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2020-12-10 BELL TEXTRON INC. (TYPE CERTIFICATE PREVIOUSLY HELD BY BELL HELICOPTER TEXTRON INC.): Amendment 39-21145; Docket No. FAA-2018-0866; Product Identifier 2018-SW-083-AD.
(a) APPLICABILITY

    This AD applies to Bell Textron Inc. (Type Certificate previously held
    by Bell Helicopter Textron Inc.)  Model  205A, 205A-1, 205B, 212, 412,
    412CF, and  412EP helicopters,  certificated in  any category,  with a
    tail rotor (T/R) blade part number 212-010-750  (all dash numbers) in-
    stalled, all serial numbers (S/Ns) except:

(1) S/Ns with a prefix of "BH"; or

(2) S/Ns with a prefix of "A" and a number 17061 or larger.

(b) UNSAFE CONDITION

    This AD defines the unsafe condition as a pit or corrosion in the for-
    ward spar of a  T/R blade. This condition  could result in a  crack in
    the T/R blade, loss of the  T/R blade,  and subsequent loss of control
    of the helicopter.

(c) AFFECTED ADS

    This AD replaces AD 2011-12-08,  Amendment 39-16715 (76 FR 35334, June
    17, 2011) ("AD 2011-12-08").

(d) EFFECTIVE DATE

    This AD becomes effective July 16, 2020.

(e) COMPLIANCE

    You are  responsible for  performing each  action required  by this AD
    within  the  specified  compliance time  unless  it  has already  been
    accomplished prior to that time.

(f) REQUIRED ACTIONS

(1) Within 25 hours time-in-service or 30 days, whichever occurs first:

(i) Remove the T/R hub and blade assembly  from the helicopter  and remove
    the T/R blade from the hub.  Remove  the  paint  from the spar area on
    both sides of the T/R blade  by following  the Accomplishment Instruc-
    tions,  paragraphs 3. through 5.,  of  the  following  Bell Helicopter
    Textron, Inc. Alert Service Bulletins,  all Revision A,  and all dated
    December 8, 2009:  Alert Service Bulletin (ASB) No. 205-09-102 for the
    Model 205A and 205A-1 helicopters;  ASB No. 205B-09-54  for  the Model
    205B helicopters;  ASB No. 212-09-134  for the  Model 212 helicopters;
    ASB No. 412CF-09-38 for the  Model 412CF helicopters;  and ASB No. 412
    -09-136 for the Model 412 and 412EP helicopters.

(ii) Using a 3-power  or  higher magnifying glass,  visually inspect  both
     sides of the T/R blade for any corrosion  or pitting  in the spar in-
     spection areas  as depicted  in Figure  1 of  the ASB  for your model
     helicopter.

(2) Before further flight:

(i) If you find any corrosion or pitting that is 0.003 inch deep  or less,
    either replace the T/R blade with an airworthy T/R blade or repair the
    T/R blade.

(ii) If you find any corrosion  or pitting that is greater than 0.003 inch
     deep, replace the T/R blade with an airworthy T/R blade.

(iii) If any parent material is removed  during the  sanding operation re-
      quired by paragraph (f)(1)(i) of this AD,  either  replace  the  T/R
      blade with an airworthy T/R blade,  or  repair  the T/R blade if the
      parent material removed is within the maximum repair damage limits.

(iv) If there is no corrosion or pitting  and no damage greater than 0.003
     inch deep, refinish the inspection areas and reinstall each T/R blade
     onto the T/R hub,  install the T/R assembly  on  the  helicopter  and
     track and balance the T/R  in accordance  with the Accomplishment In-
     structions, paragraphs 8. through 10., of the ASB for your model hel-
     icopter.

(g) CREDIT FOR PREVIOUS ACTIONS

    Actions accomplished  before the effective date of this AD  in accord-
    ance with AD 2011-12-08 are acceptable for compliance  with the corre-
    sponding actions specified in paragraph (f) of this AD.

(h) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, DSCO, FAA, may approve AMOCs for this AD.  Send your pro-
    posal to:  Kuethe Harmon,  Safety  Management  Program  Manager,  DSCO
    Branch, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone 817-
    222-5198; email 9-ASW-190-COS@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate
    or under 14 CFR part 91,  subpart K, the FAA suggests that  you notify
    your  principal  inspector,  or  lacking  a  principal  inspector, the
    manager of the local  flight standards district office  or certificate
    holding district office, before operating any aircraft complying  with
    this AD through an AMOC.

(i) SUBJECT

    Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor Blades.

(j) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference (IBR) of  the service information  listed in this  paragraph
    under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use  this service information as applicable to do the actions
    required by this AD, unless the AD specifies otherwise.

(3) The following service information was approved for IBR on July 5, 2011
    (76 FR 35334, June 17, 2011).

(i) Bell Helicopter Textron, Inc. Alert Service Bulletin (ASB) No. 205-09-
    102, Revision A, dated December 8, 2009.

(ii) Bell Helicopter Textron, Inc. ASB No. 205B-09-54,  Revision A,  dated
     December 8, 2009.

(iii) Bell Helicopter Textron, Inc. ASB No. 212-09-134,  Revision A, dated
      December 8, 2009.

(iv) Bell Helicopter Textron, Inc. ASB No. 412CF-09-38,  Revision A, dated
     December 8, 2009.

(v) Bell Helicopter Textron, Inc.  ASB No. 412-09-136,  Revision A,  dated
    December 8, 2009.

(4) For Bell Helicopter service information identified in this AD, contact
    Bell Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone 817-
    280-3391; fax 817-280-6466; or at https://www.bellcustomer.com.

(5) You may view this service information  at FAA,  Office of the Regional
    Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Ft Worth,
    TX 76177.  For information on the availability of this material at the
    FAA, call 817-222-5110.

(6) 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
    fedreg.legal@nara.gov,  or  go  to:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on June 5, 2020. Gaetano A Sciortino, Deputy Director for Strategic
Initiatives,  Compliance & Airworthiness Division,  Aircraft Certification
Service.

FOR FURTHER INFORMATION CONTACT: Kuethe Harmon,  Safety Management Program
Manager,  DSCO  Branch,  FAA,  10101 Hillwood Pkwy,  Fort Worth, TX 76177;
telephone 817-222-5198; email kuethe.harmon@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0866; Product Identifier 2018-SW-083-AD; Amendment
39-21145; AD 2020-12-10]
RIN 2120-AA64

Airworthiness Directives; Bell Textron Inc. (Type Certificate
Previously Held by Bell Helicopter Textron Inc.) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2011-12-08
for Bell Helicopter Textron Inc. (Bell), Model 205A, 205A-1, 205B, 212,
412, 412CF, and 412EP helicopters. AD 2011-12-08 required a one-time
inspection of the tail rotor (T/R) blade for corrosion and pitting.
This new AD retains the requirements of AD 2011-12-08 while excluding
certain T/R blades from the applicability. This AD was prompted by new
manufacturing and inspection procedures implemented by Bell that
correct the unsafe condition on more recently manufactured T/R blades.
The actions of this AD are intended to address an unsafe condition on
these products.

DATES: This AD is effective July 16, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 5, 2011
(76 FR 35334, June 17, 2011).

ADDRESSES: For service information identified in this final rule,
contact Bell Textron Inc., P.O. Box 482, Fort Worth, TX 76101;
telephone 817-280-3391; fax 817-280-6466; or at https://www.bellcustomer.
com. You may view this referenced service information
at the FAA, Office of the Regional Counsel, Southwest Region, 10101
Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177. It is also available
on the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2018-0866.

Examining the AD Docket

You may examine the AD docket on the internet at https://www.regulations.
gov in Docket No. FAA-2018-0866; 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 AD, any service
information that is incorporated by reference, any comments received,
and other information. The street address for Docket Operations is
Docket Operations, U.S. Room W12-140, 1200 New Jersey Avenue SE,
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Kuethe Harmon, Safety Management
Program Manager, DSCO Branch, FAA, 10101 Hillwood Pkwy, Fort Worth, TX
76177; telephone 817-222-5198; email kuethe.harmon@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to remove AD 2011-12-08, Amendment 39-16715 (76 FR 35334,
June 17, 2011) (``AD 2011-12-08'') and add a new AD. AD 2011-12-08
applied to Bell Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP
helicopters with a T/R blade, part number 212-010-750 (all dash
numbers), all serial numbers (S/Ns) except those with a prefix of ``A''
and the number 17061 or larger, and required a one-time inspection of
the T/R blade for corrosion and pitting. The NPRM published in the
Federal Register on April 11, 2019 (84 FR 14626). The NPRM proposed to
retain the requirements of AD 2011-12-08 but remove blades with an S/N
prefix of ``BH'' from the applicability. The proposed actions were
intended to correct the unsafe conditions on these products.
Since the FAA issued the NPRM, Bell Helicopter Textron Inc., has
changed its name to Bell Textron Inc. This final rule reflects that
change and updates the contact information to obtain service
documentation.

Comments

After the NPRM was published, the FAA received comments from five
commenters, four from individuals and one from the European Union
Aviation Safety Agency (EASA). The following presents the comments
received on the NPRM and the FAA's response to each comment.

Support for the NPRM

Two individual commenters supported the NPRM.

Comments Requesting More Information

EASA and an individual commenter requested that the FAA provide
more information about the unsafe condition and the related service
information.
Request: One individual requested details regarding the
manufacturing anomalies due to the chemical milling process, how the
process affected the manufacturing of other parts, and what manufacturing
changes have been made to ensure future problems do not continue.
FAA Response: The FAA agrees to provide additional information. AD
2011-12-08 was issued in 2011 to address manufacturing anomalies in the
chemical milling process. Chem-milled steps are applied to all tail
rotor metal blade spars. Pits in the spars were found along the step of
straight chem-mill cuts. Gas bubbles were trapped on the step of the
cut, and this created pits down the length of the step in the radius.
To address this, Bell advised its supplier to better agitate the tanks,
change the wetting agent, or use vertical racking instead of
horizontal. In addition to corrective actions taken by the chem-mill
supplier, Bell added inspections for chem-mill defects upon receipt of
the spars. No problems have recurred since the AD 2011-12-08 was
issued. This superseding AD does not change any of the corrective
actions from AD 2011-12-08. This superseding AD only excludes a newly
manufactured part that is not subject to the unsafe condition
identified in AD 2011-12-08.
Request: EASA requested the FAA make the Bell service bulletins
referenced in the NPRM available for review in the AD docket. EASA also
asked whether Bell will revise its service bulletins to exclude blades
with the prefix ``BH.''
FAA Response: Because the Bell service bulletins requested by EASA
were incorporated by reference in AD 2011-12-08, they are available on
the internet at https://www.regulations.gov in AD Docket No. FAA-2011-
0561. In addition, they will be available in the AD docket for this new
AD, Docket No. FAA-2018-0866. The FAA is unaware of whether Bell will
revise its service bulletins.

Request for the FAA To Inspect the T/R Blades

One commenter disagreed with the FAA's proposal to supersede the AD
by removing T/R blades with an S/N with a prefix of ``BH'' from the
applicability. The commenter stated that these blades should still be
inspected by the FAA.
FAA Response: The FAA has determined that the unsafe condition
addressed by this AD does not apply to T/R blades with an S/N with a
prefix of ``BH''. Therefore, those blades have been removed from the
applicability. In addition, neither AD 2011-12-08 nor this superseding
AD require operators to have the T/R blades inspected by the FAA.
Instead, the T/R blades must be inspected using standard requirements
under 14 CFR parts 43 and 145.

FAA's Determination

The FAA has reviewed the relevant information and determined that
an unsafe condition exists and is likely to exist or develop on other
helicopters of these same type designs and that air safety and the
public interest require adopting the AD requirements as proposed.

Related Service Information Under 1 CFR Part 51


The FAA has reviewed the following Bell Alert Service Bulletins,
all Revision A, and all dated December 8, 2009, which specify a one-
time inspection of the T/R blades for corrosion or pitting, and
repairing or replacing the T/R blade if corrosion, pitting, or other
damage is discovered:
Alert Service Bulletin (ASB) No. 205-09-102, for Model
205A and 205A-1 helicopters;
ASB No. 205B-09-54, for Model 205B helicopters;
ASB No. 212-09-134, for Model 212 helicopters;
ASB No. 412-09-136, for Model 412 and 412EP helicopters;
and
ASB No. 412CF-09-38, for Model 412CF helicopters.
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 384 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour.
Inspecting a T/R blade takes about 10 work-hours and no parts for
an estimated cost of $850 per helicopter and $326,400 for the U.S.
fleet.
Repairing a T/R blade takes about 10 work-hours and parts cost $750
for an estimated replacement cost of $1,600 per blade.
Replacing a T/R blade takes about 10 work-hours and parts cost
$28,120 for an estimated replacement cost of $28,970 per blade.

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 has determined that 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.

Adoption of 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 removing Airworthiness Directive (AD)
2011-12-08, Amendment 39-16715 (76 FR 35334, June 17, 2011), and adding
the following new AD: