[Federal Register Volume 72, Number 26 (Thursday, February 8, 2007)]
[Rules and Regulations]
[Pages 5925-5929]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-1876]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25192; Directorate Identifier 2006-NM-004-AD; 
Amendment 39-14930; AD 2007-03-19]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes. That AD currently requires repetitive 
detailed and eddy current inspections of the main fittings of the main 
landing gears (MLG) to detect discrepancies, and related investigative/
corrective actions if necessary. The AD also currently requires 
servicing the shock strut of the MLGs; inspecting the shock strut of 
the MLGs for nitrogen pressure, visible chrome dimension, and oil 
leakage; and servicing any discrepant strut. This new AD requires 
installing a new, improved MLG main fitting, which terminates the 
repetitive inspection and servicing requirements of the existing AD. 
This AD results from stress analyses that showed certain main fittings 
of the MLGs are susceptible to premature cracking, starting in the 
radius of the upper lug. We are issuing this AD to detect and correct 
premature cracking of the main fittings of the MLGs, which could result 
in failure of the fittings and consequent collapse of the MLGs during 
landing.

DATES: This AD becomes effective March 15, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 15, 
2007.
    On August 13, 2004 (69 FR 41421, July 9, 2004), the Director of the 
Federal Register approved the incorporation by reference of Bombardier 
Alert Service Bulletin A601R-32-088, including Appendices A, B, and C, 
dated February 20, 2003.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, 
Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service 
information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Richard Beckwith, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New 
York 11590; telephone (516) 228-7302; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: 

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2004-14-16, amendment 
39-13725 (69 FR 41421, July 9, 2004). The existing AD applies to 
certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) 
airplanes. That NPRM was published in the Federal Register on June 27, 
2006 (71 FR 36495). That NPRM proposed to continue to require 
installing a new, improved main landing gear (MLG) main fitting, which 
would terminate the repetitive inspection and servicing requirements of 
the existing AD.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Change Compliance Time to Cite Dates

    Bombardier notes that the proposed compliance time for the 
corrective action is quite different from that of the parallel Canadian 
airworthiness directive. The parallel Canadian airworthiness directive 
specifies a fixed compliance date of December 31, 2008, for MLG main 
fittings that have part numbers 601R85001-81 and -82. Bombardier 
calculates that operators of U.S.-registered airplanes would have 12 
months beyond that date to accomplish the proposed actions. Bombardier 
requests that we harmonize the compliance time in the NPRM with the 
compliance date in Canadian airworthiness directive CF-2003-09R1, dated 
September 21, 2005, which is the parallel Canadian airworthiness 
directive referred to in the NPRM. Bombardier points out that it worked 
with Messier-Dowty and Transport Canada Civil Aviation (TCCA) to 
consider carefully that date as it relates to fleet safety, MLG 
supplier capability/logistics, and the capacity of operators and 
overhaul facilities. Bombardier considers that the different compliance 
time will create confusion among U.S. operators and cause an 
unnecessary burden for all parties involved.
    We partially agree. We agree that we should harmonize the 
compliance times in the NPRM with the compliance dates in the Canadian 
airworthiness directive. To that end, we developed the compliance time 
of ``within 39 months after the effective date of this AD.'' This 39-
month compliance time will give U.S. operators until May 2009 to comply 
with the AD. This amount of elapsed time is equivalent to that allowed 
by the Canadian airworthiness directive's compliance date of December 
31, 2008. However, we find that this longer compliance time will not 
adversely affect the level of safety of the affected U.S.-registered 
airplanes. This issue has been coordinated with TCCA. No change has 
been made to the AD in this regard.

Request To Incorporate by Reference (IBR) the Service Information

    The Modification and Replacement Parts Association (MARPA) requests 
that we either publish the relevant service information with the AD in 
the Docket Management System (DMS), or IBR it with the NPRM. MARPA 
states that the purpose of the IBR system is brevity, to keep from 
expanding the Federal Register needlessly by publishing documents 
already in the hands of the affected individuals. Traditionally, 
``affected individuals'' have been aircraft owners and operators who 
are generally provided service information by the manufacturer. MARPA 
states that the group of affected individuals has expanded because

[[Page 5926]]

aircraft maintenance is now performed by specialty shops instead of 
aircraft owners and operators. This new class includes maintenance and 
repair organizations, component servicing and repair shops, parts 
purveyors and distributors, and organizations that manufacture or 
service alternatively certified parts under 14 CFR 21.303 (parts 
manufacturer approval (PMA)), which do not possess the proprietary 
service information referenced in the NPRM. MARPA states that the 
concept of brevity is now nearly archaic as documents exist more 
frequently in electronic format than on paper.
    MARPA also comments on our practice of IBR and referencing 
propriety service information. MARPA asserts that if we IBR proprietary 
service information with a public document, such as an AD, then that 
service information loses its protected status and becomes a public 
document. MARPA further states that ``If a service document is used as 
a mandatory element of compliance it should not simply be referenced, 
but should be incorporated into the regulatory document. Public laws by 
definition must be public, which means they cannot rely upon private 
writings.''
    We do not agree that documents should be incorporated by reference 
during the NPRM phase of rulemaking. The Office of the Federal Register 
(OFR) requires that documents that are necessary to accomplish the 
requirements of the AD be incorporated by reference during the final 
rule phase of rulemaking. This final rule incorporates by reference the 
document necessary for the accomplishment of the requirements mandated 
by this AD. Further, we point out that while documents that are 
incorporated by reference do become public information, they do not 
lose their copyright protection. For that reason, we advise the public 
to contact the manufacturer to obtain copies of the referenced service 
information.
    In regard to the commenter's request that service documents be made 
available to the public by publication in the Federal Register, we 
agree that incorporation by reference was authorized to reduce the 
volume of material published in the Federal Register and the Code of 
Federal Regulations. However, as specified in the Federal Register 
Document Drafting Handbook, the Director of the OFR decides when an 
agency may incorporate material by reference. As the commenter is 
aware, the OFR files documents for public inspection on the workday 
before the date of publication of the rule at its office in Washington, 
DC. As stated in the Federal Register Document Drafting Handbook, when 
documents are filed for public inspection, anyone may inspect or copy 
file documents during the OFR's hours of business. Further questions 
regarding publication of documents in the Federal Register or 
incorporation by reference should be directed to the OFR.
    In regard to the commenter's request to post service bulletins on 
the Department of Transportation's DMS, we are currently in the process 
of reviewing issues surrounding the posting of service bulletins on the 
DMS as part of an AD docket. Once we have thoroughly examined all 
aspects of this issue and have made a final determination, we will 
consider whether our current practice needs to be revised. No change to 
the final rule is necessary in response to this comment.

Request To Reference PMA Parts

    MARPA also states that type certificate holders in their service 
documents universally ignore the possible existence of PMA parts. 
According to MARPA, this is especially true with foreign manufacturers 
where the concept may not exist or be implemented in the country of 
origin. MARPA states that frequently the service bulletin upon which an 
AD is based will require the removal of a certain part number and the 
installation of a different part number as a corrective action. MARPA 
states that this practice runs afoul of 14 CFR 21.303, which permits 
the development, certification, and installation of alternatively 
certified parts (PMA). MARPA states that mandating the installation of 
a certain part number to the exclusion of all other parts is not a 
favored general practice. According to MARPA, such action has the dual 
effect of preventing, in some cases, the installation of perfectly good 
parts, while at the same time prohibiting the development of new parts 
permitted under 14 CFR 21.303. MARPA states that such a prohibition 
runs the risk of taking the AD out of the realm of safety and into the 
world of economics since prohibiting the development, sale, and use of 
a perfectly airworthy part has nothing to do with safety.
    We infer that the commenter would like the AD to permit 
installation of any equivalent PMA parts so that it is not necessary 
for an operator to request approval of an alternative method of 
compliance (AMOC) in order to install an ``equivalent'' PMA part. 
Whether an alternative part is ``equivalent'' in adequately resolving 
the unsafe condition can only be determined on a case-by-case basis 
based on a complete understanding of the unsafe condition. We are not 
currently aware of any such parts. Our policy is that, in order for 
operators to replace a part with one that is not specified in the AD, 
they must request an AMOC. This is necessary so that we can make a 
specific determination that an alternative part is or is not 
susceptible to the same unsafe condition.
    In response to the commenter's statement regarding a practice that 
``runs afoul of 14 CFR 21.303,'' under which the FAA issues PMAs, this 
statement appears to reflect a misunderstanding of the relationship 
between ADs and the certification procedural regulations of part 21 of 
the Federal Aviation Regulations (14 CFR part 21). Those regulations, 
including section 21.303 of the Federal Aviation Regulations (14 CFR 
21.203), are intended to ensure that aeronautical products comply with 
the applicable airworthiness standards. But ADs are issued when, 
notwithstanding those procedures, we become aware of unsafe conditions 
in these products or parts. Therefore, an AD takes precedence over 
design approvals when we identify an unsafe condition, and mandating 
installation of a certain part number in an AD is not at variance with 
section Sec.  21.303.
    The AD provides a means of compliance for operators to ensure that 
the identified unsafe condition is addressed appropriately. For an 
unsafe condition attributable to a part, the AD normally identifies the 
replacement parts necessary to obtain that compliance. As stated in 
section 39.7 of the Federal Aviation Regulations (14 CFR 39.7), 
``Anyone who operates a product that does not meet the requirements of 
an applicable airworthiness directive is in violation of this 
section.'' Unless an operator obtains approval for an AMOC, replacing a 
part with one not specified by the AD would make the operator subject 
to an enforcement action and result in a civil penalty. We have not 
changed the final rule in this regard.

Request for Compliance With FAA Order 8040.2/Agreement on Parts 
Replacement

    MARPA points out that this AD, as written, does not comply with 
proposed Order 8040.2 (AD Process for Mandatory Continuing 
Airworthiness Information (MCAI)), which states in the PMA section: 
``MCAI that require replacement or installation of certain parts could 
have replacement parts approved under 14 CFR 21.303 based on a finding 
of identicality. We have determined that any parts approved under this 
regulation and installed should be

[[Page 5927]]

subject to the actions of our AD and included in the applicability of 
our AD.'' MARPA points out that the Small Airplane Directorate has 
developed a blanket statement that resolves this issue. The statement 
includes words similar to those in the proposed Order 8040.2.
    We recognize the need for standardization on this issue and 
currently are in the process of reviewing it at the national level. The 
Transport Airplane Directorate considers that to delay this particular 
AD action would be inappropriate, since we have determined that an 
unsafe condition exists and that replacement of certain parts must be 
accomplished to ensure continued safety. Therefore, no change has been 
made to the final rule in this regard.
    The NPRM did not address PMA parts, as provided in draft FAA Order 
8040.2, because the Order was only a draft that was out for comment at 
the time. After issuance of the NPRM, the Order was revised and issued 
as FAA Order 8040.5 with an effective date of September 29, 2006. FAA 
Order 8040.5 does not address PMA parts in ADs. We acknowledge the need 
to ensure that unsafe PMA parts are identified and addressed in MCAI-
related ADs. We are currently examining all aspects of this issue, 
including input from industry. Once we have made a final determination, 
we will consider how our policy regarding PMA parts in ADs needs to be 
revised. We consider that to delay this AD action would be 
inappropriate, since we have determined that an unsafe condition exists 
and that replacement of certain parts must be accomplished to ensure 
continued safety. Therefore, no change has been made to the final rule 
in this regard.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD. There are approximately 278 airplanes of U.S. 
registry that are affected by this AD. The average labor rate is $80 
per work hour.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
              Action                 Work hours          Parts                     Cost per airplane                            Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections (required by AD 2004-             4  None.................  $320, per inspection cycle.............  $88,960, per inspection cycle.
 14-16).
Replacement (new action)..........           46  $105,732.............  $109,412...............................  $30,416,536.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 have 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 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. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-13725 (69 FR 41421, July 9, 2004) and by adding 
the following new airworthiness directive (AD):

2007-03-19 Bombardier, Inc. (Formerly Canadair): Amendment 39-14930. 
Docket No. FAA-2006-25192; Directorate Identifier 2006-NM-004-AD.

Effective Date

    (a) This AD becomes effective March 15, 2007.

Affected ADs

    (b) This AD supersedes AD 2004-14-16.

Applicability

    (c) This AD applies to Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes, serial numbers 7003 and subsequent; 
certificated in any category; equipped with main landing gear (MLG) 
main fittings, part numbers (P/N) 601R85001-81 and 601R85001-82 
(Messier Dowty Incorporated P/Ns 17064-105 and 17064-106).

Unsafe Condition

    (d) This AD results from stress analyses that showed certain 
main fittings of the MLGs are susceptible to premature cracking, 
starting in the radius of the upper lug. We are issuing this AD to 
detect and correct premature cracking of the main fittings of the 
MLGs, which could result in failure of the fittings and consequent 
collapse of the MLGs during landing.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

[[Page 5928]]

Restatement of the Requirements of AD 2004-14-16

Detailed Inspection of Main Fittings of the MLGs

    (f) Before the accumulation of 2,500 total flight cycles on the 
MLGs, or within 250 flight cycles after August 13, 2004 (the 
effective date of AD 2004-14-16), whichever occurs later: Do a 
detailed inspection on the main fittings of the MLGs to detect 
discrepancies (i.e., linear paint cracks or lack of paint (paint 
peeling), any other paint damage, adhesion, paint bulging, or 
corrosion), in accordance with Part A of the Accomplishment 
Instructions of Bombardier Alert Service Bulletin (ASB) A601R-32-
088, dated February 20, 2003; or Bombardier ASB 601R-32-088, 
Revision A, dated June 16, 2005, including Appendices, A, B, and C, 
dated February 20, 2003. Repeat the inspection thereafter at 
intervals not to exceed 100 flight cycles until paragraph (k) of 
this AD is accomplished.

    Note 1: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

Related Investigative/Corrective Actions

    (g) If any discrepancy is detected during any inspection 
required by paragraph (f) of this AD, before further flight: Do the 
related investigative/corrective actions in accordance with Part B 
or F of the Accomplishment Instructions of Bombardier ASB A601R-32-
088, including Appendices A and C, dated February 20, 2003; or 
Bombardier ASB A601R-32-088, Revision A, dated June 16, 2005, 
including Appendices A, B, and C, dated February 20, 2003. If an 
eddy current inspection (a related investigative action specified in 
Part B) is used to confirm the detailed inspection findings, the 
next eddy current required by paragraph (h) of this AD must be 
conducted within 500 flight cycles after the eddy current inspection 
specified in this paragraph, and thereafter at intervals not to 
exceed 500 flight cycles until paragraph (k) of this AD is 
accomplished.

Eddy Current Inspection of Main Fittings of the MLGs

    (h) At the time specified in paragraph (f) of this AD, do an 
eddy current inspection on the main fittings of the MLGs to detect 
cracks, in accordance with Part B of the Accomplishment Instructions 
of Bombardier ASB A601R-32-088, including Appendix A, dated February 
20, 2003; or Bombardier ASB A601R-32-088, Revision A, dated June 16, 
2005, including Appendixes, A, B, and C, dated February 20, 2003. 
Repeat the eddy current inspection thereafter at intervals not to 
exceed 500 flight cycles, until paragraph (k) of this AD is 
accomplished. If any crack is found, before further flight, replace 
the affected main fittings of the MLGs with new or serviceable 
fittings in accordance with paragraph E.(5) of Part B of the 
Accomplishment Instructions of the service bulletin or in accordance 
with paragraph (k) of this AD. If any crack is found after the 
effective date of this AD, do the replacement in accordance with 
paragraph (k) of this AD.

Servicing of Shock Struts

    (i) Before the accumulation of 2,500 total flight cycles on the 
MLGs, or within 500 flight cycles after August 13, 2004, whichever 
occurs later, service the shock strut of the MLGs in accordance with 
Part C or D, as applicable, of the Accomplishment Instructions of 
Bombardier ASB A601R-32-088, including Appendix B, dated February 
20, 2003; or Bombardier ASB A601R-32-088, Revision A, dated June 16, 
2005, including Appendices A, B, and C, dated February 20, 2003.

Shock Strut Inspection

    (j) Within 500 flight cycles after completing the servicing 
required by paragraph (i) of this AD, inspect the shock strut of the 
MLGs for nitrogen pressure, visible chrome dimension, and oil 
leakage, in accordance with Part E of the Accomplishment 
Instructions of Bombardier ASB A601R-32-088, including Appendix B, 
dated February 20, 2003; or Bombardier ASB A601R-32-088, Revision A, 
dated June 16, 2005, including Appendices A, B, and C, dated 
February 20, 2003. Repeat the inspection thereafter at intervals not 
to exceed 500 flight cycles, until paragraph (k) of this AD is 
accomplished. If the nitrogen pressure and visible chrome dimensions 
are found outside the limits (the service bulletin refers to the 
airplane maintenance manual as the source of defined limits) and/or 
oil leakage is found, before further flight, service the affected 
shock strut of the MLGs in accordance with Part C or D, as 
applicable, of the Accomplishment Instructions of the service 
bulletin.

New Requirements of This AD

Replacement

    (k) Within 39 months after the effective date of this AD: 
Replace the main fittings of the MLGs, P/Ns 601R85001-81 and 
601R85001-82 (Messier Dowty Incorporated P/Ns 17064-105 and 17064-
106), with new main fittings, P/Ns 601R85001-83 and 601R85001-84 
(Messier Dowty Incorporated P/Ns 17064-107 and 17064-108), in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 601R-32-093, Revision B, dated July 14, 2005. Doing 
this replacement terminates all requirements of paragraphs (f), (g), 
(h), (i), and (j) of this AD.

    Note 2: Bombardier Service Bulletin 601R-32-093, Revision B, 
refers to Messier-Dowty Service Bulletin M-DT SB17002-32-25, 
Revision 1, dated October 17, 2003, as an additional source of 
service information for replacing the main fittings.

Parts Installation

    (l) As of the effective date of this AD, no person may install a 
main fitting of the MLG, P/Ns 601R85001-81 and 601R85001-82 (Messier 
Dowty Incorporated P/Ns 17064-105 and 17064-106), on any airplane.

No Reporting Required

    (m) Although the Accomplishment Instructions of Bombardier ASB 
A601R-32-088, dated February 20, 2003; and ASB 601R-32-088, Revision 
A, dated June 16, 2005; specify to report certain information to the 
manufacturer, this AD does not include that action.

Actions Accomplished in Accordance with Previous Revisions of 
Service Bulletin

    (n) Actions accomplished before the effective date of this AD in 
accordance with the service bulletins listed in Table 1 of this AD 
are acceptable for compliance with the actions in paragraph (k) of 
this AD.

                                Table 1.--Previous Revisions of Service Bulletin
----------------------------------------------------------------------------------------------------------------
       Bombardier Service Bulletin                Revision level                           Date
----------------------------------------------------------------------------------------------------------------
601R-32-093..............................  Original....................  October 17, 2003.
601R-32-093..............................  A...........................  September 21, 2004.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, New York Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (p) Canadian airworthiness directive CF-2003-09R1, dated 
September 21, 2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (q) You must use the applicable service information in Table 2 
of this AD to perform the actions that are required by this AD, 
unless the AD specifies otherwise.

[[Page 5929]]



                                Table 2.--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
             Service Bulletin                     Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Bombardier Alert Service Bulletin A601R-   Original....................  February 20, 2003.
 32-088, including Appendices A, B, and C.
Bombardier Alert Service Bulletin A601R-   A...........................  June 16, 2005.
 32-088, including Appendices A, B, and
 C, dated February 20, 2003.
Bombardier Service Bulletin 601R-32-093..  B...........................  July 14, 2005.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the documents in Table 3 of this AD, 
in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

                                Table 3.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
             Service Bulletin                     Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Bombardier Alert Service Bulletin A601R-   A...........................  June 16, 2005.
 32-088, including Appendices A, B, and
 C, dated February 20, 2003.
Bombardier Service Bulletin 601R-32-093..  B...........................  July 14, 2005.
----------------------------------------------------------------------------------------------------------------

    (2) On August 13, 2004 (69 FR 41421, July 9, 2004), the Director 
of the Federal Register approved the incorporation by reference of 
Bombardier Alert Service Bulletin A601R-32-088, including Appendices 
A, B, and C, dated February 20, 2003.
    (3) Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. 
Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, 
for a copy of this service information. You may review copies at the 
Docket Management Facility, U.S. Department of Transportation, 400 
Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; 
on the Internet at http://dms.dot.gov; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at the NARA, call (202) 741-6030, or 
go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on January 29, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-1876 Filed 2-7-07; 8:45 am]
BILLING CODE 4910-13-P