Tdata AD

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PROPOSED AD	BELL HELICOPTER TEXTRON CANADA LIMITED: Docket No. FAA-2010-0866; Directorate Identifier 2010-SW-065-AD.

COMMENTS DUE DATE

(a) We must receive comments by October 14, 2010.

AFFECTED ADS

(b) None.

APPLICABILITY

(c) This AD  applies to Model  427 helicopters, all  serial numbers (SNs),
    certificated in any category.

SUBJECT

(d) Air Transport Association of America (ATA) Code 65: Tail Rotor Drive.

REASON

(e) The mandatory continuing airworthiness information (MCAI) states:

Tail rotor  driveshaft hanger  bearing bracket  part number  (P/N) 427-044
-223-101 has  been found  cracked due  to fatigue.  It has been determined
that the  fatigue cracking  was initiated  by a  tooling mark  left during
manufacture.

The  existence of  tooling marks  on the  bracket  could  lead to  bracket
failure, loss of  tail rotor drive  and, consequently, loss  of control of
the helicopter.

The MCAI requires you to  rework the tail rotor driveshaft  hanger bearing
bracket.

ACTIONS AND COMPLIANCE

(f) Unless already done, do the following actions:

(1) Applicable to SNs 56001 through 56073, and 56077: Within 30 days after
    the  effective date  of this  AD, inspect  both  sides  of the  hanger
    bracket,  P/N 427-044-223-101,  for cracks  following Bell  Helicopter
    Alert Service Bulletin No. 427-09-29, REV A, dated  November 17, 2009.

(i) If  no cracks  are found  during the  inspection required by paragraph
    (f)(1) of  this AD,  before further  flight rework  both sides  of the
    hanger bracket, P/N  427-044-223-101, following Bell  Helicopter Alert
    Service Bulletin No. 427-09-29, REV A, dated November 17, 2009.

(ii) If  cracks  are found  during the  inspection  required  by paragraph
     (f)(1) of this AD, before further flight replace the hanger  bracket,
     P/N 427-044-223-101, with a new hanger bracket, P/N  427-044-223-101,
     that  has  been  reworked  following  Bell  Helicopter  Alert Service
     Bulletin No. 427-09-29, REV A, dated November 17, 2009.

(2) Applicable to all  SNs: As of the  effective date of this  AD, you may
    not install replacement tail rotor driveshaft hanger bracket, P/N  427
    -044-223-101, unless the bracket has been inspected and found free  of
    cracks and has been  reworked following Bell Helicopter  Alert Service
    Bulletin No. 427-09-29, REV A, dated November 17, 2009.

FAA AD DIFFERENCES

NOTE: This AD differs from the MCAI and/or service information as follows:
No differences.

OTHER FAA AD PROVISIONS

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Off-
    ice, FAA, has the authority to approve AMOCs for this AD, if requested
    using the procedures found in 14 CFR 39.19. Send information to  ATTN:
    Sharon Miles,  Aerospace Engineer,  FAA, Rotorcraft  Directorate, 2601
    Meacham Blvd.,  Fort Worth,  Texas 76137;  telephone: (817)  222-5122;
    fax: (817) 222-5961. Before using any approved AMOC on any airplane to
    which the  AMOC applies,  notify your  appropriate principal inspector
    (PI) in the FAA Flight Standards District Office (FSDO), or lacking  a
    PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective
    actions from a manufacturer or other source, use these actions if they
    are FAA-approved.  Corrective actions  are considered  FAA-approved if
    they are approved by the State of Design Authority (or their delegated
    agent). You are required to assure the product is airworthy before  it
    is returned to service.

(3) Reporting Requirements: For any reporting requirement  in this AD, un-
    der the provisions of the  Paperwork Reduction Act (44 U.S.C.  3501 et
    seq.), the  Office of  Management and  Budget (OMB)  has approved  the
    information  collection  requirements  and  has  assigned  OMB Control
    Number 2120-0056.

RELATED INFORMATION

(h) Refer to MCAI Transport Canada AD No. CF-2010-17, dated June 2,  2010;
    and Bell Helicopter Alert Service Bulletin No. 427-09-29, REV A, dated
    November 17, 2009, for related information.

Issued in Fort Worth, Texas, on August 19, 2010. Mark R. Schilling, Acting
Manager, Rotorcraft Directorate, Aircraft Certification Service.

DATES: We must receive comments on this proposed AD by October 14, 2010.

PREAMBLE

DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

14 CFR Part 39

[Docket  No.  FAA-2010-0866;  Directorate  Identifier  2010-SW-065-AD] RIN
2120-AA64

AIRWORTHINESS DIRECTIVES; Bell Helicopter Textron Canada Limited Model 427
Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of  Transportat-
ion (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose  to adopt a  new airworthiness directive  (AD) for the
products listed above. This proposed AD results from mandatory  continuing
airworthiness information  (MCAI) originated  by an  aviation authority of
another country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as:

Tail rotor  driveshaft hanger  bearing bracket  part number  (P/N) 427-044
-223-101 has  been found  cracked due  to fatigue.  It has been determined
that the  fatigue cracking  was initiated  by a  tooling mark  left during
manufacture.

The  existence of  tooling marks  on the  bracket  could  lead to  bracket
failure, loss of  tail rotor drive  and, consequently, loss  of control of
the helicopter.

The proposed  AD would  require actions  that are  intended to address the
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by October 14, 2010.

ADDRESSES: You may send comments by any of the following methods:

Federal eRulemaking Portal: Go  to  http://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: U.S. Department of Transportation, Docket Operations, M-30,
West Building  Ground Floor,  Room W12-140,  1200 New  Jersey Avenue, SE.,
Washington, DC 20590,  between 9 a.m.  and 5 p.m.,  Monday through Friday,
except Federal holidays.

EXAMINING THE AD DOCKET

You may examine the AD docket on  the Internet at  http://www.regulations.
gov; or in person at the  Docket Management Facility between 9 a.m.  and 5
p.m.,  Monday  through  Friday, except  Federal  holidays.  The AD  docket
contains  this  proposed  AD,  the  regulatory  evaluation,  any  comments
received, and other information. The street address for the Docket  Office
(telephone (800) 647-5527) is in  the ADDRESSES section. Comments will  be
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sharon  Miles, Aerospace  Engineer,  FAA,
Rotorcraft  Directorate,  2601  Meacham Blvd.,  Fort  Worth,  Texas 76137;
telephone: (817) 222-5122; fax: (817) 222-5961.

SUPPLEMENTARY INFORMATION:

COMMENTS INVITED

We invite you to send any written relevant data, views, or arguments about
this  proposed AD.  Send your  comments to  an address  listed  under  the
ADDRESSES  section.   Include  "Docket   No.  FAA-2010-0866;   Directorate
Identifier  2010-SW-065-AD"  at  the   beginning  of  your  comments.   We
specifically  invite  comments   on  the  overall   regulatory,  economic,
environmental, and energy  aspects of this  proposed AD. We  will consider
all comments received by the closing  date and may amend this proposed  AD
because of those comments.

We  will  post  all  comments  we  receive,  without  change,  to  http://
www.regulations.gov, including  any personal  information you  provide. We
will also  post a  report summarizing  each substantive  verbal contact we
receive about this proposed AD.

DISCUSSION

Transport Canada, which is the  aviation authority for Canada, has  issued
AD No.  CF-2010-17, dated  June 2,  2010 (referred  to after  this as "the
MCAI"), to  correct an  unsafe condition  for the  specified products. The
MCAI states:

Tail rotor  driveshaft hanger  bearing bracket  part number  (P/N) 427-044
-223-101 has  been found  cracked due  to fatigue.  It has been determined
that the  fatigue cracking  was initiated  by a  tooling mark  left during
manufacture.

The  existence of  tooling marks  on the  bracket  could  lead to  bracket
failure, loss of  tail rotor drive  and, consequently, loss  of control of
the helicopter.

The MCAI requires you to  rework the tail rotor driveshaft  hanger bearing
bracket. You may obtain further  information by examining the MCAI  in the
AD docket.

RELEVANT SERVICE INFORMATION

Bell Helicopter has  issued Alert Service  Bulletin No. 427-09-29,  REV A,
dated November 17, 2009. The actions described in this service information
are intended to correct the unsafe condition identified in the MCAI.

FAA'S DETERMINATION AND REQUIREMENTS OF THE PROPOSED AD

This  product  has been  approved  by the  aviation  authority of  another
country, and is approved for  operation in the United States.  Pursuant to
our bilateral  agreement with  this State  of Design  Authority, they have
notified us  of the  unsafe condition  described in  the MCAI  and service
information  referenced  above.  We  are  proposing  this  AD  because  we
evaluated all information and  determined the unsafe condition  exists and
is likely to exist or develop on other products of the same type design.

DIFFERENCES BETWEEN THIS PROPOSED AD AND THE MCAI OR SERVICE INFORMATION

We have reviewed the MCAI and related service information and, in general,
agree with their substance.  But we might have  found it necessary to  use
different words from those in the MCAI to ensure the AD is clear for  U.S.
operators and is enforceable. In making these changes, we do not intend to
differ substantively from the information provided in the MCAI and related
service information.

We might also have proposed different actions in this AD from those in the
MCAI in order to follow FAA policies. Any such differences are highlighted
in a Note within the proposed AD.

COSTS OF COMPLIANCE

We  estimate  that  this  proposed AD  will  affect  30  products of  U.S.
registry.  We also  estimate that  it would  take about  4 work-hours  per
product to  comply with  the basic  requirements of  this proposed AD. The
average labor rate is $85 per work-hour.

Based on these figures,  we estimate the cost  of the proposed AD  on U.S.
operators to be $10,200, or $340 per product.

In  addition,  we  estimate that  any  necessary  follow-on actions  would
require parts costing $5,034, for a cost of $5,034 per product. We have no
way of determining the number of products that may need these actions.

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.

We are 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

We 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  responsib-
ilities 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. Is not a "significant rule" under the DOT Regulatory Policies and Proc-
   edures (44 FR 11034, February 26, 1979); and

3. Will not have a significant economic impact, positive or negative, on a
   substantial number of small entities under the criteria of the Regulat-
   ory Flexibility Act.

We prepared a regulatory evaluation of the estimated costs to comply  with
this proposed AD and placed it in the AD docket.

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 adding the following new AD: