AD 2001-03-08

[Federal Register Volume 66, Number 36 (Thursday, February 22, 2001)]
[Rules and Regulations]
[Pages 11105-11108]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-3697]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-142-AD; Amendment 39-12112; AD 2001-03-08]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Bombardier Model CL-600-2B19 series 
airplanes, that currently requires, among other actions, certain 
revisions to the Airplane Flight Manual; and removal of all elevator 
flutter dampers. That AD also requires installation of new elevator 
flutter dampers, and replacement of shear pins and shear links with new 
improved shear pins and shear links. This amendment adds airplanes to 
the applicability of the existing AD; and requires replacing certain 
shear pins with new, improved shear pins; and, for certain airplanes, 
inspection of the maintenance records to determine replacement status 
of the shear pins; and corrective actions, if necessary. This amendment 
is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by this AD are intended to prevent premature failure of the 
shear pins of the elevator damper, which may increase the likelihood of 
jamming or restricting movement of the elevator and the resultant 
adverse effect on controllability of the airplane.

DATES: Effective March 29, 2001.
    The incorporation by reference of certain publications, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of March 29, 2001.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of April 3, 1998 (63 FR 9928, February 27, 
1998).

ADDRESSES: 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 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: Serge Napoleon, Aerospace Engineer, 
ANE-171, FAA, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7512; 
fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-04-45, 
amendment 39-10356 (63 FR 9928, February 27, 1998), which is applicable 
to certain Bombardier Model CL-600-2B19 series airplanes, was published 
in the Federal Register on October 31, 2000 (65 FR 64898). The action 
proposed to continue to require, among other actions, certain revisions 
to the Airplane Flight Manual (AFM); and removal of all elevator 
flutter dampers. The action also proposed to continue to require 
installation of new elevator flutter dampers, and replacement of shear 
pins and shear links with new improved shear pins and shear links. The 
action also proposed to add airplanes to the applicability of the 
existing AD; and to require replacing certain shear pins with new, 
improved shear pins; and, for certain airplanes, inspection of the 
maintenance records to determine replacement status of the shear pins; 
and corrective actions, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 214 Bombardier Model CL-600-2B19 series

[[Page 11106]]

airplanes of U.S. registry that will be affected by this AD.
    The removal of the elevator dampers and the AFM revision that are 
currently required by AD 98-04-45, and retained in this AD, take 
approximately 6 work hours per airplane to accomplish, at an average 
rate of $60 per work hour. The FAA estimates that all affected U.S. 
operators have previously accomplished these requirements, therefore, 
the future cost impact of these requirements is minimal.
    The inspections that are currently required by AD 98-04-45, and 
retained in this AD, take approximately 26 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the inspection requirements of AD 98-
04-05 is estimated to be $1,560 per airplane.
    The installation of flutter dampers that is currently required by 
AD 98-04-45 takes approximately 12 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Required 
parts will be provided at no cost to the operators by the manufacturer. 
Based on these figures, the cost impact of the installation currently 
required AD 98-04-45 is estimated to be $720 per airplane.
    The new actions (i.e., replacement of the shear pins, check of 
maintenance records, and AFM revision) that are required in this AD 
will take approximately 21 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Required parts are estimated 
to cost $801. Based on these figures, the cost impact of these new 
requirements of this AD on U.S. operators is estimated to be $441,054, 
or $2,061 per airplane.
    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.

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

    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

    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 39-10356 (63 FR 
9928, February 27, 1998), and by adding a new airworthiness directive 
(AD), amendment 39-12112, to read as follows:

2001-03-08  Bombardier, Inc. (Formerly Canadair): Amendment 39-
12112. Docket 2000-NM-142-AD. Supersedes AD 98-04-45, Amendment 39-
10356.

    Applicability: Model CL-600-2B19 series airplanes, having serial 
numbers 7003 through 7357 inclusive, certificated in any category.

    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 prevent premature failure of the shear pins of the elevator 
damper, which may increase the likelihood of jamming or restricting 
movement of the elevator and the resultant adverse effect on 
controllability of the airplane, accomplish the following:

Restatement of Actions Required by AD 98-04-45:

Airplane Flight Manual (AFM) Revision Required by AD 98-04-45

    (a) For airplanes having serial numbers 7003 through 7054 
inclusive: Within 30 days after January 26, 1994 (the effective date 
of AD 94-01-09, amendment 39-8791), revise the Limitations Section 
of the FAA-approved AFM to include the following restrictions of 
altitude and airspeed operations under conditions of single or 
double hydraulic system failure; and advise the flight crew of these 
revised limits. Revision of the AFM may be accomplished by inserting 
a copy of this AD or AFM Revision 34, dated June 12, 1995, in the 
AFM. Restrictions of altitude and airspeed operations under 
conditions of single or double hydraulic system failure are listed 
in the following tables.

                Table 1.--Single Hydraulic System Failure
------------------------------------------------------------------------
         Altitude limit  (maximum)            Airspeed limit  (maximum)
------------------------------------------------------------------------
31,000 feet...............................  0.55 Mach
                                            (199 KIAS)
30,000 feet...............................  0.55 Mach
                                            (204 KIAS)
28,000 feet...............................  0.55 Mach
                                            (213 KIAS)
26,000 feet...............................  0.55 Mach
                                            (222 KIAS)
24,000 feet...............................  0.55 Mach
                                            (232 KIAS)
22,000 feet...............................  0.55 Mach
                                            (241 KIAS)
20,000 feet and below.....................  252 KIAS
------------------------------------------------------------------------


                Table 2.--Double Hydraulic System Failure
------------------------------------------------------------------------
         Altitude limit  (maximum)            Airspeed limit  (maximum)
------------------------------------------------------------------------
10,000 feet...............................  200 KIAS
------------------------------------------------------------------------


    Note 2: The restrictions described in the AFM Temporary Revision 
(TR) RJ/30, dated December 16, 1993, meet the requirements of this 
paragraph. Therefore, inserting a copy of TR RJ/30 in lieu of this 
AD in the AFM is considered an acceptable means of compliance with 
this paragraph.


    (b) Within 7 days after December 14, 1994 (the effective date of 
AD 94-24-02, amendment 39-9075), accomplish the

[[Page 11107]]

requirements of paragraphs (b)(1) and (b)(2) of this AD.
    (1) Remove the elevator dampers in accordance with Canadair 
Regional Jet Alert Service Bulletin S.B. A601R-27-041, dated October 
28, 1994.
    (2) Revise the Limitations Section of the FAA-approved AFM to 
include the following, which advises the flight crew of daily checks 
to verify proper operation of the elevator control system. Revision 
of the AFM may be accomplished by inserting a copy of this AD or AFM 
Revision 32, dated March 30, 1995, in the AFM.

    Note 3: The daily check described in the AFM TR RJ/40, dated 
October 28, 1994, meets the requirements of this paragraph. 
Therefore, inserting a copy of TR RJ/40 into the AFM in lieu of this 
AD is considered an acceptable means of compliance with this 
paragraph.

``Elevator, Before Engine Start (First Flight of Day)
(1) Elevator--Check: Travel range (to approximately \1/2\ travel) 
using each hydraulic system in turn, with the other hydraulic 
systems depressurized.''

Inspections Required by AD 98-04-45

    (c) For airplanes having serial numbers 7003 through 7049 
inclusive: Within 12 months after April 3, 1998 (the effective date 
of AD 98-04-45, amendment 39-10356), perform the actions required in 
paragraphs (c)(1), (c)(2), and (c)(3) of this AD, as applicable, in 
accordance with Section 2.B., Part A, of Canadair Regional Jet 
Service Bulletin S.B. 601R-27-040, Revision ``B,'' dated September 
11, 1995.
    (1) Remove the shear pins and shear links of the flutter dampers 
and perform a visual inspection to detect any deformation or 
discrepancy of the flutter damper hinge fitting and lug of the 
horizontal stabilizer. Prior to further flight, replace any deformed 
or discrepant part with a serviceable part in accordance with the 
service bulletin.
    (2) Perform a visual inspection to detect any deformation or 
discrepancy of the elevator hinge/damper fitting and shear pin lugs. 
Prior to further flight, replace any discrepant part with a 
serviceable part in accordance with the service bulletin.
    (3) Perform a fluorescent penetrant inspection and a dimensional 
inspection to detect any deformation or discrepancy of the shear pin 
lugs. If any deformation or discrepancy is found on the lugs, prior 
to further flight, replace the elevator with a new or serviceable 
elevator in accordance with the service bulletin.

    Note 4: For the purposes of this AD, a detailed visual 
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.''


    (d) For airplanes having serial numbers 7003 through 7054: 
Within 12 months after April 3, 1998 (the effective date of AD 98-
04-45, amendment 39-10356), install new elevator flutter dampers (P/
N 601R75142-7) in accordance with Section 2.B., Part B, of Canadair 
Regional Jet Service Bulletin S.B. 601R-27-040, Revision ``B,'' 
dated September 11, 1995.

New Requirements of This AD:

Installation of Shear Pins

    (e) For airplanes having serial numbers 7003 through 7142 
inclusive, and 7144: Within 12 months after the effective date of 
this AD, install new shear pins (part number (P/N) 601R24063-31/S) 
in accordance with Part A of the Accomplishment Instructions of 
Canadair Regional Jet Service Bulletin S.B. 601R-27-100, Revision 
``A,'' dated March 10, 2000. After accomplishment of the 
installation of new shear pins, Canadair Regional Jet TR RJ/68-1, 
dated February 15, 2000, may be removed from the AFM.

Inspection of Maintenance Records

    (f) For airplanes having serial numbers 7143, and 7145 through 
7357 inclusive: Within 14 days after the effective date of this AD, 
perform a one-time inspection of the maintenance records to 
determine the replacement status of the shear pins of the elevator 
flutter dampers, in accordance with Part B of the Accomplishment 
Instructions of Canadair Regional Jet Service Bulletin S.B. 601R-27-
100, Revision ``A,'' dated March 10, 2000.
    (1) If the maintenance records indicate that all shear pins were 
NOT replaced after delivery of the airplane, or if all shear pins 
were replaced with shear pins having P/N 601R24063-31/S: No further 
action is required by this AD.
    (2) If the maintenance records indicate that any shear pin was 
replaced after delivery of the airplane with a shear pin having P/N 
601R24063-31 or 601R24063-953, or if the maintenance records do not 
verify that all shear pins having P/N 601R24063-31/S are installed: 
Accomplish the requirements of paragraph (g) of this AD at the times 
specified in that paragraph.

AFM Revision and Replacement

    (g) For airplanes on which any shear pin of the elevator flutter 
dampers of the elevators was replaced after delivery of the airplane 
with a shear pin having P/N 601R24063-31 or 601R24063-953, or for 
airplanes on which verification of shear pins having P/N 601R24063-
31/S is not possible: Accomplish the requirements of paragraphs 
(g)(1) and (g)(2) of this AD at the times specified in those 
paragraphs.
    (1) Within 30 days after the effective date of this AD, revise 
the Normal Procedures Section of the AFM by inserting Canadair 
Regional Jet TR RJ/68-1, dated February 15, 2000, in the AFM, which 
advises the flight crew of an additional first-flight-of-the-day 
check of the elevator control system.
    (2) Within 12 months after the effective date of this AD, 
replace the shear pins with new, improved shear pins having P/N 
601R24063-31/S, in accordance with Part C of the Accomplishment 
Instructions of Canadair Regional Jet Service Bulletin S.B. 601R-27-
100, Revision ``A,'' dated March 10, 2000. After accomplishment of 
the installation of new shear pins, the temporary revision required 
by paragraph (g)(1) of this AD may be removed from the AFM.

Spares

    (h) As of the effective date of this AD, no person shall install 
a shear pin of the elevator flutter dampers having P/N 601R24063-31 
or 601R24063-953 on any airplane.

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 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 5: 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

    (k) Except as required by paragraphs (a) and (b)(2) of this AD, 
the actions shall be done in accordance with Canadair Regional Jet 
Alert Service Bulletin S.B. A601R-27-041, dated October 28, 1994; 
Canadair Regional Jet Service Bulletin S.B. 601R-27-040, Revision 
``B,'' dated September 11, 1995; Canadair Regional Jet Service 
Bulletin S.B. 601R-27-100, Revision ``A,'' dated March 10, 2000; and 
Canadair Regional Jet Airplane Flight Manual Temporary Revision RJ/
68-1, dated February 15, 2000; as applicable.
    (1) The incorporation by reference of Canadair Regional Jet 
Service Bulletin S.B. 601R-27-100, Revision ``A,'' dated March 10, 
2000; and Canadair Regional Jet Airplane Flight Manual Temporary 
Revision RJ/68-1, dated February 15, 2000; is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) The incorporation by reference of Canadair Regional Jet 
Alert Service Bulletin S.B. A601R-27-041, dated October 28, 1994; 
and Canadair Regional Jet Service Bulletin S.B. 601R-27-040, 
Revision ``B,'' dated September 11, 1995; was approved previously by 
the Director of the Federal Register as of April 3, 1998 (63 FR 
9928, February 27, 1998).
    (3) Copies may be obtained from Bombardier, Inc., Canadair, 
Aerospace Group, P.O. Box 6087 Station Centre-ville,

[[Page 11108]]

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 6: The subject of this AD is addressed in Canadian 
airworthiness directive CF-2000-10, dated March 23, 2000.

Effective Date

    (l) This amendment becomes effective on March 29, 2001.

    Issued in Renton, Washington, on February 8, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-3697 Filed 2-21-01; 8:45 am]
BILLING CODE 4910-13-U