AD 2004-03-13

[Federal Register Volume 69, Number 28 (Wednesday, February 11, 2004)]
[Rules and Regulations]
[Pages 6538-6539]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 04-2577]



[[Page 6538]]

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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.

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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

0
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:

[[Page 6539]]

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]

0
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