Airworthiness Directives; Bombardier, Inc., Airplanes, 7856-7859 [2023-02525]

Download as PDF 7856 Federal Register / Vol. 88, No. 25 / Tuesday, February 7, 2023 / Rules and Regulations availability of this material at the FAA, call 206–231–3195. (8) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on January 20, 2023. Gaetano A. Sciortino, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023–02526 Filed 2–6–23; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–1251; Project Identifier MCAI–2022–00588–T; Amendment 39–22308; AD 2023–02–01] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD–100–1A10 airplanes. This AD was prompted by an investigation that indicated that one of the springs in the pitch trim switch of the horizontal stabilizer had failed. The failure of the spring could result in the airplane pitching nose down when actually commanded nose up. This AD requires a verification of the serial numbers of certain pitch trim switches, and replacement of the affected pitch trim switches with new ones in the pilot and co-pilot control wheels. This AD would also prohibit the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 14, 2023. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 14, 2023. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2022–1251; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the mandatory ddrumheller on DSK120RN23PROD with RULES SUMMARY: VerDate Sep<11>2014 17:54 Feb 06, 2023 Jkt 259001 continuing airworthiness information (MCAI), any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Material Incorporated by Reference: • For service information identified in this final rule, contact Bombardier Business Aircraft Customer Response Center, 400 Coˆte Vertu Road West, Dorval, Que´bec H4S 1Y9, Canada; telephone 1–514–855–2999; email ac.yul@aero.bombardier.com; internet bombardier.com. • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available at regulations.gov under Docket No. FAA– 2022–1251. FOR FURTHER INFORMATION CONTACT: Thomas Niczky, Aerospace Engineer, Avionics and Electrical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7347; email 9-avs-nyaco-cos@ faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Bombardier, Inc., Model BD–100–1A10 airplanes. The NPRM published in the Federal Register on October 5, 2022 (87 FR 60352). The NPRM was prompted by AD CF–2022– 24, dated May 2, 2022, (referred to after this as the MCAI) issued by Transport Canada, which is the aviation authority for Canada. The MCAI states that during several in-service events, following a stab trim fault advisory message and an auto-pilot disconnect, both pilot and copilot commands to trim the horizontal stabilizer nose-up resulted in a nosedown movement of the horizontal stabilizer. In two events, the horizontal stabilizer reached the full travel nosedown position before the crew recognized the nature of the problem, and quickly recovered control of the airplane for safe landing. As a result, this led to increased crew workload and reduced safety margins. Subsequent investigation by Bombardier and the supplier of the horizontal stabilizer pitch trim switch determined that one of the springs within the pitch trim switch had failed. PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 The supplier of the springs was changed in 2019. The majority of observed pitch trim switch failures occurred in pitch trim switches that were manufactured after 2019. In the NPRM, the FAA proposed to require the replacement of the affected pitch trim switches with re-designed pitch trim switches that have reliable springs. The FAA is issuing this AD to address the failure of the springs in the pitch trim switch, which, if not corrected, could result in the airplane pitching nose down when actually commanded nose up, resulting in reduced controllability of the airplane and high control forces. The FAA is issuing this AD to address the failure of the springs in the pitch trim switch. The unsafe condition, if not corrected, could result in the airplane pitching nose down when actually commanded nose up, resulting in reduced controllability of the airplane and high control forces. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2022–1251. Discussion of Final Airworthiness Directive Comments The FAA received a comment from NetJets. The following presents the comment received on the NPRM and the FAA’s response. Request To Correct the Date for Bombardier Service Bulletin 350–27– 011 NetJets requested that the proposed AD be revised to correct the date for Bombardier Service Bulletin 350–27– 011. The date was entered incorrectly in figure 1 to paragraph (h) of the proposed AD and two times in paragraph (i) of the proposed AD as ‘‘March 21, 2002.’’ The FAA agrees with the requested change by the commenter. The FAA has corrected the date for Bombardier Service Bulletin 350–27–011 in figure 1 to paragraph (h) of this AD and two times in paragraph (i) of this AD to ‘‘March 21, 2022.’’ Conclusion This product has been approved by the aviation authority of another country and is approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA reviewed the relevant data, considered the comment received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on this product. Except for E:\FR\FM\07FER1.SGM 07FER1 7857 Federal Register / Vol. 88, No. 25 / Tuesday, February 7, 2023 / Rules and Regulations minor editorial changes, and any other changes described previously, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Related Service Information Under 1 CFR Part 51 The FAA reviewed Bombardier Service Bulletin 100–27–21, dated March 21, 2022, for Model BD–100– 1A10 (CH–300) airplanes, S/Ns 20003 to 20500. This service information specifies procedures for verifying serial numbers (S/Ns) of certain pitch trim switch part numbers in the pilot and copilot control wheels, and replacing affected pitch trim switches. The FAA has also requires Bombardier Service Bulletin 350–27– 011, dated March 21, 2022, for Model BD–100–1A10 (CH–350) airplanes, S/Ns 20501 to 20936. This service information describes procedures for verifying S/Ns of certain pitch trim switch part numbers in leather and nonleather covered pilot and co-pilot control wheels, and replacing affected pitch trim switches. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance The FAA estimates that this AD affects 697 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Switch inspection .......................................................... 1 work-hour × $85 per hour = $85 ............................... The FAA estimates the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. The FAA has no way of determining the Cost per product Parts N/A $59,245 number of aircraft that might need these on-condition actions: ESTIMATED COSTS OF ON-CONDITION ACTIONS Action Labor cost Switch replacement (Airplane S/Ns 20003–20500) ..... Switch replacement (Airplane S/Ns 20501–20936) ..... 4 work-hours × $85 per hour = $340 ........................... 4 work-hours × $85 per hour = $340 ........................... The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some or all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. ddrumheller on DSK120RN23PROD with RULES 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. VerDate Sep<11>2014 17:54 Feb 06, 2023 Jkt 259001 Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Parts Cost per product $2,352 2,442 $2,692 2,782 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: ■ 2023–02–01 Bombardier, Inc.: Amendment 39–22308; Docket No. FAA–2022–1251; Project Identifier MCAI–2022–00588–T. (a) Effective Date This airworthiness directive (AD) is effective March 14, 2023. (b) Affected ADs None. (c) Applicability This AD applies to all Bombardier, Inc., Model BD–100–1A10 airplanes, all serial numbers, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition This AD was prompted by the investigation that one of the springs in the pitch trim switch for the horizontal stabilizer had failed. The FAA is issuing this AD to address the E:\FR\FM\07FER1.SGM 07FER1 Federal Register / Vol. 88, No. 25 / Tuesday, February 7, 2023 / Rules and Regulations failure of the springs in the pitch trim switch. The unsafe condition, if not corrected, could result in the airplane pitching nose down when actually commanded nose up, and the flightcrew may not be able to regain control of the horizontal stabilizer, resulting in reduced controllability of the airplane and high control forces. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Review of the Airplane Records ddrumheller on DSK120RN23PROD with RULES Within 200 flight hours or 6 months, whichever occurs first, from the effective date of this AD, review the airplane (technical) records for the horizontal stabilizer pitch trim switches and control wheels to determine the date of replacement, if any, of the pilot or co-pilot trim switch and control wheels. (1) If the pilot or co-pilot pitch trim switch or control wheels were removed after January VerDate Sep<11>2014 17:54 Feb 06, 2023 Jkt 259001 1, 2019, and the replacement pitch trim switches have serial numbers 02000 and subsequent, then no further action is required other than compliance with paragraph (j) of this AD. (2) For airplanes with serial numbers (S/ Ns) 20003 through 20780 inclusive: If no pilot or co-pilot pitch trim switch or control wheel was replaced after January 1, 2019, then no further action is required other than compliance with paragraph (j) of this AD. (3) For airplanes with S/Ns 20901 through 20936 inclusive: If no pilot or co-pilot pitch trim switch or control wheel has been replaced on an airplane, then no further action is required other than compliance with paragraph (j) of this AD. (h) Verification and Replacement of Pitch Trim Switches For airplanes not identified in paragraphs (g)(1) through (3) of this AD: Within 200 flight hours or 6 months, whichever occurs first, from the effective date of this AD, identify the serial numbers of both the pilot PO 00000 Frm 00020 Fmt 4700 Sfmt 4725 and co-pilot pitch trim switches, and do the applicable actions specified in paragraph (h)(1) or (2) of this AD. (1) If the pilot or co-pilot pitch trim switch has a serial number that is not listed in figure 2 to paragraph (h) of this AD, before further flight re-install the pitch trim switch in accordance with Section 2.B. of the Accomplishment Instructions of the applicable service information identified in figure 1 to paragraph (h) of this AD. (2) If the pilot or co-pilot pitch trim switch has a serial number listed in figure 2 to paragraph (h) of this AD, before further flight, replace the pitch trim switch in accordance with Section 2.B. of the Accomplishment Instructions of the applicable service information identified in figure 1 to paragraph (h) of this AD. (3) Before further flight perform the operational test in accordance with Section 2.C. of the Accomplishment Instructions of the applicable service information identified Bombardier SB listed in figure 1 to paragraph (h) of this AD. E:\FR\FM\07FER1.SGM 07FER1 ER07FE23.042</GPH> ER07FE23.043</GPH> 7858 Federal Register / Vol. 88, No. 25 / Tuesday, February 7, 2023 / Rules and Regulations (i) Verification/Replacement of Pitch Trim Switches for Airplanes With S/Ns 20501 and Subsequent With Certain Control Wheel P/Ns 83912156 and 83912157 For airplanes with S/Ns 20501 and subsequent with leather-covered control wheels, pilot control wheel P/N 83912156, or co-pilot control wheel P/N 83912157: Within 200 flight hours or 6 months, whichever occurs first, from the effective date of this AD, remove and inspect both the pilot and co-pilot pitch trim switches to determine the part number of the pitch trim switch in accordance with Section 2.B. of the Accomplishment Instructions of Bombardier Service Bulletin 350–27–011, dated March 21, 2022. (1) If pitch trim switch P/N 83452541 or P/ N 83452548 is found installed in either the pilot or the co-pilot control wheel, before further flight, replace the pitch trim switch with pitch trim switch P/N 83452548, serial number 02000 and subsequent, in accordance with Section 2.B. of the Accomplishment Instructions of the applicable service information identified in figure 1 to paragraph (h) of this AD. (2) Before further flight thereafter perform the operational test in accordance with Section 2.C. of the Accomplishment Instructions of Bombardier Service Bulletin 350–27–011, dated March 21, 2022. ddrumheller on DSK120RN23PROD with RULES (j) Parts Installation Prohibition As of the effective date of this AD, no person may install, on any airplane, a trim switch P/N 83452548 or P/N 83452541 with any serial number listed in figure 2 to paragraph (h) of this AD. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO 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 certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300. 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, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (l) Additional Information (1) Refer to Transport Canada AD CF– 2022–24, dated May 2, 2022, for related VerDate Sep<11>2014 17:54 Feb 06, 2023 Jkt 259001 information. This Transport Canada AD may be found in the AD docket at regulations.gov under Docket No. FAA–2022–1251. (2) For more information about this AD, contact Thomas Niczky, Aerospace Engineer, Avionics and Electrical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7347; email 9-avs-nyacocos@faa.gov. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Bombardier Service Bulletin 350–27– 011, Basic Issue, dated March 21, 2022. (ii) Bombardier Service Bulletin 100–27– 21, Basic Issue, dated March 21, 2022. (3) For 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 1–514–855–2999; email ac.yul@aero.bombardier.com; internet bombardier.com. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on January 18, 2023. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023–02525 Filed 2–6–23; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0766; Project Identifier 2019–NE–23–AD; Amendment 39– 22312; AD 2023–02–05] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 8C1, CF34–8C5, CF34–8C5A1, CF34– 8C5B1, CF34–8C5A2, CF34–8C5A3, CF34–8E2, CF34–8E2A1, CF34–8E5, CF34–8E5A1, CF34–8E5A2, CF34–8E6, and CF34–8E6A1 model turbofan engines. This AD was prompted by a predicted reduction in the cyclic life of the combustion chamber assembly aft flange. This AD requires revisions to the airworthiness limitations section (ALS) of the existing engine manual (EM) and the operator’s existing approved maintenance or inspection program, as applicable, to incorporate initial and repetitive fluorescent penetrant inspections (FPIs) of the combustion chamber assembly. The FAA is issuing this AD to address the unsafe condition on these products. This AD is effective March 14, 2023. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 14, 2023. DATES: ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov by searching for and locating Docket No. FAA–2019– 0766; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Material Incorporated by Reference: • For GE service information identified in this final rule, contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; phone: (513) 552–3272; email: aviation.fleetsupport@ge.com; website: ge.com. • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (817) 222–5110. It is also available at regulations.gov by searching for and locating Docket No. FAA–2019– 0766. FOR FURTHER INFORMATION CONTACT: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF34– SUMMARY: 7859 Scott Stevenson, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7132; email: Scott.M.Stevenson@faa.gov. E:\FR\FM\07FER1.SGM 07FER1

Agencies

[Federal Register Volume 88, Number 25 (Tuesday, February 7, 2023)]
[Rules and Regulations]
[Pages 7856-7859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-02525]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1251; Project Identifier MCAI-2022-00588-T; 
Amendment 39-22308; AD 2023-02-01]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by 
an investigation that indicated that one of the springs in the pitch 
trim switch of the horizontal stabilizer had failed. The failure of the 
spring could result in the airplane pitching nose down when actually 
commanded nose up. This AD requires a verification of the serial 
numbers of certain pitch trim switches, and replacement of the affected 
pitch trim switches with new ones in the pilot and co-pilot control 
wheels. This AD would also prohibit the installation of affected parts. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective March 14, 2023.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 14, 
2023.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2022-1251; or in person at Docket Operations between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this final rule, the mandatory continuing airworthiness 
information (MCAI), any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.
    Material Incorporated by Reference:
     For service information identified in this final rule, 
contact Bombardier Business Aircraft Customer Response Center, 400 
C[ocirc]te Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; 
telephone 1-514-855-2999; email bombardier.com">[email protected]bombardier.com; internet 
bombardier.com.
     You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 2200 South 
216th St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195. It is also available at 
regulations.gov under Docket No. FAA-2022-1251.

FOR FURTHER INFORMATION CONTACT: Thomas Niczky, Aerospace Engineer, 
Avionics and Electrical Systems Section, FAA, New York ACO Branch, 1600 
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7347; 
email [email protected].

SUPPLEMENTARY INFORMATION: 

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to all Bombardier, Inc., 
Model BD-100-1A10 airplanes. The NPRM published in the Federal Register 
on October 5, 2022 (87 FR 60352). The NPRM was prompted by AD CF-2022-
24, dated May 2, 2022, (referred to after this as the MCAI) issued by 
Transport Canada, which is the aviation authority for Canada. The MCAI 
states that during several in-service events, following a stab trim 
fault advisory message and an auto-pilot disconnect, both pilot and co-
pilot commands to trim the horizontal stabilizer nose-up resulted in a 
nose-down movement of the horizontal stabilizer. In two events, the 
horizontal stabilizer reached the full travel nose-down position before 
the crew recognized the nature of the problem, and quickly recovered 
control of the airplane for safe landing. As a result, this led to 
increased crew workload and reduced safety margins.
    Subsequent investigation by Bombardier and the supplier of the 
horizontal stabilizer pitch trim switch determined that one of the 
springs within the pitch trim switch had failed. The supplier of the 
springs was changed in 2019. The majority of observed pitch trim switch 
failures occurred in pitch trim switches that were manufactured after 
2019.
    In the NPRM, the FAA proposed to require the replacement of the 
affected pitch trim switches with re-designed pitch trim switches that 
have reliable springs. The FAA is issuing this AD to address the 
failure of the springs in the pitch trim switch, which, if not 
corrected, could result in the airplane pitching nose down when 
actually commanded nose up, resulting in reduced controllability of the 
airplane and high control forces. The FAA is issuing this AD to address 
the failure of the springs in the pitch trim switch. The unsafe 
condition, if not corrected, could result in the airplane pitching nose 
down when actually commanded nose up, resulting in reduced 
controllability of the airplane and high control forces.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2022-1251.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from NetJets. The following presents the 
comment received on the NPRM and the FAA's response.

Request To Correct the Date for Bombardier Service Bulletin 350-27-011

    NetJets requested that the proposed AD be revised to correct the 
date for Bombardier Service Bulletin 350-27-011. The date was entered 
incorrectly in figure 1 to paragraph (h) of the proposed AD and two 
times in paragraph (i) of the proposed AD as ``March 21, 2002.''
    The FAA agrees with the requested change by the commenter. The FAA 
has corrected the date for Bombardier Service Bulletin 350-27-011 in 
figure 1 to paragraph (h) of this AD and two times in paragraph (i) of 
this AD to ``March 21, 2022.''

Conclusion

    This product has been approved by the aviation authority of another 
country and is approved for operation in the United States. Pursuant to 
the FAA's bilateral agreement with this State of Design Authority, it 
has notified the FAA of the unsafe condition described in the MCAI 
referenced above. The FAA reviewed the relevant data, considered the 
comment received, and determined that air safety requires adopting this 
AD as proposed. Accordingly, the FAA is issuing this AD to address the 
unsafe condition on this product. Except for

[[Page 7857]]

minor editorial changes, and any other changes described previously, 
this AD is adopted as proposed in the NPRM. None of the changes will 
increase the economic burden on any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Bombardier Service Bulletin 100-27-21, dated March 
21, 2022, for Model BD-100-1A10 (CH-300) airplanes, S/Ns 20003 to 
20500. This service information specifies procedures for verifying 
serial numbers (S/Ns) of certain pitch trim switch part numbers in the 
pilot and co-pilot control wheels, and replacing affected pitch trim 
switches.
    The FAA has also requires Bombardier Service Bulletin 350-27-011, 
dated March 21, 2022, for Model BD-100-1A10 (CH-350) airplanes, S/Ns 
20501 to 20936. This service information describes procedures for 
verifying S/Ns of certain pitch trim switch part numbers in leather and 
non-leather covered pilot and co-pilot control wheels, and replacing 
affected pitch trim switches.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD affects 697 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost                  Parts          product
----------------------------------------------------------------------------------------------------------------
Switch inspection.............................  1 work-hour x $85 per hour = $85             N/A         $59,245
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any 
required actions. The FAA has no way of determining the number of 
aircraft that might need these on-condition actions:

                                     Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost                  Parts          product
----------------------------------------------------------------------------------------------------------------
Switch replacement (Airplane S/Ns 20003-20500)  4 work-hours x $85 per hour =             $2,352          $2,692
                                                 $340.
Switch replacement (Airplane S/Ns 20501-20936)  4 work-hours x $85 per hour =              2,442           2,782
                                                 $340.
----------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some or all of the costs of 
this AD may be covered under warranty, thereby reducing the cost impact 
on affected operators.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2023-02-01 Bombardier, Inc.: Amendment 39-22308; Docket No. FAA-
2022-1251; Project Identifier MCAI-2022-00588-T.

(a) Effective Date

    This airworthiness directive (AD) is effective March 14, 2023.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Bombardier, Inc., Model BD-100-1A10 
airplanes, all serial numbers, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Unsafe Condition

    This AD was prompted by the investigation that one of the 
springs in the pitch trim switch for the horizontal stabilizer had 
failed. The FAA is issuing this AD to address the

[[Page 7858]]

failure of the springs in the pitch trim switch. The unsafe 
condition, if not corrected, could result in the airplane pitching 
nose down when actually commanded nose up, and the flightcrew may 
not be able to regain control of the horizontal stabilizer, 
resulting in reduced controllability of the airplane and high 
control forces.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Review of the Airplane Records

    Within 200 flight hours or 6 months, whichever occurs first, 
from the effective date of this AD, review the airplane (technical) 
records for the horizontal stabilizer pitch trim switches and 
control wheels to determine the date of replacement, if any, of the 
pilot or co-pilot trim switch and control wheels.
    (1) If the pilot or co-pilot pitch trim switch or control wheels 
were removed after January 1, 2019, and the replacement pitch trim 
switches have serial numbers 02000 and subsequent, then no further 
action is required other than compliance with paragraph (j) of this 
AD.
    (2) For airplanes with serial numbers (S/Ns) 20003 through 20780 
inclusive: If no pilot or co-pilot pitch trim switch or control 
wheel was replaced after January 1, 2019, then no further action is 
required other than compliance with paragraph (j) of this AD.
    (3) For airplanes with S/Ns 20901 through 20936 inclusive: If no 
pilot or co-pilot pitch trim switch or control wheel has been 
replaced on an airplane, then no further action is required other 
than compliance with paragraph (j) of this AD.

(h) Verification and Replacement of Pitch Trim Switches

    For airplanes not identified in paragraphs (g)(1) through (3) of 
this AD: Within 200 flight hours or 6 months, whichever occurs 
first, from the effective date of this AD, identify the serial 
numbers of both the pilot and co-pilot pitch trim switches, and do 
the applicable actions specified in paragraph (h)(1) or (2) of this 
AD.
    (1) If the pilot or co-pilot pitch trim switch has a serial 
number that is not listed in figure 2 to paragraph (h) of this AD, 
before further flight re-install the pitch trim switch in accordance 
with Section 2.B. of the Accomplishment Instructions of the 
applicable service information identified in figure 1 to paragraph 
(h) of this AD.
    (2) If the pilot or co-pilot pitch trim switch has a serial 
number listed in figure 2 to paragraph (h) of this AD, before 
further flight, replace the pitch trim switch in accordance with 
Section 2.B. of the Accomplishment Instructions of the applicable 
service information identified in figure 1 to paragraph (h) of this 
AD.
    (3) Before further flight perform the operational test in 
accordance with Section 2.C. of the Accomplishment Instructions of 
the applicable service information identified Bombardier SB listed 
in figure 1 to paragraph (h) of this AD.
[GRAPHIC] [TIFF OMITTED] TR07FE23.042

[GRAPHIC] [TIFF OMITTED] TR07FE23.043


[[Page 7859]]



(i) Verification/Replacement of Pitch Trim Switches for Airplanes With 
S/Ns 20501 and Subsequent With Certain Control Wheel P/Ns 83912156 and 
83912157

    For airplanes with S/Ns 20501 and subsequent with leather-
covered control wheels, pilot control wheel P/N 83912156, or co-
pilot control wheel P/N 83912157: Within 200 flight hours or 6 
months, whichever occurs first, from the effective date of this AD, 
remove and inspect both the pilot and co-pilot pitch trim switches 
to determine the part number of the pitch trim switch in accordance 
with Section 2.B. of the Accomplishment Instructions of Bombardier 
Service Bulletin 350-27-011, dated March 21, 2022.
    (1) If pitch trim switch P/N 83452541 or P/N 83452548 is found 
installed in either the pilot or the co-pilot control wheel, before 
further flight, replace the pitch trim switch with pitch trim switch 
P/N 83452548, serial number 02000 and subsequent, in accordance with 
Section 2.B. of the Accomplishment Instructions of the applicable 
service information identified in figure 1 to paragraph (h) of this 
AD.
    (2) Before further flight thereafter perform the operational 
test in accordance with Section 2.C. of the Accomplishment 
Instructions of Bombardier Service Bulletin 350-27-011, dated March 
21, 2022.

(j) Parts Installation Prohibition

    As of the effective date of this AD, no person may install, on 
any airplane, a trim switch P/N 83452548 or P/N 83452541 with any 
serial number listed in figure 2 to paragraph (h) of this AD.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO 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 certification 
office, send it to ATTN: Program Manager, Continuing Operational 
Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 516-228-7300. 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, New York ACO 
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or 
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If 
approved by the DAO, the approval must include the DAO-authorized 
signature.

(l) Additional Information

    (1) Refer to Transport Canada AD CF-2022-24, dated May 2, 2022, 
for related information. This Transport Canada AD may be found in 
the AD docket at regulations.gov under Docket No. FAA-2022-1251.
    (2) For more information about this AD, contact Thomas Niczky, 
Aerospace Engineer, Avionics and Electrical Systems Section, FAA, 
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7347; email [email protected].

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Bombardier Service Bulletin 350-27-011, Basic Issue, dated 
March 21, 2022.
    (ii) Bombardier Service Bulletin 100-27-21, Basic Issue, dated 
March 21, 2022.
    (3) For service information identified in this AD, contact 
Bombardier Business Aircraft Customer Response Center, 400 
C[ocirc]te Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; 
telephone 1-514-855-2999; email bombardier.com">[email protected]bombardier.com; internet 
bombardier.com.
    (4) You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 2200 
South 216th St., Des Moines, WA. For information on the availability 
of this material at the FAA, call 206-231-3195.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on January 18, 2023.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2023-02525 Filed 2-6-23; 8:45 am]
BILLING CODE 4910-13-P

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