[Federal Register Volume 68, Number 216 (Friday, November 7, 2003)]
[Rules and Regulations]
[Pages 63013-63017]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-27668]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-157-AD; Amendment 39-13360; AD 2003-22-12]
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.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
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 amendment requires revising the airplane flight 
manual to provide the flightcrew with procedures and limitations for 
operating the airplane with out-of-tolerance angle of attack (AOA) 
transducers. This amendment also requires, among other actions, 
measuring the vane angles and voltage of the AOA transducers; reworking 
the AOA transducer assemblies; repetitive measurements of the 
resistance of both AOA transducers; and follow-on and corrective 
actions, as applicable. This action is necessary to prevent flat spots 
on the potentiometers of the AOA transducers due to wear, which may 
cause a delay in the commands for stall warning, stick shaker, and 
stick pusher operation. This action is intended to address the 
identified unsafe condition.

DATES: Effective December 12, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 12, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from Bombardier, Inc., Canadair, Aerospace Group, PO Box 6087, 
Station Centreville, Montreal, Quebec H3C 3G9, Canada. This information 
may be examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 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: Luciano Castracane, Aerospace 
Engineer, Systems and Flight Test Branch, ANE-172, FAA, New York 
Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley 
Stream, New York 11581; telephone (516) 256-7535; fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an 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 was published in the Federal 
Register on February 28, 2003 (68 FR 9602). That action proposed to 
require revising the airplane flight manual to provide the flightcrew 
with procedures and limitations for operating the airplane with out-of-
tolerance angle of attack (AOA) transducers. That action also proposed 
to require, among other actions, measuring the vane angles and voltage 
of the AOA transducers; reworking the AOA transducer assemblies; 
repetitive measurements of the resistance of both AOA transducers; and 
follow-on and corrective actions, as applicable.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due

[[Page 63014]]

consideration has been given to the single comment received.
    The commenter concurs with the proposed rule.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Changes to 14 CFR Part 39/Effect on the 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. However, for clarity and consistency in this final rule, we 
have retained the language of the NPRM regarding that material.

Increase in Labor Rate

    After the proposed AD was issued, we reviewed the figures we use to 
calculate the labor rate to do the required actions. To account for 
various inflationary costs in the airline industry, we find it 
appropriate to increase the labor rate used in these calculations from 
$60 per work hour to $65 per work hour. The economic impact 
information, below, has been revised to reflect this increase in the 
specified hourly labor rate.

Cost Impact

    The FAA estimates that 424 airplanes of U.S. registry will be 
affected by this AD, and that the average labor rate is $65 per work 
hour. The estimated cost impact for airplanes affected by this AD are 
as follows:

                                               Table--Cost Impact
----------------------------------------------------------------------------------------------------------------
                                                                                                  Total cost per
                             Actions                               Work hour(s)     Parts cost       airplane
----------------------------------------------------------------------------------------------------------------
AFM revision....................................................               1            None             $65
Measurement of the vane angles and voltage of AOA transducers                  5            None             325
 (Part A).......................................................
Rework the AOA transducer assemblies and measurement of the                   17            $161           1,266
 baseline resistance of the applicable AOA transducers (Part B).
Measurement of the resistance of both AOA transducers (Part C)..               1            None              65
Inspection of the left- and right-side AOA vane decal...........               1            None              65
----------------------------------------------------------------------------------------------------------------

    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions. Manufacturer warranty remedies may be available 
for labor costs associated with this AD. As a result, the costs 
attributable to the AD may be less than stated above.

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.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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:

2003-22-12 Bombardier, Inc. (Formerly Canadair): Amendment 39-13360. 
Docket 2002-NM-157-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      1004 through 1085 inclusive.
 airplanes.
CL-600-2A12 (CL-601) series      3001 through 3066 inclusive.
 airplanes.
CL-600-2B16 (CL-601-3A and -3R)  5001 through 5194 inclusive.
 series airplanes.
CL-600-2B16 (CL-604) series      5301 and subsequent.
 airplanes.
------------------------------------------------------------------------



[[Page 63015]]

    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 (n) 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 prevent flat spots on the potentiometers of the AOA 
transducers due to wear, which may cause a delay in the commands for 
stall warning, stick shaker, and stick pusher operation, accomplish 
the following:

Revision of Airplane Flight Manual (AFM)

    (a) Before the accumulation of 300 total flight hours, or within 
7 days after the effective date of this AD, whichever occurs later: 
Revise the Limitations, Emergency Procedures, Normal Procedures, and 
Abnormal Procedures Sections of the applicable Canadair Challenger 
AFM by inserting a copy of the Temporary Revisions listed in Table 2 
of this AD, as applicable. Table 2 is as follows (some Temporary 
Revisions listed in Table 2 of this AD contain Product Support 
Publication (PSP) identifiers):

                                          Table 2.--Temporary Revisions
----------------------------------------------------------------------------------------------------------------
                                                                       Temporary
                  Model                               PSP               revision                Date
----------------------------------------------------------------------------------------------------------------
CL-600-1A11 (CL-600) series airplanes...  None......................       600/20  Nov. 26, 2001.
                                          None......................       600/21  Nov. 26, 2001.
                                          PSP 600-1-18..............     600-1/13  Nov. 26, 2001.
                                          None......................     600-1/17  Nov. 26, 2001.
CL-600-2A12 (CL-601) series airplanes...  None......................       601/25  Nov. 26, 2001.
                                          PSP 601-1A-1..............       601/13  Nov. 26, 2001.
                                          PSP 601-1A-17.............       601/24  Nov. 26, 2001.
                                          PSP 601-1A-18.............       601/25  Nov. 26, 2001.
                                          PSP 601-1B................       601/17  Nov. 26, 2001.
                                          PSP 601-1B-1..............       601/12  Nov. 26, 2001.
CL-600-2B16 (CL-601-3A and -3R) series    PSP 601A-1................       601/23  Nov. 26, 2001.
 airplanes.
                                          PSP 601A-1-1..............       601/22  Nov. 26, 2001.
                                          PSP 601A-1-17.............       601/22  Nov. 26, 2001.
                                          PSP 601A-1-18.............       601/21  Nov. 26, 2001.
                                          PSP 601A-1-18A............       601/24  Nov. 26, 2001.
                                          PSP 601A-1-20A............       601/15  Nov. 26, 2001.
CL-600-2B16 (CL-604) series airplanes...  PSP 604-1.................        604/9  Nov. 26, 2001.
----------------------------------------------------------------------------------------------------------------

Measurement

    (b) Before the accumulation of 300 total flight hours, or within 
200 flight hours after the effective date of this AD, whichever 
occurs later: Measure the vane angles and voltage of the angle of 
attack (AOA) transducers by doing all actions specified in ``PART 
A--Initial Special Check'' of the Accomplishment Instructions of the 
applicable alert service bulletin listed in Table 3 of this AD, per 
the applicable Bombardier alert service bulletin. Table 3 is as 
follows:

                                        Table 3.--Alert Service Bulletins
----------------------------------------------------------------------------------------------------------------
             For model              Alert service bulletin          Date                     Including
----------------------------------------------------------------------------------------------------------------
CL-600-1A11 (CL-600) series         A600-0715               Jan. 7, 2002........  Appendices A and B.
 airplanes.
CL-600-2A12 (CL-601) series         A601-0550               Jan. 7, 2002........  Appendices A and B.
 airplanes, and CL-600-2B16 (CL-
 601-3A and -3R) series airplanes.
CL-600-2B16 (CL-604) series         A604-27-011             Jan. 7, 2002........  Appendices A and B.
 airplanes.
----------------------------------------------------------------------------------------------------------------

Any Voltage Outside Tolerances: Replacement

    (c) If, during the measurement required by paragraph (b) of this 
AD, any recorded voltage is found to be outside the tolerances 
specified in the applicable Bombardier alert service bulletin 
identified in Table 3 of this AD, before further flight: Replace the 
stall protection computer (SPC) with a new SPC and do the follow-on 
actions (i.e., recording in Appendix A and repeat actions), per 
``PART A--Initial Special Check'' of the Accomplishment Instructions 
of the applicable Bombardier alert service bulletin identified in 
Table 3 of this AD.

All AOA Vane Angles Within Tolerances: Disconnection and Measurement

    (d) If, during the measurement required by paragraph (b) of this 
AD, all of the recorded AOA vane angles for both AOA transducers are 
found to be within the tolerances specified in the applicable 
Bombardier alert service bulletin listed in Table 3 of this AD, 
before further flight: Do the follow-on actions (i.e., disconnect 
breakout box, and measure the baseline resistance of the AOA 
transducer between certain pins), per ``PART B--AOA Transducer 
Assembly Rework/Baseline Resistance Check'' of the Accomplishment 
Instructions of the applicable Bombardier alert service bulletin 
identified in Table 3 of this AD. After doing the follow-on actions, 
the applicable AFM revision required by paragraph (a) of this AD may 
be removed from the AFM.

One or More AOA Vane Angles Outside Tolerances, But All AOA Vane Angles 
Within Expanded Tolerances

    (e) If, during the measurement required by paragraph (b) of this 
AD, one or more of the recorded AOA vane angles for either or both 
AOA transducers are found to be outside the tolerances specified in 
the applicable Bombardier alert service bulletin listed in Table 3 
of this AD, but all recorded AOA vane angles are within the expanded 
tolerances specified in ``Table A--Tolerances'' of ``PART A--Initial 
Special Check'' of the Accomplishment Instructions of the applicable 
Bombardier alert service bulletin identified in Table 3 of this AD: 
Do

[[Page 63016]]

the action specified in paragraph (e)(1) of this AD, except as 
provided by paragraph (e)(2) of this AD.
    (1) Before further flight, do the actions specified in paragraph 
(g) of this AD.
    (2) In lieu of doing the actions required by paragraph (e)(1) of 
this AD, do the actions specified in paragraphs (e)(2)(i) and 
(e)(2)(ii) of this AD.
    (i) Before further flight, measure the baseline resistance of 
the other AOA transducer (with recorded AOA vane angles within the 
tolerances specified in the applicable Bombardier alert service 
bulletin listed in Table 3 of this AD) per ``Table A--Tolerances'' 
of ``PART A--Initial Special Check'' of the Accomplishment 
Instructions of the applicable Bombardier alert service bulletin 
identified in Table 3 of this AD.
    (ii) Within 150 flight hours after doing the measurement 
required by paragraph (b) of this AD, do the actions specified in 
paragraph (g) of this AD.

Any AOA Vane Angle Outside Tolerances

    (f) If, during the measurement required by paragraph (b) of this 
AD, any recorded AOA vane angle of the AOA transducers is found to 
be outside the expanded tolerances specified in ``Table A--
Tolerances'' of ``PART A--Initial Special Check'' of the applicable 
Bombardier alert service bulletin listed in Table 3 of this AD, 
before further flight: Do the actions specified in paragraph (g) of 
this AD.

Transducer Assembly Rework and Baseline Resistance Measurement

    (g) Except as provided by paragraph (e)(2) of this AD, before 
further flight after doing the measurement required by paragraph (b) 
of this AD: Rework the AOA transducer assemblies and measure the 
baseline resistance of the applicable AOA transducers by doing all 
actions specified in ``PART B--AOA Transducer Assembly Rework/
Baseline Resistance Check'' of the Accomplishment Instructions of 
the applicable Bombardier alert service bulletin identified in Table 
3 of this AD, per the applicable Bombardier alert service bulletin. 
After doing the rework, the applicable AFM revision required by 
paragraph (a) of this AD may be removed from the AFM.

Repetitive Measurements and Corrective Actions

    (h) Within 300 flight hours after doing the measurement required 
by paragraph (b) of this AD: Measure the resistance of both AOA 
transducers by doing all actions specified in ``PART C--Repetitive 
Resistance Check/AOA Transducer Assembly Rework'' of the 
Accomplishment Instructions of the applicable alert service bulletin 
listed in Table 3 of this AD, per the applicable Bombardier alert 
service bulletin. Repeat the measurement at least every 300 flight 
hours.
    (i) If, during the measurement required by paragraph (h) of this 
AD, any recorded resistance is found to be outside the tolerances 
specified in the applicable Bombardier alert service bulletin listed 
in Table 3 of this AD (i.e., more than 20 ohms from its baseline 
resistance value), before further flight: Do corrective actions 
(e.g., replace AOA transducer with new AOA transducer; perform a 
visual inspection of the vane assembly; rework, if necessary; a 
test; and measure baseline resistance of applicable AOA transducer), 
as applicable, per PART C--Repetitive Resistance Check/AOA 
Transducer Assembly Rework'' of the Accomplishment Instructions of 
the applicable alert service bulletin listed in Table 3 of this AD.

Concurrent Requirements: Inspection

    (j) For airplanes identified in paragraphs (j)(1), (j)(2), and 
(j)(3) of this AD: Before or at the same time with accomplishment of 
the requirements of paragraph (b) of this AD, inspect the left- and 
right-side AOA vane decal to verify that the correct decal is 
installed per paragraph (j)(1), (j)(2), or (j)(3) of this AD, as 
applicable.
    (1) For Model CL-600-2A12 (CL-601) and CL-600-2B16 (CL-601-3A 
and -3R) series airplanes having serial numbers 3001 through 3066 
inclusive, and 5001 through 5194 inclusive, respectively, on which 
AOA calibration decals, part numbers (P/N) 600-52267-5 and 600-
52267-6, have been installed: Inspect per Bombardier Alert Service 
Bulletin A601-0519, dated July 30, 1999.
    (2) For Model CL-600-1A11 (CL-600) series airplanes having 
serial numbers 1004 through 1085 inclusive, on which AOA calibration 
decals, P/Ns 600-52267-5 and 600-52267-6, have been installed: 
Inspect per Bombardier Alert Service Bulletin A600-0693, dated July 
30, 1999.
    (3) For Model CL-600-2B16 (CL-604) series airplanes having 
serial numbers 5301 through 5990 inclusive, on which AOA calibration 
decals, P/Ns 600-52267-5 and 600-52267-6, have been installed: 
Inspect per Bombardier Alert Service Bulletin A604-11-009, dated 
July 30, 1999.

Concurrent Requirements: Corrective Actions

    (k) If either of the AOA vane decals is found to be incorrect 
during the inspection required by paragraph (j) of this AD, before 
further flight: Replace the AOA vane decal(s) with new vane 
decal(s), and ensure that the new decal(s) is the correct type, per 
the applicable alert service bulletin identified in paragraph 
(j)(1), (j)(2), or (j)(3) of this AD; except as provided by 
paragraph (l) of this AD.
    (l) If replacement decals are not available, before further 
flight: Remove existing decals and do the alignment check(s) of the 
AOA vane transducers per the applicable alert service bulletin 
identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD.

Parts Installation

    (m) As of the effective date of this AD, no person shall install 
an AOA transducer assembly on any airplane, unless the actions 
required by paragraphs (b) through (l) of this AD, as applicable, 
have been done.

Alternative Methods of Compliance

    (n) 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 Aircraft Certification 
Office (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 2: 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

    (o) 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

    (p) The actions shall be done in accordance with the following 
Bombardier service bulletins and Temporary Revisions to the 
applicable Canadair Challenger Airplane Flight Manual, as 
applicable:

                       Table 4.--Service Documents
------------------------------------------------------------------------
         Document No.                  PSP             Document date
------------------------------------------------------------------------
Alert Service Bulletin A600-    None.............  July 30, 1999.
 0693.
Alert Service Bulletin A600-    None.............  Jan. 7, 2002.
 0715, including Appendices A
 and B.
Alert Service Bulletin A601-    None.............  July 30, 1999.
 0519.
Alert Service Bulletin A601-    None.............  Jan. 7, 2002.
 0550, including Appendices A
 and B.
Alert Service Bulletin A604-11- None.............  July 30, 1999.
 009.
Alert Service Bulletin A604-27- None.............  Jan. 7, 2002.
 011, including Appendices A
 and B.
Temporary Revision 600/20.....  None.............  Nov. 26, 2001.
Temporary Revision 600/21.....  None.............  Nov. 26, 2001.
Temporary Revision 600-1/13...  PSP 600-1-18.....  Nov. 26, 2001.
Temporary Revision 600-1/17...  None.............  Nov. 26, 2001.
Temporary Revision 601/12.....  PSP 601-1B-1.....  Nov. 26, 2001.
Temporary Revision 601/13.....  PSP 601-1A-1.....  Nov. 26, 2001.

[[Page 63017]]

 
Temporary Revision 601/15.....  PSP 601A-1-20A...  Nov. 26, 2001.
Temporary Revision 601/17.....  PSP 601-1B.......  Nov. 26, 2001.
Temporary Revision 601/21.....  PSP 601A-1-18....  Nov. 26, 2001.
Temporary Revision 601/22.....  PSP 601A-1-1.....  Nov. 26, 2001.
Temporary Revision 601/22.....  PSP 601A-1-17....  Nov. 26, 2001.
Temporary Revision 601/23.....  PSP 601A-1.......  Nov. 26, 2001.
Temporary Revision 601/24.....  PSP 601-1A-17....  Nov. 26, 2001.
Temporary Revision 601/24.....  PSP 601A-1-18A...  Nov. 26, 2001.
Temporary Revision 601/25.....  None.............  Nov. 26, 2001.
Temporary Revision 601/25.....  PSP 601-1A-18....  Nov. 26, 2001.
Temporary Revision 604/9......  PSP 604-1........  Nov. 26, 2001.
------------------------------------------------------------------------

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, PO Box 6087, Station Centre-ville, 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 3: The subject of this AD is addressed in Canadian 
airworthiness directive CF-2002-05, dated January 18, 2002.

Effective Date

    (q) This amendment becomes effective on December 12, 2003.

    Issued in Renton, Washington, on October 29, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-27668 Filed 11-6-03; 8:45 am]
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