[Federal Register Volume 84, Number 88 (Tuesday, May 7, 2019)]
[Proposed Rules]
[Pages 19879-19881]
[FR Doc No: 2019-09256]

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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.

========================================================================

Federal Register / Vol. 84, No. 88 / Tuesday, May 7, 2019 / Proposed
Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0251; Product Identifier 2019-NM-057-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus SAS Model A320-251N and -271N airplanes; and A321-251N,
-253N, -271N, and -272N airplanes. This proposed AD was prompted by a
report that during a calibration check, some torqueing tools used on
the final assembly line have been found out of tolerance. This proposed
AD would require retorqueing each affected connection of sense and fire
extinguishing lines within the pylon area to a correct torque value, as
specified in a European Aviation Safety Agency (EASA) AD, which will be
incorporated by reference. We are proposing this AD to address the
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by June 21, 2019.

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 http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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 the incorporation by reference (IBR) material described in the
``Related IBR material under 1 CFR part 51'' section in SUPPLEMENTARY
INFORMATION, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 89990 1000; email<EMAIL_ADDRESS>
internet www.easa.europa.eu. You may find this IBR material on the EASA
website at https://ad.easa.europa.eu. You may view this IBR material at
the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines,
WA. For information on the availability of this material at the FAA,
call<PHONE_NUMBER>. It is also available in the AD docket on the
internet at http://www.regulations.gov.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0251; 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 regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (telephone 800-
647-5527) is in the ADDRESSES section. Comments will be available in
the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2019-0251;
Product Identifier 2019-NM-057-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM based on
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 NPRM.

Discussion

    The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2019-0081, dated April 3, 2019
(``EASA AD 2019-0081'') (also referred to as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Airbus SAS Model A320-251N and -271N airplanes;
and A321-251N, -253N, -271N, and -272N airplanes. The MCAI states:

    During periodic calibration check, some torqueing tools used on
the final assembly line have been found out-of-tolerance. The
subsequent investigation determined that connections of sense and
fire extinguishing lines within the pylon area have been under-
torqued on a group of aeroplanes.
    This condition, if not corrected, could lead to leaks or
disconnections of those lines, possibly resulting in reduced engine
control and/or reduced safety margin in case of engine fire.
    To address this potential unsafe condition, Airbus issued the
applicable SB [service bulletin], providing instructions to restore
the correct torque value of those affected connections.
    For the reason described above, this [EASA] AD requires re-
torqueing to the correct value the affected connections.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2019-0081 describes procedures for retorqueing each
affected connection of sense and fire extinguishing lines within the
pylon area to a correct torque value. This material 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, and it is publicly available through the EASA
website.

FAA's Determination and Requirements of This 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 the State of Design Authority, we have
been notified

of the unsafe condition described in the MCAI referenced above. We are
proposing this AD because we evaluated all pertinent information and
determined an unsafe condition exists and is likely to exist or develop
on other products of the same type design.

Proposed Requirements of This NPRM

    This proposed AD would require accomplishing the actions specified
in EASA AD 2019-0081, described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA worked with Airbus and EASA to develop a process to
use certain EASA ADs as the primary source of information for
compliance with requirements for corresponding FAA ADs. As a result,
EASA AD 2019-0081 will be incorporated by reference in the FAA final
rule. This proposed AD would, therefore, require compliance with the
provisions specified in EASA AD 2019-0081, through that incorporation,
except for any differences identified as exceptions in the regulatory
text of this proposed AD. Service information specified in EASA AD
2019-0081 that is required for compliance with EASA AD 2019-0081 will
be available on the internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2019-0251 after the FAA final rule is
published.

Costs of Compliance

    We estimate that this proposed AD affects 15 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
10 work-hours x $85 per hour = $850..........................              $0             $850          $12,750
----------------------------------------------------------------------------------------------------------------

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.
    This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.

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 responsibilities 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 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.

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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness
directive (AD):

Airbus SAS: Docket No. FAA-2019-0251; Product Identifier 2019-NM-
057-AD.

(a) Comments Due Date

    We must receive comments by June 21, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus SAS Model A320-251N and -271N
airplanes; and A321-251N, -253N, -271N, and -272N airplanes;
certificated in any category, as identified in European Aviation
Safety Agency (EASA) AD 2019-0081, dated April 3, 2019 (``EASA AD
2019-0081'').

(d) Subject

    Air Transport Association (ATA) of America Code 26, Fire
protection.

(e) Reason

    This AD was prompted by a report that during a calibration
check, some torqueing tools used on the final assembly line have
been found out of tolerance. We are issuing this AD to address sense
connections and fire extinguishing lines within the pylon area that
have been under-torqued, which could lead to leaks or disconnections
of those lines and possibly result in reduced engine control and
reduced safety margin in case of engine fire.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2019-0081.

(h) Exceptions to EASA AD 2019-0081

    (1) For purposes of determining compliance with the requirements
of this AD: Where EASA AD 2019-0081 refers to its

effective date, this AD requires using the effective date of this
AD.
    (2) The ``Remarks'' section of EASA AD 2019-0081 does not apply
to this AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards 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 International Section, send it to the attention of
the person identified in paragraph (j)(2) of this AD. Information
may be emailed to<EMAIL_ADDRESS>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.
    (2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's
EASA Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): For any service information
referenced in EASA AD 2019-0081 that contains RC procedures and
tests: Except as required by paragraphs (h)(1) and (h)(2) of this
AD, RC procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.

(j) Related Information

    (1) For information about EASA AD 2019-0081, contact the EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
89990 6017; email<EMAIL_ADDRESS>Internet www.easa.europa.eu.
You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. You may view this EASA AD at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195. EASA AD 2019-0081 may be found in the AD docket on the
internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0251.
    (2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax<PHONE_NUMBER>.

    Issued in Des Moines, Washington, on April 25, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-09256 Filed 5-6-19; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register: December 4, 2009 (Volume 74, Number 232)]
[Rules and Regulations]
[Page 63587-63590]
[DOCID:fr04de09-16]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0565; Directorate Identifier 2008-NM-217-AD;
Amendment 39-16112; AD 2009-24-18]
RIN 2120-AA64

Airworthiness Directives; Bombardier Model CL-600-2A12 (CL-601)
and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This 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:

    * * * [I]ncidents of throttle jam and engine shutdowns, caused
by premature wear of the rack and pinion mechanism of part number
(P/N) 2100140-005 and -007 Engine Throttle Control Gearbox (ETCG),
installed on Bombardier CL-601 and 604 aircraft.
* * * * *

We are issuing this AD to require actions to correct the unsafe
condition on these products.

DATES: This AD becomes effective January 8, 2010.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 8,
2010.

ADDRESSES: You may examine the AD docket on the Internet at http://
www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Rocco Viselli, Aerospace Engineer,
Airframe and Mechanical Systems, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on June 23, 2009 (74 FR
29632). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:

    There have been various reported incidents of throttle jam and
engine shutdowns, caused by premature wear of the rack and pinion
mechanism of part number (P/N) 2100140-005 and -007 Engine Throttle
Control Gearbox (ETCG), installed on Bombardier CL-601 and 604
aircraft.
    Bombardier issued service bulletins (SB) 601-0583 (CL601/601-3A,
-3R) and 604-76-004 (CL 604), introducing periodic inspection of the
affected ETCG rack and pinion mechanisms for wear.
    Subject inspection requirement tasks have now been incorporated
into the applicable CL601 and CL604 Time Limits Maintenance Checks
(TLMCs) through Temporary Revisions (TR), TR 5-236 (for CL601), TR
5-236 (for CL601-3A & -3R) and TR 5-2-40 (for CL604).

The required action is revising the Airworthiness Limitations Section
of the Instructions for Continued Airworthiness to incorporate new
repetitive functional tests of the ETCG. You may obtain further
information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.

New Note

    We have added Note 1 to this AD to clarify compliance with section
91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c)).

Updated Contact Information

    We have updated paragraph (g)(1) of this AD to provide the
appropriate contact information to use when submitting requests for
approval of an alternative method of compliance (AMOC).

Conclusion

    We reviewed the available data and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.

Differences Between This 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 required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a Note within the AD.

Costs of Compliance

    We estimate that this AD will affect 377 products of U.S. registry.
We also estimate that it will take about 1 work-hour per product to
comply with the basic requirements of this AD. The average labor rate
is $80 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $30,160, or $80 per product.

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

Examining the AD Docket

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2009-24-18 Bombardier, Inc. (Formerly Canadair): Amendment 39-16112.
Docket No. FAA-2009-0565; Directorate Identifier 2008-NM-217-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January
8, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Bombardier Model CL-600-2A12 (CL-601)
and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes,
certificated in any category.

    Note 1:  This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (g)(1) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued operational safety of the airplane.

Subject

    (d) Air Transport Association (ATA) of America Code 76: Engine
controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI)
states:
    There have been various reported incidents of throttle jam and
engine shutdowns, caused by premature wear of the rack and pinion
mechanism of part number (P/N) 2100140-005 and -007 Engine Throttle
Control Gearbox (ETCG), installed on Bombardier CL-601 and 604
aircraft.
    Bombardier issued service bulletins (SB) 601-0583 (CL601/601-3A,
-3R) and 604-76-004 (CL 604), introducing periodic inspection of the
affected ETCG rack and pinion mechanisms for wear.
    Subject inspection requirement tasks have now been incorporated
into the applicable CL601 and CL604 Time Limits Maintenance Checks
(TLMCs) through Temporary Revisions (TR), TR 5-236 (for CL601), TR
5-236 (for CL601-3A & -3R) and TR 5-2-40 (for CL604).

The required action is revising the Airworthiness Limitations
Section of the Instructions for Continued Airworthiness to
incorporate new repetitive functional tests of the ETCG.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 30 days after the effective date of this AD: Revise
the Airworthiness Limitations section of the Instructions for
Continued Airworthiness by incorporating the applicable task in the
TR listed in Table 1 of this AD.

                      Table 1--Temporary Revisions to the Airworthiness Limitations Section
----------------------------------------------------------------------------------------------------------------
                                         Use Canadair
                                          Challenger                                    To the Airworthiness
        For Bombardier model--             Temporary             Dated--              Limitations section of--
                                          Revision--
----------------------------------------------------------------------------------------------------------------
CL-600-2A12 (CL-601) airplanes........           5-236  July 25, 2008............  Section 5-10-30 of Chapter 5
                                                                                of the Canadair Challenger
                                                                                Time Limits/Maintenance
                                                                                Checks, PSP 601-5.
CL-600-2B16 (CL-601-3A, and CL-601-3R)           5-236  March 22, 2007...........  Section 5-10-30 of Chapter 5
 airplanes.                                                                         of the Canadair Challenger
                                                                                Time Limits/Maintenance
                                                                                Checks, PSP 601A-5.
CL-600-2B16 (CL-604) airplanes........          5-2-40  July 28, 2008............  Section 5-10-40 of Chapter 5
                                                                                of the Canadair Challenger
                                                                                CL-604 Time Limits/
                                                                                Maintenance Checks.
----------------------------------------------------------------------------------------------------------------

     (2) For the new TLMC tasks identified in Canadair Challenger
Temporary Revision 5-236, dated July 25, 2008; Temporary Revision 5-
2-40, dated July 28, 2008; and Temporary Revision 5-236, dated March
22, 2007: Initial compliance with the new TLMC tasks must be carried
out in accordance with the phase-in schedule detailed in the
Canadair Challenger TRs 5-236 and TR 5-2-40, as applicable, after
the effective date of this AD. Thereafter, except as provided by
paragraph (g)(1) of this AD, no alternative TLMC task intervals may
be used.
    (3) When information in a TR specified in paragraph (f)(1) has
been included in the general revisions of the applicable
Airworthiness Limitations section, the TR may be removed from that
Airworthiness Limitations section of the Instruction for Continued
Airworthiness.

FAA AD Differences

    Note 2:  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, New
York Aircraft Certification Office, ANE-170, 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: Program Manager,
Continuing Operational Safety, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards District Office. The AMOC
approval letter must specifically reference this AD.
    (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, under the provisions of the Paperwork Reduction Act, 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 Canadian Airworthiness Directive CF-2008-32R2,
dated November 17, 2008, and the service information identified in
Table 2 of this AD for related information.

                 Table 2--Referenced Service Information
------------------------------------------------------------------------
                                                    To the Airworthiness
 Canadair Challenger Temporary       Dated--        Limitations section
          Revision--                                        of--
------------------------------------------------------------------------
5-236.........................  July 25, 2008....  Section 5-10-30 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    Time Limits/
                                                    Maintenance Checks,
                                                    PSP 601-5.

5-236.........................  March 22, 2007...  Section 5-10-30 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    Time Limits/
                                                    Maintenance Checks,
                                                    PSP 601A-5.
5-2-40........................  July 28, 2008....  Section 5-10-40 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    CL-604 Time Limits/
                                                    Maintenance Checks.
------------------------------------------------------------------------

Material Incorporated by Reference

    (i) You must use the applicable service information contained in
Table 3 of this AD to do the actions required by this AD, unless the
AD specifies otherwise.

               Table 3--Material Incorporated by Reference
------------------------------------------------------------------------
                                                    To the Airworthiness
 Canadair Challenger Temporary       Dated--        Limitations section
          Revision--                                        of--
------------------------------------------------------------------------
5-236.........................  July 25, 2008....  Section 5-10-30 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    Time Limits/
                                                    Maintenance Checks,
                                                    PSP 601-5.
5-236.........................  March 22, 2007...  Section 5-10-30 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    Time Limits/
                                                    Maintenance Checks,
                                                    PSP 601A-5.
5-2-40........................  July 28, 2008....  Section 5-10-40 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    CL-604 Time Limits/
                                                    Maintenance Checks.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
    (2) 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<PHONE_NUMBER>; fax 514-855-
7401; e-mail<EMAIL_ADDRESS>Internet http://
www.bombardier.com.
    (3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call<PHONE_NUMBER> or<PHONE_NUMBER>.
    (4) You may also review copies of the 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<PHONE_NUMBER>, or go to: http://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Renton, Washington, on November 19, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-28554 Filed 12-3-09; 8:45 am]

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