Airworthiness Directives; Bombardier, Inc., Airplanes, 78251-78265 [2023-24007]
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Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
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Dated: November 8, 2023.
Joyce Connery,
Chair.
[FR Doc. 2023–25074 Filed 11–14–23; 8:45 am]
BILLING CODE 3670–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–2000; Project
Identifier MCAI–2023–00415–T]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier, Inc., Model BD–
700–1A10 and BD–700–1A11 airplanes.
This proposed 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 proposed AD would
require maintenance records
verification, and if an affected part is
installed, would prohibit the use of
certain Master Minimum Equipment
SUMMARY:
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78251
List (MMEL) items under certain
conditions by requiring revising the
operator’s existing MEL. This proposed
AD would also 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. This proposed AD
would also prohibit the installation of
affected parts under certain conditions.
The FAA is proposing this AD to
address the unsafe condition on these
products.
The FAA must receive comments
on this proposed AD by January 2, 2024.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
regulations.gov. Follow the instructions
for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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 NPRM, the mandatory
continuing airworthiness information
(MCAI), any comments received, and
other information. The street address for
Docket Operations is listed above.
Material Incorporated by Reference:
• For Bombardier service information
identified in this NPRM, 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 NPRM, contact Liebherr-Aerospace
Toulouse SAS, 408, Avenue des EtatsUnis—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
DATES:
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Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7300;
email: 9-avs-nyaco-cos@faa.gov. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
availability of this material at the FAA,
call 206–231–3195.
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:
ddrumheller on DSK120RN23PROD with PROPOSALS1
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2023–2000; Project Identifier
MCAI–2023–00415–T’’ at the beginning
of your comments. The most helpful
comments reference a specific portion of
the proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend the proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to
regulations.gov, including any personal
information you provide. The agency
will also post a report summarizing each
substantive verbal contact received
about this NPRM.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to Steven Dzierzynski,
Aviation Safety Engineer, FAA, 1600
Background
Transport Canada, which is the
aviation authority for Canada, has
issued Transport Canada AD CF–2023–
17, dated March 8, 2023 (Transport
Canada AD CF–2023–17) (also referred
to after this as the MCAI), to correct an
unsafe condition on certain Bombardier,
Inc., Model BD–700–1A10 and BD–700–
1A11 airplanes. 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.
The FAA is proposing 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.
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;
• Bombardier Service Bulletin 700–
36–6002 Basic Issue, dated December
23, 2022; and
• Bombardier Service Bulletin 700–
36–6501 Basic Issue, dated December
23, 2022.
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.
FAA’s Determination
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 and service
information described above. The FAA
is issuing this NPRM after determining
that the unsafe condition described
previously is likely to exist or develop
on other products of the same type
design.
Proposed AD Requirements in This
NPRM
This proposed AD would require
maintenance records verification. If an
affected part is installed, this proposed
AD would prohibit the use of certain
MMEL items unless specific dispatch
instructions are followed by revising the
operator’s existing MEL and
accomplishing the actions specified in
the service information already
described. For certain airplanes, this
proposed AD would also require testing
each 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 proposed
AD would also prohibit the installation
of affected parts under certain
conditions.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 160
airplanes of U.S. registry. The FAA
estimates the following costs to comply
with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per product
Up to 140 work-hours × $85 per hour =
Up to $11,900.
$0
Up to $11,900 .......................................
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Cost on U.S. operators
Up to $1,904,000.
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The FAA has received no definitive
data on which to base the cost estimates
for the on-condition actions specified in
this proposed AD. The FAA estimates it
would take up to 1.5 hours to replace a
sensing element.
The FAA has included all known
costs in its cost estimate. According to
the manufacturer, however, some or all
of the costs of this proposed 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.
ddrumheller on DSK120RN23PROD with PROPOSALS1
Regulatory Findings
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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 this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
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(3) Would 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 Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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:
■
Bombardier, Inc.: Docket No. FAA–2023–
2000; Project Identifier MCAI–2023–
00415–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by January 2,
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.
(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
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78253
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 4910–12–P
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'Aeroplane Model
(Marketing Designation)
Applicable 8A SB
B0-700-1A10
(Global Express & Global Exprea XRS)
SB 700-36-026 Basic Issue, dated 23 December
2022, or later revisions approved by the Chief,
Continuing Aiwonhineu, Transport Canada
B0-700-tA11
(Global S000)
SB 700-1A11-36-005 Basic Issue, dated 23
Oecember 2022, or later reviaion& approved by
the Chiltf, Continung Airworthiness, Transport
Canada
BO-700-1A11
(Global 5000 featuring Global Vision Flight Deck)
SB 700..36-5002 Balk Jstue, dated 23 December
2022, or tater revisions approved by the Chief,
Continuing AirM>nhiness, Traneport Canada
BO-70Q..1A10
(Global 6000}
S8 700-36-6002 Basie Issue, dated 23 December
2022, or later revilions approved by the Chief,
Continuing Airworthiness, Traneport Canada
80-700-1At1
(Glo.,_I 5500)
SB 700-36-S501 Baslc lstUe, dated 23 December
2022, or later reviaione approved by the Chief,
Contwluing Airworthiness, Transport Canada
BO-700-1A10
(Global 6500)
SB 700-36-6501 Basic issue, de1ed 23 December
2022, or later revisions approved by the Chief,
Continuing Airwof'Ulinesa, Tranaport Canada
(3) A serviceable part is a sensing element
that is not an affected part.
ddrumheller on DSK120RN23PROD with PROPOSALS1
(h) Maintenance Records Verification
For Groups A and C whose airplane date
of manufacture, as identified on the
identification plate of the airplane, 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
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manufacture, as identified on the
identification plate of the airplane.
(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
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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.
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78255
Figure 2 to paragraph (i)-MMEL Item 36-12-01
MNEL Jtem.36-12-01
1. ~em& sequence
a Number
2. Nllmbet·
Installed
NO Item
Fl>t
C>ispatch
Ni>mtire
NO<te systeme/Hrie:
d'M:icle
art1e1e
4.. Remarks or Exceptions
Required
NOmbre
insta11es
d'articles:
aexpedler
36 c PNEUMATICS
12-01 BleedLeak,Detection
Loops
18
(0) Either loopAor loop.B may be
9
inoperative proVidedredundant loop.in
C
the same zone is ..operative,
t. PLACARD
(1).. Put.aBLEEO .LEAK DETECTION LOOPS. INOPERATIVE plai;iafd:Oifthe ihsttumentpanel,
2. OPERATIONS /Ol
Before eaohflight:
(1J .Make sore rnautte aeroplanels not poWered on and that enginesaridAPUare OFF
a.. Conneot ele¢fiical power to: the aefoplane as folloWs:
Note: bo.notuseaJet.AitstartCarf.or High PressureGtbundCart..
Ccinne-ctexternatACpoWer, 08
if;
starttheAPUas:fbllOWs'.
1, Oh the E1£CTRIC;q control panel, setlt:\e BATT MASTER sWitchto.
ON,
2.
ontneBl..EEDIAlffCON□ cohtrol pane(
make sure thafthe APU
BLEEDswitoh issetto OFF.
s: OhtheAPUcoiiliol panel, tum.the APU sWitchfoSTART.
b. When externafAC poweris on or APU is running, wait a minimum of 6 minutes.
.-0, After 6 minutes, make surethaUhe EICAS.primary display .shows as follows:
lfthe AdVisoryL BLEED FAULT .or R BLEEOFAULT shows; DISPATCH IS
PERMITTED:
Note: lftheAdvi!>ory LBLEEci i=ft.lJLT or RBLE;EtJ FAULrshO'.Vs,lt-0ont1rrris it
is not heat related and therefore cannot be a poteril:ial leak in the presence of an
affected part
ii: If thEl Acivi!S9ry 4BLsEPP,lJLTor RaLEli:PFAVLT goes nm show; PISPAlt:8
IS NOT PER~ITTED:
NQfEl: i(tfieA~lSOty L BLEED Fftptr or ~BLEEP FAULT dQE!S n()t ~how, it
confirms thattt i~ heat TE;/lated ~net t~refor:e qoµld t?e:a potential le~k inthe
PTEl'S¢(1~. of an affE!Ctecl par[
cl,
.~ r~qQfred, remove extemafAC powerlrorrrthea~rop~o:e:
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e, If required, set APU BLEEbtoAUto.
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Figure 3 to paragraph (i)-MMEL Item 36-12-01-1
MMEL Item 38-1~01-1
1. System & Sequence
NO Item
2. Number
Installed
NO de systeme/serie
article
Nombre
d'article
installes
3.
Number
Required
For
Dispatch
4. Remarks or Exceptions
Nombre
d'articles
a expedier
36 - PN5UMATICS
12-0.1 Bleed Leak Detecti_on
L,oops
18
(0) Either loop A or loop B may be
9
inoperative provided redundant loop
C
in the same.zone is operative.
1_2
1) Wing Anti-Ice Leak
(M) (O) One loop _in each section may
6
be inoperative provided:
C
a) Power-up BiT test is performed
on systl:!m prior to each dispatch
into icing, and
b) Cause of WING ANTI-ICE
FAULT Advisory message is
confirmed by maintenance.
1.
PLACARD
(1) Put a WING ANTI-ICE LEAK INOPERATIVE placard on the instrument panel.
2. OPERATIONS (Ol
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 JetAirstart Cart or High Pressure Ground Cart.
i. Conne_ct external AC power; OR
ii. start the APU as foHows:
1. On the E:LECiRICAL control 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 to OFF.
3. On the APU bbntrol panel, tum the APU switch to ST ART.
b. When external AC power is on or APU is running, wait a minimum of 6 minutes.
c.
After 6 minutes, make sure that the EICAS primary display shows as follows:
i. If the Advisory WING A/ICE FAULT shows, DISPATCH IS PERMITTED Unless
step (2) of the Maintenance (M) procedure under (3) below does not pass, in
Which case DISPATCH IS NOT PERMITTED.
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ddrumheller on DSK120RN23PROD with PROPOSALS1
Note: If the Advisory WING NICE FAULT shows, it confirms it is notheat related
and therefore cannot be a potential leak in the presence of an affebted part.
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
ii.
78257
If the Advisory WING A/ICE FAULT does not show, DISPATCH IS NOT
PERMITTED.
Note; If the Advisory WING A/ICE 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.
3,
d.
If required, remove external AC power from the aeroplane.
e.
If required, set APU BLEED to AUTO.
MAINTENANCE (Ml
The requirement to perform.this section is conditional on (1)(C)(i) under the Operations (0) procedure
above.
(1) Power-up BIT test is performed on system prior lo each dispatch into icing.
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ddrumheller on DSK120RN23PROD with PROPOSALS1
(2) The cause of the WING ANTI-ICE FAULT Advisory message is to be confirmed by maintenance
personnel to make sure that no section has encountered a dual loop failure.
78258
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
Figure 4 to paragraph (i) -MMEL Item 36-12-01-2
MMEL Item 36•12-01-2
1. System & Sequence
No Item
2. Number
Installed
NO de systl}me/serle
article
Nombre
d'article
installes
36 • ENl;;k.!Mfil!QS
12-01 Bleed Leak Detection
Loops
18
3.
Number
Required
For
Dispatch
4.
Remarks or Exceptions
Nombre
d'articles
aexpedier
9
(0) Either loop A or loop B may be
ihoperative provided redundant loop
C
in the same zone is operative .
..
"'
2) Trim Air Leak
(O) Except for ER. operations; one
1
2
,
loop may be inoperative.
C
1. PLACARD
(1) Put a TRIM AIR LEAK INOPERATIVE placard on the instrument panel.
2. QEERfillONS
Before each flight:
<Ol
(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 or High Pressure Ground cart.
i. Connect external AC power, OR
ii. Start the APU as follows:
1.
On the ELECTRICAL control 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 to OFF,
3.
b.
On the APU control panel 1 turn the APU switch to. ST ART.
When external AC power is on or APU is running, wait a minimum of 6 minutes.
c. After 6 minutes, make sure that the EICAS primary display shows as follows:
If the Advisory TRIM AIR FAULT shows, DISPATCH IS PERMITTED.
Note: If the Advisory TRIM AIR FAULT shows, it confirms it is not heat related
and therefore cannot be a potential leak In the presence ofan affected psrt.
ii. If the Advisory TRIM AIR FAULT does notshow, DISPATCH IS NOT
PERMITTED.
VerDate Sep<11>2014
16:31 Nov 14, 2023
d.
If required, remove external AC power from the aeroplane.
e.
If required, set APU BLEED to AUTO.
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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.
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
78259
Figure 5 to paragraph (i) - L BLEED FA ULT
L BLEED FAULT
CAS Indication
1.
2.
Dispatch Consideration
L BLEED FAULT
C
(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 ANTI-ICE FAIL Caution;
-XBLEED FAIL Caution;
- R BLEED FAULT Advisory;
- WING ANTI-ICE FAULT Advisory;
b) Left PRV and left HPSOV open and close
correctly in response to L BLEED OFF switch
selection, as indicated on Synoptic Page;
c) Left HPSOV is open at engine idle and
closed at high thrust settings, as indicated on
Synoptic Page;
d) WING XBLEED FROM R is selected and
remains open; and
e) Operations are not conducted in known or
forecast icing conditions.
(Advisory)
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:
Note: Do not use a Jet Airstart Cart or High Pressure Ground Cart.
VerDate Sep<11>2014
16:31 Nov 14, 2023
Jkt 262001
Connect external AC power, OR
Start the APU as follows:
1.
on the ELECTRICAL control 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 to OFF.
3.
On the APU control panel, turn the APU switch to ST ART
When external AC power is on or APU is running, wait a minimum of 6 minutes.
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ddrumheller on DSK120RN23PROD with PROPOSALS1
b.
i.
ii.
78260
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
c.
After 6 minutes, make sure that the EICAS primary display shows as follows:
i.
If the Advisory L BLEED FAULT shows, DISPATCH IS PERMITTED.
Note: If the Advisory L BLEED FAULT shows, it confirms it is not heat related
and therefore cannot be a potential leak in the presence of an affected part
ii
If the Advisory L BLEED FAULT does not show, DISPATCH IS NOT
PERMITTED.
Note: If the Advisory L BLEED 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
2.
d
If required, remove external AC power from the aeroplane.
e.
If required, set APU BLEED to AUTO.
OPERATIONS (Ol
Before each flight and after engine start:
(1) On the EICAS primary display, make sure that the messages that follow do not show:
- R BLEED SYS FAIL (Caution)
R WING ANTI-ICE FAIL (Caution)
-XBLEED FAIL (Caution)
- R BLEED FAULT (Advisory)
- WING ANTI-ICE FAULT (Advisory)
(2) Make sure that the left Pressure Regulator Valve (PRV) and left High Pressure Shut Off Valve
(HPSOV) open and close as follows:
a.
On the BLEED/AIR COND control panel, set the LENG BLEED switch to OFF.
b.
On the BLEED/ANTI-ICE synoptic page, make sure that the left PRV and left HPSOV
show closed.
c.
On the BLEED/AIR COND control panel, set the LENG BLEED switch to AUTO.
d.
On the BLEED/ANTI-ICE synoptic page, make sure that the left PRV and left HPSOV
show open.
(3) Make sure that the left High Pressure Shut Off Valve {HPSOV) switching operates as follows:
a.
Slowly advance the left throttle to high thrust setting.
b.
On the BLEED/ANTI-ICE synoptic page, make sure that the left HPSOV shows closed
c.
Slowly retard the left throttle to engine idle.
d
On the BLEED/ANTI-ICE synoptic page, make sure that the left HPSOV shows open.
(4) On the ANTI-ICE control panel, set the WING XBLEED to FROM R for the rest of the flight
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ddrumheller on DSK120RN23PROD with PROPOSALS1
(5) Operations are not conducted in known or forecast icing conditions.
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
78261
Figure 6 to paragraph (i) - R BLEED FA ULT
R BLEED FAULT
CAS Indication
1.
2.
Dispatch Consideration
R BLEED FAULT
(Advisory)
C
(0)
Aircraft may be dispatched provided, prior to
each flight:
a) None of the following messages are also
posted:
- L BLEED SYS FAIL Caution;
- L WING ANTI-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 is open at engine idle and
closed at high thrust settings, as indicated on
Synoptic Page.;
d) WING XBLEED FROM L is selected and
remains open; and
e) Operations are not conducted in known or
forecast icing conditions.
1. OPERATIONS (Ol
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 notuse a Jet Airstart cart or High Pressure Ground Cart.
i. Connect external AC power, OR
ii. Start the APU as follows:
t
On the ELECTRICAL control 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 to OFF.
3.
On the APU control panel, turn the APU switch to ST ART.
b.
When external AC power is on or APU is running, wait a minimum of 6 minutes,
c.
After 6 minutes, make sure that the EICAS primary display shows as follows:
If the Advisory R BLEED FAULT shows, DI.SPATCH JS PERMITTED.
Note: If the Advisory R BLEED FAULT shows, ii confirms it is not heat related
and therefore oa.nnot be a potential leak in the presence of an affected part.
ii: If the Advisory R BLEED FAULT does not show, DISPATCH IS NOT
PERMITTED.
Note: lrlhe Advisory R BLEED FAULT does not show, ifconfirms that it is heat
related and therefore could be a potential leak in the presence of an affected.
part.
2.
d.
If recuired, remqve external.AC power from the aeroplane.
e.
If required, set APU BLEED to AUTO,
OPERATIONS (Ol
Before each flight and after engine start:
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ddrumheller on DSK120RN23PROD with PROPOSALS1
(1} On the EICAS primary. display, make sure that the messages that follow do not shoW:
78262
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
- L BLEED SYS FAIL (Caution)
- L WING ANTI-ICE FAIL (Caution)
-XBLEED FAIL (Caution)
- L BLEED FAULT (Advisory)
-WING ANTl•ICE FAULT (Advisory)
(2) Make sure that the right Pressure Regulator Valve (PRV) and right High Pressure Shut Off Valve
(HPSOV) open and close as follows:
a.
On the BLEED/AIR COND control panel, set the R ENG BLEED switch to OFF.
b. On the BLEED/ANTI-ICE synoptic page, make sure that the right PRY and right HPSOV
show closed.
•
c.
On the BLEED/AIR COND control panel, set the R ENG BLEED switch to AUTO.
d
On the BLEED/ANTI-ICE synoptic page, make sure that the right PRV and right HPSOV
show open.
(3) Make sure that the right High Pressure Shut Off Valve (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 that the right HPSOV shows closed.
c.
Slowly retard the right throttle to engine idle.
d.
On the BLEED/ANTI-ICE synoptic page, make sure thatthe right HPSOV shows open.
(4) On the ANTI-.ICE control panel, set the WING XBLEED to FROM L for the rest of the flight
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ddrumheller on DSK120RN23PROD with PROPOSALS1
(5) Opar11tions are not conducted in. known or forecast icing conditions.
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
78263
Figure 7 to paragraph (i)- WING A/ICE FAULT
WIN(3.AJICEF,~ULT
CAS: IN<ttcatlon.
1..
2.
WING A/ICE FAULT
(AdviSOI)')
C
(d) .Aircraft may be dispatched provided, prior to.
-each departure:
a) Flight is not conducted in known or-forecast
icing conditions;
ti) A power,uptest is performed·t,y cycling
• WiNG A/ICE swttch from OFFto,bN;arid
.c) None of the following CAS messages are
also posted'
~ ICE DETECT FAILCaution;
-LBLEED SYS FAIL Caution;
~-R BLEEDSYSFAILCaution;
~ ICE DETECT FAULT AclVisory;a
-LBLEED FAULTAdvisoiy; ••
'"' R BLEED FAULT Advisory:
t
Dlspatch.Co,nslderatlon
QPi:RAtfONs /bi
Bef9re eacl1 tligt,t
ch Mai<e sure tkat frie aetop\ar1e ~ r1of pqwered or1 and that englres ani;l APllare OFF:
a:, Conne<:t e11!Ctiicaipower tcrifie,aeroprar,e as.follows::
Note: Do,:rititJJse a, Jet Airatattcart or High Pl:eS$Ure Gttiuhd Catt
c~crexternal AC powar, OR
ii: stattthi'!APUaS.f6110W$:
,. Qrith.al:;LECTRICALcOhtrol pa/'lel,setthe SATT MASTER siiiiti:;hto
ON.
•
2. On.the BLEED!AIR"COND control panel; make sure.1hiitttie APU
BLEED .switeh is,se.t to OFF.
3;. OntheAPUcontrol panel, !umlhe APU swltchtoSTART,
be \Nheh externaLA¢ pc;w¢ris on or ARU l¢running, wai!a mkilmurn Of 6minutes.
1;
After 6 rrtlrtlltes; tnaka$urelhatltte EICAS primary diilplat.shoWS'lis follbws:
lflhe Advisory WING AIICE FAULT st!QWs, DISPATCH ISPi:;RMITTEQ
Note: lfthe-Adliistify WING A/ICE FAULT shows, itbbhfiifnS:iti$ niltheane1ared
.and. thereto re cannot be .a PQtentiaueak ii:lthe priis11r1ce.oi-an affected part:
ii: Jfthe AdviisoryWING A/ICE FAULT doe&nbfshoW, DISPATCH IS NOT
PERMITTED.
Note! lfthaAdlli$tify WING A/ICE FAULT dtiei:l hOt shaw; ltcOi:lfifrlis that jfis
heal related abd.'theretote could be a potential.leak ih thej)resenceorart
affeeted part.
'd;.
lt required, remove extematAC powerfromlheaeroplare.
e: lf.required,.set APU BLEEDto.AUTO.
2, bPt~ATIONS fOl
Before each fligh\ arid atterenglnEl star.t.
(1) Perf()rmaPo'IY,~r'!lptesfa!Sfol[Qws:
ir.. Ori the ANtHdE ¢0ntr()l panel, eyeie tf\eWloo sWitefi rrontGFFjo:bN.
b: drtihe EiCA$ primary :display, make !>Uta Jtlat the /oli0wir1g CAS i.~tus rrtei;sage ill
showr:r
-WINGAliCEON
c on tne!':lCAS prmiarydlspfay, make·sure lnat lhefoiillwfog c:As messaties are not
shown:
-L WING A/ICE FAIL (Caution)
- R VVING A/1CE FAIL (Caution)
-JCE 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)
(;3} Operations are not conducted in known or forecast icing condltioilSa
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ddrumheller on DSK120RN23PROD with PROPOSALS1
(2J On the EICAS primary display, tnake sure thatthe following GAS messages are not stiown:
78264
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
Figure 8 to paragraph (i) - TRIM AIR FA ULT
TRIM AIR FAULT
CAS lndicatfon
1,
TRIM AlR FAOLi"
(M/iS()ry}
C.
2.
Di$patch(fonslderation
(0) Aircraft ma{~ dispatched provided:
.
a) Ouct te1nperatutl:! indiqatiQT1$ are tiperaliVl:l
f<lfall three ttuc~;
b) Eith$r HA$QV sfiQWirtg iJ"iCQ~t;t fl'.i91catkin
ort'$Ynoptic page is Vli!tjfi!ld QLQ$ED; al'id
¢) LJW:;K FAIL or R PA9l(FAJL Caution
rnessa9es.are•notdisplayed.
1. OPERATIONS (0)
Before eactUlight
(1J Make sure that.the aetop1aners not powered oh aridthatengines.ahdAPUare C>FF:
.ai Connect electrical power to. theaeroplane asiollows:
Note: Do. not use a Jet AirstartCarf or High Pressure Ground'Cart
t :Connect external AC-power, OR
it Start the,APUasfOliows•
1. Qnthe El..l:::CfRJCAL control pal'iE!r, seHhe BAIT MASTER sw~ctdo
ON.
2: Ohthel3LEEO/AIRCONOcOl'ittOl pane~ make surethatthe A.PU
13LEEDSWitCh iss.et t9 OFF.
ti
3: Ohtlifi.APVtOnti"QI pane~ tuth.the APlJ sWitchtOSTART.
When ext.ernatAc poweris on 0t APtJ isNnntng, wa.it a minimum c:;f s minutes.
c;
Afters
minutes, fhake.sutetnatthe ElCASprima:fy diSpJayshoWsas follows:
L lftheAdVisofyTRlM AlRFAULTshOw.S; DISPATCH IS PERMITTED,.
Note: rftheAdvisoryTRIM AlR FAULT shows;itconfirmsit is.not heat related
and therefore cannot be a potentiaUeak ih,the presence of an affected part:
iL lfthe Adviso.ryTRIM AIRFAUt..Tdo.es not Show, DlSPATCHISNOT
PERMITTED
Note: lfthe.Atlvisory TRIM AIR FAULT does notshOw, it confirms that it is heat
related and therefore.could bea potential leak in the.presence of·an affected
part.
cf;
e,,
lf required, remove externaLAC powedrom the,aeroplane,
If requirecl, ~t AP\,) BLEEP tc,,),.UfO,
2. OPERATIONS lb)
Before eachflight and afterengine $fart:
(''I}
on the AIR ¢QfJbtT1qNlt\J$ syno.ptit paQI:!\ make $Utet~fthe dtidtempe~ure JndicatiohS are
◊Pl:ltaliye foran three duqts:
(2) Make sure that either f-!ASO\hhat shows ihdorrect indicatian.◊nthe AIR coNbmbN1NG
syn◊pticpage
is verified CLOSED as foflQ'NS:
a, Oh the 13LEEO!AIRCQND cOntrol pahel, attetnatethe TRIM AIR switchfrorh ON to OFF
tOON.
b'.
c,
Atthe same:Jlme, orfthaAIRCONDIT10NINS synqpticpage, id&htifytfie HASOVthat
shows incorreet indication;
•
lh the flight eompartml:!nt, oh the EMscou, open the applicable circuit bi'eakeras
d.
SYSTEMNAME
CIRCUIT BREAKER
NAME
BUS NAME
AIR COND/PRESS
LECSHASOV
DCESS
AIR COND/PRESS
RECSHASOV
DCESS
In the aft equipment compartment, make sure that any identified HASOV is in the
CLOSED position.
(3) On the EICAS primary display, make sure that the following CAS messages are not shown:
-LPACK FAIL (Caution)
- R PACK FAIL (Caution}
BILLING CODE 4910–13–C
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ddrumheller on DSK120RN23PROD with PROPOSALS1
fOIIOWS:
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules
(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
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.
ddrumheller on DSK120RN23PROD with PROPOSALS1
(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) 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
VerDate Sep<11>2014
16:31 Nov 14, 2023
Jkt 262001
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
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: 9-avs-nyaco-cos@faa.gov.
(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: www.liebherr.aero.
(5) You may view this service information
at the FAA, Airworthiness Products Section,
PO 00000
Frm 00023
Fmt 4702
Sfmt 4702
78265
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.
Issued on October 26, 2023.
Caitlin Locke,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2023–24007 Filed 11–14–23; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[[Docket No. FAA–2023–2247; Airspace
Docket No. 23–ACE–4]
RIN 2120–AA66
Amendment of VOR Federal Airway V–
132 and Revocation of VOR Federal
Airways V–131, V–307, and V–350 in
the Vicinity of Chanute, KS
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
amend Very High Frequency
Omnidirectional Range (VOR) Federal
airway V–132 and revoke VOR Federal
airways V–131, V–307, and V–350. The
FAA is proposing this action due to the
planned decommissioning of the VOR
portion of the Chanute, KS (CNU), VOR/
Distance Measuring Equipment (VOR/
DME) navigational aid (NAVAID). The
Chanute VOR is being decommissioned
in support of the FAA’s VOR Minimum
Operational Network (MON) program.
DATES: Comments must be received on
or before January 2, 2024.
ADDRESSES: Send comments identified
by FAA Docket No. FAA–2023–2247
and Airspace Docket No. 23–ACE–4
using any of the following methods:
* Federal eRulemaking Portal: Go to
www.regulations.gov and follow the
online instructions for sending your
comments electronically.
* Mail: Send comments to Docket
Operations, M–30; U.S. Department of
Transportation, 1200 New Jersey
Avenue SE, Room W12–140, West
Building Ground Floor, Washington, DC
20590–0001.
* Hand Delivery or Courier: Take
comments to Docket Operations in
Room W12–140 of the West Building
SUMMARY:
E:\FR\FM\15NOP1.SGM
15NOP1
]]>Agencies
[Federal Register Volume 88, Number 219 (Wednesday, November 15, 2023)]
[Proposed Rules]
[Pages 78251-78265]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-24007]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2000; Project Identifier MCAI-2023-00415-T]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11
airplanes. This proposed 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 proposed AD would require
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 MEL. This proposed AD would also 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. This proposed AD would also prohibit the installation
of affected parts under certain conditions. The FAA is proposing this
AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by January 2,
2024.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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 NPRM, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
For Bombardier service information identified in this
NPRM, 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 NPRM, 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
[[Page 78252]]
availability of this material at the FAA, call 206-231-3195.
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:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2023-2000; Project Identifier
MCAI-2023-00415-T'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Steven Dzierzynski, Aviation Safety Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone 516-228-7300; email: [email protected]. Any commentary that the FAA receives which is not
specifically designated as CBI will be placed in the public docket for
this rulemaking.
Background
Transport Canada, which is the aviation authority for Canada, has
issued Transport Canada AD CF-2023-17, dated March 8, 2023 (Transport
Canada AD CF-2023-17) (also referred to after this as the MCAI), to
correct an unsafe condition on certain Bombardier, Inc., Model BD-700-
1A10 and BD-700-1A11 airplanes. 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.
The FAA is proposing 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.
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;
Bombardier Service Bulletin 700-36-6002 Basic Issue, dated
December 23, 2022; and
Bombardier Service Bulletin 700-36-6501 Basic Issue, dated
December 23, 2022.
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.
FAA's Determination
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
and service information described above. The FAA is issuing this NPRM
after determining that the unsafe condition described previously is
likely to exist or develop on other products of the same type design.
Proposed AD Requirements in This NPRM
This proposed AD would require maintenance records verification. If
an affected part is installed, this proposed AD would prohibit the use
of certain MMEL items unless specific dispatch instructions are
followed by revising the operator's existing MEL and accomplishing the
actions specified in the service information already described. For
certain airplanes, this proposed AD would also require testing each 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 proposed AD would also prohibit the
installation of affected parts under certain conditions.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 160 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
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.
Up to $11,900.
----------------------------------------------------------------------------------------------------------------
[[Page 78253]]
The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions specified in this proposed AD.
The FAA estimates it would take up to 1.5 hours to replace a sensing
element.
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some or all of the costs of
this proposed 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
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
Bombardier, Inc.: Docket No. FAA-2023-2000; Project Identifier MCAI-
2023-00415-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by January 2, 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.
(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 4910-12-P
[[Page 78254]]
[GRAPHIC] [TIFF OMITTED] TP15NO23.038
(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, 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.
(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.
[[Page 78255]]
[GRAPHIC] [TIFF OMITTED] TP15NO23.039
[[Page 78256]]
[GRAPHIC] [TIFF OMITTED] TP15NO23.040
[[Page 78257]]
[GRAPHIC] [TIFF OMITTED] TP15NO23.041
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[GRAPHIC] [TIFF OMITTED] TP15NO23.042
[[Page 78259]]
[GRAPHIC] [TIFF OMITTED] TP15NO23.043
[[Page 78260]]
[GRAPHIC] [TIFF OMITTED] TP15NO23.044
[[Page 78261]]
[GRAPHIC] [TIFF OMITTED] TP15NO23.045
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[GRAPHIC] [TIFF OMITTED] TP15NO23.046
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[GRAPHIC] [TIFF OMITTED] TP15NO23.047
[[Page 78264]]
[GRAPHIC] [TIFF OMITTED] TP15NO23.048
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[[Page 78265]]
(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 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) 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: 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 October 26, 2023.
Caitlin Locke,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2023-24007 Filed 11-14-23; 8:45 am]
BILLING CODE 4910-13-P
