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PROPOSED AD BELL TEXTRON CANADA LIMITED (TYPE CERTIFICATE PREVIOUSLY HELD BY BELL HELICOPTER TEXTRON CANADA LIMITED): Docket No. FAA-2021-1178; Project Identifier MCAI-2021-00986-R.
(a) COMMENTS DUE DATE

    The FAA must receive comments  on  this  airworthiness directive  (AD)
    action by February 28, 2022.

(b) AFFECTED ADS

    This  AD  replaces AD  2020-20-06,  Amendment 39-21262  (85  FR 60356,
    September 25, 2020) (AD 2020-20-06).

(c) APPLICABILITY

    This  AD  applies to  Bell  Textron Canada  Limited  (type certificate
    previously held by Bell  Helicopter Textron Canada Limited)  Model 429
    helicopters, certificated in any  category, with a bellcrank  assembly
    part number (P/N) 429-001-523-101, 429-001-523- 103,  429-001-532-101,
    or 429-001-532-103 installed.

(d) SUBJECT

    Joint Aircraft  Service Component  (JASC) Code:  2700, Flight  Control
    System.

(e) UNSAFE CONDITION

    This AD  was prompted  by new  bellcrank assemblies,  which have  been
    upgraded with corrosion resistant  steel bearings. The FAA  is issuing
    this AD to  prevent corrosion of  the bearings due  to pooling at  the
    bellcrank assembly from  precipitation in the  forward portion of  the
    roof structure. The unsafe  condition, if not addressed,  could result
    in  restrictions  in  the collective,  directional,  or  pitch control
    systems, and subsequent loss of helicopter control.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) REQUIRED ACTIONS

(1) For Model 429 helicopters serial number  (S/N) 57001 through 57296 in-
    clusive, within 12 months after the helicopter was manufactured or  30
    days after the effective date of this AD, whichever occurs later,  and
    thereafter at intervals not to exceed 6 months:

(i) Disconnect the forward ends of the collective control tube, longitudi-
    nal stability  and control  augmentation system  (SCAS) actuator,  and
    lateral SCAS actuator. Stow the collective control tube and each  SCAS
    actuator to prevent binding.

(ii) Move the cyclic stick fore, aft,  and laterally,  and  the collective
     stick up  and down  from stop  to stop  to determine  if there is any
     roughness. If there  is any roughness  in the flight  control system,
     before further flight, remove each pivot bearing P/N MS27646-41, each
     arm assembly  bearing P/N  MS27643-4, and  each sleeve  P/N 120-13-4A
     from service and  install bellcrank assemblies  P/N 429-001-523-101FM
     and 429-001-532-101FM; or 429-001-523-107FM and 429-001-532-107FM; or
     429-001-523-107 and 429-001-532-107.

(iii) Inspect the collective arm assembly P/N 429-001-525-101, the lateral
      arm assembly P/N 429-001-527-101, and the longitudinal arm  assembly
      P/N  429-001-530-101,  by  rotating  each  bearing  and  determining
      whether each bearing rotates freely. If there is any binding in  any
      arm end bearing  or on the  longitudinal bellcrank assembly,  before
      further flight, remove each  pivot bearing P/N MS27646-41,  each arm
      assembly bearing P/N MS27643-4,  and each sleeve P/N  120-13-4A from
      service and install  bellcrank assemblies P/N  429-001-523-101FM and
      429-001-532-101FM;  or 429-001-523-107FM  and 429-001-532-107FM;  or
      429-001-523-107 and 429-001-532-107.

(2) For  Model 429 helicopters  S/N 57001 through 57296 inclusive,  unless
    already accomplished  by following  paragraphs (g)(1)(ii)  or (iii) of
    this AD, within 24 months after the effective date of this AD, install
    bellcrank assemblies P/N  429-001-523-101FM and 429-001-532-101FM;  or
    429-001-523-107FM and  429-001-532-107FM; or  429-001-523-107 and  429
    -001-532-107.

(3) As of the effective date of this AD,  installing  bellcrank assemblies
    P/N 429-001-523-101FM and 429-001-532-101FM; or 429-001-523-107FM  and
    429-001-532-107FM; or 429-001-523-107 and 429-001-532-107, constitutes
    a  terminating  action  for  the  recurring  inspections  required  by
    paragraph (g)(1) of this AD.

(4) As of the effective date of this AD,  do  not  install  any  bellcrank
    assembly P/N 429-001-523-101, 429-001-523-103, 429-001-532-101 or  429
    -001-532-103 on any helicopter.

(h) SPECIAL FLIGHT PERMITS

    Special flight permits are prohibited.

(i) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) 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 local Flight Standards District Office, as
    appropriate. If  sending information  directly to  the manager  of the
    International  Validation  Branch, send  it  to the  attention  of the
    person identified in paragraph (j)(1)  of this AD. Information may  be
    emailed to: 9-AVS-AIR730-AMOC@faa.gov.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector, or lacking  a principal inspector,  the manager of  the local
    flight standards district office/certificate holding district office.

(j) RELATED INFORMATION

(1) For more information about this AD,  contact Andrea Jimenez, Aerospace
    Engineer,  COS Program Management Section,  Operational Safety Branch,
    Compliance & Airworthiness Division, FAA, 1600 Stewart Ave, Suite 410,
    Westbury, NY 11590; telephone (516) 228-7330; email andrea.jimenez@faa
    .gov.

(2) For service information  identified in this AD,  contact  Bell Textron
    Canada  Limited,  12,800  Rue de l’Avenir,  Mirabel,  Quebec  J7J 1R4,
    Canada; telephone 1-450-437-2862 or 1-800-363-8023; fax 1-450-433-0272
    email productsupport@bellflight.com; or at https://www.bellflight.com/
    support/contactsupport.  You may view this referenced service informa-
    tion  at  the FAA,  Office of the Regional Counsel,  Southwest Region,
    10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.  For informa-
    tion on the availability of this material at the FAA,  call (817) 222-
    5110.

(3) The subject of this AD  is  addressed  in Transport Canada AD CF-2016-
    11R3, dated August 30, 2021.  You may view  the Transport Canada AD on
    the Internet  at https://www.regulations.gov  in  Docket No. FAA-2021-
    1178.

Issued on January 4, 2022. Ross Landes, Deputy Director for Regulatory Op-
erations, Compliance & Airworthiness Division, Aircraft Certification Ser-
vice.

DATES: The FAA must receive comments  on this proposed AD  by February 28,
2022.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-1178; Project Identifier MCAI-2021-00986-R]
RIN 2120-AA64

Airworthiness Directives; Bell Textron Canada Limited (Type
Certificate Previously Held by Bell Helicopter Textron Canada Limited)
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2020-20-06, which applies to certain Bell Helicopter Textron Canada
Limited (now Bell Textron Canada Limited) Model 429 helicopters. AD
2020-20-06 requires repetitive inspections of certain cyclic and
collective assembly bearings. Since the FAA issued AD 2020-20-06, the
collective and cyclic bellcrank assemblies have been upgraded with
corrosion resistant steel bearings. This proposed AD would retain some
of the requirements of AD 2020-20-06 and depending on the inspection
results, would require removing certain parts from service and
installing the upgraded cyclic and collective bellcrank assemblies.
This proposed AD would also require installing the upgraded collective
and cyclic bellcrank assemblies on certain helicopters if not already
installed, and would prohibit installing certain bellcrank assemblies.
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 February
28, 2022.

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 https://www.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.
For service information identified in this NPRM, contact Bell
Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J
1R4, Canada; telephone 1-450-437-2862 or 1-800-363-8023; fax 1-450-433-
0272; email productsupport@bellflight.com; or at https://www.bellflight.com/
support/contact-support. You may view this service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. For
information on the availability of this material at the FAA, call (817)
222-5110.

Examining the AD Docket

You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-1178; 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
Transport Canada AD, any comments received, and other information. The
street address for Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer,
COS Program Management Section, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228-7330; email andrea.jimenez@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-2021-1178; Project Identifier
MCAI-2021-00986-R'' 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
this 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
https://www.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 Andrea Jimenez, Aerospace Engineer, COS Program Management
Section, Operational Safety Branch, Compliance & Airworthiness
Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590;
telephone (516) 228-7330; email andrea.jimenez@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

The FAA issued AD 2020-20-06, Amendment 39-21262 (85 FR 60356,
September 25, 2020) (AD 2020-20-06), for Bell Helicopter Textron Canada
Limited Model 429 helicopters with a bellcrank assembly part number (P/
N) 429-001-523-101, 429-001-523-103, 429-001-532-101, or 429-001-532-
103 installed. AD 2020-20-06 requires within 12 months after the
helicopter was manufactured or 30 days after the effective date of AD
2020-20-06, whichever occurs later, and thereafter at intervals not to
exceed 6 months, disconnecting the forward ends of the collective
control tube, longitudinal stability and control augmentation system
(SCAS) actuator, and lateral SCAS actuator and stowing the collective
control tube and each SCAS actuator to prevent binding. AD 2020-20-06
requires slowly moving the cyclic fore/aft and laterally, and the
collective up/down from stop to stop to determine if there is any
roughness. If there is any roughness in the flight control system, AD
2020-20-06 requires, before further flight, replacing the six pivot
bearings in the collective lateral bellcrank assembly and the
longitudinal bellcrank assembly. Finally, AD 2020-20-06 requires
inspecting each arm end bearing at the end of the collective, lateral,
and longitudinal arm assemblies by rotating each bearing and ensuring
each bearing rotates freely. If there is any binding in any arm end
bearing or on the longitudinal bellcrank assembly, AD 2020-20-06
requires replacing each arm end bearing before further flight.
AD 2020-20-06 was prompted by Transport Canada AD CF-2016-11R2,
dated October 18, 2017 (Transport Canada AD CF-2016-11R2), issued by
Transport Canada, which is the aviation authority for Canada, to
correct an unsafe condition for Bell Helicopter Textron Canada Model
429 helicopters equipped with a bellcrank assembly P/N 429-001-523-101,
429-001-523-103, 429-001-532-101, or 429-001-532-103. Transport Canada
advised that in-service reports show that bearings in the roof-mounted
flight control bellcranks are adversely affected by precipitation.
Pooling can occur at the forward portion of the roof, providing a
source of contamination for bearings in the roof-mounted flight
controls. Precipitation may reduce the effectiveness of the grease in
the bearings, allowing corrosion to occur. This can result in
intermittent restrictions, such as binding and roughness in the flight
controls. Transport Canada also advised that an undetected corroded
bearing could lead to restrictions in the collective, directional, or
pitch control systems, resulting in difficulty controlling the
helicopter.
Transport Canada AD CF-2016-11R2 required within 12 months after
the helicopter was manufactured and thereafter at intervals not to
exceed 6 months, inspecting the flight controls and replacing any
discrepant bearings. If the helicopter's age exceeded 12 months,
Transport Canada AD CF-2016-11R2 required the 12-month inspection
within 30 days. Transport Canada AD CF-2016-11R2 also required, within
30 days, performing a functional check and replacement, if applicable,
of the bearings if the most recent functional check of the helicopter
was performed with the alternate procedure of using a hydraulic test
stand or if the inspection method was unknown.

Actions Since AD 2020-20-06 Was Issued

Since the FAA issued AD 2020-20-06, Transport Canada issued AD CF-
2016-11R3, dated August 30, 2021 (Transport Canada AD CF-2016-11R3),
which supersedes Transport Canada AD CF-2016-11R2. Transport Canada
advises of new collective and cyclic bellcrank assemblies which have
been upgraded with corrosion resistant steel bearings.
Accordingly, Transport Canada AD CF-2016-11R3 requires, for certain
serial-numbered helicopters, within 12 months from the helicopter
manufacture date, or for helicopters that have exceeded the age
threshold of 12 months from the helicopter manufacturer date, within 30
days, and thereafter at intervals not to exceed 6 months, performing a
functional check of the flight controls to detect roughness in the
pivot bearings and binding of the collective, lateral, or longitudinal
arm end bearings of the bellcrank assemblies. If any roughness or
binding is detected, Transport Canada AD CF-2016-11R3 requires
replacement of each affected bellcrank assembly before further flight.
Transport Canada AD CF-2016-11R3 also requires, within 24 months,
installing the upgraded collective and cyclic bellcrank assemblies and
considers this action a terminating action to the recurring
inspections. Finally, Transport Canada AD CF-2016-11R3 prohibits an
affected bellcrank assembly from being installed on any helicopter.

FAA's Determination

These helicopters have been approved by the aviation authority of
Canada and are approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with Canada, Transport Canada, its
technical representative, has notified the FAA of the unsafe condition
described in its AD. The FAA is proposing this AD after evaluating all
known relevant information and determining that the unsafe condition
described previously is likely to exist or develop on other helicopters
of the same type design.

Related Service Information

The FAA reviewed Bell Technical Bulletin 429-18-58, Revision B,
dated August 23, 2021 (TB 429-18-58 Rev B), which specifies procedures
to upgrade certain part-numbered bellcrank assemblies to the bellcrank
assemblies that utilize the corrosion resistant steel bearings.
The FAA also reviewed Bell Helicopter Alert Service Bulletin 429-
15-21, Revision C, dated August 23, 2021 (ASB 429-15-21 Rev C), which
specifies moving the cyclic stick fore, aft, and laterally, and the
collective stick up and down from stop to stop to detect deteriorated
pivot bearings. ASB 429-15-21 Rev C also specifies inspecting to
determine whether the bearings in the collective, lateral, and
longitudinal arm assemblies rotate freely. If discrepant arm bearings
are found, ASB 429-15-21 Rev C specifies contacting Bell Product
Support Engineering to report the findings and replacing the discrepant
parts with serviceable parts.

Proposed AD Requirements in This NPRM

This proposed AD would retain some of the requirements of AD 2020-
20-06. This proposed AD would require, for certain serial-numbered
helicopters, within 12 months after the helicopter was manufactured or
30 days after the effective date of this AD, whichever occurs later,
and thereafter at intervals not to exceed 6 months, disconnecting
certain parts, stowing certain parts to prevent binding, and moving the
cyclic stick and the collective stick to inspect for roughness in the
flight control system and binding in the collective, lateral, and
longitudinal arm assemblies. If any of these conditions exist, this
proposed AD would require, before further flight, removing certain
parts from service and installing upgraded bellcrank assemblies.
This proposed AD would also require, for certain serial-numbered
helicopters that do not have the upgraded bellcrank assemblies
installed, within 24 months after the effective date of this AD,
installing the upgraded bellcrank assemblies, which would provide a
terminating action for the recurring inspections. Finally, this
proposed AD would prohibit installing any affected bellcrank assembly
on any helicopter.

Differences Between This Proposed AD and Transport Canada AD
CF-2016-11R3


Transport Canada AD CF-2016-11R3 provides requirements if the most
recent functional check was performed using a hydraulic test stand as
an alternate procedure. This proposed AD provides no such alternate
procedure. Transport Canada AD CF-2016-11R3 provides requirements for
helicopters that have exceeded the age threshold of 12 months from the
helicopter manufacturer date to complete the initial functional check
within 30 days from the effective date of its AD. This proposed AD
would require the initial inspection within 12 months after the
helicopter was manufactured or 30 days after the effective date of this
proposed AD, whichever occurs later. Transport Canada AD CF-2016-11R3
allows credit for the corrective actions of Part I if the initial
functional check was accomplished prior to the effective date of
Transport Canada AD CF-2016-11R3, whereas this proposed AD does not.

Costs of Compliance

The FAA estimates that this AD, if adopted as proposed, would
affect 64 helicopters of U.S. Registry. Labor rates are estimated at
$85 per work-hour. Based on these numbers, the FAA estimates the
following costs to comply with this proposed AD.
Inspecting the cyclic and the collective bellcrank assemblies for
roughness in the pivot bearings and binding in the collective, lateral,
and longitudinal arm end bearings would take about 3 work-hours for an
estimated cost of $255 per inspection cycle.
Installing the upgraded collective and cyclic bellcrank assemblies
would take about 18 work-hours and parts would cost about $1,750 for an
estimated cost of $3,280 per upgrade installation.
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some 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, 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.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by:

a. Removing Airworthiness Directive 2020-20-06, Amendment 39-21262 (85
FR 60356, September 25, 2020); and

b. Adding the following new airworthiness directive: