[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
