[Federal Register Volume 60, Number 188 (Thursday, September 28, 1995)]
[Rules and Regulations]
[Pages 50089-50091]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-21593]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-18-AD; Amendment 39-9354; AD 95-18-07]
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: Final rule.
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SUMMARY: This amendment supersedes 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 amendment requires 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
amendment also adds airplanes to the applicability of the existing AD.
This amendment is prompted by the development of a modification, which,
when installed, will positively address the identified unsafe
condition. The actions specified by this AD are intended to prevent
loss of rudder control due to stress corrosion of the rudder control
quadrant.
DATES: Effective October 30, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 30, 1995.
ADDRESSES: The service information referenced in this AD 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
Federal Aviation Administration (FAA), Transport Airplane Directorate,
Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA,
New York Aircraft Certification Office, Engine and Propeller
Directorate, 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 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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding 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, was published in the Federal Register on May 18,
1995 (60 FR 26700). The action proposed to require 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. The action also proposed to expand the
[[Page 50090]]
applicability of the existing rule to include additional airplanes that
have been identified as subject to the addressed unsafe condition.
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.
The FAA has revised paragraphs (a)(1) and (b) of the final rule to
correct a service bulletin citation for Model CL-600-2B19 series
airplanes. The proposed rule incorrectly specified the service bulletin
number for Canadair Service Bulletin S.B. 601R-27-015, Revision `A,'
dated October 31, 1994, as ``Canadair Service Bulletin S.B. A601R-27-
015.'' (The preamble to the proposed rule reflected the correct service
bulletin citation.)
After careful review of the available data, the FAA has determined
that air safety and the public interest require the adoption of the
rule with the change previously described. The FAA has determined that
this change will neither increase the economic burden on any operator
nor increase the scope of the AD.
The FAA estimates that 212 airplanes of U.S. registry will be
affected by this AD.
Accomplishment of the inspection will 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 inspection action
on U.S. operators is estimated to be $50,880, or $240 per airplane.
Accomplishment of the modification will take approximately 20 work
hours per airplane, at an average labor rate of $60 per work hour.
Required parts will be provided by the manufacturer at no cost to
operators. Based on these figures, the total cost impact of the
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
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 requirements of this AD action, and that no
operator would accomplish those actions in the future if this AD were
not adopted.
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 USC 106(g), 40101, 40113, 44701.
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), amendment 39-9354, to read as follows:
95-18-07 Bombardier, Inc. (Formerly Canadair): Amendment 39-9354.
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) of this AD 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, 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 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
Service Bulletin S.B. 601R-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 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,
[[Page 50091]]
Revision 1, dated November 15, 1994 (for Model CL-600-2A12 and -2B16
series airplanes); or Canadair Service Bulletin S.B. 601R-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.
(e) The inspections and modifications shall be done in
accordance with Canadair Challenger Service Bulletin No. 600-0637,
Revision 1, dated November 15, 1994; Canadair Challenger Service
Bulletin No. 601-0426, Revision 1, dated November 15, 1994; 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; or Canadair Service Bulletin S.B. 601R-27-
015, Revision `A,' dated October 31, 1994; as applicable. This
incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Copies may be obtained from Canadair, Aerospace Group, P.O. Box
6087, Station Centre-ville, Quebec H3C 3G9, Canada. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft
Certification Office, Engine and Propeller Directorate, 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.
(f) This amendment becomes effective on October 30, 1995.
Issued in Renton, Washington, on August 29, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-21593 Filed 9-27-95; 8:45 am]
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