[Federal Register: May 17, 2004 (Volume 69, Number 95)]
[Rules and Regulations]
[Page 27831-27833]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17my04-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-199-AD; Amendment 39-13634; AD 2004-10-04]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-215-6B11 (CL215T
Variant), and CL-215-6B11 (CL415 Variant) Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Bombardier Model CL-215-6B11 series
airplanes, that currently 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 requires adding repetitive detailed
inspections to detect cracking in the rear engine mount struts and
replacement of struts with new struts, if necessary. This amendment
also expands the applicability of the existing AD and makes the
replacement of all struts with new, machined struts an optional
terminating action for the repetitive inspections. 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. This action is
intended to address the identified unsafe condition.
DATES: Effective June 21, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 21, 2004.
The incorporation by reference of Canadair Alert Service Bulletin
215-A3040, dated September 2, 1992, as listed in the regulations, was
approved previously by the Director of the Federal Register as of April
4, 1994 (59 FR 10272, March 4, 1994).
ADDRESSES: The service information referenced in this AD may be
obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box
6087, Station Centre-ville, 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; at the FAA, New York Aircraft Certification
Office, 1600 Stewart Avenue, suite 410, Westbury, New York; or at the
National Archives and Records Administration (NARA). For information on
the availability of this material at NARA, call 202-741-6030, or go to:
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: David Lawson, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Westbury, New York 11590;
telephone (516) 228-7327; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 94-04-02,
amendment 39-8820 (59 FR 10272, March 4, 1994), which is applicable to
certain Bombardier Model CL-215-6B11 series airplanes, was published in
the Federal Register on February 13, 2004 (69 FR 7179). The action
proposed
[[Page 27832]]
to continue to require 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.
The action also proposed to require adding repetitive detailed
inspections to detect cracking in the rear engine mount struts and
replacement of struts with new struts, if necessary. The action also
proposed to expand the applicability of the existing AD and make the
replacement of all struts with new, machined struts an optional
terminating action for the repetitive inspections.
Comments
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.
Explanation of Change to Cost Impact
The Cost Impact section of the proposed AD states that
approximately 3 airplanes of U.S. registry would be affected by the
proposed AD. Since the issuance of the proposed AD, we have determined
that there are no airplanes currently on the U.S. Register that will be
affected by this AD. We have revised the Cost Impact section of this
final rule accordingly.
Conclusion
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.
Cost Impact
Currently, there are no affected airplanes on the U.S. Register.
However, if an affected airplane is imported and placed on the U.S.
Register in the future, the costs stated below would apply.
The actions that are currently required by AD 94-04-02 would take
about 10 work hours per airplane to accomplish, at an average labor
rate of $65 per work hour. Required parts would be provided by the
manufacturer at no cost to the operators. Based on these figures, we
estimate that the cost impact of the currently required actions would
be about $650 per airplane.
The new inspections that are required by this AD action would take
about 3 work hours per airplane to accomplish, at an average labor rate
of $65 per work hour. Based on these figures, the cost impact of these
inspections would be about $195 per airplane, per inspection cycle.
Regulatory Impact
The regulations adopted herein will not have a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
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
0
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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. Section 39.13 is amended by removing amendment 39-8820 (59 FR 10272,
March 4, 1994), and by adding a new airworthiness directive (AD),
amendment 39-13634, to read as follows:
2004-10-04 Bombardier, Inc. (Formerly Canadair): Amendment 39-13634.
Docket 2003-NM-199-AD. Supersedes AD 94-04-02, Amendment 39-8820.
Applicability: Model CL-215-6B11 (CL215T Variant) series
airplanes, serial numbers 1056, 1057, 1061, 1080, 1109, 1113 through
1122 inclusive, 1124, and 1125; and Model CL-215-6B11 (CL415
Variant) series airplanes, serial numbers 2001 through 2067
inclusive; 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:
Restatement of Requirements of AD 94-04-02
Inspection and Corrective Action
(a) For Model CL-215-6B11 series airplanes, serial numbers 1057,
1061, 1080, 1113 through 1115 inclusive, 1121, 1122, 1124, and 1125;
turboprop versions only: Within 50 hours time-in-service after April
4, 1994 (the effective date of AD 94-04-02, amendment 39-8820),
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) For Model CL-215-6B11 series airplanes, serial numbers 1057,
1061, 1080, 1113 through 1115 inclusive, 1121, 1122, 1124, and 1125;
turboprop versions only: Within 2 years after April 4, 1994, 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 paragraph (a) of this AD.
(c) For Model CL-215-6B11 series airplanes, serial numbers 1057,
1061, 1080, 1113 through 1115 inclusive, 1121, 1122, 1124, and 1125;
turboprop versions only: As of April 4, 1994, no person shall
install a rear engine mount strut, P/N 87110016-003, on any
airplane.
New Requirements of This AD
Inspection and Corrective Action
(d) For all airplanes: Within 50 flight hours after the
effective date of this AD, perform a detailed inspection to detect
cracking in the rear mount strut assemblies of the engines in
accordance with Bombardier Alert Service Bulletin 215-A3111,
Revision 2, dated January 23, 2003 (Model CL-215-6B11 (CL215T
Variant) series airplanes); or Bombardier Alert Service Bulletin
215-A4287, Revision 2, dated January 23, 2003 (Model CL-215-6B11
(CL415 Variant) series airplanes); as applicable. Accomplishment of
this detailed inspection constitutes terminating action for the
requirements of paragraph (a) of this AD.
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
[[Page 27833]]
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
(1) If no cracking is detected, repeat the detailed inspection
thereafter at intervals not to exceed 250 flight hours until the
requirements of paragraph (e) of this AD are accomplished.
(2) If any crack is detected, before further flight, do the
replacement in either paragraph (d)(2)(i) or (d)(2)(ii) of this AD
in accordance with the applicable service bulletin.
(i) Replace the rear engine mount strut with a new, welded
strut, P/N 87110016-009 or -011. Repeat the detailed inspection
thereafter at intervals not to exceed 250 flight hours until the
requirements of paragraph (e) of this AD are accomplished.
(ii) Replace the rear engine mount strut with a new, machined
strut, P/N 87110047-001. Repeat the detailed inspection thereafter
at intervals not to exceed 500 flight hours for the new, machined
strut until the requirements of paragraph (e) of this AD are
accomplished.
Optional Terminating Replacement
(e) Replace both rear engine mount struts with new, machined
struts, P/N 87110047-001, in accordance with Bombardier Alert
Service Bulletin 215-A3111, Revision 2, dated January 23, 2003
(Model CL-215-6B11 (CL215T Variant) series airplanes); or Bombardier
Alert Service Bulletin 215-A4287, Revision 2, dated January 23, 2003
(Model CL-215-6B11 (CL415 Variant) series airplanes); as applicable.
Replacement constitutes terminating action for the repetitive
inspections required by this AD.
Parts Installation
(f) As of the effective date of this AD, no person shall install
a rear engine mount strut, P/N 87110016-003, on any airplane.
Reporting Paragraph in Service Bulletins
(g) Although the service bulletins referenced in this AD specify
to submit certain information to the manufacturer, this AD does not
include such a requirement.
Alternative Methods of Compliance
(h) In accordance with 14 CFR 39.19, the Manager, New York
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance (AMOCs) for this AD.
Incorporation by Reference
(i) The actions shall be done in accordance with Canadair Alert
Service Bulletin 215-A3040, dated September 2, 1992; Bombardier
Alert Service Bulletin 215-A3111, Revision 2, dated January 23,
2003; and Bombardier Alert Service Bulletin 215-A4287, Revision 2,
dated January 23, 2003; as applicable.
(1) The incorporation by reference of Bombardier Alert Service
Bulletin 215-A3111, Revision 2, dated January 23, 2003; and
Bombardier Alert Service Bulletin 215-A4287, Revision 2, dated
January 23, 2003; is approved by the Director of the Federal
Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The incorporation by reference of Canadair Alert Service
Bulletin 215-A3040, dated September 2, 1992, was approved previously
by the Director of the Federal Register as of April 4, 1994 (59 FR
10272).
(3) Copies may be obtained from Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal,
Quebec H3C 3G9, Canada. Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; at the FAA, New York Aircraft Certification Office, 1600
Stewart Avenue, suite 410, Westbury, New York; or at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Note 2: The subject of this AD is addressed in Canadian
airworthiness directive CF-2003-02, dated February 28, 2003.
Effective Date
(j) This amendment becomes effective on June 21, 2004.
Issued in Renton, Washington, on May 5, 2004.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-10739 Filed 5-14-04; 8:45 am]
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