[Federal Register Volume 60, Number 96 (Thursday, May 18, 1995)]
[Proposed Rules]
[Pages 26700-26702]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-12208]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-18-AD]
Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600),
CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A and -3R), and 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-600-1A11, CL-600-2A12, CL-600-2B16, and CL-600-2B19 series
airplanes, that currently requires an inspection to detect cracking in
the rudder control quadrant; replacement of any cracked quadrant with a
new assembly; and retorquing of the castellated nut, as necessary. This
action would require a follow-on inspection of certain rudder control
quadrants to detect cracks that start at the inside root radius of the
spigot; modification of any cracked quadrant; and eventual modification
of certain quadrants. This action also would add airplanes to the
applicability of the existing AD. This proposal is prompted by the
development of a modification, which, when installed, will positively
address the identified unsafe condition. The actions specified by the
proposed AD are intended to prevent loss of rudder control due to
stress corrosion of the rudder control quadrant.
DATES: Comments must be received by June 19, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-18-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 Canadair, Aerospace Group, P.O. Box 6087, Station Centre-
ville, 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, 10 Fifth Street, Third Floor, Valley
Stream, New York.
FOR FURTHER INFORMATION CONTACT: Franco Pieri, Aerospace Engineer,
Airframe Branch, ANE-172, 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 (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 95-NM-18-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. 95-NM-18-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On November 1, 1993, the FAA issued AD 93-22-04, amendment 39-8729
(58 FR 59161, November 8, 1993), which is applicable to certain
Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-
2B16 (CL-601-3A and -3R), and CL-600-2B19 (Regional Jet Series 100)
series airplanes. That AD requires a one-time ultrasonic or fluorescent
penetrant inspection to detect cracking in the rudder control quadrant;
replacement of any cracked quadrant with a new assembly; and retorquing
of the castellated nut, as necessary. That action was prompted by a
report of an in-flight failure of a rudder control quadrant, which
resulted from stress corrosion. The requirements of that AD are
intended to prevent loss of rudder control.
In the preamble to AD 93-22-04, the FAA indicated that it
considered that AD to be interim action, and that further rulemaking
action would be considered once final action was identified. Bombardier
has now developed a modification that will positively address the
unsafe condition described in the AD by providing better resistance of
the rudder quadrant against stress corrosion.
Bombardier has issued the following service bulletins, which
describe procedures for a one-time ultrasonic inspection of certain
rudder control quadrants to detect cracks that start at the inside root
radius of the spigot, and modification of any cracked quadrant.
1. Canadair Challenger Service Bulletin No. 600-0637, Revision 1,
dated November 15, 1994 (for Model CL-600-1A11 series airplanes);
2. Canadair Challenger Service Bulletin No. 601-0426, Revision 1,
dated November 15, 1994 (for Model CL-600-2A12 and -2B16 series
airplanes); and [[Page 26701]]
3. Canadair Regional Jet Alert Service Bulletin S.B. A601R-27-011,
Revision `A,' dated September 21, 1993, as revised by Notice of
Revision A601R-27-011A-1, dated October 6, 1993, or Notice of Revision
A601R-27-011A-2, dated June 14, 1994 (for Model CL-600-2B19 series
airplanes).
The first two service bulletins also describe procedures for
eventual modification of certain rudder control quadrants. (Bombardier
issued Canadair Service Bulletin S.B. 601R-27-015, Revision `A,' dated
October 31, 1994, to specify these procedures for Model CL-600-2B19
series airplanes.) The modification involves removal and disassembly of
the quadrant assembly and installation of a modified quadrant assembly.
Transport Canada Aviation, which is the airworthiness authority for
Canada, classified these service bulletins as mandatory and issued
Canadian airworthiness directive CF-94-23, dated December 1, 1994, in
order to assure the continued airworthiness of these airplanes in
Canada.
These airplane models are manufactured in Canada and are type
certificated for operation in the United States under the provisions of
Sec. 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.
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 93-22-04. It
would no longer require the inspections currently specified in that AD,
but would require instead a one-time ultrasonic inspection of certain
rudder control quadrants to detect cracks that start at the inside root
radius of the spigot; modification of any cracked quadrant; and
eventual modification of certain quadrants. These actions would be
required to be accomplished in accordance with the service bulletins
described previously.
This proposed AD also would expand the applicability of the
existing rule to include additional airplanes that have been identified
as subject to the addressed unsafe condition.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been included in this notice to clarify this long-standing requirement.
The FAA estimates that 212 airplanes of U.S. registry would be
affected by this proposed AD.
Accomplishment of the proposed inspection would take approximately
4 work hours per airplane, at an average labor rate of $60 per work
hour. Based on these figures, the total cost impact of the proposed
inspection action on U.S. operators is estimated to be $50,880, or $240
per airplane.
Accomplishment of the proposed modification would take
approximately 20 work hours per airplane, at an average labor rate of
$60 per work hour. Required parts would be provided by the manufacturer
at no cost to operators. Based on these figures, the total cost impact
of the proposed modification action on U.S. operators is estimated to
be $254,400, or $1,200 per airplane.
Based on the figures discussed above, the total cost impact of this
proposed rule on U.S. operators is estimated to be $305,280. This total
cost impact figure is based on assumptions that no operator has yet
accomplished any of the proposed requirements of this AD action, and
that no operator would accomplish those actions in the future if this
AD were not adopted.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-8729 (58 FR
59161, November 8, 1993), and by adding a new airworthiness directive
(AD), to read as follows:
Bombardier, Inc. (Formerly Canadair): Docket 95-NM-18-AD.
Supersedes AD 93-22-04, Amendment 39-8729.
Applicability: Model CL-600-1A11 (CL-600) series airplanes,
serial numbers 1004 through 1085 inclusive; Model CL-600-2A12 (CL-
601) series airplanes, serial numbers 3001 through 3066 inclusive;
Model CL-600-2B16 (CL-601-3A and -3R) series airplanes, serial
numbers 5001 through 5147 inclusive; and CL-600-2B19 (Regional Jet
Series 100) series airplanes, serial numbers 7003 through 7038
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 use the authority
provided in paragraph (c) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition; or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification,
[[Page 26702]] alteration, or repair remove any airplane from the
applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of rudder control, accomplish the following:
(a) Within 45 days after the effective date of this AD, perform
an ultrasonic inspection to detect cracks at the inside root radius
of the spigot of the rudder quadrant, part number (P/N) 600-92614-1
(original quadrant) or P/N 600-92614-3 (quadrant modified with
undercut), in accordance with the procedures specified in Canadair
Challenger Service Bulletin No. 600-0637, Revision 1, dated November
15, 1994 (for Model CL-600-1A11 series airplanes); Canadair
Challenger Service Bulletin No. 601-0426, Revision 1, dated November
15, 1994 (for Model CL-600-2A12 and -2B16 series airplanes); or
Canadair Regional Jet Alert Service Bulletin S.B. A601R-27-011,
Revision `A,' dated September 21, 1993, as revised by Notice of
Revision A601R-27-011A-1, dated October 6, 1993, and Notice of
Revision A601R-27-011A-2, dated June 14, 1994 (for Model CL-600-2B19
series airplanes); as applicable. A fluorescent penetrant inspection
may be accomplished in lieu of the ultrasonic inspection provided
that the rudder control quadrant assembly is removed prior to
inspection. Accomplishment of the modification required by paragraph
(b) of this AD eliminates the need for the inspection required by
this paragraph, provided that the modification is accomplished
within 45 days after the effective date of this AD.
Note 2: Rudder quadrants having P/N's 600-92614-1 and -3 are
part of the rudder quadrants having P/N's 600-92619-1 and -5,
respectively.
(1) If any crack is detected, prior to further flight, modify
the rudder control quadrant in accordance with Canadair Service
Bulletin No. 600-0637, Revision 1, dated November 15, 1994 (for
Model CL-600-1A11 series airplanes); Canadair Service Bulletin No.
601-0426, Revision 1, dated November 15, 1994 (for Model CL-600-2A12
and -2B16 series airplanes); or Canadair Service Bulletin S.B.
A601R-27-015, Revision `A,' dated October 31, 1994 (for Model CL-
600-2B19 series airplanes); as applicable.
(2) If no crack is detected, no further action is required by
paragraph (a) of this AD.
(b) Within 6 months after the effective date of this AD, modify
the rudder control quadrant, P/N 600-92619-1 or 600-92619-5, in
accordance with Canadair Service Bulletin No. 600-0637, Revision 1,
dated November 15, 1994 (for Model CL-600-1A11 series airplanes);
Canadair Service Bulletin No. 601-0426, Revision 1, dated November
15, 1994 (for Model CL-600-2A12 and -2B16 series airplanes); or
Canadair Service Bulletin S.B. A601R-27-015, Revision `A,' dated
October 31, 1994 (for Model CL-600-2B19 series airplanes); as
applicable. Accomplishment of this modification eliminates the need
for the inspection required by paragraph (a) of this AD.
(c) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(d) 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 May 12, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-12208 Filed 5-17-95; 8:45 am]
BILLING CODE 4910-13-U
