AD 2003-08-12

[Federal Register Volume 68, Number 78 (Wednesday, April 23, 2003)]
[Rules and Regulations]
[Pages 19940-19944]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-9690]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-317-AD; Amendment 39-13125; AD 2003-08-12]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600), 
CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-
604) Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL-600-
2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) 
series airplanes. This action requires a detailed inspection to detect 
cracks of the vane brackets of the inboard flap actuator beam, and 
follow-on repetitive detailed inspections or corrective actions, as 
applicable. This action also provides for two optional terminating 
actions for the detailed inspection(s). This action is necessary to 
detect and correct gaps between the flap vane bracket and the adjacent 
lower skin and between the flap vane bracket and vane actuator beam of 
the wing flap systems, and premature cracking of the flap vane 
brackets, which could result in failure of the flap vane bracket(s) 
when the flaps are extended and the flap vane is aerodynamically 
loaded. Loss or warping of the flap vane in flight could decrease the 
lift on one side of the airplane, which could lead to reduced 
controllability of the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Effective May 8, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 8, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before May 23, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-317-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
<a href="/cdn-cgi/l/email-protection#9ca5b1fdf2f1b1f5fdeefff3f1f1f9f2e8dcfafdfdb2fbf3ea"><span class="__cf_email__" data-cfemail="70495d111e1d5d191102131f1d1d151e04301611115e171f06">[email&#160;protected]</span></a>. Comments sent via the Internet must contain 
``Docket No. 2002-NM-317-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via fax or the Internet as 
attached electronic files must be formatted in Microsoft Word 97 for 
Windows or ASCII text.
    The service information referenced in this AD may be obtained from 
Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station 
Centre-ville, Montreal, Quebec H3C 3G9, Canada. This information may be 
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, 
SW., Renton, Washington; or at the FAA, New York Aircraft Certification 
Office, 10 Fifth Street, Third Floor, Valley Stream, New York; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Serge Napoleon, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New 
York; telephone (516) 256-7512; fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: Transport Canada Civil Aviation (TCCA), 
which is the airworthiness authority for Canada, notified the FAA that 
an unsafe condition may exist on certain Bombardier Model CL-600-1A11 
(CL-

[[Page 19941]]

600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and 
CL-604) series airplanes. TCCA advises that several occurrences of gaps 
were found between the flap vane bracket and the adjacent lower skin 
and between the flap vane bracket and vane actuator beam. (There are 
two vane brackets on each of the three vane actuator beams of both the 
left and right wings.) During a detailed investigation, it was found 
that an incorrect production process for the installation of the vane 
bracket resulted in an uneven contact with the adjacent skin and with 
the vane actuator beam. Such gaps can cause premature cracking of the 
flap vane brackets of the vane actuator beams, which could lead to the 
failure of the flap vane bracket(s) when the flaps are extended and the 
flap vane is aerodynamically loaded. Loss or warping of the flap vane 
in flight could decrease the lift on one side of the airplane, which 
could lead to reduced controllability of the airplane.

Canadian Airworthiness Directives

    TCCA classified the alert service bulletins specified in Table 2 of 
this AD and the Time Limits/Maintenance Checks (TLMC) (all described 
below) as mandatory and issued Canadian airworthiness directives CF-
2002-36 and CF-2002-37, effective August 30, 2002, in order to assure 
the continued airworthiness of these airplanes in Canada.

Explanation of Relevant Service Information

    Bombardier has issued the alert service bulletins specified in 
Table 2 of this AD, which describe procedures for a detailed inspection 
to detect cracks of the vane brackets of the inboard flap actuator 
beam, and follow-on repetitive detailed inspections or corrective 
actions (i.e., Part B or Part C), as applicable.
    Part B corrective actions include:
    [sbull] Doing a detailed inspection to detect gaps at flap stations 
60.0, 98.5, and 137.0 between the flap vane bracket(s) and adjacent 
lower skin and between the flap vane bracket and vane actuator beam, 
and repair if necessary;
    [sbull] Measuring the minimum edge distance (MED) for the fastener 
holes in all flap vane brackets and actuator beams, and replacing any 
out-of-tolerance bracket and/or actuator beam with a certain new 
bracket and/or actuator beam; and
    [sbull] Doing a nondestructive test (NDT) inspection on all vane 
brackets for cracks, and corrective actions (e.g., remove gaps, ensure 
that the MED requirements for the replacement brackets meet the 
allowable values, and replace any cracked vane bracket with a new 
bracket that meets the MED requirements).
    Part C corrective actions include:
    [sbull] Replacing all 12 vane brackets with new brackets that meet 
the MED requirements (including removal of any gap between the flap 
vane brackets and the adjacent lower skin and between the flap vane 
bracket and actuator beams); and
    [sbull] Measuring the MED for the fastener holes in all replacement 
flap vane brackets and actuator beams (including a detailed inspection 
for gaps); and replacing any out-of-tolerance bracket and/or actuator 
beam with a certain new bracket and/or actuator beam that meets the MED 
requirements, and removing any gap, if necessary.
    Accomplishment of Part B or Part C corrective actions eliminates 
the need for the detailed inspection(s) to detect cracks of the vane 
brackets of the inboard flap actuator beams, described previously.

Explanation of Relevant Time Limits/Maintenance Checks

    After doing either Part B or Part C corrective actions, Canadian 
airworthiness directives CF-2002-36 and CF-2002-37 require compliance 
with the applicable TLMC threshold and repeat interval of the Airplane 
Maintenance Manual (AMM) for the flap vane brackets.

FAA's Conclusions

    These airplane models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, TCCA has kept the FAA informed of 
the situation described above. The FAA has examined the findings of 
TCCA, reviewed all available information, and determined that AD action 
is necessary for products of this type design that are certificated for 
operation in the United States.

Explanation of Requirements of Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, this AD is being issued to detect and correct 
gaps between the flap vane bracket and the adjacent lower skin and 
between the flap vane bracket and vane actuator beam of the wing flap 
systems, which can cause premature cracking in this area, and 
consequent failure of the flap vane bracket(s) when the flaps are 
extended and the flap vane is aerodynamically loaded. Loss or warping 
of the flap vane in flight could decrease the lift on one side of the 
airplane, which could lead to reduced controllability of the airplane. 
This AD requires a detailed inspection to detect cracks of the vane 
brackets of the inboard flap actuator beam, and follow-on repetitive 
detailed inspections or corrective actions, as applicable. This AD also 
provides for two optional terminating actions for the detailed 
inspection(s). The actions, if accomplished, are required to be 
accomplished in accordance with the applicable alert service bulletin 
described previously, except as discussed below.

Differences Between the Alert Service Bulletins and This AD

    Although the alert service bulletins describe procedures for 
identifying and returning all cracked vane brackets to Bombardier, 
neither the Canadian airworthiness directives nor this AD require such 
actions.
    In addition, although the alert service bulletins specify that the 
manufacturer may be contacted for disposition of certain repair 
conditions, this AD requires the repair of those conditions to be 
accomplished per a method approved by either the FAA, or TCCA (or its 
delegated agent). In light of the type of repair that is required to 
address the identified unsafe condition, and in consonance with 
existing bilateral airworthiness agreements, the FAA has determined 
that, for this AD, a repair approved by either the FAA or TCCA will be 
acceptable for compliance with this AD.

Clarification Between the AD and Canadian Airworthiness Directives/
Referenced Alert Service Bulletins

    Operators should note that, although the parallel Canadian 
airworthiness directives require compliance with the applicable TLMC 
threshold and repeat interval of the AMM for the flap vane brackets, 
this AD first requires a revision of the Airworthiness Limitation 
Section (ALS) of the Instructions for Continued Airworthiness to 
incorporate those new threshold and repeat inspection intervals. 
Revising the ALS, rather than requiring individual repetitive 
inspections, is advantageous for operators because it allows them to 
record AD compliance status only at the time that they make the 
revision, rather than after every inspection. It also has the advantage 
of keeping all airworthiness limitations, whether imposed by original 
certification or by

[[Page 19942]]

AD, in one place with the operator's maintenance program, thereby 
reducing the risk of non-compliance because of oversight or confusion.

Interim Action

    This is considered to be interim action. The FAA is currently 
considering requiring Part B or Part C corrective actions (described 
previously), which will constitute terminating action for the detailed 
inspection(s) to detect cracks of the vane brackets of the inboard flap 
actuator beam required by this AD action. However, the planned 
compliance time for the Part B or Part C corrective actions is 
sufficiently long so that notice and opportunity for prior public 
comment will be practicable.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the alert 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the AD is 
being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-317-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-08-12 Bombardier, Inc. (Formerly Canadair): Amendment 39-13125. 
Docket 2002-NM-317-AD.

    Applicability: This AD applies to the airplanes listed in Table 
1 of this AD, certificated in any category. Table 1 is as follows:

                         Table 1.--Applicability
------------------------------------------------------------------------
                   Model                             Serial Nos.
------------------------------------------------------------------------
CL-600-1A11 (CL-600) series airplanes.....  1004 through 1085 inclusive.
CL-600-2A12 (CL-601) series airplanes.....  3001 through 3066 inclusive.
CL-600-2B16 (CL-601-3A and CL-601-3R)       5001 through 5194 inclusive.
 series airplanes.
CL-600-2B16 (CL-604) series airplanes.....  5301 through 5499 inclusive.
------------------------------------------------------------------------


    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (i) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct gaps between the flap vane bracket and the 
adjacent lower skin and between the flap vane bracket and vane 
actuator beam of the wing flap systems, and premature cracking of 
the flap vane brackets, which could result in failure of the flap 
vane bracket(s) when the flaps are extended and the flap vane is 
aerodynamically loaded, and consequent reduced controllability of 
the airplane, accomplish the following:

    Note 2:
    Where there are differences between the applicable Bombardier 
alert service bulletin specified in Table 2 of this AD and this AD, 
the AD prevails.

Inspection

    (a) Do a detailed inspection to detect cracks of the vane 
brackets of the inboard flap actuator beam, per Part A of the 
Accomplishment Instructions of the applicable Bombardier alert 
service bulletin specified in Table 2 of this AD; at the

[[Page 19943]]

applicable time indicated in Table 3 of this AD. Table 2 is as 
follows:

                    Table 2.--Alert Service Bulletins
------------------------------------------------------------------------
                                Bombardier alert
         For model--            service bulletin          Excluding
------------------------------------------------------------------------
CL-600-1A11 (CL-600) series   A600-0699, Revision   Service Bulletin
 airplanes.                    01, dated July 8,     Incorporation
                               2002.                 Sheet, Flap Vane
                                                     Bracket Inspection
                                                     Program page, and
                                                     Minimum Edge
                                                     Distance Inspection
                                                     pages.
-----------------------------
CL-600-2A12 (CL-601) series   A601-0532, Revision   Service Bulletin
 airplanes, and CL-600-2B16    01, dated July 8,     Incorporation
 (CL-601-3A and CL-601-3R)     2002.                 Sheet, Flap Vane
 series airplanes.                                   Bracket Inspection
                                                     Program page, and
                                                     Minimum Edge
                                                     Distance Inspection
                                                     pages.
-----------------------------
CL-600-2B16 (CL-604) series   A604-27-007,          Service Bulletin
 airplanes.                    Revision 01, dated    Incorporation
                               July 8, 2002.         Sheet, Flap Vane
                                                     Bracket Inspection
                                                     Program page, and
                                                     Minimum Edge
                                                     Distance Inspection
                                                     pages.
------------------------------------------------------------------------

    Table 3 is as follows:

                        Table 3.--Compliance Time
------------------------------------------------------------------------
   For airplanes that have accumulated--           Compliance time
------------------------------------------------------------------------
1,200 total landings or less as of the      Before the accumulation of
 effective date of this AD.                  1,300 total landings.
-------------------------------------------
More than 1,200 total landings, but less    Within 100 landings after
 than 3,000 total landings as of the         the effective date of this
 effective date of this Ad.                  AD.
-------------------------------------------
3,000 total landings or more as of the      Within 50 landings after the
 effective date of this AD.                  effective date of this AD.
------------------------------------------------------------------------


    Note 3:
    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.''

No Crack Findings: Repetitive Inspections

    (b) If no crack is detected during the detailed inspection 
required by paragraph (a) of this AD, repeat that inspection 
thereafter at intervals not to exceed 100 landings.

Crack Findings: Corrective Actions

    (c) If any crack is detected during the detailed inspection 
required by paragraph (a) of this AD, before further flight, do the 
actions specified in paragraph (d) or (e) of this AD.

Optional Terminating Actions

    (d) Do the actions specified in paragraphs (d)(1), (d)(2), and 
(d)(3) of this AD per Part B of the Accomplishment Instructions of 
the applicable alert service bulletin identified in Table 2 of this 
AD, unless otherwise specified in this AD. Accomplishment of these 
actions constitutes compliance with the requirements of paragraphs 
(a), (b), and (c) of this AD.
    (1) Do a detailed inspection to detect gaps at flap stations 
60.0, 98.5, and 137.0 between the vane bracket(s) and adjacent lower 
skin and vane actuator beam. If any gap is in excess of the limits 
specified in the applicable alert service bulletin, before further 
flight, repair per a method approved by either the Manager, New York 
Aircraft Certification Office (ACO), FAA; or Transport Canada Civil 
Aviation (TCCA) (or its delegated agent).
    (2) Measure the minimum edge distance (MED) for the fastener 
holes in all flap vane brackets and actuator beams. If the MED 
requirements for any bracket or actuator beam do not meet the 
allowable values specified in Figure 2 of the applicable alert 
service bulletin, before further flight, replace the out-of-
tolerance bracket and/or actuator beam with a new bracket and/or 
actuator beam that meet the MED requirements specified in Figure 2 
of the applicable alert service bulletin.
    (3) Do a nondestructive test (NDT) inspection on all vane 
brackets for cracks. If any crack is found, before further flight, 
accomplish the corrective actions (e.g., remove gaps, ensure that 
the MED requirements for the replacement brackets meet the allowable 
values specified in Figure 2 of the applicable alert service 
bulletin, and replace any cracked vane bracket with a new bracket 
that meets the MED requirements specified in Figure 2 of the 
applicable alert service bulletin). Although the applicable alert 
service bulletin describes procedures for identifying and returning 
all cracked vane brackets to Bombardier, this AD does not require 
such actions.
    (e) In lieu of the actions specified in paragraph (d) of this 
AD, do the actions specified in paragraphs (e)(1) and (e)(2) of this 
AD per Part C of the Accomplishment Instructions of the applicable 
alert service bulletin identified in Table 2 of this AD. 
Accomplishment of these actions constitutes compliance with the 
requirements of paragraphs (a), (b), and (c) of this AD.
    (1) Replace all 12 vane brackets with new brackets that meet the 
MED requirements specified in Figure 2 of the applicable alert 
service bulletin (including removal of any gap between the vane 
brackets and the adjacent lower skin and actuator beams).
    (2) Measure the MED for the fastener holes in all replacement 
flap vane brackets and actuator beams (including a detailed 
inspection for gaps).
    (i) If the MED requirements for any bracket or actuator beam do 
not meet the allowable values specified in Figure 2 of the 
applicable alert service bulletin, before further flight, replace 
the out-of-tolerance bracket and/or actuator beam with a new bracket 
and/or actuator beam that meets the MED requirements specified in 
Figure 2 of the applicable alert service bulletin.
    (ii) If any gap is detected, before further flight, repair the 
gap.

Other Means of Acceptable Compliance With Paragraph (e) of This AD

    (f) Accomplishment of the inspections and modifications per Part 
B or Part C of the applicable alert service bulletin listed in Table 
4 of this AD; and the MED dimension checks for the flap brackets and 
the actuator beams as specified in drawing K600-14251, including any 
required rework; is considered acceptable for compliance with the 
requirements of paragraph (e) of this AD. Table 4 of this AD is as 
follows:

        Table 4.--Acceptable Basic Issue Alert Service Bulletins
------------------------------------------------------------------------
                                              Bombardier alert service
                For model--                          bulletin--
------------------------------------------------------------------------
CL-600-1A11 (CL-600) series airplanes.....  A600-0699, Basic Issue,
                                             dated November 29, 2001.
-------------------------------------------

[[Page 19944]]

 
CL-600-2A12 (CL-601) series airplanes, and  A601-0532, Basic Issue,
 CL-600-2B16 (CL-601-3A and CL-601-3R)       dated November 29, 2001.
 series airplanes.
-------------------------------------------
CL-600-2B16 (CL-604) series airplanes.....  A604-27-007, Basic Issue,
                                             dated November 29, 2001.
------------------------------------------------------------------------

Time Limits/Maintenance Checks

    (g) After doing the actions specified in paragraph (d) or (e) of 
this AD, revise the Airworthiness Limitation Section (ALS) of the 
Instructions for Continued Airworthiness to state the following 
(this may be accomplished by inserting a copy of this AD in the 
ALS):
    ``Do the applicable Time Limits/Maintenance Checks (TLMC) 
inspection task for the flap vane brackets at the times specified in 
the following table:

                   Table 5.--Compliance Time for TLMCs
------------------------------------------------------------------------
      Condition of brackets and gaps               Compliance time
------------------------------------------------------------------------
No gap or crack in any flap vane bracket..  Continue using existing TLMC
                                             bracket schedule as
                                             published in the applicable
                                             ALS.
-------------------------------------------
No crack in any flap vane bracket, but      For Model CL-600-1A11 (CL-
 shims added.                                600), CL-600-2A12 (CL-601),
                                             and CL-600-2B16 (CL-601-3A
                                             and CL-601-3R) series
                                             airplanes:
                                            Repeat inspections remain at
                                             600 landings from rework.
                                           -----------------------------
                                            For Model CL-600-2B16 (CL-
                                             604) series airplanes:
                                            Repeat inspections remain at
                                             1,800 landings from rework.
-------------------------------------------
All 12 flap vane brackets have been         For Model CL-600-1A11 (CL-
 replaced.                                   600), CL-600-2A12 (CL-601),
                                             and CL-600-2B16 (CL-601-3A
                                             and CL-601-3R) series
                                             airplanes:
                                            New threshold of 7,000
                                             landings from installation
                                             of new flap vane brackets.
                                             Repeat inspections remain
                                             at 600 landings.
                                           -----------------------------
                                            For Model CL-600-2B16 (CL-
                                             604) series airplanes:
                                            New threshold of 7,200
                                             landings from installation
                                             of new flap vane brackets.
                                             Repeat inspections remain
                                             at 1,800 landings.''
------------------------------------------------------------------------

    (h) After doing the requirements of paragraph (g) of this AD, 
except as provided in paragraph (i) of this AD, no alternative 
inspection times may be approved for these flap vane brackets.

Alternative Methods of Compliance

    (i) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, New York ACO, FAA. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, New York ACO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York ACO.

Special Flight Permits

    (j) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference (IBR)

    (k) Unless otherwise specified in this AD, the actions shall be 
done in accordance with the Bombardier alert service bulletin 
specified in Table 5 of this AD, as applicable.
    Table 5 is as follows:

                  Table 6.--IBR Alert Service Bulletins
------------------------------------------------------------------------
          Alert service bulletin                      Excluding
------------------------------------------------------------------------
Bombardier Alert Service Bulletin A600-     Service Bulletin
 0699, Revision 01, dated July 8, 2002.      Incorporation Sheet, Flap
                                             Vane Bracket Inspection
                                             Program page, and Minimum
                                             Edge Distance Inspection
                                             pages.
-------------------------------------------
Bombardier Alert Service Bulletin A601-     Service Bulletin
 0532, Revision 01, dated July 8, 2002.      Incorporation Sheet, Flap
                                             Vane Bracket Inspection
                                             Program page, and Minimum
                                             Edge Distance Inspection
                                             pages.
-------------------------------------------
Bombardier Alert Service Bulletin A604-27-  Service Bulletin
 007, Revision 01, dated July 8, 2002.       Incorporation Sheet, Flap
                                             Vane Bracket Inspection
                                             Program page, and Minimum
                                             Edge Distance Inspection
                                             pages.
------------------------------------------------------------------------

This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Bombardier, Inc., Canadair, 
Aerospace Group, P.O. Box 6087, Station A, Montreal, Quebec H3C 3G9, 
Canada. Copies may be inspected at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
FAA, New York Aircraft Certification Office, 10 Fifth Street, Third 
Floor, Valley Stream, New York; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

    Note 5: The subject of this AD is addressed in Canadian 
airworthiness directives CF-2002-36 and CF-2002-37, effective August 
30, 2002.

Effective Date

    (l) This amendment becomes effective on May 8, 2003.

    Issued in Renton, Washington, on April 14, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-9690 Filed 4-22-03; 8:45 am]
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