preamble attached >>>
ADs updated daily at www.Tdata.com
2021-24-09 BELL TEXTRON CANADA LIMITED:
Amendment 39-21830; Docket No. FAA-2021-1011; Project Identifier MCAI-2021-00867-R.

(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective December 7, 2021.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to Bell Textron Canada Limited Model 430  helicopters,
    having serial number 49001  through 49129, inclusive, certificated  in
    any category.

(d) SUBJECT

    Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor Head.

(e) UNSAFE CONDITION

    This AD was prompted by an  in-flight failure of the main rotor  (M/R)
    pitch link clevis (clevis) due  to fatigue damage and excessive  wear.
    The FAA is issuing this AD  to detect and address any wear  and damage
    of the M/R clevis neck or threaded area. The unsafe condition, if  not
    addressed, could result in crack initiation at the M/R clevis neck and
    failure of the  M/R pitch link,  resulting in loss  of control of  the
    helicopter.

(f) COMPLIANCE

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

(g) REQUIRED ACTIONS

(1) Within 25 hours time-in-service (TIS)  or  30 days,  whichever  occurs
    first, after the effective date of this AD:

(i) Remove and disassemble each M/R pitch link assembly  part number (P/N)
    430-010-411-105, or P/N 430-010-411-107, but do not remove the inserts
    from the tube. Visually inspect the M/R clevis P/N 430-010-432-101 and
    rod end  for wear,  corrosion, and  damage, which  for the purposes of
    this inspection may be indicated  by distortion, bending, a crack,  or
    damaged M/R clevis threads. If there is any wear, corrosion or damage,
    before further flight, remove the affected M/R clevis or the  affected
    rod end from service.

(ii) Visually inspect each universal bearing P/N 212-010-412-001 for bind-
     ing, stiffness, wear,  looseness, excess axial  and radial play,  and
     damage, which for the purposes of this inspection may be indicated by
     distortion, bending, or a crack.

(A) If there is any wear,  looseness,  excess axial  and  radial play,  or
    damage and the M/R pitch  link assembly is P/N 430-010-411-105  or P/N
    430-010-411-107 and  has accumulated  5,000 or  less total  hours TIS,
    before further  flight, remove  the universal  bearing P/N 212-010-412
    -001 from service and replace with an airworthy part.

(B) If there is any binding or stiffness  and  the M/R pitch link assembly
    is P/N 430-010-411-105 or P/N 430-010-411-107 and has accumulated more
    than  5,000  total  hours  TIS,  before  further  flight,  remove  the
    universal bearing P/N 212-010-412-001 and M/R clevis from service  and
    replace with airworthy parts.

(C) If there is any wear,  looseness,  excess axial  and  radial play,  or
    damage and the M/R pitch link assembly is P/N 430-010-411-105  or  P/N
    430-010-411-107  and  has accumulated more than 5,000 total hours TIS,
    before further flight,  remove the universal bearing  P/N 212-010-412-
    001 from service and replace with an airworthy part.

(iii) Purge grease the bearings of each universal bearing.

(iv) Perform a magnetic particle inspection  for  any  crack  on  each M/R
     clevis  by following the Accomplishment Instructions,  Part I,  para-
     graphs 8. through 8.d.,  of  Bell  Alert Service Bulletin  430-21-60,
     dated July 13, 2021  (ASB 430-21-60).  If there is any crack,  before
     further flight,  remove  each  affected  M/R clevis from service.  If
     there is no crack,  before further flight,  perform a selective brush
     cadmium plating to replace  any  missing  cadmium plating and apply a
     chromate conversion coating.

(2) Within 50 hours TIS  after completion of paragraph (g)(1)  of this AD,
    and thereafter at intervals not to exceed 50 hours TIS:

(i) Using a 10X magnifying glass,  visually inspect  the neck and threaded
    area of each M/R clevis for wear, corrosion, and damage, which for the
    purposes of this inspection may be indicated by distortion, bending, a
    crack, or damaged M/R clevis threads. Refer to Figure 3 of ASB  430-21
    -60 for  a depiction  of the  area to  inspect on  each M/R clevis. If
    there is any wear, corrosion, or damage, before further flight, remove
    the affected  M/R clevis  from service  and replace  with an airworthy
    part.

(ii) Perform the actions  required in paragraph (g)(1)(iv)  of this AD for
     each M/R clevis.

(3) Within 150 hours TIS  after the completion of paragraph (g)(1) of this
    AD, and thereafter at intervals not to exceed 150 hours TIS,  visually
    inspect and  purge grease  each universal  bearing, by  performing the
    actions as required in paragraphs (g)(1)(ii) and (iii) of this AD.

(h) SPECIAL FLIGHT PERMITS

    A special flight permit  may be permitted  provided  that there are no
    passengers onboard.

(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-AIR-730-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 Hal Jensen, Aerospace Eng-
    ineer, Operational Safety Branch, Compliance & Airworthiness Division,
    FAA,  950 L'Enfant Plaza N SW,  Washington, DC 20024;  telephone (202)
    267-9167; email hal.jensen@faa.gov.

(2) The subject of this AD is addressed in Transport Canada CF-2021-26 AD,
    dated July 26, 2021.  You may view the Transport Canada AD at https://
    www.regulations.gov in Docket No. FAA-2021-1011.

(k) 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 the AD specifies otherwise.

(i) Bell Alert Service Bulletin 430-21-60, dated July 13, 2021.

(ii) [Reserved]

(3) 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/contact-support.

(4) 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.

(5) You may view this service information  that is incorporated  by refer-
    ence 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:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on November 16, 2021.  Ross Landes,  Deputy Director for Regulatory
Operations,  Compliance & Airworthiness Division,  Aircraft  Certification
Service.

FOR FURTHER INFORMATION CONTACT:  Hal Jensen,  Aerospace Engineer,  Opera-
tional  Safety Branch,  Compliance  &  Airworthiness  Division,  FAA,  950
L'Enfant Plaza N SW, Washington, DC 20024; telephone (202) 267-9167; email
hal.jensen@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-1011; Project Identifier MCAI-2021-00867-R;
Amendment 39-21830; AD 2021-24-09]
RIN 2120-AA64

Airworthiness Directives; Bell Textron Canada Limited Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bell Textron Canada Limited Model 430 helicopters. This AD was
prompted by an in-flight failure of the main rotor (M/R) pitch link
clevis (clevis) due to fatigue damage and excessive wear. This AD
requires a visual inspection of the M/R clevis, rod end, and a certain
part-numbered universal bearing, performing a purge grease, and
performing a magnetic particle inspection of each M/R clevis. Depending
on the visual inspection and magnetic particle inspection results, this AD requires
removing certain parts from service, replacing certain parts, and
performing additional actions. This AD also requires recurring
inspections of each M/R clevis and each universal bearing. The FAA is
issuing this AD to address the unsafe condition on these products.

DATES: This AD becomes effective December 7, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of December 7,
2021.
The FAA must receive comments on this AD by January 6, 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 final rule, 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. It is also available at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-1011.

Examining the AD Docket

You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-1011; 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
Transport Canada AD, any comments received, and other information. The
street address for Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Hal Jensen, Aerospace Engineer,
Operational Safety Branch, Compliance & Airworthiness Division, FAA,
950 L'Enfant Plaza N SW, Washington, DC 20024; telephone (202) 267-
9167; email hal.jensen@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

Transport Canada, which is the aviation authority for Canada, has
issued Transport Canada AD CF-2021-26, dated July 26, 2021 (Transport
Canada AD CF-2021-26), to correct an unsafe condition for Bell Textron
Canada Limited Model 430 helicopters, serial numbers 49001 through
49129. Transport Canada advises of an in-flight failure of an M/R
clevis which resulted in loss of control of the helicopter and fatal
injuries to occupants. Transport Canada further advises that the M/R
clevis part number (P/N) 430-010-432-101 fractured at the exposed
thread area above the nut, which was consistent with fatigue damage.
Transport Canada also advises an inspection of the failed part
determined universal bearing P/N 212-010-412-001 of the M/R pitch link
assembly had excessive wear and increased resistance to rotation.
Transport Canada states a similar accident previously occurred on the
same model helicopter in which the M/R clevis was found to have
fractured at the neck area due to fatigue damage. Transport Canada
states the restriction in freedom of movement of the universal bearing
can cause increased loads on the M/R pitch link assembly and subsequent
fatigue failure of the M/R clevis prior to its life limit. Finally,
Transport Canada advises the accident investigation is still ongoing.
This condition, if not addressed, could result in crack initiation at
the M/R clevis neck or threaded area and failure of the M/R pitch link,
resulting in loss of control of the helicopter.
Accordingly, Transport Canada AD CF-2021-26 requires visually
inspecting the M/R clevis and rod end for wear and damage and
performing corrective actions. Transport Canada AD CF-2021-26 also
requires for certain part-numbered M/R rotor pitch link assemblies that
have accumulated 5000 hours air time or less and have a universal
bearing P/N 212-010-412-001 that is unserviceable, replacing the
universal bearing. Transport Canada AD CF-2021-26 requires for certain
part-numbered M/R pitch link assemblies that have accumulated more than
5,000 hours air time and have a universal bearing P/N 212-010-412-001
with signs of binding or stiffness, replacing both the universal
bearing and the M/R clevis or if the universal bearing is unserviceable
but there are no signs of binding or stiffness, replacing only the
universal bearing.
Transport Canada AD CF-2021-26 requires performing a purge grease
of each universal bearing and performing a magnetic particle inspection
of the M/R clevis to detect cracks, replacing any M/R clevis with
cracks, or if the M/R clevis does not have any cracks, replacing any
missing cadmium plating.
Additionally, Transport Canada AD CF-2021-26 requires after the
initial visual and magnetic particle inspections, performing recurring
visual inspections of the M/R clevis for corrosion and mechanical
damage and performing corrective actions as needed. Transport Canada AD
CF-2021-26 also requires performing recurring visual inspections of the
universal bearing for binding, stiffness, wear, damage looseness,
excess axial and radial play, and performing corrective actions as
needed. Transport Canada AD CF-2021-26 requires reporting any cracks or
M/R clevises that are beyond published limits to Bell Product Support
Engineering. Transport Canada considers its AD an interim action and
states that further AD action may follow.

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 issuing 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 these same type designs.

Related Service Information Under 1 CFR Part 51

The FAA reviewed Bell Alert Service Bulletin 430-21-60, dated July
13, 2021. This service information specifies procedures to visually
inspect the M/R clevis and rod ends for wear or damage, the M/R clevis
for corrosion or mechanical damage and the universal bearings for
binding, stiffness, wear, looseness, excess axial and radial play, and
damage. This service information also specifies procedures to perform a
magnetic particle inspection, and recurring inspections of each M/R
clevis and each universal bearing.
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.

AD Requirements

This AD requires within 25 hours time-in-service (TIS) or 30 days,
whichever occurs first after the effective date of this AD, removing
and dissembling a certain part-numbered M/R pitch link assembly and
visually inspecting a certain part-numbered M/R clevis and rod end for
wear, corrosion, and damage, which may be indicated by distortion,
bending, a crack, or damaged M/R clevis threads, and removing any
affected parts from service before further flight. This AD also
requires visually inspecting a certain part-numbered universal bearing
for binding, stiffness, wear, looseness, excess axial and radial play,
and damage, which may be indicated by distortion, bending, or a crack.
If certain discrepancies are found, and a certain part-numbered M/R
pitch link assembly that has accumulated 5,000 or less total hours TIS
is installed, this AD requires before further flight, removing a
certain part-numbered universal bearing from service. If certain
discrepancies are found, and a certain part-numbered M/R pitch link
assembly that has accumulated more than 5,000 total hours TIS is
installed, this AD requires before further flight and depending on the
discrepancies, removing a certain part-numbered universal bearing and
the M/R clevis from service or removing only the universal bearing from
service.
This AD also requires performing a purge grease of each universal
bearing and performing a magnetic particle inspection of each M/R
clevis for a crack in accordance with the applicable service
information. Following the magnetic particle inspection, if there is a
crack, this AD requires before further flight, removing each affected
M/R clevis from service. If there is no crack, this AD requires
performing a selective brush cadmium plating and applying a chromate
conversion coating.
This AD requires within 50 hours TIS after completion of the
initial inspections required by this AD, and thereafter at intervals
not to exceed 50 hours TIS, using a 10X magnifying glass, visually
inspecting the neck and threaded area of each M/R clevis for wear,
corrosion, and damage, which may be indicated by distortion, bending, a
crack, or damaged M/R clevis threads, and depending on the inspection
results before further flight, removing the affected part from service
and replacing with an airworthy part, and repeating the magnetic
particle inspection of each M/R clevis.
Finally, AD requires within 150 hours TIS after the completion of
the initial inspections required by this AD, and thereafter at
intervals not to exceed 150 hours TIS, repeating the visual inspection
of each universal bearing for binding, stiffness, wear, looseness,
excess axial and radial play, and damage, and performing a purge grease
of each universal bearing.

Differences Between This AD and Transport Canada AD CF-2021-26

Transport Canada AD CF-2021-26 specifies compliance times in terms
of air time, whereas this AD requires using hours TIS. Where the
service information required by Transport Canada AD CF-2021-26
specifies to report any signs of cracking to Bell Product Support
Engineering, this AD does not require reporting any information.
Transport Canada AD CF-2021-26 specifies replacing any affected part,
whereas this AD requires removing the affected part from service and
then replacing with an airworthy part.

Interim Action

The FAA considers this AD to be an interim action. Once final
action has been identified, the FAA might consider further rulemaking.

Justification for Immediate Adoption and Determination of the Effective
Date


Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and
comment procedures for rules when the agency, for ``good cause,'' finds
that those procedures are ``impracticable, unnecessary, or contrary to
the public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies foregoing notice and comment prior to adoption of this rule
because if not corrected, the unsafe condition could lead to crack
initiation at the M/R clevis neck or threaded area and consequent
failure of the M/R pitch link, resulting in loss of control of the
helicopter.
In addition, the compliance time for the required actions is within
25 hours TIS or 30 days, whichever occurs first after the effective
date of this AD, a shorter time period than the time necessary for the
public to comment and for publication of the final rule.
Therefore, notice and opportunity for prior public comment are
impracticable and contrary to public interest pursuant to 5 U.S.C.
553(b)(3)(B). In addition, the FAA finds that good cause exists
pursuant to 5 U.S.C. 553(d) for making this amendment effective in less
than 30 days, for the same reasons the FAA found good cause to forgo
notice and comment.

Comments Invited

The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments to an address listed under
ADDRESSES. Include ``Docket No. FAA-2021-1011; Project Identifier MCAI-
2020-00867-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the final rule, 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 final rule 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 final rule.

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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to Hal
Jensen, Aerospace Engineer, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 950 L'Enfant Plaza N SW, Washington, DC
20024; telephone (202) 267-9167; email hal.jensen@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.

Regulatory Flexibility Act

The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without prior notice and
comment, RFA analysis is not required.

Costs of Compliance

The FAA estimates that this AD affects 29 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 AD.
Removing and disassembling each M/R pitch link assembly and
inspecting each M/R clevis and rod end takes about 4 work-hours for an
estimated cost of $340 per inspection and $9,860 for the U.S. fleet.
Inspecting each universal bearing takes about 4 work-hours for an
estimated cost of $340 per inspection and $9,860 for the U.S. fleet.
If required, replacing each universal bearing takes about 4 work-
hours for an estimated cost of $340 and parts cost about $1,000 for an
estimated cost of $1,340 per replacement.
If required, replacing each universal bearing and each M/R clevis
takes about 8 work-hours for an estimated cost of $680 and parts cost
about $3,000 for an estimated cost of $3,680 per replacement of both
parts.
Performing a purge grease on each universal bearing takes about
0.25 work-hours for an estimated cost of $22 per purge.
Performing a magnetic particle inspection of each M/R clevis takes
about 2 work-hours for an estimated cost of $170 per inspection.
Performing a selective brush cadmium plating takes about 4 work-
hours for an estimated cost of $340 per helicopter.

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, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866, and
(2) Will not affect intrastate aviation in Alaska.

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

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 adding the following new airworthiness
directive: