[Federal Register Volume 69, Number 30 (Friday, February 13, 2004)]
[Proposed Rules]
[Pages 7179-7181]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-3206]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-199-AD]
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: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the supersedure of 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 action would require adding repetitive
detailed inspections to detect cracking in the rear engine mount struts
and replacement of struts with new struts, if necessary. This action
would also 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. The actions
specified by the proposed 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: Comments must be received by March 15, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-199-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
[email protected]. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-199-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 for Windows or
ASCII text.
The service information referenced in the proposed rule 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 FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York
Aircraft Certification Office, 1600 Stewart Avenue, Westbury, New York.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
Submit comments using the following format:
Organize comments issue-by-issue. For example,
discuss a request to change the compliance time and a request to change
the service bulletin reference as two separate issues.
For each issue, state what specific change to
the proposed AD is being requested.
Include justification (e.g., reasons or data)
for each request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2003-NM-199-AD.'' The postcard will be date stamped
and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 2003-NM-199-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On February 4, 1994, the FAA issued AD 94-04-02, amendment 39-8820
(59 FR 10272, March 4, 1994), applicable to certain Bombardier Model
CL-215-6B11 series airplanes, 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. That action was
[[Page 7180]]
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
requirements of that 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.
Actions Since Issuance of Previous Rule
Since the issuance of AD 94-04-02, Transport Canada Civil Aviation
(TCCA), which is the airworthiness authority for Canada, has received
reports that welded struts installed as terminating action for that AD
(reference Canadian airworthiness directive CF-92-22, dated November
17, 1992) have failed in service. Weakness in the welded struts can
result in cracks in the rear engine mount struts. This condition, if
not corrected, could reduce structural integrity of the nacelle and
engine support structure.
Explanation of Relevant Service Information
Bombardier has issued Alert Service Bulletin 215-A3111, Revision 2,
dated January 23, 2003 (for Model CL-215-6B11 (CL215T Variant) series
airplanes); and Alert Service Bulletin 215-A4287, Revision 2, dated
January 23, 2003 (for Model CL-215-6B11 (CL415 Variant) series
airplanes). The service bulletins describe repetitive detailed
inspections to detect cracking in the rear mount strut assemblies of
the engines, and replacement of struts with new, machined or welded
struts, if necessary. Replacement of all struts with new, machined
struts would eliminate the need for the repetitive inspections.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition. TCCA
classified these service bulletins as mandatory and issued Canadian
airworthiness directive CF-2003-02, dated February 28, 2003, in order
to assure the continued airworthiness of these airplanes in Canada.
FAA's Conclusions
These airplane models are manufactured in Canada and are type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, TCCA has kept the FAA informed of
the situation described above. The FAA has examined the findings of
TCCA, reviewed all available information, and determined that AD action
is necessary for products of this type design that are certificated for
operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would supersede AD 94-04-02 to
continue to require inspections to detect cracking in the rear engine
mount struts, and replacement of struts with new struts, if necessary.
This new action proposes adding repetitive detailed inspections for
new, welded struts, expanding the applicability of the existing AD, and
making replacement of all struts with new, machined struts an optional
terminating action for the repetitive inspections (replacement of
struts with new, welded struts is no longer an optional terminating
action). The actions would be required to be accomplished in accordance
with the service bulletins described previously, except as described
below.
Difference Between Service Bulletins and Proposed AD
Although the service bulletins specify to submit certain
information to the manufacturer, this proposed AD does not include such
a requirement.
Change Made to Inspection Terminology
The inspection for cracks in AD 94-04-02 is called a ``visual
inspection.'' However, the inspection for cracks in the proposed AD is
called a ``detailed inspection'' and the definition of ``detailed
inspection'' is added to clarify the inspection type.
Optional Terminating Replacement
Operators should also note that, to be consistent with the findings
of the TCCA, the FAA has determined that the repetitive inspections
proposed by this AD can be allowed to continue in lieu of
accomplishment of a terminating action. In making this determination,
the FAA considers that, in this case, long-term continued operational
safety will be adequately assured by accomplishing the repetitive
inspections to detect cracks before it represents a hazard to the
airplane.
Cost Impact
There are approximately 3 airplanes of U.S. registry that would be
affected by this proposed AD.
The actions that are currently required by AD 94-04-02 take
approximately 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,
the cost impact of the currently required actions on U.S. operators is
estimated to be $1,950, or $650 per airplane.
The new inspections that are proposed in this AD action take
approximately 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 the proposed inspections of this AD on U.S. operators is
estimated to be $585, or $195 per airplane, per inspection cycle.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the current or proposed
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted. The cost
impact figures discussed in AD rulemaking actions represent only the
time necessary to perform the specific actions actually required by the
AD. These figures typically do not include incidental costs, such as
the time required to gain access and close up, planning time, or time
necessitated by other administrative actions.
Regulatory Impact
The regulations proposed herein would 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 proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
[[Page 7181]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (14 CFR part 39) as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
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), to read as follows:
Bombardier, Inc. (Formerly Canadair): 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
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.
Note 2: The subject of this AD is addressed in Canadian
airworthiness directive CF-2003-02, dated February 28, 2003.
Issued in Renton, Washington, on February 5, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-3206 Filed 2-12-04; 8:45 am]
BILLING CODE 4910-13-P