[Federal Register Volume 62, Number 22 (Monday, February 3, 1997)]
[Proposed Rules]
[Pages 4941-4944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-2519]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-108-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional
Jet Series 100) Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain Bombardier Model
CL-600-2B19 (Regional Jet Series 100) series airplanes. That AD
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 new proposed action would 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 require replacement
of discrepant parts with serviceable parts. This proposed action also
would require installation of new elevator flutter dampers, and
replacement of shear pins and shear links with new, improved pins and
links.
DATES: Comments must be received by March 14, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-108-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule 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 FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and
Propeller Directorate, New York Aircraft Certification Office, 181
South Franklin Avenue, Valley Stream, New York.
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;
[[Page 4942]]
telephone (516) 256-7526; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 96-NM-108-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 96-NM-108-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On November 17, 1994, the FAA issued AD 94-24-02, amendment 39-9075
(59 FR 60888, November 29, 1994), applicable to certain Bombardier
Model CL-600-2B19 series airplanes. That AD requires:
1. the removal of all elevator flutter dampers; and
2. a revision to the FAA-Approved 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.
In addition, that AD retained the requirements from AD 94-01-09,
amendment 39-8791 (59 FR 1471, January 11, 1994), to revise the AFM to
restrict altitude and airspeed operations under conditions of single or
double hydraulic system failure.
That AD was prompted by reports that the installation of certain
shear pins may jam or restrict movement of the elevator. The
requirements of that AD are intended to prevent failure of the lugs
and/or pins. Such failure could increase the likelihood of jamming or
restricting movement of the elevator, which could result in an adverse
effect on the controllability of the airplane.
Actions Since Issuance of Previous Rule
Since the issuance of that AD, the manufacturer has issued Canadair
Regional Jet Service Bulletin S.B. 601R-27-040, Revision `B,' dated
September 11, 1995. For certain airplanes, this service bulletin
describes procedures for a visual inspection to detect deformation or
discrepancies of the flutter damper hinge fitting and lug of the
horizontal stabilizer, and of the elevator hinge/damper fitting and
shear pin lugs; a fluorescent penetrant inspection and a dimensional
inspection to detect any deformation or discrepancy of the shear pin
lugs; and replacement of discrepant parts with serviceable parts. For
these and other airplanes, this service bulletin also describes
procedures for installation of a new elevator flutter damper having a
reduced load capacity, and for replacement of the shear pins and shear
links with new, improved shear pins and links.
Accomplishment of the actions described in that service bulletin
will improve the integrity of the elevator damping system and increase
the service fatigue life of the flutter damper.
The manufacturer also has issued two general revisions to the AFM
for these airplanes:
Revision 32, dated March 30, 1995, which advises the
flight crew of the need to perform daily checks to verify proper
operation of the elevator control system.
Revision 34, dated June 12, 1995, which specifies certain
altitude and airspeed restrictions to prevent flight control undamped
vibration during hydraulic system failure.
Transport Canada Aviation, which is the airworthiness authority for
Canada, classified the service bulletin and AFM revisions as mandatory,
and issued Canadian airworthiness directive CF-94-21R1, dated November
3, 1995, in order to assure the continued airworthiness of these
airplanes in Canada.
FAA's Conclusions
This airplane model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, Transport Canada Aviation has kept
the FAA informed of the situation described above. The FAA has examined
the findings of Transport Canada Aviation, reviewed all available
information, and determined that AD action is necessary for products of
this type design that are certificated for operation in the United
States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would supersede AD 94-24-02. It
would continue to require the removal of the originally installed
elevator dampers. It also would continue to require revisions to the
Limitations Section of the FAA-approved 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.
As stated in this proposal, these revisions could be accomplished by
inserting a copy of this AD or the new AFM revisions, described
previously, in the AFM.
For certain airplanes, this new proposed AD would require
inspections to detect deformation or discrepancies of the flutter
damper hinge fitting and lug of the horizontal stabilizer, the elevator
hinge/damper fitting, and the shear pin lugs; and 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. These actions would be required to be
accomplished in accordance with the service bulletin described
previously.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Difference Between the Proposed AD and the Service Information
Operators should note that, the effectivity listing of AFM Revision
32, dated March 30, 1995 (which advises the flight crew of the need to
perform
[[Page 4943]]
daily checks of the elevator control system), indicates that it applies
only to those airplanes having serial numbers 7002 through 7054 and on
which Canadair Regional Jet Service Bulletin S.B. 601R-27-040 (Part A)
has not been accomplished. However, this proposed AD would require that
the AFM revision be accomplished for those airplanes, regardless of
whether or not the procedures specified in the Canadair service
bulletin have been accomplished. The FAA has been specifically advised
by Transport Canada Aviation that the accomplishment of the service
bulletin procedures should not be considered as a ``terminating
action'' for the AFM revision. Further, the parallel Canadian
airworthiness directive continues to require this revision of the AFM.
In light of this, the FAA has determined that, until final action
addressing the unsafe condition is developed, the revision of the AFM
must be required in addition to the procedures specified in the
Canadair Regional Jet service bulletin.
Cost Impact
There are approximately 21 Bombardier Model CL-600-2B19 (Regional
Jet Series 100) series airplanes of U.S. registry that would be
affected by this proposed AD.
The actions that are currently required by AD 94-24-02, and
retained in this proposal, 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 on U.S. operators of the actions
currently required 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 airplanes that would require the inspections that are proposed
in this AD, it would 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 proposed inspections on U.S.
operators is estimated to be $1,560 per airplane.
The installations that are proposed in this AD would take
approximately 12 work hours per airplane to accomplish them, at an
average labor rate of $60 per work hour. Required parts would be
provided by the manufacturer at no cost to the operator. Based on these
figures, the cost impact on U.S. operators of the proposed
installations 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 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 proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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), to read as follows:
Bombardier, Inc. (Formerly Canadair): 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
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 (d) 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 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.
------------------------------------------------------------------------
Altitude limit (maximum) Airspeed limit (maximum)
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Single Hydraulic System Failure
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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).
26,00 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
------------------------------------------------------------------------
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.
[[Page 4944]]
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
paragraph (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.
Issued in Renton, Washington, on January 27, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-2519 Filed 1-31-97; 8:45 am]
BILLING CODE 4910-13-U
