[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]



=======================================================================
-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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]
BILLING CODE 4910-13-U