Proposed Rule2022-21573
Airworthiness Directives; Bombardier, Inc., Airplanes
Primary source
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Published
October 5, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-100-1A10 airplanes. This proposed 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 proposed AD would require 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 proposed AD would also prohibit the installation of affected parts. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 87 Issue 192 (Wednesday, October 5, 2022)</title>
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[Federal Register Volume 87, Number 192 (Wednesday, October 5, 2022)]
[Proposed Rules]
[Pages 60352-60356]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-21573]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-1251; Project Identifier MCAI-2022-00588-T]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Bombardier, Inc., Model BD-100-1A10 airplanes. This proposed 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 proposed AD would require 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 proposed AD would also prohibit
the installation of affected parts. 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 November
21, 2022.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> 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.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Bombardier
Business Aircraft Customer Response
[[Page 60353]]
Center, 400 C[ocirc]te Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9,
Canada; telephone 1-514-855-2999; email <a href="/cdn-cgi/l/email-protection#1e7f7d30676b725e7f7b6c7130227f3e766c7b7823" http: bombardier.com">bombardier.com</a>">ac.yul@aero.<a href="http://bombardier.com">bombardier.com</a></a>;
internet <a href="http://bombardier.com">bombardier.com</a>. 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.
Examining the AD Docket
You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> by searching for
and locating 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 NPRM, the mandatory
continuing airworthiness information (MCAI), any comments received, and
other information. The street address for Docket Operations is listed
above.
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 <a href="/cdn-cgi/l/email-protection#d4edf9b5a2a7f9baadb5b7bbf9b7bba794b2b5b5fab3bba2"><span class="__cf_email__" data-cfemail="97aebaf6e1e4baf9eef6f4f8baf4f8e4d7f1f6f6b9f0f8e1">[email protected]</span></a>.
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-2022-1251; Project Identifier
MCAI-2022-00588-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
<a href="http://regulations.gov">regulations.gov</a>, 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
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 <a href="/cdn-cgi/l/email-protection#7c45511d0a0f5112051d1f13511f130f3c1a1d1d521b130a"><span class="__cf_email__" data-cfemail="d6effbb7a0a5fbb8afb7b5b9fbb5b9a596b0b7b7f8b1b9a0">[email protected]</span></a>. 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 Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued TCCA AD CF-2022-24, dated May 2, 2022
(TCCA AD CF-2022-24) (also referred to after this as the MCAI), to
correct an unsafe condition on all Bombardier, Inc., Model BD-100-1A10
airplanes. 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.
TCCA AD CF-2022-24 requires 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.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2022-1251.
Related Service Information Under 1 CFR Part 51
The FAA has 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 describes 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 reviewed 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.
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 the State of Design Authority,
the FAA has been notified of the unsafe condition described in the MCAI
and service information referenced above. The FAA is proposing this AD
because the FAA evaluated all the relevant information and determined
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 accomplishing the actions specified
in the service information already described. This proposed AD would
also prohibit the installation of affected pitch trim switches.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 697 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
[[Page 60354]]
Estimated Costs for Required Actions
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Cost per
Action Labor cost Parts product
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Switch inspection............................. 1 work-hour x $85 per hour = $85 N/A $59,245
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Estimated Costs of On-Condition Actions
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Cost per
Action Labor cost Parts product
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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.
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The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some or all of the costs of
this proposed AD may be covered under warranty, thereby reducing the
cost impact on affected operators.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
Bombardier, Inc.: Docket No. FAA-2022-1251; Project Identifier MCAI-
2022-00588-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by November 21, 2022.
(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 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
[[Page 60355]]
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.
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TP05OC22.040
[GRAPHIC] [TIFF OMITTED] TP05OC22.041
BILLING CODE 4910-13-C
(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, 2002.
(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, 2002.
(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) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) TCCA AD CF-2022-24, dated May 2, 2022, for related
information. This MCAI may be found in the AD docket at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2022-1251.
[[Page 60356]]
(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 <a href="/cdn-cgi/l/email-protection#1b22367a6d683675627a7874367874685b7d7a7a357c746d"><span class="__cf_email__" data-cfemail="0b32266a7d782665726a6864266864784b6d6a6a256c647d">[email protected]</span></a>.
(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 <a href="/cdn-cgi/l/email-protection#78191b56010d1438191d0a1756441958100a1d1e45" http: bombardier.com">bombardier.com</a>">ac.yul@aero.<a href="http://bombardier.com">bombardier.com</a></a>; internet
<a href="http://bombardier.com">bombardier.com</a>. 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.
Issued on September 29, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-21573 Filed 10-4-22; 8:45 am]
BILLING CODE 4910-13-P
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