[Federal Register: February 28, 2003 (Volume 68, Number 40)]
[Proposed Rules]
[Page 9602-9607]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28fe03-41]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-157-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).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to
[[Page 9603]]
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 proposal would require revising the Airplane Flight Manual (AFM)
to provide the flightcrew with procedures and limitations for operating
the airplane with out-of-tolerance angle of attack (AOA) transducers.
This proposal also would 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. 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: Comments must be received by March 31, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-157-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:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-157-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, 10 Fifth Street, Third Floor, Valley
Stream, New York.
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:
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:
[sbull] 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.
[sbull] For each issue, state what specific change to the proposed
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 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 2002-NM-157-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. 2002-NM-157-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
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-600), CL-600-2A12
(CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series
airplanes. TCCA advises that, during testing of an airplane, flat spots
were discovered on the potentiometers of the angle of attack (AOA)
transducers due to wear. Since the AOA transducers work in conjunction
with the stall protection system (SPS), these flat spots, if not
corrected, may cause a delay in the commands for stall warning, stick
shaker, and stick pusher operation.
Explanation of Relevant Service Information
The manufacturer has issued the applicable Canadair Challenger
temporary revisions to the Airplane Flight Manual (AFM) listed in Table
2 of this AD. The temporary revisions describe procedures for revising
the Limitations, Emergency Procedures, Normal Procedures, and Abnormal
Procedures Sections of the FAA-approved Canadair Challenger AFM, as
applicable, to provide the flightcrew with procedures and limitations
for operating the airplane with out-of-tolerance AOA transducers.
The manufacturer also has issued the applicable Bombardier service
bulletins listed in Table 3 of this AD, which describe the following
procedures:
[sbull] Measuring the vane angles and voltage of the AOA
transducers; follow-on and corrective actions, as applicable; and
recording and reporting incorporation of the service bulletin to
Bombardier. The follow-on and corrective actions include replacing the
stall protection computer (SPC) with a new SPC; recording and repeating
actions; disconnecting the breakout box; measuring the baseline
resistance of the AOA transducer between certain pins; and measuring
the baseline resistance of the other AOA transducer for temporary
deferral of reworking the AOA transducer assemblies; as applicable.
Certain follow-on actions eliminate the need for the AFM revisions
described previously.
[sbull] Reworking the AOA transducer assemblies and measuring the
baseline resistance of the applicable AOA transducers, which eliminate
the need for the AFM revisions described previously;
[sbull] Performing repetitive measurements of the resistance of
both AOA transducers, and doing applicable corrective actions. The
corrective actions include replacement of the AOA transducer with new
AOA transducer; visual inspection of the vane assembly; rework, if
necessary; a test; and measurement of baseline resistance of the
applicable AOA transducer.
In addition, the manufacturer has issued Bombardier Alert Service
[[Page 9604]]
Bulletin A601-0519, dated July 30, 1999, including Service Bulletin
Incorporation Sheet (for Model CL-600-2A12 (CL-601) and CL-600-2B16
(CL-601-3A and -3R) series airplanes); Bombardier Alert Service
Bulletin A600-0693, dated July 30, 1999, including Service Bulletin
Incorporation Sheet (for Model CL-600-1A11 (CL-600) series airplanes);
and Bombardier Alert Service Bulletin A604-11-009, dated July 30, 1999,
including Service Bulletin Incorporation Sheet (for Model CL-600-2B16
(CL-604) series airplanes); as applicable. These service bulletins
describe procedures for performing an inspection of the left- and
right-side AOA vane decal to verify that the correct decal is
installed; performing corrective action if necessary; and recording and
reporting incorporation of the service bulletin to Bombardier. The
corrective action includes replacing the incorrect AOA vane decal(s)
with new, correct vane decal(s), and ensuring that the new decal(s) is
the correct type; or removing existing decals, and doing alignment
check(s) of the AOA vane transducers, if replacement decals are not
available.
Accomplishment of the actions specified in the applicable temporary
revisions and service bulletins is intended to adequately address the
identified unsafe condition. TCCA has issued Canadian airworthiness
directive CF-2002-05, dated January 18, 2002, in order to assure the
continued airworthiness of these airplanes in Canada.
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 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 require accomplishment of
the actions specified in the applicable temporary revisions and service
bulletins described previously, except as discussed below.
Differences Between Proposed Rule and Canadain Airworthiness Directive
Operators should note that, although the parallel Canadian
airworthiness directive requires operators to forward a copy of the
Test Result Sheets and Service Bulletin Incorporation Sheets of the
applicable service bulletin to Bombardier, this proposed AD would not
require those actions.
Cost Impact
The FAA estimates that 424 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 of U.S. registry would be affected by this
proposed AD. Table--Cost Impact shows the estimated cost impact for
airplanes affected by this AD. The average labor rate is $60 per work
hour.
Table.--Cost Impact
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Total cost per
Actions Work hour(s) Parts cost airplane
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AFM revision.................................. 1 none............................ $60
Measurement of the vane angles and voltage of 5 none............................ 300
AOA transducers (Part A).
Rework the AOA transducer assemblies and 17 $161............................ 2,737
measurement of the baseline resistance of the
applicable AOA transducers (Part B).
Measurement of the resistance of both AOA 1 none............................ 60
transducers (Part C).
Inspection of the left- and right-side AOA 1 none............................ 60
vane decal.
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The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the proposed 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 proposed AD. As a result, the
costs attributable to the proposed AD may be less than stated above.
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:
[[Page 9605]]
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 adding the following new
airworthiness directive:
Bombardier, Inc. (Formerly Canadair): 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.--Applicability
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Model Serial Nos.
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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 -3R) series 5001 through 5194 inclusive.
airplanes.
CL-600-2B16 (CL-604) series airplanes..... 5301 and subsequent.
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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, as applicable, of the applicable
Canadair Challenger AFM by inserting a copy of the applicable
Temporary Revision listed in Table 2 of this AD. 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
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Temporary
Model PSP revision Date
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CL-600-1A11 (CL-600) series airplanes none.................... 600/21 November 26, 2001.
none.................... 600/20 November 26, 2001.
none.................... 600-1/17 November 26, 2001.
PSP 600-1-18............ 600-1/13 November 26, 2001
CL-600-2A12 (CL-601) series airplanes none.................... 601/25 November 26, 2001.
PSP 601-1A-1............ 601/13 November 26, 2001.
PSP 601-1A-17........... 601/24 November 26, 2001.
PSP 601-1A-18........... 601/25 November 26, 2001.
PSP 601-1B.............. 601/17 November 26, 2001.
PSP-601-1B-1............ 601/12 November 26, 2001.
CL-600-2B16 (CL-601-3A and -3R) PSP 601A-1.............. 601/23 November 26, 2001.
series airplanes. PSP 601A-1-1............ 601/22 November 26, 2001.
PSP 601A-1-17........... 601/22 November 26, 2001.
PSP 601A-1-18........... 601/21 November 26, 2001.
PSP 601A-1-18A.......... 601/24 November 26, 2001.
PSP 601A-1-20A.......... 601/15 November 26, 2001.
CL-600-2B16 (CL-604) series airplanes PSP 604-1............... 604/9 November 26, 2001.
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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; except that it is
not necessary to complete the Test Results and Service Bulletin
Incorporation Sheets. Table 3 is as follows:
Table 3.--Alert Service Bulletins
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For model-- Alert service bulletin Date Including--
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CL-600-1A11 (CL-600) series A600-0715................ January 7, 2002......... Service Bulletin
airplanes. Compliance Sheet and
Appendices A and B.
CL-600-2A12 (CL-601) series A601-0550................ January 7, 2002......... Service Bulletin
airplanes, and CL-600-2B16 (CL- Compliance Sheet and
600-3A and -3R) series airplanes. Appendices A and B.
CL-600-2B16 (CL-604) series A604-27-011.............. January 7, 2002......... Service Bulletin
airplanes. Compliance Sheet and
Appendices A and B.
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[[Page 9606]]
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 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 Vane Angles
Within 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 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 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 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 tolerances specified in 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, excluding Service Bulletin
Compliance Sheet.
(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, excluding Service Bulletin Compliance Sheet.
(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, excluding Service Bulletin Compliance Sheet.
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.
Note 3: The subject of this AD is addressed in Canadian
airworthiness directive CF-2002-05, dated January 18, 2002.
[[Page 9607]]
Issued in Renton, Washington, on February 21, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-4739 Filed 2-27-03; 8:45 am]
BILLING CODE 4910-13-P