Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Rules and Regulations 52009 

August 9, 2002, as of October 10, 2002 (67 

FR 60117, September 25, 2002). 

(3) Contact Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, Station 

Centreville, 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 http:// 

dms.dot.gov; 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 http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on August 

24, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–17333 Filed 8–31–05; 8:45 am] 

BILLING CODE 4910–13–P 

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. 

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 http:// 

dms.dot.gov 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 http://dms.dot.gov 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 

52010 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Rules and Regulations 

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 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 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 

Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Rules and Regulations 52011 

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

Service 

bulletin Revision level Date 

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. 

(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

Service 

bulletin Revision level Date 

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. 

(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

Service 

bulletin Revision level Date 

Canadair Alert Service Bulletin 215–A454 ......................................................................................... 1 May 25, 1995. 

Canadair Alert Service Bulletin 215–A463 ......................................................................................... 1 May 25, 1995. 

(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 http:// 

dms.dot.gov; 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 http://www.archives.gov/federal_

register/code_of_federal_regulations/ibr_

locations.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