[Federal Register Volume 69, Number 30 (Friday, February 13, 2004)]
[Proposed Rules]
[Pages 7170-7174]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-3133]


 ========================================================================
 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. 69, No. 30 / Friday, February 13, 2004 / 
Proposed Rules  

[[Page 7170]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-175-AD]
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: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Bombardier 
transport category airplanes, that currently 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. That AD also provides for two 
optional terminating actions for the detailed inspection(s). This 
action would require performing one or the other of the terminating 
actions. The actions specified by the proposed AD are intended 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, 
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. This action is intended to address the 
identified unsafe condition.

DATES: Comments must be received by March 15, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-175-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: [email protected]. Comments sent via fax or the Internet must contain 
``Docket No. 2003-NM-175-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule 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, 1600 Stewart Ave., Westbury, New York.

FOR FURTHER INFORMATION CONTACT: Serge Napoleon, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Westbury, New York 11590; 
telephone (516) 228-7312; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, 
discuss a request to change the compliance time and a request to change 
the service bulletin reference as two separate issues.
     For each issue, state what specific change to 
the proposed AD is being requested.
     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 proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-175-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2003-NM-175-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On April 14, 2003, the FAA issued AD 2003-08-12, amendment 39-13125 
(68 FR 19940, April 23, 2003), 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, to require 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. That AD also provides for two 
optional terminating actions for the detailed inspection(s). That 
action was prompted by reports of several occurrences of gaps found 
between the flap vane bracket and the adjacent lower skin and between 
the flap vane bracket and vane actuator beam. 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. The requirements of 
that AD are intended to detect and correct gaps

[[Page 7171]]

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.

Actions Since Issuance of Previous Rule

    When AD 2003-08-12 was issued, it contained a provision for two 
optional terminating actions for the detailed inspections. In the 
preamble to AD 2003-08-12, the FAA indicated that the actions required 
by that AD were considered to be ``interim action'' and that further 
rulemaking action was being considered to require performing either one 
of the two corrective actions, which would constitute terminating 
action for the detailed inspections. We now have determined that 
further rulemaking is indeed necessary, and this proposed AD follows 
from that determination.

Canadian Airworthiness Directives

    Transport Canada Civil Aviation (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, both 
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 proposed 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:
     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;
     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
     Doing a nondestructive test 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:
     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
     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. 
Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition.

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 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the TCCA has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the 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 Proposed 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, the proposed AD would supersede AD 2003-08-12 to 
continue to require 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 
proposed AD also would require performing either one of the two 
corrective actions, which would constitute terminating action for the 
detailed inspections. The actions would be required to be accomplished 
in accordance with the service bulletins described previously, except 
as discussed below.

Differences Between the Alert Service Bulletins and This Proposed 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 proposed AD 
would require such actions.
    In addition, although the alert service bulletins specify that the 
manufacturer may be contacted for disposition of certain repair 
conditions, this proposed AD would require 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 proposed AD, a repair approved by either 
the FAA or TCCA will be acceptable for compliance with this proposed 
AD.

Clarification Between This 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 proposed 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

[[Page 7172]]

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

Changes to 14 CFR Part 39/Effect on the Proposed AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance (AMOCs). Because we have now included this material in part 
39, only the office authorized to approve AMOCs is identified in each 
individual AD. Therefore, Notes 1 and 4 and paragraphs (i) and (j) of 
AD 2003-08-12 are not included in this proposed AD.

Change to Labor Rate Estimate

    We have reviewed the figures we have used over the past several 
years to calculate AD costs to operators. To account for various 
inflationary costs in the airline industry, we find it necessary to 
increase the labor rate used in these calculations from $60 per work 
hour to $65 per work hour. The cost impact information, below, reflects 
this increase in the specified hourly labor rate.

Cost Impact

    There are approximately 411 airplanes of U.S. registry that would 
be affected by this proposed AD.
    The detailed inspection that is currently required by AD 2003-08-
12, amendment 39-13125, takes approximately 11 work hours per airplane 
to accomplish, at an average labor rate of $65 per work hour. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators is estimated to be $293,865, or $715 per airplane, per 
inspection cycle.
    The terminating corrective actions specified in Part B of the 
Accomplishment Instructions of the applicable alert service bulletin 
identified in Table 2 of this AD, take approximately 24 work hours per 
airplane to accomplish the inspections and between 4 and 48 work hours 
per airplane to accomplish the replacement of the vane bracket(s), at 
an average labor rate of $65 per work hour. Required parts would cost 
between $535 and $6,414 for the vane brackets. Based on these figures, 
the cost impact of the proposed terminating corrective actions on U.S. 
operators is estimated to be between $967,905 and $4,559,634, or 
between $2,355 and $11,094 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    The optional terminating corrective actions specified in Part C of 
the Accomplishment Instructions of the applicable alert service 
bulletin identified in Table 2 of this AD, takes approximately 80 work 
hours per airplane to accomplish, at an average labor rate of $65 per 
work hour. Required parts would cost approximately $6,414 for the vane 
brackets. Based on these figures, the cost impact of the proposed 
terminating corrective actions on U.S. operators is estimated to be 
$4,773,354 or between $11,614 per airplane.

Regulatory Impact

    The regulations proposed herein 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. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that 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); 
and (3) if promulgated, 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. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (14 CFR part 39) as 
follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-13125 (68 FR 
19940, April 23, 2003), and by adding a new airworthiness directive 
(AD), to read as follows:

Bombardier, Inc.: Docket 2003-NM-175-AD. Supersedes AD 2003-08-12, 
Amendment 39-13125.

    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) series     5001 through 5194 inclusive.
 airplanes.
CL-600-2B16 (CL-604) series airplanes..........  5301 through 5499 inclusive.
----------------------------------------------------------------------------------------------------------------

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


[[Page 7173]]



Restatement of Requirements of AD 2003-08-12

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

                    Table 2.--Alert Service Bulletins
------------------------------------------------------------------------
                                Bombardier alert
            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-
                 -                         The compliance time is--
------------------------------------------------------------------------
1,200 total landings or less as of   Before the accumulation of 1,300
 May 8, 2003 (the effective date of   total landings.
 AD 2003-08-12).
More than 1,200 total landings, but  Within 100 landings after May 8,
 less than 3,000 total landngs as     2003 (the effective date of AD
 of May 8, 2003 (the effective date   2003-08-12).
 of AD 2003-08-12).
3,000 total landings or more as of   Within 50 landings after May 8,
 May 8, 2003 (the effective date of   2003 (the effective date of AD
 AD 2003-08-12).                      2003-08-12).
------------------------------------------------------------------------


    Note 2: 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 (e) or (f) of this AD.

New Requirements of This AD

Terminating Actions

    (d) Do the actions specified in paragraph (e) or (f) of this AD, 
at the applicable time listed in Table 4--Compliance Time--
Terminating Actions.

             Table 4.--Compliance Time--Terminating Actions
------------------------------------------------------------------------
For airplanes that have accumulated-
                 -                         The compliance time is--
------------------------------------------------------------------------
Less than 2,000 total landings as    Within 600 total landings after the
 of the effective date of this AD.    effective date of this AD.
2,000 or more total landings as of   Within 400 total landings after the
 the effective date of this AD.       effective date of this AD.
------------------------------------------------------------------------

    (e) Do the actions specified in paragraphs (e)(1), (e)(2), and 
(e)(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 meets 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

[[Page 7174]]

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.
    (f) In lieu of the actions specified in paragraph (e) of this 
AD, do the actions specified in paragraphs (f)(1) and (f)(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 (f) of this AD

    (g) Accomplishment of the inspections and modifications per Part 
B or Part C of the applicable alert service bulletin listed in Table 
5 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 (f) of this AD. Table 5 of this AD is as 
follows:

        Table 5.--Acceptable Basic Issue Alert Service Bulletins
------------------------------------------------------------------------
                                         Use bombardier alert service
            For model--                           bulletin--
------------------------------------------------------------------------
CL-600-1A11 (CL-600) series          A600-0699, Basic Issue, dated
 airplanes.                           November 29, 2001.
CL-600-2A12 (CL-601) series
 airplanes, and.
CL-600-2B16 (CL-601-3A and CL-601-   A601-0532, Basic Issue, dated
 3R) series airplanes.                November 29, 2001.
CL-600-2B16 (CL-604) series          A604-27-007, Basic Issue, dated
 airplanes.                           November 29, 2001.
------------------------------------------------------------------------

Time Limits/Maintenance Checks

    (h) After doing the actions specified in paragraph (e) or (f) 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.--Compliance Time for TLMCs
------------------------------------------------------------------------
  Condition of brackets and gaps               Compliance time
------------------------------------------------------------------------
No gap or crack in any flap vane    Continue using existing TLMC bracket
 bracket.                            schedule as published in the
                                     applicable ALS.
-----------------------------------
No crack in any flap vane bracket,  For Model CL-600-1A11 (CL-600), CL-
 but shims added.                    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      For Model CL-600-1A11 (CL-600), CL-
 been replaced.                      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
                                     remains at 1,800 landings.''
------------------------------------------------------------------------

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

Alternative Methods of Compliance

    (j) In accordance with 14 CFR 39.19, the Manager, New York ACO, 
FAA, is authorized to approve alternative methods of compliance 
(AMOCs) for this AD.

    Note 3: The subject of this AD is addressed in Canadian 
airworthiness directives CF-2002-36 and CF-2002-37, both effective 
August 30, 2002.


    Issued in Renton, Washington, on February 5, 2004.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-3133 Filed 2-12-04; 8:45 am]
BILLING CODE 4910-13-P