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2015-02-06 BOMBARDIER, INC.: Amendment 39-18073. Docket No. FAA-2014-0231; Directorate Identifier 2013-NM-163-AD.
(a) EFFECTIVE DATE

    This AD becomes effective March 6, 2015.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant)
    airplanes,  certificated  in  any category,  serial  numbers  5301 and
    subsequent, equipped with  horizontal stabilizer trim  actuator (HSTA)
    part number (P/N) 604-92305-3  (vendor P/N 8454-1) or  P/N 604-92305-5
    (vendor P/N 8454-2).

(d) SUBJECT

    Air Transport Association (ATA) of America Code 27, Flight Controls.

(e) REASON

    This AD was prompted by reports  of loose, broken, or backed out  spur
    gear bolts on the horizontal  stabilizer trim actuator (HSTA). We  are
    issuing this AD  to detect and  correct loose spur  gear bolts on  the
    HSTA, which, if  combined with the  failure of the  primary load path,
    could lead to failure of the HSTA and subsequent loss of the airplane.

(f) COMPLIANCE

    Comply  with this  AD within  the compliance  times specified,  unless
    already done.

(g) AIRPLANE FLIGHT MANUAL (AFM) REVISION

    Within 30 days after the effective date of this AD, revise the  Normal
    Procedures section  of the  applicable Bombardier  AFM to  include the
    information in  the applicable  temporary revision  (TR) specified  in
    paragraph  (g)(1) or  (g)(2) of  this AD.  The TRs  introduce  revised
    procedures for the stabilizer trim system check. Operate the  airplane
    according to the limitations and procedures in the applicable TR.  The
    revision  may  be  done  by inserting  a  copy  of  the applicable  TR
    specified in paragraph (g)(1) or (g)(2) of this AD into the AFM.  When
    the TR  has been  included in  the general  revisions of  the AFM, the
    general revisions may be inserted into the AFM, provided the  relevant
    information  in  the general  revision  is identical  to  that in  the
    applicable TR, and the TR may be removed.

(1) Bombardier Temporary Revision (TR) 604/37,  dated May 21, 2013, to the
    Bombardier Challenger CL-604 Airplane Flight Manual, PSP 604-1.

(2) Bombardier TR 605/18, dated May 21, 2013, to the Bombardier Challenger
    CL-605 Airplane Flight Manual, PSP 605-1.

(h) MAINTENANCE OR INSPECTION PROGRAM REVISION

    Within  30  days after  the  effective date  of  this AD:  Revise  the
    maintenance  or inspection  program, as  applicable, by  incorporating
    procedures for an Operational Test (BITE) of the Horizontal Stabilizer
    Trim Controls System (HSTCS), in accordance with a method approved  by
    the Manager,  New York  Aircraft Certification  Office (ACO), ANE-170,
    FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier,  Inc.'s
    TCCA Design Approval Organization  (DAO). The initial compliance  time
    for  the  operational  test  is  within  100  flight  hours  after the
    effective date of this AD.

Note  1  to  paragraph  (h)  of  this  AD:  Bombardier  Task 27-41-00-101,
Operational Test (BITE) of the Horizontal Stabilizer Trim Controls  System
(HSTCS), provides guidance for the operational test specified in paragraph
(h) of this AD. Bombardier Task 27-41-00-101 is included in the Bombardier
Challenger 604 Time  Limits/Maintenance Checks (TLMC)  Manual; and in  the
Bombardier Challenger 605 TLMC Manual.

(i) NO ALTERNATIVE ACTIONS OR INTERVALS

    After  the  maintenance or  inspection  program has  been  revised, as
    required by paragraph  (h) of this  AD, no alternative  actions (e.g.,
    inspections) or intervals may be used unless the actions or  intervals
    are  approved  as  an  alternative  method  of  compliance  (AMOC)  in
    accordance with the procedures  specified in paragraph (m)(1)  of this
    AD.

(j) HSTA REPLACEMENT

    For airplanes equipped with a HSTA having P/N 604-92305-3 (vendor  P/N
    845401) or P/N  604-92305-5 (vendor P/N  8454-2): Within 3,000  flight
    hours or  26 months  after the  effective date  of this  AD, whichever
    occurs  first, replace  any HSTA  having P/N  604-92305-3 (vendor  P/N
    845401) or P/N 604-92305-5 (vendor P/N 8454-2) with a HSTA having  P/N
    604-92305-7 (vendor P/N 8454-3), in accordance with the Accomplishment
    Instructions of Bombardier  Service Bulletin 604-27-032,  Revision 02,
    dated  April  22,  2014; or  Bombardier  Service  Bulletin 605-27-002,
    Revision 02, dated April 22, 2014; as applicable.

(k) CREDIT FOR PREVIOUS ACTIONS

    This paragraph provides credit  for the actions required  by paragraph
    (j) of this  AD if those  actions were performed  before the effective
    date of this AD using the service information identified in paragraphs
    (k)(1)  through  (k)(4)  of  this  AD,  as  applicable.  This  service
    information is not incorporated by reference in this AD.

(1) Bombardier Service Bulletin 604-27-032, dated September 10, 2012.

(2) Bombardier Service Bulletin 604-27-032,  Revision 01,  dated April 29,
    2013.

(3) Bombardier Service Bulletin 605-27-002, dated September 10, 2012.

(4) Bombardier Service Bulletin 605-27-002, Revision 01, April 29, 2013.

(l) PARTS INSTALLATION PROHIBITION

    As of the effective  date of this AD,  no person may install  any HSTA
    having P/N 604-92305-3 (vendor P/N 8454-1) or 604-92305-5 (vendor  P/N
    8454-2) on any airplane.

(m) OTHER FAA AD PROVISIONS

    The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs):  The Manager, New York ACO,
    ANE-170,  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  ACO, send  it to  ATTN: Program Manager,
    Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue,
    Suite 410,  Westbury, NY  11590; telephone  516-228-7300; fax  516-794
    -5531.  Before  using  any  approved  AMOC,  notify  your  appropriate
    principal inspector, or lacking a principal inspector, the manager  of
    the  local  flight   standards  district  office/certificate   holding
    district office. The AMOC approval letter must specifically  reference
    this AD.

(2) Contacting the Manufacturer:  For any requirement in this AD to obtain
    corrective  actions   from  a   manufacturer,  the   action  must   be
    accomplished using  a method  approved by  the Manager,  New York ACO,
    ANE-170; or TCCA; or Bombardier,  Inc.'s TCCA Design DAO. If  approved
    by the DAO, the approval must include the DAO-authorized signature.

(n) RELATED INFORMATION

(1) Refer   to   Mandatory  Continuing  Airworthiness  Information  (MCAI)
    Canadian Airworthiness Directive CF-2013-18  dated July 16, 2013,  for
    related  information.  This MCAI may be found in the  AD docket on the
    Internet  at   http://www.regulations.gov/#!documentDetail;D=FAA-2014-
    0231-0002.

(2) Service information identified in this AD  that is not incorporated by
    reference is available at the addresses specified in paragraphs (o)(3)
    and (o)(4) of this AD.

(o) 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 this AD specifies otherwise.

(i) Bombardier Service Bulletin 604-27-032,  Revision 02,  dated April 22,
    2014.

(ii) Bombardier Service Bulletin 605-27-002, Revision 02,  dated April 22,
     2014.

(iii) Bombardier Temporary Revision 604/37,  dated  May 21, 2013,  to  the
      Bombardier Challenger CL-604 Airplane Flight Manual, PSP 604-1.

(iv) Bombardier  Temporary Revision 605/18,  dated  May 21, 2013,  to  the
     Bombardier Challenger CL-605 Airplane Flight Manual, PSP 605-1.

(3) For  service information identified  in this AD,  contact  Bombardier,
    Inc., 400 Cote Vertu Road West, Dorval, Quebec H4S 1Y9, Canada;  tele-
    phone 514-855-5000;  fax 514-855-7401;  email thd.crj@aero.bombardier.
    com; Internet http://www.bombardier.com.

(4) You may view this service information at the FAA,  Transport  Airplane
    Directorate, 1601 Lind Avenue SW., Renton, WA.  For information on the
    availability of this material at the FAA, call 425-227-1221.

(5) 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, call
    202-741-6030,  or go to: http://www.archives.gov/federal-register/cfr/
    ibr-locations.html.

Issued  in  Renton,  Washington,  on  January 11, 2015. Jeffrey  E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification Service.

FOR  FURTHER  INFORMATION  CONTACT:  Ricardo  Garcia,  Aerospace Engineer,
Airframe  and   Propulsion  Branch,   ANE-171,  FAA,   New  York  Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY  11590;
telephone 516-28-7331; fax 516-794-5531.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0231; Directorate Identifier 2013-NM-163-AD;
Amendment 39-18073; AD 2015-02-06]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD
was prompted by reports of loose, broken, or backed-out spur gear bolts
on the horizontal stabilizer trim actuator (HSTA). This AD requires a
revision to the airplane flight manual, a revision to the maintenance
or inspection program, as applicable, and replacement of HSTAs having
certain part numbers. We are issuing this AD to detect and correct
loose spur gear bolts on the HSTA, which, if combined with the failure
of the primary load path, could lead to failure of the HSTA and
subsequent loss of the airplane.

DATES: This AD becomes effective March 6, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 6,
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0231; or in person at
the Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
For service information identified in this AD, contact Bombardier,
Inc., 400 C[ocirc]te Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9,
Canada; telephone 514-855-5000; fax 514-855-7401; email
thd.crj@aero.bombardier.com; Internet http://www.bombardier.com. You
may view this referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.

FOR FURTHER INFORMATION CONTACT: Ricardo Garcia, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-28-7331; fax 516-794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Bombardier, Inc.
Model CL-600-2B16 (CL-604 Variant) airplanes. The NPRM published in the
Federal Register on April 15, 2014 (79 FR 21158). Transport Canada
Civil Aviation (TCCA), which is the aviation authority for Canada, has
issued Canadian Airworthiness Directive CF-2013-18, dated July 16, 2013
(referred to after this as the Mandatory Continuing Airworthiness Information,
or ``the MCAI''), to correct an unsafe condition for certain Bombardier,
Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. The MCAI states:

There have been a number of reports where the HSTA spur gear
bolts were found loose, broken or backed out. Investigation revealed
that the root cause of the bolt loosening is due to incorrect
bending of the anti-rotation tab washer and the improper application
of Loctite glue during installation. Loose bolt(s) on the HSTA spur
gear combined with the failure of the primary load path, could lead
to failure of the HSTA and subsequent loss of the aeroplane.
Bombardier Aerospace has introduced a modified HSTA [part
number] P/N 604-92305-5 (vendor P/N 8454-2) to rectify the loose
bolt problem. However, this modified HSTA has several quality
control problems which could affect safety.
This AD is issued to mandate the replacement of the affected
HSTA with the new HSTA P/N 604-92305-7 (vendor P/N 8454-3).

In addition to requiring the replacement of any HSTA having the
affected part number, this AD requires revising both the airplane
flight manual and airplane maintenance or inspection program.
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0231-0002.

Comments

We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM (79 FR
21158, April 15, 2014) and the FAA's response to the comment.

Request To Refer to Revised Service Information

Mher Krikorian stated that the current revision of the service
information is not referenced in the NPRM (79 FR 21158, April 15, 2014)
and requested that the NPRM be revised to refer to Bombardier Service
Bulletin 604-27-032, Revision 02, dated April 22, 2014; and Bombardier
Service Bulletin 605-27-002, Revision 02, dated April 22, 2014. Mr.
Krikorian suggested that referring to the current revision of the
service information would help to avoid requests for approval of
alternative methods of compliance.
We agree with the commenter's request and have revised paragraph
(j) of this AD to refer to Bombardier Service Bulletin 604-27-032,
Revision 02, dated April 22, 2014; and Bombardier Service Bulletin 605-
27-002, Revision 02, dated April 22, 2014. The revised service
information includes only minor changes and does not include any
substantive changes or new actions. We also added a new paragraph (k)
to this AD to provide credit for actions accomplished prior to the
effective date of this AD using Bombardier Service Bulletin 604-27-032,
dated September 10, 2012; 604-27-032, Revision 01, dated April 29,
2013; 605-27-002, dated September 10, 2012; or Bombardier Service
Bulletin 605-27-002, Revision 01, April 29, 2013; as applicable. We
redesignated the subsequent paragraphs accordingly.

"Contacting the Manufacturer" Paragraph in This AD

Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
We have become aware that some operators have misunderstood or
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of
deviations during the accomplishment of an AD-mandated action. The
Airworthy Product paragraph does not approve messages or other
information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this AD to obtain corrective actions from a
manufacturer, the actions must be accomplished using a method approved
by the FAA, TCCA, or Bombardier, Inc.'s TCCA Design Approval
Organization (DAO).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DAO, the approval must include the DAO-authorized
signature. The DAO signature indicates that the data and information
contained in the document are TCCA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DAO-authorized are not TCCA-approved, unless
TCCA directly approves the manufacturer's message or other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``design approval holder (DAH) with State of
Design Authority design organization approval,'' but instead we have
provided the specific delegation approval granted by the State of
Design Authority for the DAH throughout this AD.

Additional Changes to This AD

We revised paragraph (h) of this AD to require operators to revise
the maintenance or inspection program, as applicable, by incorporating
procedures for an Operational Test (BITE) of the Horizontal Stabilizer
Trim Controls System (HSTCS), in accordance with a method approved by
the Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s
TCCA DAO. Bombardier Task 27-41-00-101, Operational Test (BITE) of the
Horizontal Stabilizer Trim Controls System (HSTCS), is referenced as
guidance material in new Note 1 to paragraph (h) of this AD.

Conclusion

We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD with the changes described previously, and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 21158, April 15, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 21158, April 15, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Related Service Information

We reviewed Bombardier Temporary Revision (TR) 604/37, dated May
21, 2013, to the Bombardier Challenger CL-604 Airplane Flight Manual,
PSP 604-1; and Bombardier TR 605/18, dated May 21, 2013, to the
Bombardier Challenger CL-605 Airplane Flight Manual, PSP 605-1. This
service information describes procedures for the stabilizer trim system
check. We also reviewed Bombardier Service Bulletin 604-27-032,
Revision 02, dated April 22, 2014; and Bombardier Service Bulletin 605-
27-002, Revision 02, dated April 22, 2014. This service information
describes procedures for replacing HSTAs. You can find this information
at http://www.regulations.gov by searching for and locating Docket No.
FAA-2014-0231.

Costs of Compliance

We estimate that this AD affects 125 airplanes of U.S. registry.
We also estimate that it will take about 21 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $0 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $223,125, or $1,785 per product.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.

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 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. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. 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.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0231; 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 AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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 adding the following new airworthiness
directive (AD):