[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]
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