show:
-21 AIR COND / PRESS-IASC lB INOP info
VerDate Sep<11>2014
15:34 Apr 30, 2024
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ddrumheller on DSK120RN23PROD with RULES1
Note: Confirm the airplane has electrical power to activate the synoptic page.
34982
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- 21 AIR COND / PRESS - IASC 2B INOP info
-21 AIR COND / PRESS-IASC lB FAULT info
-21 AIR COND / PRESS-IASC 2B FAULT info
(j) Testing and Replacement of Affected
Overheat Detection Sensing Elements
For airplane serial numbers 70005 and
subsequent: Within 3,500 flight hours or 120
months, whichever occurs first, from the
effective date of this AD, test the overheat
detection sensing elements to determine if
they are serviceable, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 700–36–7503, dated
December 23, 2022.
(1) For each sensing element that is
serviceable, before further flight, mark the
sensing element with a witness mark in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
700–36–7503, dated December 23, 2022.
(2) For each sensing element that is not
serviceable, before further flight, replace the
sensing element with a serviceable part in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
700–36–7503, dated December 23, 2022.
(k) Parts Installation Prohibition
As of the effective date of this AD, no
person may install, on any airplane, any
affected part unless it is a serviceable part.
ddrumheller on DSK120RN23PROD with RULES1
(l) No Reporting Requirement
Although Bombardier Service Bulletin
700–36–7503, dated December 23, 2022,
specifies to submit certain information to the
manufacturer, this AD does not include that
requirement.
(m) 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 manager of the International Validation
Branch, mail it to ATTN: Program Manager,
Continuing Operational Safety, at the address
identified in paragraph (n)(2) of this AD or
email to: 9-avs-nyaco-cos@faa.gov. If mailing
information, also submit information by
email. 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
VerDate Sep<11>2014
15:34 Apr 30, 2024
Jkt 262001
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.
Issued on March 18, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
(n) Additional Information
DEPARTMENT OF TRANSPORTATION
(1) Refer to Transport Canada AD CF–
2023–18, dated March 9, 2023, for related
information. This Transport Canada AD may
be found in the AD docket at regulations.gov
under Docket No. FAA–2023–2139.
(2) For more information about this AD,
contact Steven Dzierzynski, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone 516–
228–7300; email: 9-avs-nyaco-cos@faa.gov.
[FR Doc. 2024–09341 Filed 4–30–24; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–2240; Project
Identifier MCAI–2023–00936–T; Amendment
39–22717; AD 2024–06–12]
RIN 2120–AA64
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 700–36–
7503, dated December 23, 2022.
(ii) Liebherr Service Bulletin CFD–F1958–
26–01, dated May 6, 2022.
(3) For Bombardier service information
identified in this AD, 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.
(4) For Liebherr-Aerospace Toulouse SAS
service information identified in this AD,
contact Liebherr-Aerospace Toulouse SAS,
408, Avenue des Etats-Unis—B.P.52010,
31016 Toulouse Cedex, France; telephone
+33 (0)5.61.35.28.28; fax +33
(0)5.61.35.29.29; email: techpub.toulouse@
liebherr.com; website: www.liebherr.aero.
(5) 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.
(6) 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.
PO 00000
Frm 00030
Fmt 4700
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Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2021–24–
20, which applied to all Airbus SAS
Model A350–941 and –1041 airplanes,
and AD 2023–03–05, which applied to
certain Airbus SAS Model A350–941
and –1041 airplanes. AD 2021–24–20
required repetitive water drainage and
plug cleaning of the left- and right-hand
slat geared rotary actuators (SGRAs)
having a certain part number installed
on slat 5 track 12 with certain functional
item numbers. AD 2023–03–05 required
revising the existing maintenance or
inspection program, as applicable, to
incorporate new or more restrictive
airworthiness limitations. This AD was
prompted by a determination that new
or more restrictive airworthiness
limitations are necessary. This AD
continues to require certain actions in
AD 2021–24–20 and AD 2023–03–05
and requires revising the existing
maintenance or inspection program, as
applicable, to incorporate new or more
restrictive airworthiness limitations, as
specified in a European Union Aviation
Safety Agency (EASA) AD, which is
incorporated by reference. The FAA is
SUMMARY:
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BILLING CODE 4910–13–C
]]>Agencies
[Federal Register Volume 89, Number 85 (Wednesday, May 1, 2024)]
[Rules and Regulations]
[Pages 34961-34982]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-09341]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2139; Project Identifier MCAI-2023-00435-T;
Amendment 39-22713; AD 2024-06-08]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was
prompted by reports from the supplier that some overheat detection
sensing elements of the bleed air leak detection system were
manufactured with insufficient salt fill, which can result in an
inability to detect hot bleed air leaks. This AD requires maintenance
records verification, and if an affected part is installed, prohibits
the use of certain Master Minimum Equipment List (MMEL) items under
certain conditions by requiring revising the operator's existing
Minimum Equipment List (MEL). This AD also requires testing the
overheat detection sensing elements, marking each serviceable sensing
element with a witness mark, and replacing each nonserviceable part
with a serviceable part. This AD also prohibits the installation of
affected parts under certain conditions. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective June 5, 2024.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 5, 2024.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-2139; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket
[[Page 34962]]
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 Bombardier 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.
For Liebherr-Aerospace Toulouse SAS service information
identified in this final rule, contact Liebherr-Aerospace Toulouse SAS,
408, Avenue des Etats-Unis--B.P.52010, 31016 Toulouse Cedex, France;
telephone +33 (0)5.61.35.28.28; fax +33 (0)5.61.35.29.29; email:
[email protected]; website: www.liebherr.aero.
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. It is also available in
the AD docket at regulations.gov under Docket No. FAA-2023-2139.
FOR FURTHER INFORMATION CONTACT: Steven Dzierzynski, 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 by adding an AD that would apply to certain Bombardier,
Inc., Model BD-700-2A12 airplanes. The NPRM published in the Federal
Register on November 8, 2023 (88 FR 77044). The NPRM was prompted by AD
CF-2023-18, dated March 9, 2023, issued by Transport Canada, which is
the aviation authority for Canada (Transport Canada AD CF-2023-18)
(also referred to as the MCAI). The MCAI states that Bombardier
received reports from the supplier of the overheat detection sensing
elements of a manufacturing quality escape. Some of the sensing
elements of the bleed air leak detection system were manufactured with
insufficient salt fill. This condition can result in an inability to
detect hot bleed air leaks, which can cause damage to surrounding
structures and systems and prevent continued safe flight and landing.
In the NPRM, the FAA proposed to require maintenance records
verification, and if an affected part is installed, prohibit the use of
certain MMEL items under certain conditions by requiring revising the
operator's existing MEL. The NPRM also proposed to require testing the
overheat detection sensing elements, marking each serviceable sensing
element with a witness mark, and replacing each nonserviceable part
with a serviceable part. The NPRM also proposed to prohibit the
installation of affected parts under certain conditions. 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-2023-2139.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment from NetJets. The following presents the
comment received on the NPRM and the FAA's response to the comment.
Request for Clarification on Location of Date of Manufacture
NetJets requested a statement be added to paragraph (h) of the
proposed AD indicating that the date of manufacture can be found in the
aircraft maintenance logbook, in addition to the identification plate
of the airplane on certain airplanes. This information is stated in
Transport Canada AD CF-2023-18, Part II, paragraph A. NetJets further
stated that Bombardier no longer stamps a date on the airframe data
plate.
The FAA agrees the date of manufacture can be found either on the
identification plate of certain airplanes or in the aircraft
maintenance logbook. The FAA has amended paragraph (h) of this AD to
specify the two locations where the date of manufacture can be found.
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, considered the
comment received, and determined that air safety requires adopting this
AD as proposed. Accordingly, the FAA is issuing this AD to address the
unsafe condition on this product. Except for minor editorial changes,
and any other changes described previously, this AD is adopted as
proposed in the NPRM. None of the changes will increase the economic
burden on any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Liebherr Service Bulletin CFD-F1958-26-01, dated
May 6, 2022, which specifies part numbers for affected sensing
elements.
The FAA reviewed Bombardier Service Bulletin 700-36-7503, dated
December 23, 2022, which specifies procedures for testing each leak
detection loop (LDL) sensing element installed on the airplane, marking
each serviceable sensing element with a witness mark, and replacing
each nonserviceable part with a serviceable part.
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 19 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 214 work-hours x $85 per hour $0 Up to $18,190............... Up to $345,610.
= Up to $18,190.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions specified in this AD. The FAA
estimates it takes up to 1.5 hours to replace a sensing element.
[[Page 34963]]
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some or all 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 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:
2024-06-08 Bombardier, Inc.: Amendment 39-22713; Docket No. FAA-
2023-2139; Project Identifier MCAI-2023-00435-T.
(a) Effective Date
This airworthiness directive (AD) is effective June 5, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc., Model BD-700-2A12
airplanes, certificated in any category, having serial numbers 70005
and subsequent.
(d) Subject
Air Transport Association (ATA) of America Code: 36, Pneumatic.
(e) Unsafe Condition
This AD was prompted by reports that some overheat detection
sensing elements of the bleed air leak detection system were
manufactured with insufficient salt fill. The FAA is issuing this AD
to address non-conforming sensing elements of the bleed air leak
detection system. The unsafe condition, if not addressed, could
result in an inability to detect hot bleed air leaks and consequent
damage to surrounding structures and systems, which could prevent
continued safe flight and landing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definitions
For the purpose of this AD, the definitions specified in
paragraphs (g)(1) and (2) of this AD apply.
(1) An affected part is a sensing element marked with a date
code before A2105 and having an LTS/Kidde part number specified in
Liebherr Service Bulletin CFD-F1958-26-01, dated May 6, 2022, unless
that sensing element meets the criteria specified in paragraph
(g)(1)(i) or (ii) of this AD.
(i) The sensing element has been tested as specified in Section
3 of the Accomplishment Instructions of Kidde Aerospace and Defense
Service Bulletin CFD-26-1, Revision 6, dated February 28, 2022, or
earlier revisions, and has been found to be serviceable; and the
sensing element has been marked on one face of its connector hex nut
and packaged as specified in Section 3.C. of the Accomplishment
Instructions of Kidde Aerospace and Defense Service Bulletin CFD-26-
1, Revision 6, dated February 28, 2022, or earlier revisions.
(ii) The sensing element has been tested and found to be
serviceable as specified in paragraph (j) of this AD; and the
sensing element has been marked on one face of one connector hex nut
with one green mark, as specified in Figure 33 of Bombardier Service
Bulletin 700-36-7503, dated December 23, 2022, as applicable (the
figure is representative for all sensing elements).
(2) A serviceable part is a sensing element that is not an
affected part.
(h) Maintenance Records Verification
For airplane serial numbers 70097 and subsequent whose airplane
date of manufacture, as identified on the identification plate of
the airplane or in the aircraft maintenance logbook, is on or before
the effective date of this AD: Within 60 days after the effective
date of this AD, examine the airplane maintenance records to verify
whether any affected part has been installed since the airplane date
of manufacture, as identified on the identification plate of the
airplane or in the aircraft maintenance logbook.
(1) If the maintenance records confirms that an affected part
has been installed, or if it cannot be confirmed that an affected
part has not been installed, paragraphs (i) and (j) of this AD must
be complied with within the compliance time specified in paragraphs
(i) and (j) of this AD.
(2) If the maintenance records confirm that no affected parts
have been installed since airplane date of manufacture, then
paragraphs (i) and (j) of this AD are not applicable.
(i) Minimum Equipment List (MEL) Revision
For all airplanes: Within 90 days after the effective date of
this AD, revise the operator's existing MEL by incorporating the
information specified in figures 1 through 7 to paragraph (i) of
this AD, as applicable. This may be done by inserting a copy of this
information into the operator's existing MEL.
Figure 1 to Paragraph (i)--MMEL Item 21-0425
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Figure 2 to Paragraph (ii)--MMEL Item 30-0055
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Figure 3 to Paragraph (i)--MMEL Item 30-0060
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Figure 4 to Paragraph (i)--MMEL Item 30-0090
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Figure 5 to Paragraph (i)--MMEL Item 30-0095
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Figure 6 to Paragraph (i)--MMEL Item 36-0050
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Figure 7 to Paragraph (i)--MMEL Item 36-0105
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(j) Testing and Replacement of Affected Overheat Detection Sensing
Elements
For airplane serial numbers 70005 and subsequent: Within 3,500
flight hours or 120 months, whichever occurs first, from the
effective date of this AD, test the overheat detection sensing
elements to determine if they are serviceable, in accordance with
the Accomplishment Instructions of Bombardier Service Bulletin 700-
36-7503, dated December 23, 2022.
(1) For each sensing element that is serviceable, before further
flight, mark the sensing element with a witness mark in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
700-36-7503, dated December 23, 2022.
(2) For each sensing element that is not serviceable, before
further flight, replace the sensing element with a serviceable part
in accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 700-36-7503, dated December 23, 2022.
(k) Parts Installation Prohibition
As of the effective date of this AD, no person may install, on
any airplane, any affected part unless it is a serviceable part.
(l) No Reporting Requirement
Although Bombardier Service Bulletin 700-36-7503, dated December
23, 2022, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.
(m) 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 manager of the
International Validation Branch, mail it to ATTN: Program Manager,
Continuing Operational Safety, at the address identified in
paragraph (n)(2) of this AD or email to: [email protected]. If
mailing information, also submit information by email. 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.
(n) Additional Information
(1) Refer to Transport Canada AD CF-2023-18, dated March 9,
2023, for related information. This Transport Canada AD may be found
in the AD docket at regulations.gov under Docket No. FAA-2023-2139.
(2) For more information about this AD, contact Steven
Dzierzynski, Aviation Safety Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone 516-228-7300; email: [email protected].
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 700-36-7503, dated December 23,
2022.
(ii) Liebherr Service Bulletin CFD-F1958-26-01, dated May 6,
2022.
(3) For Bombardier 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) For Liebherr-Aerospace Toulouse SAS service information
identified in this AD, contact Liebherr-Aerospace Toulouse SAS, 408,
Avenue des Etats-Unis--B.P.52010, 31016 Toulouse Cedex, France;
telephone +33 (0)5.61.35.28.28; fax +33 (0)5.61.35.29.29; email:
[email protected]; website: www.liebherr.aero.
(5) 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.
(6) 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 March 18, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-09341 Filed 4-30-24; 8:45 am]
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