[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]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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]
BILLING CODE 4910-13-U