[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]


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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).

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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