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