[Federal Register Volume 63, Number 39 (Friday, February 27, 1998)]
[Rules and Regulations]
[Pages 9928-9930]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-4250]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-108-AD; Amendment 39-10356; AD 98-04-45]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100) 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 (Regional Jet 
Series 100) series airplanes, that currently requires revisions to the 
Airplane Flight Manual (AFM) to advise the flight crew of the need to 
perform daily checks to verify proper operation of the elevator control 
system, and to restrict altitude and airspeed operations under certain 
conditions. That AD also requires removal of all elevator flutter 
dampers. That AD was prompted by reports that the installation of 
certain shear pins may jam or restrict movement of the elevator. The 
actions specified by that AD are intended to prevent such jamming or 
restricting movement of the elevator and the resultant adverse effect 
on the controllability of the airplane. This amendment adds inspections 
of certain airplanes to detect deformation or discrepancies of the 
flutter damper hinge fittings and lug of the horizontal stabilizer, the 
elevator hinge/damper fitting, and the shear pin lugs; and requires 
replacement of discrepant parts with serviceable parts. This amendment 
also requires installation of new elevator flutter dampers, and 
replacement of shear pins and shear links with new, improved pins and 
links.

DATES: Effective April 3, 1998.
    The incorporation by reference of Canadair Regional Jet Service 
Bulletin S.B. 601R-27-040, Revision `B,' dated September 11, 1995, as 
listed in the regulations, is approved by the Director of the Federal 
Register as of April 3, 1998.
    The incorporation by reference of Canadair Regional Jet Alert 
Service Bulletin S.B. A601R-27-041, dated October 28, 1994, as listed 
in the regulations, was approved previously by the Director of the 
Federal Register as of December 14, 1994 (59 FR 60888, November 29, 
1994).

ADDRESSES: The service information referenced in this AD may be 
obtained

[[Page 9929]]

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, Engine and Propeller 
Directorate, 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: Franco Pieri, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, New York Aircraft 
Certification Office, FAA, Engine and Propeller Directorate, 10 Fifth 
Street, Third Floor, Valley Stream, New York 11581; telephone (516) 
256-7526; fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 94-24-02, 
amendment 39-9075 (59 FR 60888, November 29, 1994), applicable to 
certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series 
airplanes, was published in the Federal Register on February 3, 1997 
(62 FR 4941). That action proposed to continue to require the removal 
of the originally installed elevator dampers. That action also proposed 
to continue to require revisions to the Limitations Section of the FAA-
approved Airplane Flight Manual (AFM) to restrict altitude and airspeed 
operations under conditions of single or double hydraulic system 
failure, and to advise the flight crew of the need to perform daily 
checks to verify proper operation of the elevator control system.
    For certain airplanes, this new action proposes to add inspections 
of certain airplanes to detect deformation or discrepancies of the 
flutter damper hinge fittings and lug of the horizontal stabilizer, the 
elevator hinge/damper fitting, and the shear pin lugs; and requires 
replacement of discrepant parts with serviceable parts. For those and 
other airplanes, the proposed AD also would require installation of new 
elevator flutter dampers, and replacement of shear pins and shear links 
with new, improved pins and links.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

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 21 Bombardier Model CL-600-2B19 (Regional 
Jet Series 100) series airplanes of U.S. registry that will be affected 
by this AD.
    The actions that are currently required by AD 94-24-02, and 
retained in this AD, take approximately 6 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 previously required actions on 
U.S. operators is estimated to be $7,560, or $360 per airplane. The FAA 
estimates that all affected U.S. operators have previously accomplished 
these requirements, therefore, the future cost impact of these 
requirements is minimal.
    For operators that are required to accomplish the inspections in 
this new AD, it will take approximately 26 work hours per airplane to 
accomplish them, at an average labor rate of $60 per work hour. Based 
on these figures, the cost impact of the new inspection requirements of 
this AD on U.S. operators is estimated to be $1,560 per airplane.
    The installations that are required in this AD will take 
approximately 12 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will be provided by the 
manufacturer at no cost to the operator. Based on these figures, the 
cost impact of the installations required by this AD on U.S. operators 
is estimated to be $15,120, or $720 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.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 39-9075 (59 FR 
60888, November 29, 1994), and by adding a new airworthiness directive 
(AD), amendment 39-10356, to read as follows:

98-04-45 Bombardier, Inc. (Formerly Canadair): Amendment 39-10356. 
Docket 96-NM-108-AD. Supersedes AD 94-24-02, Amendment 39-9075.

    Applicability: Model CL-600-2B19 (Regional Jet Series 100) 
series airplanes, having serial numbers 7003 through 7054 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 (d) of 
this AD.

[[Page 9930]]

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 failure of lugs and/or pins, 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 Requirements of AD 94-01-09

    (a) 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 Airplane Flight Manual (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.

                     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.                   
------------------------------------------------------------------------


                     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.

Restatement of Requirements of AD 94-24-02

    (b) Within 7 days after December 14, 1994 (the effective date of 
AD 94-24-02, amendment 39-9075), accomplish the requirements of 
paragraphs (b)(1) and (b)(2) of this AD:
    (1) Until the requirements of paragraph (c)(2) of this AD are 
accomplished, 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 Temporary Revision 
(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.''                 
                                                                        

New Requirements of This AD

    (c) Within 12 months after the effective date of this AD, 
perform the requirements of paragraphs (c)(1) and (c)(2) of this AD, 
as applicable, in accordance with Canadair Regional Jet Service 
Bulletin S.B. 601R-27-040, Revision `B,' dated September 11, 1995.
    (1) For airplanes having serial numbers 7003 through 7049, 
inclusive: Perform the inspections specified in paragraphs 
(c)(1)(i), (c)(1)(ii), and (c)(1)(iii) of this AD in accordance with 
Section 2.B., Part A, of the service bulletin.
    (i) 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.
    (ii) 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.
    (iii) 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.
    (2) For airplanes having serial numbers 7003 through 7054, 
inclusive: Install new shear pins [part number (P/N) 601R24063-953] 
and new elevator flutter dampers (P/N 601R75142-7) in accordance 
with Section 2.B., Part B, of the service bulletin:
    (d) 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, Engine and Propeller Directorate. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, New York ACO.

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

    (e) 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.
    (f) The actions shall be done in accordance with Canadair 
Regional Jet Service Bulletin S.B. 601R-27-040, Revision `B,' dated 
September 11, 1995, and Canadair Regional Jet Alert Service Bulletin 
S.B. A601R-27-041, dated October 28, 1994.
    (1) The incorporation by reference of Canadair Regional Jet 
Service Bulletin S.B. 601R-27-040, Revision `B,' dated September 11, 
1995, 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 was 
approved previously by the Director of the Federal Register as of 
December 14, 1994 (59 FR 60888, November 29, 1994).
    (3) Copies may be obtained from Bombardier, Inc., Canadair, 
Aerospace Group, P.O. 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, Engine and Propeller Directorate, New 
York Aircraft Certification Office, 10 Fifth Street, Third Floor, 
Valley Stream, New York; or at the Office of the Federal Register, 
800 North Capitol Street, NW., suite 700, Washington, DC.

    Note 5: The subject of this AD is addressed in Canadian 
airworthiness directive CF-94-21R1, dated November 3, 1995.

    (g) This amendment becomes effective on April 3, 1998.

    Issued in Renton, Washington, on February 12, 1998.
Gilbert L. Thompson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-4250 Filed 2-26-98; 8:45 am]
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