AD 2005-18-05

[Federal Register Volume 70, Number 169 (Thursday, September 1, 2005)]
[Rules and Regulations]
[Pages 52009-52011]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 05-17323]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21595; Directorate Identifier 2002-NM-321-AD; 
Amendment 39-14245; AD 2005-18-05]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-215-1A10 (Water 
Bomber), CL-215-6B11 (CL215T Variant), and CL-215-6B11 (CL415 Variant) 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Bombardier Model CL-215-1A10 and CL-215-
6B11 series airplanes. That AD currently requires repetitive ultrasonic 
inspections to detect cracking of the lower caps of the wing front spar 
and rear spar, and corrective action if necessary. This new AD reduces 
the threshold to do the initial inspections and revises the repetitive 
inspection interval. This new AD also adds a repetitive ultrasonic 
inspection of the wing lower skin. This AD results from reports of 
cracks in the front and rear spar lower caps. We are issuing this AD to 
detect and correct cracking of the lower caps of the wing front spar 
and rear spar, which could result in reduced structural integrity of 
the airplane.

DATES: This AD becomes effective October 6, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of October 6, 
2005.
    On March 4, 1998 (63 FR 7640, February 17, 1998), the Director of 
the Federal Register approved the incorporation by reference of 
Canadair Alert Service Bulletin 215-A454, Revision 1, dated May 25, 
1995; and Canadair Alert Service Bulletin 215-A463, Revision 1, dated 
May 25, 1995.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a> or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, 
Station Centreville, Montreal, Quebec H3C 3G9, Canada, for service 
information identified in this AD.

FOR FURTHER INFORMATION CONTACT: David Lawson, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New 
York 11590; telephone (516) 228-7327; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a> 
or in person at the Docket Management Facility office between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays. The Docket 
Management Facility office (telephone (800) 647-5227) is located on the 
plaza level of the Nassif Building at the street address stated in the 
ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 98-04-08, amendment 39-
10321 (63 FR 7640, February 17, 1998). The existing AD applies to 
certain Bombardier Model CL-215-1A10 and CL-215-6B11 series airplanes. 
That NPRM was published in the Federal Register on June 22, 2005 (70 FR 
36075). That NPRM proposed to continue to require repetitive ultrasonic 
inspections to detect cracking of the lower caps of the wing front spar 
and rear spar, and corrective action if necessary. That NPRM also 
proposed to require reducing the threshold in the existing AD for doing 
the initial inspections and revising the repetitive inspection 
interval, and to add a repetitive ultrasonic inspection of the wing 
lower skin.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the NPRM or 
on the determination of the cost to the public.

Explanation of Change in Applicability

    We have revised the applicability of the final rule to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.

Conclusion

    We have carefully reviewed the available data, and determined that 
air safety and the public interest require adopting the AD with the 
change described previously. We have determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Costs of Compliance

    This AD affects about 3 airplanes of U.S. registry.
    The actions that are required by AD 98-04-08 and retained in this 
AD take about 16 work hours per airplane, at an average labor rate of 
$65 per work hour. Based on these figures, the estimated cost of the 
currently required actions is $1,040 per airplane, per inspection 
cycle.
    The new inspections required by this AD will take about 1 work hour 
per airplane, at an average labor rate of $65 per work hour. Based on 
these figures, the estimated cost of the new inspections specified in 
this AD for U.S. operators is $195 per inspection cycle, or $65 per 
airplane, per inspection cycle.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for

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safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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]

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2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-10321 (63 FR 7640, February 17, 1998) and by 
adding the following new airworthiness directive (AD):

2005-18-05 Bombardier, Inc. (Formerly Canadair): Amendment 39-14245. 
Docket No. FAA-2005-21595; Directorate Identifier 2002-NM-321-AD.

Effective Date

    (a) This AD becomes effective October 6, 2005.

Affected ADs

    (b) This AD supersedes AD 98-04-08.

Applicability

    (c) This AD applies to Bombardier Model CL-215-1A10 (Water 
Bomber), CL-215-6B11 (CL215T Variant), and CL-215-6B11 (CL415 
Variant) airplanes; certificated in any category; serial numbers 
1001 through 1125 inclusive.

Unsafe Condition

    (d) This AD results from reports of cracks in the front and rear 
spar lower caps. We are issuing this AD to detect and correct 
cracking of the lower caps of the wing front spar and rear spar, 
which could result in reduced structural integrity of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Certain Requirements of AD 98-04-08

Initial Inspection of AD 98-04-08 With New Threshold

    (f) At the time specified in paragraph (g) of this AD: Perform 
an ultrasonic inspection to detect cracking of the lower cap of the 
wing front and rear spars at wing station 51, in accordance with the 
Accomplishment Instructions of Canadair Alert Service Bulletin 215-
A463, Revision 1, dated May 25, 1995, or Bombardier Alert Service 
Bulletin 215-A463, Revision 2, dated March 13, 2001 (for the front 
spar); and Canadair Alert Service Bulletin 215-A454, Revision 1, 
dated May 25, 1995, Bombardier Alert Service Bulletin 215-A454, 
Revision 2, dated January 27, 1999, or Bombardier Alert Service 
Bulletin 215-A454, Revision 3, dated March 13, 2001 (for the rear 
spar). As of the effective date of this AD, the inspection must be 
done in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin 215-A463, Revision 2, dated March 
13, 2001 (for the front spar); and Bombardier Alert Service Bulletin 
215-A454, Revision 3, dated March 13, 2001 (for the rear spar).
    (g) Do the inspections required by paragraph (f) of this AD at 
the earlier of the times specified in paragraphs (g)(1) and (g)(2) 
of this AD.
    (1) Prior to the accumulation of 3,000 total flight hours, or 
within 25 flight hours after March 4, 1998 (the effective date of AD 
98-04-08), whichever occurs later.
    (2) At the later of the times specified in paragraphs (g)(2)(i) 
and (g)(2)(ii) of this AD.
    (i) Prior to the accumulation of 2,500 total flight hours, or 
8,000 total water drops, whichever occurs first.
    (ii) Within 50 flight hours or 150 water drops after the 
effective date of this AD, whichever occurs first.

Repetitive Inspections With New Intervals

    (h) Repeat the ultrasonic inspection specified in paragraph (f) 
of this AD at the times specified in paragraph (h)(1) or (h)(2) of 
this AD, as applicable.
    (1) For airplanes on which any ultrasonic inspection required by 
paragraph (a) of AD 98-04-08 has been done before the effective date 
of this AD: Within 600 flight hours after the last ultrasonic 
inspection, do the ultrasonic inspection specified in paragraph (f) 
of this AD. Repeat the ultrasonic inspection specified in paragraph 
(f) of this AD thereafter at intervals not to exceed 600 flight 
hours or 2,000 water drops, whichever occurs first.
    (2) For airplanes on which the ultrasonic inspection required by 
paragraph (a) of AD 98-04-08 has not been done before the effective 
date of this AD: After accomplishing the initial ultrasonic 
inspection specified in paragraph (f) of this AD, repeat the 
ultrasonic inspection specified in paragraph (f) of this AD 
thereafter at intervals not to exceed 600 flight hours or 2,000 
water drops, whichever occurs first.

New Requirements of This AD

New Ultrasonic Inspection

    (i) At the later of the times specified in paragraphs (i)(1) and 
(i)(2) of this AD, do an ultrasonic inspection for cracks of the 
wing lower skin, in accordance with Bombardier Alert Service 
Bulletin 215-A454, Revision 3, dated March 13, 2001. Thereafter, do 
the ultrasonic inspection for cracks of the wing lower skin at the 
times specified for the ultrasonic inspection in paragraph (h) of 
this AD.
    (1) Within 50 flight hours or 150 water drops after the 
effective date of this AD, whichever occurs first.
    (2) Before further flight after accomplishing the first 
ultrasonic inspection required by paragraph (f) or (h) of this AD 
after the effective date of this AD.

Cracking Detected

    (j) If any cracking is detected during any inspection required 
by paragraph (f), (h), or (i) of this AD, before further flight, 
accomplish paragraphs (j)(1) and (j)(2) of this AD.
    (1) Rework the lower cap of the front or rear spar, as 
applicable, in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin 215-A463, Revision 2, dated March 
13, 2001 (for the front spar); and Bombardier Alert Service Bulletin 
215-A454, Revision 3, dated March 13, 2001 (for the rear spar).
    (2) After doing the rework specified in paragraph (j)(1) of this 
AD, do a general visual inspection, from inside the wing box, to 
detect cracks of the front spar web or rear spar web, as applicable, 
and the lower skin area, in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin 215-A463, Revision 
2, dated March 13, 2001 (for the front spar); and Bombardier Alert 
Service Bulletin 215-A454, Revision 3, dated March 13, 2001 (for the 
rear spar). If any cracking is detected, before further flight, 
repair in accordance with a method approved by the Manager, New York 
Aircraft Certification Office (ACO), FAA; or Transport Canada Civil 
Aviation (TCCA) (or its delegated agent).

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of

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inspection is made from within touching distance unless otherwise 
specified. A mirror may be necessary to ensure visual access to all 
surfaces in the inspection area. This level of inspection is made 
under normally available lighting conditions such as daylight, 
hangar lighting, flashlight, or droplight and may require removal or 
opening of access panels or doors. Stands, ladders, or platforms may 
be required to gain proximity to the area being checked.''

Actions Accomplished According to Previous Issues of the Service 
Bulletins

    (k) Actions accomplished before the effective date of this AD in 
accordance with Canadair Alert Service Bulletin 215-A463, dated 
April 8, 1993; Canadair Alert Service Bulletin 215-A463, Revision 1, 
dated May 25, 1995; Canadair Alert Service Bulletin 215-A454, dated 
October 13, 1993; Canadair Alert Service Bulletin 215-A454, Revision 
1, dated May 25, 1995; and Bombardier Alert Service Bulletin 215-
A454, Revision 2, dated January 27, 1999; are considered acceptable 
for compliance with the corresponding actions specified in this AD.

Actions Accomplished According to Alert Wire

    (l) Actions accomplished before the effective date of this AD in 
accordance with Bombardier Alert Wire 215-A454, dated December 23, 
1992; and Bombardier Alert Wire 215-A463, dated March 26, 1993; are 
considered acceptable for compliance with the corresponding actions 
specified in this AD.

Reporting Requirement

    (m) For any inspection required by this AD that is accomplished 
after the effective date of this AD, within 30 days after 
accomplishing the inspection, submit a report of any inspection 
results (both positive and negative findings) to Bombardier, Inc., 
Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, 
Montreal, Quebec H3C 3G9, Canada. Under the provisions of the 
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office 
of Management and Budget (OMB) has approved the information 
collection requirements contained in this AD, and assigned OMB 
Control Number 2120-0056.

Alternative Methods of Compliance (AMOCs)

    (n) The Manager, New York ACO, FAA, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.

Related Information

    (o) Canadian airworthiness directives CF-1992-26R1, dated 
September 24, 2002, and CF-1993-07R1, dated September 25, 2002, also 
address the subject of this AD.

Material Incorporated by Reference

    (p) You must use the service information listed in Table 1 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise.

                                  Table 1.--Material Incorporated by Reference
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               Service  bulletin                Revision level                        Date
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Bombardier Alert Service Bulletin 215-A454....               2  January 27, 1999.
Bombardier Alert Service Bulletin 215-A454....               3  March 13, 2001.
Bombardier Alert Service Bulletin 215-A463....               2  March 13, 2001.
Canadair Alert Service Bulletin 215-A454......               1  May 25, 1995.
Canadair Alert Service Bulletin 215-A463......               1  May 25, 1995.
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    (1) The Director of the Federal Register approved the 
incorporation by reference of the documents listed in Table 2 of 
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

                               Table 2.--Material Newly Incorporated by Reference
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               Service  bulletin                Revision level                        Date
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Bombardier Alert Service Bulletin 215-A454....               2  January 27, 1999.
Bombardier Alert Service Bulletin 215-A454....               3  March 13, 2001.
Bombardier Alert Service Bulletin 215-A463....               2  March 13, 2001.
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    (2) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in 
Table 3 of this AD on March 4, 1998 (63 FR 7640, February 17, 1998).

                             Table 3.--Material Previously Incorporated by Reference
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               Service  bulletin                Revision level                        Date
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Canadair Alert Service Bulletin 215-A454......               1  May 25, 1995.
Canadair Alert Service Bulletin 215-A463......               1  May 25, 1995.
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    (3) Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. 
Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, 
for a copy of this service information. You may review copies at the 
Docket Management Facility, U.S. Department of Transportation, 400 
Seventh Street SW., room PL-401, Nassif Building, Washington, DC; on 
the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at the NARA, call (202) 741-6030, or go to <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a> html.

    Issued in Renton, Washington, on August 24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-17323 Filed 8-31-05; 8:45 am]
BILLING CODE 4910-13-P