[Federal Register Volume 62, Number 179 (Tuesday, September 16, 1997)]
[Rules and Regulations]
[Pages 48477-48479]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-24341]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-48-AD; Amendment 39-10132; AD 97-19-11]
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 series 
airplanes, that currently requires revising the Limitations Section of 
the Airplane Flight Manual (AFM) to provide the flight crew with 
procedures to check the travel range of the aileron. That AD also 
requires inspection for damage of the shear pins of the aileron flutter 
damper and aileron hinge fittings, and various follow-on actions. This 
amendment adds a requirement for accomplishment

[[Page 48478]]

of an installation that eliminates the need for the AFM revision. This 
amendment also adds airplanes to the applicability of the existing AD. 
This amendment is prompted by reports of failure of shear pins in the 
aileron flutter damper. The actions specified by this AD are intended 
to prevent damage to the aileron hinge fittings due to failed shear 
pins, and consequent reduced controllability of the airplane.

DATES: Effective October 21, 1997.
    The incorporation by reference of Canadair Service Bulletin S.B. 
601R-27-065, dated September 16, 1996, as listed in the regulations, is 
approved by the Director of the Federal Register as of October 21, 
1997.
    The incorporation by reference of Canadair Regional Jet Alert 
Service Bulletin S.B. A601R-27-058, Revision `A,' dated September 8, 
1995, as listed in the regulations, was approved previously by the 
Director of the Federal Register as of January 4, 1996 (60 FR 65521, 
December 20, 1995).

ADDRESSES: The service information referenced in this AD may be 
obtained from Bombardier, Inc., Canadair Aerospace Group, P.O. Box 
6087, Station Centre-ville, Quebec H3C 3G9, Canada. This information 
may be examined at the Federal Aviation Administration (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.

FOR FURTHER INFORMATION CONTACT: Franco Pieri, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7526; 
fax (568) 258-2716.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 95-26-07, 
amendment 39-9465 (60 FR 65521, December 20, 1995), which is applicable 
to certain Bombardier Model CL-600-2B19 series airplanes, was published 
in the Federal Register on April 15, 1997 (62 FR 18302). The action 
proposed to continue to require a revision to the Limitations Section 
of the Airplane Flight Manual (AFM) to provide the flight crew with 
procedures to check the travel range of the aileron. It also proposed 
to continue to require inspection for damage of the shear pins of the 
aileron flutter damper and aileron hinge fittings, and various follow-
on actions. In addition, the action proposed to add a requirement for 
accomplishment of an installation that eliminates the need for the AFM 
revisions, and to add airplanes to the applicability of the existing 
AD.
    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 41 Bombardier Model CL-600-2B19 series 
airplanes of U.S. registry that will be affected by this AD.
    The actions that are currently required by AD 95-26-07 take 
approximately 10 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 currently required actions on U.S. operators is estimated 
to be $24,600, or $600 per airplane.
    The new actions that are required in this AD action will take 
approximately 7 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will be supplied by the 
manufacturer at no cost to the operators. Based on these figures, the 
cost impact of the requirements of this AD on U.S. operators is 
estimated to be $17,220, or $420 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.

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 39-9465 (60 FR 
65521, December 20, 1995), and by adding a new airworthiness directive 
(AD), to read as follows:

97-19-11  Bombardier, Inc. (Formerly Canadair): Amendment 39-10132. 
Docket 97-NM-48-AD. Supersedes AD 95-26-07, Amendment 39-9465.

    Applicability: Model CL-600-2B19 (Regional Jet Series 100) 
series airplanes, serial numbers 7003 through 7134 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 
otherwise 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 damage to the aileron hinge fittings due to failure 
of the shear pins, and

[[Page 48479]]

consequent reduced controllability of the airplane, accomplish the 
following:

Restatement of Actions Required by AD 95-26-07

    (a) For airplanes having serial numbers 7003 through 7079 
inclusive: Within 7 days after January 4, 1996 (the effective date 
of AD 95-26-07, amendment 39-9465), revise the Limitations Section 
of the FAA-approved Airplane Flight Manual (AFM) to include the 
following. This may be accomplished by inserting a copy of this AD 
in the AFM.
    ``Before engine start, prior to the first flight of each day, 
the flight crew or certificated maintenance personnel shall perform 
a check of the travel range of the aileron as follows:

Aileron--Check travel range (to approx 1/2 travel) using each 
hydraulic system in turn, with the other hydraulic systems 
depressurized.''

    Note 2: This AFM revision may also be accomplished by inserting 
a copy of Temporary Revision RJ/45, dated September 7, 1995, or 
Temporary Revision RJ/45-2, dated April 30, 1996, in the AFM. When 
these temporary revisions have been incorporated into general 
revisions of the AFM, the general revisions may be inserted in the 
AFM, provided the information contained in the general revisions is 
identical to that specified in Temporary Revision RJ/45 or RJ/45-2.
    Note 3: Operators should note that operation of the aircraft 
remains restricted to the altitude and airspeed limits currently 
specified in the FAA-approved AFM, Revision 34, Chapter 5, Abnormal 
Procedures, Section 13, Hydraulic Power, Paragraphs ``A'' through 
``C'' and ``M'' through ``O.''

    (b) For airplanes having serial numbers 7003 through 7079 
inclusive: Perform a visual inspection to detect damage of the shear 
link, the shear pin, and the aileron attachment fitting, in 
accordance with Canadair Regional Jet Alert Service Bulletin S.B. 
A601R-27-058, Revision 'A,' dated September 8, 1995, at the time 
specified in paragraph (b)(1) or (b)(2) of this AD, as applicable.
    (1) For airplanes having serial numbers 7003 through 7054 
inclusive: Inspect at the next scheduled shear pin replacement, but 
no later than 30 days after January 4, 1996.
    (2) For airplanes having serial numbers 7055 through 7079 
inclusive: Inspect at the next scheduled shear pin replacement, but 
no later than 400 flight hours after January 4, 1996.
    (c) If no shear pin is found to be damaged during the inspection 
required by paragraph (b) of this AD, accomplish the requirements of 
either paragraph (c)(1) or (c)(2), as applicable, at the times 
specified:
    (1) For airplanes having serial numbers 7003 through 7054 
inclusive: At the next scheduled shear pin replacement, but no later 
than 400 flight hours after accomplishing the inspection specified 
in paragraph (b) of this AD, remove the aileron flutter dampers, 
shear link, and pivot, in accordance with Canadair Regional Jet 
Alert Service Bulletin S.B. A601R-27-058, Revision `A,' dated 
September 8, 1995. Following removal of the flutter dampers, the 
shear pin replacement in accordance with the FAA-approved 
maintenance program is not required.
    (2) For airplanes having serial numbers 7055 through 7079 
inclusive: Repeat the inspection required by paragraph (b) of this 
AD at intervals not to exceed 400 flight hours. At the next 
scheduled shear pin replacement, but no later than 1,500 landings 
after accomplishing the initial inspection specified in paragraph 
(b) of this AD, remove the aileron flutter dampers, shear link, and 
pivot, in accordance with Canadair Regional Jet Alert Service 
Bulletin S.B. A601R-27-058, Revision `A,' dated September 8, 1995. 
Following removal of the flutter dampers, the shear pin replacement 
in accordance with the FAA-approved maintenance program is not 
required.
    (d) If any shear pin is found to be damaged during the 
inspection required by paragraph (b) of this AD, prior to further 
flight, remove the aileron flutter dampers, shear link, and pivot, 
in accordance with Canadair Regional Jet Alert Service Bulletin S.B. 
A601R-27-058, Revision `A,' dated September 8, 1995. Following 
removal of the flutter dampers, shear pin replacement in accordance 
with the FAA-approved maintenance program is not required.
    (e) If any aileron hinge fitting is found to be damaged during 
the inspection required by paragraph (b) of this AD, prior to 
further flight, repair in accordance with Canadair Regional Jet 
Alert Service Bulletin S.B. A601R-27-058, Revision `A,' dated 
September 8, 1995.

New Actions Required by this AD

    (f) For airplanes having serial numbers 7080 through 7134 
inclusive: Within 7 days after the effective date of this AD, revise 
the Limitations Section of the FAA-approved AFM to include the 
following. This may be accomplished by inserting a copy of this AD 
in the AFM.
    ``Before engine start, prior to the first flight of each day, 
the flight crew or certificated maintenance personnel shall perform 
a check of the travel range of the aileron as follows:

    Aileron--Check travel range (to approx \1/2\ travel) using each 
hydraulic system in turn, with the other hydraulic systems 
depressurized.''

    Note 4: This AFM revision may also be accomplished by inserting 
a copy of Temporary Revision RJ/45-2, dated April 30, 1996, in the 
AFM. When this temporary revision has been incorporated into general 
revisions of the AFM, the general revisions may be inserted in the 
AFM, provided the information contained in the general revisions is 
identical to that specified in Temporary Revision RJ/45-2.
    Note 5: Operators should note that operation of the aircraft 
remains restricted to the altitude and airspeed limits currently 
specified in the FAA-approved AFM, Revision 34, Chapter 5, Abnormal 
Procedures, Section 13, Hydraulic Power, Paragraphs ``A'' through 
``C'' and ``M'' through ``O.''

    (g) For airplanes having serial numbers 7003 through 7134 
inclusive: Within 18 months after the effective date of this AD, 
install redesigned aileron flutter damper shear pins and shear 
links, aileron flutter dampers, pivots, and new shear link 
assemblies; in accordance with Canadair Service Bulletin S.B. 601R-
27-065, dated September 16, 1996. Accomplishment of this 
installation constitutes terminating action for the AFM revisions 
required by paragraphs (a) and (f) of this AD.
    (h) As of the effective date of this AD, no person shall install 
an aileron flutter damper assembly, part number 600-10179-1, on any 
airplane.
    (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, 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 6: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York ACO.

    (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.
    (k) The inspections, removal, and repair shall be done in 
accordance with
    [Canadair Regional Jet Alert Service Bulletin S.B. A601R-27-058, 
Revision `A,' dated September 8, 1995. The incorporation by 
reference of that document was approved previously by the Director 
of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51, as of January 4, 1996 (60 FR 65521, December 20, 1995). 
The installation shall be done in accordance with Canadair Service 
Bulletin S.B. 601R-27-065, dated September 16, 1996. The 
incorporation by reference of this document is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Copies of either document may be obtained from 
Bombardier, Inc., Canadair Aerospace Group, P.O. Box 6087, Station 
Centreville, Quebec H3C 3G9, Canada. Copies may be inspected at the 
Federal Aviation Administration (FAA), Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 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.
    (l) This amendment becomes effective on October 21, 1997.

    Issued in Renton, Washington, on September 9, 1997.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-24341 Filed 9-15-97; 8:45 am]
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