Airworthiness Directives; Bombardier, Inc., Airplanes, 22069-22083 [2024-06626]
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Federal Register / Vol. 89, No. 62 / Friday, March 29, 2024 / Rules and Regulations
Authority: 12 U.S.C. 1814–1817, 1819–
1820, 1828, 1831u and 2901–2908, 3103–
3104, and 3108(a).
§ 345.27
[Amended]
26. Amend § 345.27 in the headings of
paragraphs (c)(4) and (c)(4)(i) by
removing the text ‘‘[Operations
subsidiaries or operating subsidiaries]’’
wherever it appears and adding the text
‘‘Operating subsidiaries’’ in its place.
■
§ 345.51
[Amended]
27. Amend § 345.51 in paragraph
(a)(2)(i) by removing the text ‘‘§§ 345.12
through 345.15, 345.17 through 345.30,
and 345.42(a)’’ and adding the text
‘‘§§ 345.12 through 345.30, 345.42(a),
345.43, and 345.44’’ in its place.
■
Appendix B to Part 345 [Amended]
28. Amend appendix B in paragraphs
III.c.1 and 2 by removing ‘‘12 CFR
25.42(b), 228.42(b), or 345.42(b)’’ and
adding ‘‘§ 345.42(b) or 12 CFR 25.42(b)
or 228.42(b)’’ in its place.
■ 29. Amend appendix G by revising
§ 345.12(u)(1) to read as follows:
■
Appendix G to Part 345—Community
Reinvestment Regulations
*
*
§ 345.12
*
*
*
*
*
Definitions.
*
*
*
(u) * * *
(1) Definition. Small bank means a bank
that, as of December 31 of either of the prior
two calendar years, had assets of less than
$1.564 billion. Intermediate small bank
means a small bank with assets of at least
$391 million as of December 31 of both of the
prior two calendar years and less than $1.564
billion as of December 31 of either of the
prior two calendar years.
*
*
*
*
*
§ 346.6
PART 346—DISCLOSURE AND
REPORTING OF CRA-RELATED
AGREEMENTS
30. The authority citation for part 346
continues to read as follows:
Authority: 12 U.S.C. 1831y.
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Fulfillment of the CRA.
(a) * * *
(2) Activities given favorable CRA
consideration. Performing any of the
following activities if the activity is of
the type that is likely to receive
favorable consideration by a Federal
banking agency in evaluating the
performance under the CRA of the
insured depository institution that is a
party to the agreement or an affiliate of
a party to the agreement—
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32. Amend § 346.6 in paragraph (b)(7)
by removing the text ‘‘12 CFR 345.43’’
and adding the text ‘‘§ 345.43 of
appendix G to 12 CFR part 345’’ in its
place.
§ 346.11
[Amended]
33. Amend § 346.11 in paragraph (d)
by removing the text ‘‘12 CFR 345.43’’
and adding the text ‘‘§ 345.43 of
appendix G to 12 CFR part 345’’ in its
place.
■
31. Amend § 346.4 by revising
paragraph (a)(2) to read as follows:
■
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[Amended]
■
■
§ 346.4
(i) Home-purchase, homeimprovement, small business, small
farm, community development, and
consumer lending, as described in
§ 345.22 of appendix G to 12 CFR part
345, including loan purchases, loan
commitments, and letters of credit;
(ii) Making investments, deposits, or
grants, or acquiring membership shares,
that have as their primary purpose
community development, as described
in § 345.23 of appendix G to 12 CFR part
345;
(iii) Delivering retail banking services
as described in § 345.24(d) of appendix
G to 12 CFR part 345;
(iv) Providing community
development services, as described in
§ 345.24(e) of appendix G to 12 CFR part
345;
(v) In the case of a wholesale or
limited-purpose insured depository
institution, community development
lending, including originating and
purchasing loans and making loan
commitments and letters of credit,
making qualified investments, or
providing community development
services, as described in § 345.25(c) of
appendix G to 12 CFR part 345;
(vi) In the case of a small insured
depository institution, any lending or
other activity described in § 345.26(a) of
appendix G to 12 CFR part 345; or
(vii) In the case of an insured
depository institution that is evaluated
on the basis of a strategic plan, any
element of the strategic plan, as
described in § 345.27(f) of appendix G to
12 CFR part 345.
*
*
*
*
*
Michael J. Hsu,
Acting Comptroller of the Currency.
By order of the Board of Governors of the
Federal Reserve System.
Ann E. Misback,
Secretary of the Board.
Federal Deposit Insurance Corporation.
By order of the Board of Directors.
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22069
Dated at Washington, DC, on March 21,
2024.
James P. Sheesley,
Assistant Executive Secretary.
[FR Doc. 2024–06497 Filed 3–28–24; 8:45 am]
BILLING CODE 4810–33–P; 6210–01–P; 6714–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–2000; Project
Identifier MCAI–2023–00415–T; Amendment
39–22678; AD 2024–03–08]
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–700–1A10
and BD–700–1A11 airplanes. 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,
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, would
prohibit 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 May 3, 2024.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 3, 2024.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–2000; 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
SUMMARY:
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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
liebherr.aero.
• You may view this material 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–
2023–2000.
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:
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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–700–1A10 and BD–700–1A11
airplanes. The NPRM published in the
Federal Register on November 15, 2023
(88 FR 78251). The NPRM was
prompted by AD CF–2023–17, dated
March 8, 2023 (Transport Canada AD
CF–2023–17) (also referred to as the
MCAI), issued by Transport Canada,
which is the aviation authority for
Canada. 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
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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, would 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–2023–2000.
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 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–2023–17, 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.
Change to NPRM Applicability
Paragraph (c) of this AD has been
revised to clarify that the applicability
is limited to certain serial numbers,
which are also identified in Transport
Canada AD CF–2023–17.
Conclusion
This product has been approved by
the aviation authority of another
country and is approved for operation in
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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 the following
Bombardier service bulletins, which
specify 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. These documents are distinct since
they apply to different airplane models
and configurations.
• Bombardier Service Bulletin 700–
1A11–36–005, Basic Issue, dated
December 23, 2022;
• Bombardier Service Bulletin 700–
36–026, Basic Issue, dated December 23,
2022;
• Bombardier Service Bulletin 700–
36–5002, Basic Issue, dated December
23, 2022;
• Bombardier Service Bulletin 700–
36–5501, Basic Issue, dated December
23, 2022; and
• Bombardier Service Bulletin 700–
36–6002, Basic Issue, dated December
23, 2022;
• Bombardier Service Bulletin 700–
36–6501, Basic Issue, dated December
23, 2022.
This material is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD
affects 160 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
Up to 140 work-hours × $85 per hour = $11,900 .............................................................
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 one sensor.
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.
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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
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Cost per
product
Parts cost
$0
Up to $11,900 .....
Cost on U.S.
operators
Up to $1,904,000.
under the criteria of the Regulatory
Flexibility Act.
systems, which could prevent continued safe
flight and landing.
List of Subjects in 14 CFR Part 39
(f) Compliance
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 adding
the following new airworthiness
directive:
■
2024–03–08 Bombardier, Inc.: Amendment
39–22678; Docket No. FAA–2023–2000;
Project Identifier MCAI–2023–00415–T.
(a) Effective Date
This airworthiness directive (AD) is
effective May 3, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc.,
Model BD–700–1A10 and BD–700–1A11
airplanes, certificated in any category, serial
numbers 9002 through 9879 inclusive, 9998,
and 60001 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
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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) through (3) of
this AD apply.
(1) The following Model BD–700–1A10
and BD–700–1A11 airplane groups are
identified in (g)(1)(i) through (iv) of this AD:
(i) Group A airplanes: serial numbers (S/N)
9002 through 9151 inclusive, and 9153.
(ii) Group B airplanes: S/N 9152, 9154
through 9879 inclusive, 9998, 60001 through
60041 inclusive, 60043, 60044, 60045, and
60051.
(iii) Group C airplanes: S/N 60042, 60046,
60047, 60049, 60053, and subsequent.
(iv) Group D airplanes: S/N 60048, 60050,
and 60052.
(2) An affected part is a sensing element
marked with a date code A0448 through
A2104 inclusive 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)(2)(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 4 (the figure is
representative for all sensing elements) in the
Accomplishment Instructions of the
applicable Bombardier service bulletin (BA
SB) in figure 1 to paragraph (g)(2)(ii) of this
AD.
Figure 1 to Paragraph (g)(2)(ii)—Applicable
Service Information
BILLING CODE 4910–13–P
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Airplane Model
(Marketing Designation)
BD-700-lAlO
(Global Express & Global Express XRS)
BD-700-lAll
(Global 5000)
BF-700-lAl 1
(Global 5000 featuring Global Vision
Flight Deck)
BD-700-lAlO
(Global 6000)
BD-700-lAll
(Global 5500)
BD-700-lAlO
(Global 6500)
(3) A serviceable part is a sensing element
that is not an affected part.
(h) Maintenance Records Verification
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For Groups A and C whose airplane date
of manufacture, as identified on the
identification plate of the airplane or in the
aircraft maintenance logbook, is on or before
July 27, 2022 (the effective date of Transport
Canada AD CF–2022–38): 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
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Applicable BA SB
SB 700-36-026
SB 700-lAl 1-36-005
SB 700-36-5002
SB 700-36-6002
SB 700-36-5501
SB 700-36-6501
airplane or in the aircraft maintenance
logbook.
(1) If the maintenance records confirm 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
applicable compliance times specified in
paragraphs (i) and (j) of this AD.
(2) For Groups A and C airplanes: 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.
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(i) Minimum Equipment List (MEL) Revision
For Groups B and D airplanes, and Groups
A and C airplanes required by paragraph (h)
of this AD: Within 90 days after the effective
date of this AD, revise the operator’s existing
MEL by incorporating the information
specified in figures 2 through 8 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 2 to Paragraph (i)—MMEL Item 36–
12–01
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MMEL Item 36-12-41
1. System & sequence
NO Item
2.
Number
Installed
3.
Nombre
d'articte
installes
No de systeme/serie
article
Number
Required
For
Dispatch
4.
Remarks or Exceptions
Nombre
d'artictes
a.expedier
36- Pt:JE!,.!MATICS
12-01 Bteedleak Detection
Loops
18
9
(0) Either loop A or loop B may be
inoperati11e provided redundant loop in
C
the same zone is .operative.
1. PLACARD
(1) Put a BLEED LEAK DETECTION LOOPS INOPERATIVE placard ori the instrlu'.(ierit paneL
2.
OPERATIONS (Oj
Before each flight:
(1) Make sure that the aeroplane is not powered on and that engines and APU are.OFF.
a
Connect electrical power to the aeroplane as fallows:
Note: Do not. use a Jet. Alrstart Cart or High Pressure Ground. Cart.
L Connect external AC power, OR
it Start the APU as follQWS:
1. On the ELECTRICAL Coritrol panel, set the BATT MASTER switch to
ON.
2
on the BLEED/AIR COND.control panel, make sure that the APU
BLEED switch is set lo OFF.
3: On the APU control pane~ turn the APU switch to.START.
b: When external AC power is on or APU is running, wail a minimum of 6 minutes.
c. After 6 minutes, make surethatthe EICAS primary display shows as follows:
If the Advisory L BLEED FAULT or R BLEED.FAULT shows, DISPATCH IS
PERMlTTED.
Note: If the Advisory L BLEED FAULT or R BLEED FAULT shows, rt confirms it
is not heal related and therefore cannot be a potential teak in the presence of an
affected part.
it lfthe Advisory LBLEEO FAUJ.J or R BLEED FAWLtdoes not show, DISPATCH
IS NOT PERM ITTEO.
Nole!: If the Advisory L BLEED FAULT or R BLEED FAULT does not show, if
confirmsthat ii is heat related and therefore could be a potentif!l leak in the
presence of an affecled part.
ct.
If required, remove external AC powerfromtheaeroplf!ne.
e.
If required, set APU BLEED to AUTO.
Figure 3 to Paragraph (i)—MMEL Item
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MMEL ltem36-12-01°1
1.
System & Sequence
NO Item
2. Number
Installed
NO de sys~me/serie
article
Nombre
d'artlcte
installes
3.
Number
Required
For
Dispatch
4.
Remarks or Exceptions
Nombre
d'articles
aexpedier
36 - PNEUMATICS
12-01 Blee_d Leak.Detection
loops
9
18
(OJ Eithe_r foopAor loopB may
l:le
inoperative provided redundant loop
t
in the same zone is operative.
1) Wing Anti-tee Leak
1.2
(M) (QJ One loop in e1;1ch section may
6
be inoperative Provided:
C
a} Power-up BIT test is performed
on syi,tern prior to ~ch dlspatch
into icing, and
b) cause of WING ANTI-ICE
FAULT Advisory message is
confirmed bymaintenance.
1.
PLACARD
{1} Puta WING ANTI-ICE LEAK INOPERATIVE placard on the instrumeril parief.
2, OPERATIONS (0)
Before each fllght:
(1} Make sure that the aeroplane is not powered on and that engines and APUare OFF.
a.
Connect electrical power to the aeroplane as fallciws:
Note: Do not use a Jet Airstart cart or High Pressure Ground Cart.
Connect external AC power, OR
ii. Start the APUasfQllows:
1.
On the ELECTRICAL control panel, set the BATT MASTER switch ta
ON.
2.
On the BtEE01AI R COND CQntrQI panel, make sure thqt .the APL)
BLEED switch is set ta OFF.
3.
On the APU control panel, turn the APU Switch to.ST ART
b.
Whan external AC pQwer IS an or APU is ruhnin9, wait amiriimum of 6 rhiriutes.
c,
After 6 minutes, make sure that the EICAS primary display shows as follows:
i.
lfthe Advisory WING NICE FAULT shows, DISPATCH iS PERMITTED unless
step (2) of the Maintenance (M) procedure under (3} below does not pass, iri
Which case DISPATCH !SNOT PERMITTED.
•
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Nate: If the Advisory WING A/ICE FAULT shows, if confirms it is nol heat related
and therefore cannot be .a potential teak in the presence of an affected• part.
Federal Register / Vol. 89, No. 62 / Friday, March 29, 2024 / Rules and Regulations
22075
iL lHhe Advisory WING NICE FAULT does.not show, DISPATCH IS NOT
PERMliTED.
Note: fftheAdvisoty WING A/ICE FAULT do.es not Show, itcolifirms that itis
heat related and therefore could be a potentiaUeak in the presence of an
affected part.
3.
d.
If required, remove external AC powertrom the aeroplane.
e:
If required, set APU BLEED to AUTO.
MAINTENANCE [M)
The requirement to perform this section is conctitiohal o:n (1 )(c)(i) under the Operatfolis CO) procedure
aoove.
(1) Pow.er~up BIT test is perfornied on system prior ta each dispatch into ieing.
(2} 'The cause of the WING ANTl~ICE FAULT Advisory message is ta be confirmed by maintenance
personnel to make sure that no section has encountered a dual loop failure.
Figure 4 to Paragraph (i)—MMEL Item
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BILLING CODE 36–12–01–2
22076
Federal Register / Vol. 89, No. 62 / Friday, March 29, 2024 / Rules and Regulations
MMEL Item 36-12-01-2
1. System & Sl!quence
NO Item
2.
Number
lnstalll!d
NO de systeme/serie
article
Nombre
d'article
installes
3.
Number
Required
For
Dispatch
4. Remarks or Exceptions
Nombre.
d'arficles
~expedier
36- PNEUMATICS
12-01 Bleed Leak Detection
Loops
18
(O} Either loop Aor loop B rnay be
9
inoperative prov1ded redundant loop
C
in the same zone.is operative.
...
...
2) Trim Air Leak
2
{O) Except for ERoperations,. one
1
loop may be inoperative.
C
t
PLACARD
{1) Put a TRIM AIR LEAK INOPERATIVE placard on the instrument panel.
2,
OPERATIONS /0)
Before each ffight:
(1) Make sure that the aeroplane ,s nof powered on anctthat engines and .APU are OFF:
a. Connect electrical power to the aeropla11¢ as. follows:
Note: Do not u.se a -Jet Airstart Cart or High Pressure Ground Cart.
i. Connect external AC power, OR
ii: start the APU. as fallows:
1.
Oh the ELECTRICAL control panel, set.the BATT MASTER .Swi.tCh to
ON.
2.. on the.BLEED/AIR COND control panel, make sure that ttte APU
BLEED switch is set to OFF.
3.
On theAPU Control panel, tt.Jro the APU S:Wi1;Ch to START.
b. When external AC power is oh or APU is ruhning, wa.it a minimum of 6 minutes.
c.
After 6 rninutea, rnal<e sure that the EIGAS primary displayshows as follaws:
i. lfthe AdVisory TRIM AIR FAULT shows, DISPATCH IS PERMITTED.Note: If the Advisory TRIM AIR FAULT shows, it confirms it is not neat refated
and therefore cannot be a potential leak lnthe presence of an affected. part.
ii. If the AdvisoryTRIM AIR FAULT does not show, DISPATCH fSNOT
PERMITTED.
Note: If the :Actvisory TRIM AtR FAULT does not show, it confirms that it Is heat
related and therefore could be a potentiaf leak in the presence of·an affected
part
d.
If required; remove external AC power from the aeroplane.
e.
If required, set APU BLEED lo AUTO.
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Figure 5 to Paragraph (i)—L BLEED FAULT
Federal Register / Vol. 89, No. 62 / Friday, March 29, 2024 / Rules and Regulations
22077
L BLEED FAULT
CAS Indication
1.
L BLEED FAULT
C
(Advisory)
2.
Dispatch Consideration
(0) Aircraft may be dispatched provided, prior to
each flight
a) None of the following messages are also
posted:
- R BLEED SYS FAIL Caution;
- R WING ANTl-lCEFAIL Caution;
-XBLEED FAIL caution;
-RBLEEDFAULT Advisoty;
-WING ANTI-ICE FAUL.T Advisory;
b) Left:PRVand left HPSOV open and close
correctly in response to L BLEED OFF switch
.selection, as indicated onSynoptic Page;
c) Left HPSOV is open at engine idle arid
closed at high thrust.settings, as indk)a!ed on
Synopttc Page;
d) WING XBLEED FROM R is selected and
remains open; and
e) Operatioos are not conducted in known or
forecast icing conditions.
1. OPERATIONS {O}
Before each flight:
.(1) Make sure that the aeroplane is not powered on and that engines and APU are OFF.
a.. connect electrical power to the.aeroplane as follows•
Note: Do not use a Jet Airstart Cart Qr High Pressure Ground Cart.
i. Connect external AC power, OR
ii.
VerDate Sep<11>2014
15:53 Mar 28, 2024
1.
On the ELECTRICAL control panel, set the BATT MASTE;Rswitchto
ON.
2.
On the BLEED/AIR COND control panel, make sure that the APU
BLEED .Switoli is set to OFF.
3.
On the.APU coottol panel, turn.the APU switch to ST ART.
Wheh external AC power is on or APU is. running, wait a minimum of 6 minutes.
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b.
starttheAPUasfollows:
22078
Federal Register / Vol. 89, No. 62 / Friday, March 29, 2024 / Rules and Regulations
c,
After 6 minutes, make sure that the EICAS primary display shows as fallows:
i.
If the Actvisory L BLEED FAULT Shaws, DISPATCH IS PERMITTED.
Nate: If the Actvisory L Bl.EEO FAULT shows, tt confirms it is not heat.related
.and therefqre cannot be a potential leak in the presence of an affected part:
ii. If the Advisory L BLEED FAULT does not shaw, DISPATCH ts NOT
PERMITTED.
NotEi' If.the Actvisary L BLEED FAULT does not show, it confirms that it is tleat
related and therefore cciuld be a potential leak ih the presence Of an.affected
part.
2.
ct
If required, remove external AC power from the aeroplane.
e.
If required, set APlJ BLEED ta AUTO.
OPERATIONS (0)
Before each flight and after engine start
(1). On the EICAS primary display,make sure that the messages that fallow do not shaw:
- R Bl.EEO SYS FAIL (Caution)
- R WING ANTI-ICE FAIL (Cauticin)
-XBLEED FAIL(Cautian)
- R BLEEDFAULT (Actvisory)
-WING ANTI-ICE FAULT (Advisory)
(2J Make sure that the left Pressure Regulator Valve (PR\/) and left High Pressure $hut OffValve
(HPSOV) open and clcrse as follows:
a. On the BLEED/AIR COND control panel, set the L ENG BLEED switch to OFF.
b.. On the BLEED/ANTI-ICE synaptic page, make $Ure thatthe left PRV ancl left HPSOV
shaw closed.
c.
On the BLEEDIAIRCOND control panel, set the LENG BLEEDsWitch to AUTO.
d. On.the BLEED/ANTI-ICE synaptic page, make sure that the left PRVahd leftHPSOV
show open.
{3) Make sure that.the left High Pressure Shl.lt Off Vc11Ve (HPSOV) switching operates as fonows:
a.
srowry actvance the left thrdttle to high thrust setting,
b. Ort the BLEED/ANTI-ICE synoptic page, make sure that the left HPSOV shows closed.
c.
Slowly retard the left throttle ta engine idle.
d. On the !3LEEDIANTI-ICE synaptic page, make sure that the left HPSOV shows open.
(4) On the ANTl,ICE control panel, set the WING XBLEED to FROM R far the rest of the flight.
(5} Operations are not conclucted in known or forecast icing conditions.
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Figure 6 to paragraph (i)—R BLEED FAULT
Federal Register / Vol. 89, No. 62 / Friday, March 29, 2024 / Rules and Regulations
22079
R BLEED FAULT
CAS Indication
1.
2.
Dispatch Consideration
RBLEED FAULT
(Advisory}
C
(0)
Aircraft may l:)e dispatched provided, prior to
each flight:
a) None ofthe following messages are also
posted:
- L BLEED SYS FAIL Caution;
- L WING ANTl~ICE FAIL Caution;
.-XBLEED FAIL Caution;
- L BLEED FAULT Advisory;
-WING ANTI-ICE FAULT Advisory;
b) Right PRV and right HPSOV open and close
correctly in response to R BLEED OFF
switch selection, as indicated on Synoptic
Page;
c) Right HPSOV /s open at engine idle and
closed at high thrust settings, as indicated on
Synoptic Page;
cl} WING XBLEED FROM L is selected and
remains open; and
e) Operations are not conducted In known or
forecast icing conditions.
1. OPl::RATIONS (0)
BefQre each flight:
(1) Make sure that the aeroplane is not powered an and that engines and APU are OFF.
.a.
Connect electrical power to the aeroplane as foll~:
Note: Do not use a Jet Aitstartcart or High Pressure Qround cart
Connect.external AC power, OR
ii. Startthe APUasfollows:
1. On the ELECTRICAL control panel, set the BATT MASTER switch to
ON.
Z. Ort the BLEED/AIR COND control panel, make sure that lhe APU
BLEED SWiteh ($ 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, make sure thatthe EICAS primary display shows as follows•
If the Advisory R BLEED FAULT stiows, DISPATCH IS PERMITTED.
Note: If the Advisory R BLEED FAULT shows, it confirms it is not t)eaf related
and therefore cannot oo a potential leak in the presence of an affected part.
ii.
Ff the Aclvisory R BLEED FAULT does notsl1oW, DISPATCH IS NOT
PERMITTED
Note: If the Advisory~ BLEED FAULT dpes not. show, i! confirms.that it is heat
relate.cl and therefore could be a potential leak in the presence of an affectei;J
part.
2.
d.
If required, remove exfernal AC power frorn the aeroplane.
e:
If required, set APU BLEED to AUTO.
OPERATIONS (0)
Before eabli flight and after .engine start:
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{1} oo the EICAS primary display, make sure that the messages thatfolfoWdo not show:
22080
Federal Register / Vol. 89, No. 62 / Friday, March 29, 2024 / Rules and Regulations
- L BLEED SYS FAIi- (Gaution)
- L WING ANTI-ICE FAIL {Caution)
-XBLEE:D FAIL (Cautidn)
- L BLEED FAULT (Advisory)
-WING ANTI-ICE FAULT (Advisory)
(2) Make sure that the right Pressure Regulator Valv.e (PRV) and right High Pressure Shut Off Valve
(HPSOV) open and close as fcrnows:
a.
On the .BLEED/Al R COND control panel, set the R ENG BLEED Switch to OFF.
0.
on theBLEED/ANT[-ICE synoptic page, make sure that the right PRV and right HPSOV
show closed.
c.
on the BLEED/AIR COND control panel, set the R ENG BLEED switch to AUTO.
ct On theBLEED/ANTHCE synoptic page, make sure that the rightPRV and right HPSOV
show open.
(3) Make sure that the right High Pressure Shut Offl/alve (HPSOV) switching operates as follows:
a. Slowly advance the right throttle to high thrust setting.
b.
On the BLEED/ANTI-ICE synoptic page, make sure thaHhe right HPSOV shows closed.
c.
Slowly retard the rightthrottle to engine idle.
t:l
On the BLEED/ANTI-ICE synoptic page, make sure that the right HPSOV shows open,
(4) On I.he ANTHCE control panel, set the WING x;BLEEO to FROM L for the rest of the flrght.
(5J operations are not conducted in known or forecast iqing conditions.
Figure 7 to Paragraph (i)—WING A/ICE
FAULT
WING A/ICE FAULT
CAS Indication
1.
2.
WING A/ICE FAULT
(Advisory)
C
(0) Aircraft may be dispatched prov\ded, prior to
1.
Dispatch Consideration
each departure:
a) Flight is not conducted in known or forecast
icing conditions;
b) A power-up test is performed b',' cycling
WING A/ICE switch fromOFF to ON; and
c) None of the following GAS messages are
also posted:
- ICE DETECT FAIL Caution;
- L BLEED SYS FAIL Caution;
-R BLEED SYS FAIL Caution;
- ICE DETECT FAULT Advisory;
-L BLEED FAULT Advisory;
.-R BLEED FAULT Advisory,
OPERATIONS (01
Before each flight:
(1) Make sure that the aeroplane is not powered on and that engines and APU are OFF.
a.
Connect efectttcat power lo the aeroplane as follows:
Note: Do not use a Jet Airstar:t Cart or High Pressure Ground cart
i. Connect.external AG power, OR
start the APUasfoltews:
OR the ELECTRICAL control panel, set the BATT MASTER switch fo.
ON.
2.
Oh the. BLEED/AlR COND control panel, make sure !hatfhe APU
BLEED switch is.set to OFF.
3.
OntheAPU control panel, turn the APU switch to START.
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1.
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ii.
Federal Register / Vol. 89, No. 62 / Friday, March 29, 2024 / Rules and Regulations
22081
b. When external AC power is on or APU is running, wait a minimum of 6 minwtes.
c.
After 6 minutes, make sure that the ELGAS primary display shows as follows:
i. If the AclvisoryWING Al!CE FAULT shows.DISPATCH IS-PERMITTED.
Note: If the Advisory WING A/ICE FAULT shows, it confirms it is not heat related
and.therefore cannot be a potentiaUEiakin the presence of an affected part
ii. If the Advisory WING Al!CE FAULT does notshow, DISPATCH IS NOT
PERMITTED.
Note: lfthe Advisory WING AflCE FAULT does not show, it 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 fromthe aeroplane,
e.
Jf required,sel APU BLEEDto AUTO.
2. OPtRATIONS (0)
Before each flight and after engine start:
(1} Perform a power-up test as follows;
a.
On the ANTI-ICE i:;ontrol panel, cycle the WING switch from OFF to()(',!_
b. On the EICAS primary display, make sure that the following GAS status message is
shown:
- WING-AflCE ON
c.
On the EICAS primary display, make sure that the following CAS message$ are not
shown:
-L WING NICE FAIL{GaUtionJ
- R WING AflCE FAIL (Caution)
(2) On the EICAS primary display, make sure that ttie following GAS hiessases are riot shown:
- ICE DETECT FAIL (Caution)
- L BLEED SYS F,ll;IL (Cautiol'.1}
- R BLEED SYS FAIL (Caution)
- ICE DETECT FAULT (Advisory}
- L BLEED FAULT (Advisory)
~R BLEED FAULT (Advisory}
(3) Operations are not conducted iii known or forecast icing conditions.
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Figure 8 to Paragraph (i)—TRIM AIR
FAULT
22082
Federal Register / Vol. 89, No. 62 / Friday, March 29, 2024 / Rules and Regulations
TRIM AIR FAULT
CAS Indication
1.
2.
Dispatch Consideration
TR1M AIR FAULT
(Advis.Oly)
C
(0)
Aircraft may l:ie dispatched provide'd:
.a) Duct temperature indications are operative
forall three ducts;
b) Either HASOV showing inGQrrect indication
on Synoptic page is verified CLOSED; and
c) L PACK FAIL or R PACK FAIL Caution
messages are .not displayed.
1.
OPERATIONS (0)
Before each flight:
(1) Make sure that the aeroplane is not powered on and that engines and APU are OFF.
a.
Connect electrical power to the aeroplane as follows:
Nole: Do not use a.Jet Airstart Cart or High Pressure Ground Ca1t
i.
Connect.external ACpower, OR
ii. Startthe APU.asfollows:
1.
On the ELECTRl~AL control panel, set the BATT MASTER switcn 10
ON.
2.
Oh the BLEED/AIR COND control panel, make sure that the APU
BLEED switch is s~ to OFF.
3.
on the APU control Jjanel, turn the APU switch to ST ART.
b.
Wheh external AC power is on at APU is running, wait a fni nimum of 6 minutes.
c.
After 6 minutes, make sure that the EICAS prlmary display shows as follows•
If.the Advisory TRIM AIR FAULT shows, DISPATCH IS PERMITTED.
i.
Note: lf!he Advisory TRIM AIR FAULT shows, it confirms ii is not heat related
and therefore cannot be ·a potential leak in the presence of an affected part.
iL
If the Advisory TRIM AlR FAULT does not show, DISPATCH IS NOT
PERMITTED.
Note: If the Advisory TRIM AIR FAULT does not show, it 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 aeroplane.
e.
If required, set APU BLEED to AUTO.
2. OPERATIONS 10\
Before each flight and after engine start:
(1} On the AIR CONDITIONING synoptic page, make sure thatthe duct temperature indications are
operative for all three dllcts.
(2) Make sure thateifher HASOV that shows fncOrrect indi()atidti on the AIR CONDITIONING
synoptic page is verified CLOSED c1s follows:
a.
On the BLEEQfAIR COND control pc1nel, .alternate the TRIM AIR switch from ON to OFF
to ON.
b,
At. the same time, on the AIR CONDITIONING synbptic page, identifythe HASOV that
shows incorrect indication,
c.
In the flight compartment, on the EMSCDU, open the applicable circuit breaker c1s
follows:
d.
SYSTEM NAME
CIRCUIT BREAKER
NAME
BUS NAME
AIR C0NDIPRES8
LECSHASOV
DCESS
AIR CONDJPRES8
RECSHASOV
DCESS
In the aft equipment compartment, make sure that any identified HA80Vis in the
CLOSED position.
BILLING CODE 4910–13–C
(j) Testing and Replacement of Affected
Overheat Detection Sensing Elements
(1) For Group B and D airplanes, and
Group A and C airplanes required by
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paragraph (h) of this AD: Within 2,000 flight
hours or 120 months, whichever occurs first,
from the effective date of this AD, test the
overheat detection sensing elements to
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- L PACK FAIL (Caution)
- R PACK FAIL (caution)
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(;3) bn the EICAS primary display, make sure that the following GAS messages are not shown:
Federal Register / Vol. 89, No. 62 / Friday, March 29, 2024 / Rules and Regulations
determine if they are serviceable, in
accordance with the Accomplishment
Instructions of the applicable Bombardier
service bulletin in paragraphs (j)(1)(i) through
(vi) of this AD.
(i) For Model BD–700–1A11 (Global 5000)
airplanes: Bombardier Service Bulletin 700–
1A11–36–005, Basic Issue, dated December
23, 2022.
(ii) For Model BD–700–1A10 (Global
Express and Global Express XRS) airplanes:
Bombardier Service Bulletin 700–36–026,
Basic Issue, dated December 23, 2022.
(iii) For Model BD–700–1A11 (Global 5000
featuring Global Vision Flight Deck)
airplanes: Bombardier Service Bulletin 700–
36–5002, Basic Issue, dated December 23,
2022.
(iv) For Model BD–700–1A11 (Global 5500)
airplanes: Bombardier Service Bulletin 700–
36–5501, Basic Issue, dated December 23,
2022.
(v) For Model BD–700–1A10 (Global 6000)
airplanes: Bombardier Service Bulletin 700–
36–6002, Basic Issue, dated December 23,
2022.
(vi) For Model BD–700–1A10 (Global 6500)
airplanes: Bombardier Service Bulletin 700–
36–6501, Basic Issue, dated December 23,
2022.
(2) For each sensing element that is
serviceable, as determined by paragraph (j)(1)
of this AD, before further flight, mark the
sensing element with a witness mark in
accordance with the Accomplishment
Instructions in the applicable Bombardier
service bulletin in paragraphs (j)(1)(i) through
(vi) of this AD.
(3) For each sensing element that is not
serviceable, as determined by paragraph (j)(1)
of this AD, before further flight, replace the
sensing element with a serviceable part in
accordance with the Accomplishment
Instructions in the applicable Bombardier
Service Bulletin in paragraphs (j)(1)(i)
through (vi) of this AD.
(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.
khammond on DSKJM1Z7X2PROD with RULES
(l) No Reporting Requirement
Although Bombardier service bulletins in
figure 1 to paragraph (g)(2)(ii) and paragraphs
(j)(1)(i) through (vi) of this AD specify 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
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15:53 Mar 28, 2024
Jkt 262001
22083
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.
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locationsoremailfr.inspection@nara.gov.
(n) Additional Information
(1) Refer to Transport Canada AD CF–
2023–17, dated March 8, 2023, for related
information. This Transport Canada AD may
be found in the AD docket at regulations.gov
under Docket No. FAA–2023–2000.
(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.
24 CFR Part 1005
(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 700–1A11–
36–005, Basic Issue, dated December 23,
2022.
(ii) Bombardier Service Bulletin 700–36–
026, Basic Issue, dated December 23, 2022.
(iii) Bombardier Service Bulletin 700–36–
5002, Basic Issue, dated December 23, 2022.
(iv) Bombardier Service Bulletin 700–36–
5501, Basic Issue, dated December 23, 2022.
(v) Bombardier Service Bulletin 700–36–
6002, Basic Issue, dated December 23, 2022.
(vi) Bombardier Service Bulletin 700–36–
6501, Basic Issue, dated December 23, 2022.
(vii) 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 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
PO 00000
Frm 00043
Fmt 4700
Sfmt 4700
Issued on February 8, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–06626 Filed 3–28–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOUSING AND
URBAN DEVELOPMENT
[Docket No. FR–5593–C–03]
RIN 2577–AD01
Strengthening the Section 184 Indian
Housing Loan Guarantee Program;
Correction
Office of the Assistant
Secretary for Public and Indian
Housing, U.S. Department of Housing
and Urban Development (HUD).
ACTION: Final rule; correction.
AGENCY:
The Department of the
Housing and Urban Development (HUD)
is correcting a final rule entitled,
‘‘Strengthening the Section 184 Indian
Housing Loan Guarantee Program’’ that
published in the Federal Register on
March 20, 2024.
DATES: Effective June 18, 2024.
FOR FURTHER INFORMATION CONTACT:
With respect to this technical
correction, contact Aaron Santa Anna,
Associate General Counsel for
Legislation and Regulations, Department
of Housing and Urban Development,
451 7th Street SW, Room 10238,
Washington, DC 20410; telephone
number 202–708–1793 (this is not a tollfree number). HUD welcomes and is
prepared to receive calls from
individuals who are deaf or hard of
hearing, as well as individuals with
speech or communication disabilities.
To learn more about how to make an
accessible telephone call, please visit
https://www.fcc.gov/consumers/guides/
telecommunications-relay-service-trs.
SUPPLEMENTARY INFORMATION: On March
20, 2024 (89 FR 20032) (FR Doc. 2024–
05515), HUD published a final rule that
amends its regulations governing the
Section 184 Indian Housing Loan
Guarantee Program (Section 184
Program). The rule clarifies the rules
governing Tribal participation in the
Section 184 Program by establishing
underwriting requirements, closing and
endorsement processes, and stronger
and clearer servicing requirements. The
rule also strengthens the Section 184
SUMMARY:
E:\FR\FM\29MRR1.SGM
29MRR1
]]>Agencies
[Federal Register Volume 89, Number 62 (Friday, March 29, 2024)]
[Rules and Regulations]
[Pages 22069-22083]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-06626]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2000; Project Identifier MCAI-2023-00415-T;
Amendment 39-22678; AD 2024-03-08]
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-700-1A10 and BD-700-1A11 airplanes.
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, 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, would prohibit 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 May 3, 2024.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 3, 2024.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-2000; 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
[[Page 22070]]
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 liebherr.aero.
You may view this material 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-2023-2000.
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-700-1A10 and BD-700-1A11 airplanes. The NPRM published
in the Federal Register on November 15, 2023 (88 FR 78251). The NPRM
was prompted by AD CF-2023-17, dated March 8, 2023 (Transport Canada AD
CF-2023-17) (also referred to as the MCAI), issued by Transport Canada,
which is the aviation authority for Canada. 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, would 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-2023-2000.
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 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-2023-17, 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.
Change to NPRM Applicability
Paragraph (c) of this AD has been revised to clarify that the
applicability is limited to certain serial numbers, which are also
identified in Transport Canada AD CF-2023-17.
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 the following Bombardier service bulletins, which
specify 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. These documents are distinct since they apply
to different airplane models and configurations.
Bombardier Service Bulletin 700-1A11-36-005, Basic Issue,
dated December 23, 2022;
Bombardier Service Bulletin 700-36-026, Basic Issue, dated
December 23, 2022;
Bombardier Service Bulletin 700-36-5002, Basic Issue,
dated December 23, 2022;
Bombardier Service Bulletin 700-36-5501, Basic Issue,
dated December 23, 2022; and
Bombardier Service Bulletin 700-36-6002, Basic Issue,
dated December 23, 2022;
Bombardier Service Bulletin 700-36-6501, Basic Issue,
dated December 23, 2022.
This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 160 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
[[Page 22071]]
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 140 work-hours x $85 per hour $0 Up to $11,900................ Up to $1,904,000.
= $11,900.
----------------------------------------------------------------------------------------------------------------
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 one sensor.
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:
2024-03-08 Bombardier, Inc.: Amendment 39-22678; Docket No. FAA-
2023-2000; Project Identifier MCAI-2023-00415-T.
(a) Effective Date
This airworthiness directive (AD) is effective May 3, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc., Model BD-700-1A10 and BD-
700-1A11 airplanes, certificated in any category, serial numbers
9002 through 9879 inclusive, 9998, and 60001 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) through (3) of this AD apply.
(1) The following Model BD-700-1A10 and BD-700-1A11 airplane
groups are identified in (g)(1)(i) through (iv) of this AD:
(i) Group A airplanes: serial numbers (S/N) 9002 through 9151
inclusive, and 9153.
(ii) Group B airplanes: S/N 9152, 9154 through 9879 inclusive,
9998, 60001 through 60041 inclusive, 60043, 60044, 60045, and 60051.
(iii) Group C airplanes: S/N 60042, 60046, 60047, 60049, 60053,
and subsequent.
(iv) Group D airplanes: S/N 60048, 60050, and 60052.
(2) An affected part is a sensing element marked with a date
code A0448 through A2104 inclusive 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)(2)(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 4 (the figure is
representative for all sensing elements) in the Accomplishment
Instructions of the applicable Bombardier service bulletin (BA SB)
in figure 1 to paragraph (g)(2)(ii) of this AD.
Figure 1 to Paragraph (g)(2)(ii)--Applicable Service Information
BILLING CODE 4910-13-P
[[Page 22072]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.003
(3) A serviceable part is a sensing element that is not an
affected part.
(h) Maintenance Records Verification
For Groups A and C whose airplane date of manufacture, as
identified on the identification plate of the airplane or in the
aircraft maintenance logbook, is on or before July 27, 2022 (the
effective date of Transport Canada AD CF-2022-38): 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 confirm 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 applicable compliance times specified in
paragraphs (i) and (j) of this AD.
(2) For Groups A and C airplanes: 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 Groups B and D airplanes, and Groups A and C airplanes
required by paragraph (h) of this AD: Within 90 days after the
effective date of this AD, revise the operator's existing MEL by
incorporating the information specified in figures 2 through 8 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 2 to Paragraph (i)--MMEL Item 36-12-01
[[Page 22073]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.004
Figure 3 to Paragraph (i)--MMEL Item
BILLING CODE 36-12-01-1
[[Page 22074]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.005
[[Page 22075]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.006
Figure 4 to Paragraph (i)--MMEL Item
BILLING CODE 36-12-01-2
[[Page 22076]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.007
Figure 5 to Paragraph (i)--L BLEED FAULT
[[Page 22077]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.008
[[Page 22078]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.009
Figure 6 to paragraph (i)--R BLEED FAULT
[[Page 22079]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.010
[[Page 22080]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.011
Figure 7 to Paragraph (i)--WING A/ICE FAULT
[GRAPHIC] [TIFF OMITTED] TR29MR24.012
[[Page 22081]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.013
Figure 8 to Paragraph (i)--TRIM AIR FAULT
[[Page 22082]]
[GRAPHIC] [TIFF OMITTED] TR29MR24.014
[GRAPHIC] [TIFF OMITTED] TR29MR24.015
BILLING CODE 4910-13-C
(j) Testing and Replacement of Affected Overheat Detection Sensing
Elements
(1) For Group B and D airplanes, and Group A and C airplanes
required by paragraph (h) of this AD: Within 2,000 flight hours or
120 months, whichever occurs first, from the effective date of this
AD, test the overheat detection sensing elements to
[[Page 22083]]
determine if they are serviceable, in accordance with the
Accomplishment Instructions of the applicable Bombardier service
bulletin in paragraphs (j)(1)(i) through (vi) of this AD.
(i) For Model BD-700-1A11 (Global 5000) airplanes: Bombardier
Service Bulletin 700-1A11-36-005, Basic Issue, dated December 23,
2022.
(ii) For Model BD-700-1A10 (Global Express and Global Express
XRS) airplanes: Bombardier Service Bulletin 700-36-026, Basic Issue,
dated December 23, 2022.
(iii) For Model BD-700-1A11 (Global 5000 featuring Global Vision
Flight Deck) airplanes: Bombardier Service Bulletin 700-36-5002,
Basic Issue, dated December 23, 2022.
(iv) For Model BD-700-1A11 (Global 5500) airplanes: Bombardier
Service Bulletin 700-36-5501, Basic Issue, dated December 23, 2022.
(v) For Model BD-700-1A10 (Global 6000) airplanes: Bombardier
Service Bulletin 700-36-6002, Basic Issue, dated December 23, 2022.
(vi) For Model BD-700-1A10 (Global 6500) airplanes: Bombardier
Service Bulletin 700-36-6501, Basic Issue, dated December 23, 2022.
(2) For each sensing element that is serviceable, as determined
by paragraph (j)(1) of this AD, before further flight, mark the
sensing element with a witness mark in accordance with the
Accomplishment Instructions in the applicable Bombardier service
bulletin in paragraphs (j)(1)(i) through (vi) of this AD.
(3) For each sensing element that is not serviceable, as
determined by paragraph (j)(1) of this AD, before further flight,
replace the sensing element with a serviceable part in accordance
with the Accomplishment Instructions in the applicable Bombardier
Service Bulletin in paragraphs (j)(1)(i) through (vi) of this AD.
(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 bulletins in figure 1 to paragraph
(g)(2)(ii) and paragraphs (j)(1)(i) through (vi) of this AD specify
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-2023-17, dated March 8,
2023, for related information. This Transport Canada AD may be found
in the AD docket at regulations.gov under Docket No. FAA-2023-2000.
(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 700-1A11-36-005, Basic Issue,
dated December 23, 2022.
(ii) Bombardier Service Bulletin 700-36-026, Basic Issue, dated
December 23, 2022.
(iii) Bombardier Service Bulletin 700-36-5002, Basic Issue,
dated December 23, 2022.
(iv) Bombardier Service Bulletin 700-36-5501, Basic Issue, dated
December 23, 2022.
(v) Bombardier Service Bulletin 700-36-6002, Basic Issue, dated
December 23, 2022.
(vi) Bombardier Service Bulletin 700-36-6501, Basic Issue, dated
December 23, 2022.
(vii) 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 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/[email protected]">www.archives.gov/federal-register/cfr/[email protected].
Issued on February 8, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-06626 Filed 3-28-24; 8:45 am]
BILLING CODE 4910-13-P
