Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 78251 

and duplication, as applicable to 

different categories of requesters, to 

respond to requests under § 1703.105. 

Direct costs include, for example, the 

hourly salary and projected benefits 

costs of agency employees who search 

for, review, or duplicate records in 

response to a request. Overhead 

expenses such as cost of space, and 

heating or lighting the facility in which 

DNFSB records are stored are not 

included in direct costs. 

* * * * * 

(2) Fees. (i) If documents are 

requested for commercial use, DNFSB 

shall charge the hourly salary and 

projected benefits costs of agency 

employees who search for and review 

records in response to a request, and for 

the costs of duplication as set out in 

subsection (b)(6) of this section. 

(ii) If documents are not sought for 

commercial use and the request is made 

by an educational or noncommercial 

scientific institution, whose purpose is 

scholarly or scientific research, or a 

representative of the news media, 

DNFSB’s charges shall be limited to the 

direct costs of duplication as set out in 

subsection (b)(6) of this section. 

(iii) For a request not described in 

paragraphs (b)(2) (i) or (ii) of this 

section, DNFSB shall charge the hourly 

salary and projected benefits costs of the 

agency’s employee(s) who search for 

records in response to a request and the 

direct costs of duplication as set out in 

subsection (b)(6) of this section. There 

shall be no charge for document review 

time, and the first 100 pages of 

reproduction and the first two hours of 

search time will be provided without 

charge. 

* * * * * 

(6) Schedule of Fees. (1) To the extent 

authorized by these regulations, DNFSB 

is authorized to seek the following fees 

to recover costs incurred in responding 

to FOIA requests: 

(i) Document Search Charges 

(A) Manual: Salary rate(s) (basic 

hourly pay plus 16 percent) of 

employee(s) performing records search 

or review. 

(B) Electronic: Salary rate(s) (basic 

hourly pay plus 16 percent) of 

employee(s) performing search or 

review. 

(ii) Document Review Charges: Salary 

rate(s) (basic hourly pay plus 16 

percent) of employee(s) performing 

search or review. 

(2) DNFSB will charge requesters who 

seek records for commercial purposes 

for the cost of reviewing them to 

determine whether they are exempt 

from mandatory disclosure. The agency 

will assess these charges only when the 

records are first analyzed to determine 

the applicability of a specific exemption 

to a record or portion thereof. DNFSB 

will not charge for the review of an 

exemption previously applied at the 

administrative review level. If a record 

or portion thereof was withheld in full 

under an exemption that is 

subsequently found inapplicable, it may 

be reviewed again to determine the 

applicability of other exemptions not 

previously considered. DNFSB may 

charge for the cost of such review. 

(3) Copying Charges 

(i) Paper: $.05 per page, if done inhouse, or generally available 

commercial rate, approximately $0.10 

per page. 

(ii) Electronic Media: Direct cost, 

including operator time (employee’s 

basic hourly pay plus 16 percent). 

(iii) Audio and Video Cassette: Actual 

commercial rates. 

(iv) Duplication of CD or DVD: Direct 

cost, including operator time 

(employee’s basic hourly pay plus 16 

percent). 

(v) Large Documents, e.g., maps or 

diagrams: Actual commercial rates. 

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 

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 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 


ddrumheller on DSK120RN23PROD with PROPOSALS1
78252 Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 

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: 

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: 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. 

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 × $85 per hour = 

Up to $11,900.

$0 Up to $11,900 ....................................... Up to $1,904,000. 


ddrumheller on DSK120RN23PROD with PROPOSALS1
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 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 

■ 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 

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 


ddrumheller on DSK120RN23PROD with PROPOSALS1
78254 Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 

(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. 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.038</GPH>

'

Aeroplane Model Applicable 8A SB 

(Marketing Designation) 

B0-700-1A10 SB 700-36-026 Basic Issue, dated 23 December 

(Global Express & Global Exprea XRS) 2022, or later revisions approved by the Chief, 

Continuing Aiwonhineu, Transport Canada 

B0-700-tA11 SB 700-1A11-36-005 Basic Issue, dated 23 

(Global S000) Oecember 2022, or later reviaion& approved by 

the Chiltf, Continung Airworthiness, Transport 

Canada 

BO-700-1A11 SB 700..36-5002 Balk Jstue, dated 23 December 

(Global 5000 featuring Global Vision Flight Deck) 2022, or tater revisions approved by the Chief, 

Continuing AirM>nhiness, Traneport Canada 

BO-70Q..1A10 S8 700-36-6002 Basie Issue, dated 23 December 

(Global 6000} 2022, or later revilions approved by the Chief, 

Continuing Airworthiness, Traneport Canada 

80-700-1At1 SB 700-36-S501 Baslc lstUe, dated 23 December 

(Glo.,_I 5500) 2022, or later reviaione approved by the Chief, 

Contwluing Airworthiness, Transport Canada 

BO-700-1A10 SB 700-36-6501 Basic issue, de1ed 23 December 

(Global 6500) 2022, or later revisions approved by the Chief, 

Continuing Airwof'Ulinesa, Tranaport Canada 
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 78255 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.039</GPH>

Figure 2 to paragraph (i)-MMEL Item 36-12-01 

MNEL Jtem.36-12-01 

1. ~em& sequence 

NO Item 

2. Nllmbet· 

Installed 

a Number 4.. Remarks or Exceptions 

Required 

NO<te systeme/Hrie: 

art1e1e 

Ni>mtire 

d'M:icle 

insta11es 

Fl>t 

C>ispatch 

NOmbre 

d'articles: 

aexpedler 

36 c PNEUMATICS 

12-01 BleedLeak,Detection 18 

Loops 

9 (0) Either loopAor loop.B may be 

inoperative proVidedredundant loop.in 

the same zone is .. operative, C 

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 R aLEli: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: 

e, If required, set APU BLEEbtoAUto. 
78256 Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.040</GPH>

Figure 3 to paragraph (i)-MMEL Item 36-12-01-1 

MMEL Item 38-1~01-1 

1. System & Sequence 2. Number 3. Number 4. Remarks or Exceptions 

NO Item Installed Required 

For 

Nombre Dispatch 

NO de systeme/serie d'article Nombre article installes d'articles 

a expedier 

36 - PN5UMATICS 

12-0.1 Bleed Leak Detecti_on 18 9 (0) Either loop A or loop B may be 

L,oops inoperative provided redundant loop 

C in the same.zone is operative. 

1) Wing Anti-Ice Leak 1_2 6 (M) (O) One loop _in each section may 

C be inoperative provided: 

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. 

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 78257 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.041</GPH>

ii. 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. 

d. If required, remove external AC power from the aeroplane. 

e. If required, set APU BLEED to AUTO. 

3, 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. 

(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 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.042</GPH>

Figure 4 to paragraph (i) -MMEL Item 36-12-01-2 

MMEL Item 36•12-01-2 

1. System & Sequence 2. Number 3. Number 4. Remarks or Exceptions 

No Item Installed Required 

For 

Nombre Dispatch 

NO de systl}me/serle d'article Nombre article installes d'articles 

aexpedier 

36 • ENl;;k.!Mfil!QS 

12-01 Bleed Leak Detection 18 9 (0) Either loop A or loop B may be 

Loops ihoperative provided redundant loop 

C in the same zone is operative . 

"' .. , 

2) Trim Air Leak 2 1 (O) Except for ER. operations; one 

C loop may be inoperative. 

1. PLACARD 

(1) Put a TRIM AIR LEAK INOPERATIVE placard on the instrument panel. 

2. QEERfillONS <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 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. On the APU control panel1 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 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. 

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. 
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 78259 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.043</GPH>

Figure 5 to paragraph (i) - L BLEED FA ULT 

L BLEED FAULT 

CAS Indication 

L BLEED FAULT 

(Advisory) 

1. OPERATIONS (0) 

Before each flight: 

1. 2. 

C (0) 

Dispatch Consideration 

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. 

(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. 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. 
78260 Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.044</GPH>

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 

d If required, remove external AC power from the aeroplane. 

e. If required, set APU BLEED to AUTO. 

2. 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 

(5) Operations are not conducted in known or forecast icing conditions. 
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 78261 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.045</GPH>

Figure 6 to paragraph (i) - R BLEED FA ULT 

R BLEED FAULT 

CAS Indication 1. 2. Dispatch Consideration 

R BLEED FAULT C (0) Aircraft may be dispatched provided, prior to 

(Advisory) 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. 

d. If recuired, remqve external.AC power from the aeroplane. 

e. If required, set APU BLEED to AUTO, 

2. 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: 
78262 Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.046</GPH>

- 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 

(5) Opar11tions are not conducted in. known or forecast icing conditions. 
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 78263 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.047</GPH>

Figure 7 to paragraph (i)- WING A/ICE FAULT 

WIN(3.AJICEF,~ULT 

CAS: IN<ttcatlon. 

WING A/ICE FAULT 

(AdviSOI)') 

t QPi:RAtfONs /bi 

Bef9re eacl1 tligt,t 

1.. 2. Dlspatch.Co,nslderatlon 

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: 

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 6 minutes. 

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) 

(2J On the EICAS primary display, tnake sure thatthe following GAS messages are not stiown: 

-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 
78264 Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 

BILLING CODE 4910–13–C 


ddrumheller on DSK120RN23PROD with PROPOSALS1EP15NO23.048</GPH>

Figure 8 to paragraph (i) - TRIM AIR FA ULT 

TRIM AIR FAULT 

CAS lndicatfon 

TRIM AlR FAOL i" 

(M/iS()ry} 

1, 2. Di$patch(fonslderation 

C. (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. 

3: Ohtlifi.APVtOnti"QI pane~ tuth.the APlJ sWitchtOSTART. 

ti 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; lf required, remove externaLAC powedrom the,aeroplane, 

e,, 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'. Atthe same:Jlme, orfthaAIRCONDIT10NINS synqpticpage, id&htifytfie HASOVthat 

shows incorreet indication; • 

c, lh the flight eompartml:!nt, oh the EMscou, open the applicable circuit bi'eakeras 

fOIIOWS: 

SYSTEMNAME 

AIR COND/PRESS 

AIR COND/PRESS 

CIRCUIT BREAKER 

NAME 

LECSHASOV 

RECSHASOV 

BUS NAME 

DCESS 

DCESS 

d. 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} 
Federal Register / Vol. 88, No. 219 / Wednesday, November 15, 2023 / Proposed Rules 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: 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, 

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 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: 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 


ddrumheller on DSK120RN23PROD with PROPOSALS1