[Federal Register Volume 59, Number 43 (Friday, March 4, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-3104]
[[Page Unknown]]
[Federal Register: March 4, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-NM-135-AD; Amendment 39-8820, AD 94-04-02]
Airworthiness Directives; Canadair Model Turboprop CL-215-6B11
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-215-6B11 series airplanes, that
requires inspections to detect cracking in the rear engine mount
struts, and replacement of struts with new struts, if necessary; and
the eventual replacement of all struts with new struts. This amendment
is prompted by reports of failures of these rear engine mount struts
due to cracking that was caused by rosette welds on the shank of the
struts not achieving full weld penetration during manufacture. The
actions specified by this AD are intended to prevent failure of the
rear engine mount struts, which could subsequently result in reduced
structural integrity of the nacelle and engine support structure.
DATES: Effective April 4, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 4, 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: Jeff Casale, Aerospace Engineer,
Airframe Branch, ANE-172, FAA, Engine and Propeller Directorate, New
York Aircraft Certification Office, 181 South Franklin Avenue, room
202, Valley Stream, New York 11581; telephone (516) 791-6220; 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-215-6B11 series airplanes was
published in the Federal Register on October 13, 1993 (58 FR 52931).
That action proposed to require repetitive visual inspections to detect
cracking in the rear engine mount struts, and replacement of struts
with new struts, if necessary. That action also proposed to require the
eventual replacement of all struts with new struts; such replacement
would constitute terminating action for the visual inspections.
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.
Currently, there are no Canadair Model CL-215-6B11 series airplanes
on the U.S. Register. However, should an affected airplane be imported
and placed on the U.S. Register in the future, it would take
approximately 10 work hours per airplane to accomplish the required
actions, and that the average labor rate is $55 per work hour. Required
parts will be provided by the manufacturer at no cost to the operators.
Based on these figures, the total cost impact of the AD will be $550
per airplane.
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:
94-04-02 Canadair: Amendment 39-8820. Docket 93-NM-135-AD.
Applicability: Model CL-215-6B11 series airplanes, serial
numbers 1057, 1061, 1080, 1113 through 1115 inclusive, 1121, 1122,
1124, and 1125; turboprop versions only; certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the rear engine mount struts, which could
subsequently result in reduced structural integrity of the nacelle
and engine support structure, accomplish the following:
(a) Within 50 hours time-in-service after the effective date of
this AD, perform a visual inspection to detect cracking in the rear
engine mount struts, part number (P/N) 87110016-003, in accordance
with Canadair Alert Service Bulletin 215-A3040, dated September 2,
1992.
(1) If no cracking is detected, repeat the visual inspection
thereafter at intervals not to exceed 50 hours time-in-service,
until the requirements of paragraph (b) of this AD are accomplished.
(2) If any cracking is detected, prior to further flight,
replace the engine rear mount strut with a new strut, P/N 87110016-
009 or -011, in accordance with the service bulletin.
(b) Within 2 years after the effective date of this AD, replace
all engine rear mount struts, with new struts, P/N 87110016-009 or -
011, in accordance with Canadair Alert Service Bulletin 215-A3040,
dated September 2, 1992. Such replacement constitutes terminating
action for the inspections required by this AD.
(c) As of the effective date of this AD, no person shall install
a rear engine mount strut, P/N 87110016-003, on any airplane.
(d) 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: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(e) Special flight permits may be issued in accordance with
Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the
airplane to a location where the requirements of this AD can be
accomplished.
(f) The inspections and replacement shall be done in accordance
with Canadair Alert Service Bulletin 215-A3040 dated September 2,
1992. 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.
(g) This amendment becomes effective on April 4, 1994.
Issued in Renton, Washington, on February 4, 1994.
N.B. Martenson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-3104 Filed 3-3-94; 8:45 am]
BILLING CODE 4910-13-U
