[Federal Register Volume 59, Number 76 (Wednesday, April 20, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-9338]


[[Page Unknown]]

[Federal Register: April 20, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 93-NM-188-AD; Amendment 39-8888; AD 94-08-15]

 

Airworthiness Directives; Canadair Model CL-600-2A12 (CL-601) and 
CL-600-2B16 (CL-601-3A) Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Canadair Model CL-600-2A12 and CL-600-2B16 series 
airplanes, that requires a one-time visual inspection to verify proper 
installation of shoulder bolts and to detect damage of the adjacent 
flap actuator housings, and correction of discrepancies. This amendment 
is prompted by a report of failure of the flap actuator on the left 
wing inboard flap. The actions specified by this AD are intended to 
prevent asymmetric deployment or retraction (blow back) of the flaps, 
which could reduce controllability of the airplane.

DATES: Effective May 20, 1994.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 20, 1994.

ADDRESSES: The service information referenced in this AD may be 
obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 
6087, Station A, 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, 181 South Franklin Avenue, room 202, 
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: Danko Kramar, Aerospace Engineer, 
Systems and Equipment Branch, ANE-173, FAA, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 181 South Franklin 
Avenue, room 202, Valley Stream, New York 11581; telephone (516) 791-
6428; fax (516) 791-9024.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations to include an airworthiness directive (AD) that is 
applicable to certain Canadair Model CL-600-2A12 and CL-600-2B16 series 
airplanes was published in the Federal Register on December 29, 1993 
(58 FR 68789). That action proposed to require a one-time visual 
inspection to verify proper installation of shoulder bolts and to 
detect damage of adjacent flap actuator housings, and correction of 
discrepancies.
    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 determined that air safety and the public interest require 
the adoption of the rule as proposed.
    The FAA estimates that 196 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the required visual inspection, and that the 
average labor rate is $55 per work hour. Based on these figures, the 
total cost impact of the AD on U.S. operators is estimated to be 
$10,780, or $55 per airplane.
    The total cost impact figure discussed above 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.
    If replacement of any hinge fitting lug, shoulder bolt, or flap 
actuator is necessary, accomplishment of such replacement will entail 
approximately 12 work hours, at an average labor rate of $55 per work 
hour. Required parts will be provided by the manufacturer at no cost to 
the operator. Based on these figures, the total cost of any necessary 
replacement is estimated to be $660 per replaced item.
    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 14 CFR part 
39 of the Federal Aviation Regulations 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 adding the following new 
airworthiness directive:

94-08-15 Canadair: Amendment 39-8888. Docket 93-NM-188-AD.

    Applicability: Model CL-600-2A12 series airplanes, serial 
numbers 3002 through 3066, inclusive; and Model CL-600-2B16 series 
airplanes, serial numbers 5001 through 5131, inclusive; certificated 
in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent asymmetric deployment or retraction (blow back) of 
the flaps, which could reduce the controllability of the airplane, 
accomplish the following:
    (a) Within 30 days after the effective date of this AD, conduct 
a visual inspection to verify the proper installation of shoulder 
bolts, and to detect damage of adjacent flap actuator housings, in 
accordance with Canadair Alert Service Bulletin A601-0415, dated 
June 25, 1993 (hereafter referred to as ``the alert service 
bulletin'').

    Note 1: Inspections accomplished prior to the effective date in 
accordance with Canadair Alert Service Wire TA601-0415-036, dated 
May 3, 1993, are considered to be in compliance with this paragraph.

    (b) If all shoulder bolts are found to be installed properly and 
no flap actuator housings are found to be damaged, no further action 
is required by this AD.
    (c) If any shoulder bolt is found to be improperly installed, 
but no flap actuator housing is found to be damaged, prior to 
further flight, remove the improperly installed shoulder bolt and 
reinstall it in accordance with the alert service bulletin.
    (d) If any flap actuator housing is found to be damaged (as 
defined in the alert service bulletin), prior to further flight, 
accomplish the requirements of paragraphs (d)(1) and (d)(2) of this 
AD:
    (1) Perform either an eddy current inspection or a dye penetrant 
inspection to detect cracking of the hinge fitting lugs on the flap 
actuator in accordance with the alert service bulletin. If any 
cracking is detected, prior to further flight, replace the hinge 
fitting lug with new or serviceable parts in accordance with the 
alert service bulletin.
    (2) Replace the shoulder bolt and damaged flap actuator with new 
or serviceable parts in accordance with the alert service bulletin.
    (e) 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York ACO.

    (f) 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.
    (g) The inspections, replacement, removal, and reinstallation 
shall be done in accordance with Canadair Alert Service Bulletin 
A601-0415, dated June 25, 1993, including Appendix 1. 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 Bombardier, Inc., Canadair, 
Aerospace Group, P.O. Box 6087, Station A, 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, 181 South Franklin Avenue, room 202, Valley 
Stream, New York; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.
    (h) This amendment becomes effective on May 20, 1994.

    Issued in Renton, Washington, on April 13, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-9338 Filed 4-19-94; 8:45 am]
BILLING CODE 4910-13-U