6538 Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–139–AD; Amendment 

39–13457; AD 2004–03–13] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–215–1A10 and CL–215–6B11 

Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Bombardier Model 

CL–215–1A10 and CL–215–6B11 series 

airplanes, that currently requires 

repetitive inspections to detect cracking 

of main landing gear (MLG) axles that 

have been reworked by chromium 

plating, and replacement of cracked 

axles with serviceable axles. This 

amendment requires a dimensional 

check and follow-on corrective actions, 

mandates terminating action for certain 

airplanes, and adds three airplanes to 

the applicability in the existing AD. The 

actions specified by this AD are 

intended to prevent cracking of the 

inner bearing surface of the MLG axles, 

which could result in failure of an axle, 

subsequent separation of the wheel from 

the airplane, and consequent reduced 

controllability of the airplane during 

takeoff or landing. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective March 17, 2004. 

The incorporation by reference of a 

certain publication, as listed in the 

regulations, is approved by the Director 

of the Federal Register as of March 17, 

2004. 

The incorporation by reference of a 

certain other publication, as listed in the 

regulations, was approved previously by 

the Director of the Federal Register as of 

November 8, 1995 (60 FR 54421, 

October 24, 1995).

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; or at the FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Westbury, New York; 

or at the Office of the Federal Register, 

800 North Capitol Street, NW., suite 

700, Washington, DC.

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 11581; 

telephone (516) 228–7300; fax (516) 

794–5531.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 95–22–04, 

amendment 39–9411 (60 FR 54421, 

October 24, 1995), which is applicable 

to certain Canadair Model CL–215–

1A10 and CL–215–6B11 series 

airplanes, was published in the Federal 

Register on December 5, 2003 (68 FR 

67971). The action proposed to require 

inspections to detect cracking of main 

landing gear (MLG) axles that have been 

reworked by chromium plating, and 

replacement of cracked axles with 

serviceable axles. That action also 

proposed to add a dimensional check 

and follow-on corrective actions, 

mandate terminating action for certain 

airplanes, and add three airplanes to the 

applicability in the existing AD.

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. 

Conclusion 

The FAA has determined that air 

safety and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

There are approximately 3 airplanes 

of U.S. registry that will be affected by 

this AD. 

The inspections that are currently 

required by AD 95–22–04 take about 2 

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 currently required 

inspections on U.S. operators is 

estimated to be $390, or $130 per 

airplane, per inspection cycle. 

The dimensional check and ultrasonic 

inspection required by this AD action 

will take about 2 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 

checks and inspections on U.S. 

operators is estimated to be $390, or 

$130 per airplane, per cycle. 

The replacement required by this AD 

action, if done, will take about 8 work 

hours per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Required parts will cost approximately 

$13,000 per assembly (two per airplane). 

Based on these figures, the cost impact 

of the replacement required by this AD 

on U.S. operators is estimated to be 

$26,520 per airplane. 

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the 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 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

■ 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:

Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 6539

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. Section 39.13 is amended by 

removing amendment 39–9411 (60 FR 

54421, October 24, 1995), and by adding 

a new airworthiness directive (AD), 

amendment 39–13457, to read as 

follows:

2004–03–13 Bombardier, Inc. (Formerly 

Canadair): Amendment 39–13457. 

Docket 2003–NM–139–AD. Supersedes 

AD 95–22–04, Amendment 39–9411.

Applicability: Model CL–215–1A10 

(piston) and CL–215–6B11 (turboprop) series 

airplanes, having serial numbers 1001 

through 1125 inclusive, certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent cracking in the inner bearing 

surface of the main landing gear (MLG) axles, 

which could result in failure of an axle, 

subsequent separation of the wheel from the 

airplane, and consequent reduced 

controllability of the airplane during takeoff 

or landing, accomplish the following: 

Restatement of Certain Requirements of AD 

95–22–04

Repetitive Inspections/Corrective Action 

(a) Within 60 days after November 8, 1995 

(the effective date of AD 95–22–04, 

amendment 39–9411), perform either an 

eddy current inspection or a chemical 

inspection of the inner bearing surface area 

of the left and right MLG axles to determine 

if they have been reworked using chromium 

plating, in accordance with Canadair Alert 

Service Bulletin 215–A462, dated June 2, 

1993; or Bombardier Alert Service Bulletin 

215–A462, Revision 3, dated January 17, 

2000. If the inner bearing surface of the MLG 

axle has not been reworked using chromium 

plating, no further action is required by this 

paragraph for that axle only. 

(b) If the inner bearing surface of the MLG 

axle has been reworked using chromium 

plating, prior to further flight, perform an 

ultrasonic inspection to detect cracking in 

the axle, in accordance with Canadair Alert 

Service Bulletin 215–A462, dated June 2, 

1993; or Bombardier Alert Service Bulletin 

215–A462, Revision 3, dated January 17, 

2000. 

(1) If no crack is detected during this 

inspection, repeat the ultrasonic inspection 

at intervals not to exceed 150 landings. 

(2) If any crack is detected during this 

inspection, prior to further flight, remove the 

cracked axle and replace it with a serviceable 

axle that does not have an inner bearing 

surface that has been reworked using 

chromium plating, in accordance with the 

service bulletin. 

New Requirements of This AD 

Dimensional Check/Follow-on Corrective 

Actions 

(c) Within 150 landings after the effective 

date of this AD: Do a dimensional check by 

measuring the diameter of the left and right 

MLG axles to determine if they have been 

reworked outside the dimensions specified in 

Canadair CL–215 Overhaul Manual PSP 298, 

or if the axle has unknown rework 

dimensions or the service life of that axle 

cannot be determined, in accordance with 

Bombardier Alert Service Bulletin 215–A462, 

Revision 3, dated January 17, 2000. 

(1) If any axle has been reworked outside 

the specified dimensions, or has unknown 

rework dimensions, or if the service life of 

that axle cannot be determined: Prior to 

further flight, do an ultrasonic inspection to 

detect cracking of the axle, in accordance 

with the alert service bulletin, and replace 

the axle with a serviceable axle before the 

accumulation of 1,050 total landings, in 

accordance with the alert service bulletin. 

Such replacement ends the repetitive 

inspections for that axle only. 

(i) If no cracking is detected during the 

inspection required by paragraph (c)(1) of 

this AD, repeat the inspection at intervals not 

to exceed 150 landings, and replace with a 

serviceable axle before the accumulation of 

1,050 total landings, in accordance with the 

alert service bulletin. 

(ii) If any cracking is detected during the 

inspection required by paragraph (c)(1) of 

this AD, prior to further flight, replace the 

axle with a serviceable axle in accordance 

with the alert service bulletin. 

(2) If the service life of the axle is known, 

and the axle has not been reworked outside 

the specified dimensions, no further action is 

required by this AD for that axle only. 

Actions Done per Previous Issues of Service 

Bulletin 

(d) Inspections and replacements done 

before the effective date of this AD in 

accordance with Canadair Alert Service 

Bulletin 215–A462, dated June 2, 1993; or 

Bombardier Alert Service Bulletin 215–A462, 

Revision 1, dated August 26, 1996; or 

Revision 2, dated March 3, 1999; are 

considered acceptable for compliance with 

the applicable actions specified in this AD. 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, New York Aircraft Certification 

Office, FAA, is authorized to approve 

alternative methods of compliance for this 

AD. 

Incorporation by Reference 

(f) The actions shall be done in accordance 

with Canadair Alert Service Bulletin 215–

A462, dated June 2, 1993; and Bombardier 

Alert Service Bulletin 215–A462, Revision 3, 

dated January 17, 2000; as applicable. 

(1) The incorporation by reference of 

Bombardier Alert Service Bulletin 215–A462, 

Revision 3, dated January 17, 2000; 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–A462, 

dated June 2, 1993; was approved previously 

by the Director of the Federal Register as of 

November 8, 1995 (60 FR 54421, October 24, 

1995). 

(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; or at the FAA, 

New York Aircraft Certification Office, 1600 

Stewart Avenue, Westbury, New York; or at 

the Office of the Federal Register, 800 North 

Capitol Street, NW., suite 700, Washington, 

DC.

Note 1: The subject of this AD is addressed 

in Canadian airworthiness directive CF–

1993–08R3, dated March 30, 2000.

Effective Date 

(g) This amendment becomes effective on 

March 17, 2004.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2577 Filed 2–10–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–116–AD; Amendment 

39–13462; AD 2004–03–18] 

RIN 2120–AA64 

Airworthiness Directives; Aerospatiale 

Model ATR42 and ATR72 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Aerospatiale Model 

ATR42 and ATR72 series airplanes, that 

requires replacement of the swinging 

lever spacers in the left and right leg 

assemblies of the main landing gear 

with new, improved spacers. This 

action is necessary to prevent 

propagation of fatigue cracking, which 

could result in failure of the spacer base 

and could affect the symmetrical 

functioning of the braking system. 

Asymmetrical braking could result in 

the airplane overrunning the runway 

during takeoff or landing. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective March 17, 2004. 

The incorporation by reference of 

certain publications listed in the