[Federal Register Volume 60, Number 205 (Tuesday, October 24, 1995)]
[Rules and Regulations]
[Pages 54421-54423]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-25990]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-173-AD; Amendment 39-9411; AD 95-22-04]


Airworthiness Directives; Canadair Model CL-215-1A10 and CL-215-
6B11 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Canadair Model CL-215-1A10 and CL-215-6B11 series 
airplanes. This action requires inspections to detect cracking of main 
landing gear (MLG) axles that have been reworked by chromium plating, 
and replacement of cracked axles. This amendment is prompted by reports 
of fatigue cracking found on several MLG wheel axes that had been 
chromium-plated during rework. The actions specified in this AD are 
intended to prevent such cracking, which can result in failure of the 
axle, separation of the wheel from the aircraft, and consequent reduced 
controllability of the airplane during takeoff or landing.

DATES: Effective November 8, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 8, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before December 26, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-173-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The service information referenced in this AD may be obtained from 
Bombardier, Inc., Canadair Aerospace Group, P.O. Box 6087, Station 
Centre-ville, 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, Engine and Propeller Directorate, 10 Fifth Street, Third Floor, 
, Valley Stream, New York; or at the Office of the Federal Register, 
800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jeff Casale, Aerospace Engineer, 
Systems and Equipment Branch, ANE-171, FAA, New York Aircraft 
Certification Office, Engine and Propeller Directorate, 10 Fifth 
Street, Third Floor, Valley Stream, New York 11581; telephone (516) 
256-7521; fax (206) 568-2716.

SUPPLEMENTARY INFORMATION: Transport Canada Aviation, which is the 
airworthiness authority for Canada, recently notified the FAA that an 
unsafe condition may exist on certain Canadair Model CL-215-1A10 and 
CL-215-6B11 series airplanes. Transport Canada Aviation advises that 
there have been reports of fatigue cracking found on several main 
landing gear (MLG) wheel axles on in-service airplanes. In three cases, 
such cracking has resulted in complete failure of the axle and 
subsequent separation of the wheel from the airplane. Investigation has 
revealed that this cracking occurs only on axles that have been 
reworked by chromium plating the wheel inner bearing surface. Such 
cracking, if not detected and corrected in a timely manner, can lead to 
failure of the axle and separation of the wheel from the airplane. 
Since each MLG has only a single wheel, loss of the 

[[Page 54422]]
wheel could result in reduced controllability of the airplane during 
take-off or landing.
    The number of reworked axles currently in the fleet is unknown; 
however, at least nine MLG axles were reworked by chromium plating 
during manufacture prior to their installation on the airplane. In 
light of this, Transport Canada Aviation has advised that, irrespective 
of the number of flight hours accumulated on the airplane or axle, the 
potential for cracking exists in all of these affected airplanes.
    Canadair has issued Alert Service Bulletin 215-A462, dated June 2, 
1993, which describes procedures for conducting an eddy current or 
chemical inspection of the inner bearing surface area of the left and 
right MLG axles to determine whether they have been reworked using 
chromium plating. For axles that have been so reworked, the service 
bulletin provides instructions for conducting repetitive ultrasonic 
inspections to detect cracks in the chromium-plated inner bearing 
surface. The service bulletin also describes procedures for removing 
cracked axles and replacing them with serviceable units. Transport 
Canada Aviation classified this service bulletin as mandatory and 
issued Canadian Airworthiness Directive CF-93-08R2, dated June 20, 
1994, in order to assure the continued airworthiness of these airplanes 
in Canada.
    This airplane model is manufactured in Canada and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.19) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, Transport Canada Aviation has kept 
the FAA informed of the situation described above. The FAA has examined 
the findings of Transport Canada Aviation, 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.
    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, this AD is being issued to prevent cracking of 
the chromium-plated inner bearing surface of the MLG axle. Such 
cracking can lead to failure of the axle, separation of the wheel from 
the aircraft, and consequent reduced controllability of the airplane 
during takeoff or landing. This AD requires an eddy current or 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. 
For axles that have been reworked, this AD requires repetitive 
ultrasonic inspections to detect cracking in the chromium-plated inner 
bearing surface. If cracking is found, the cracked axle must be removed 
and replaced with a serviceable unit. The actions are required to be 
accomplished in accordance with the service bulletin described 
previously.
    Additionally, operators must submit a report of all ultrasonic 
inspection findings to the manufacturer.
    None of the Model CL-215-1A10 or CL-215-6B11 series airplanes 
affected by this action is on the U.S. Register. All airplanes included 
in the applicability of this rule currently are operated by non-U.S. 
operators under foreign registry; therefore, they are not directly 
affected by this AD action. However, the FAA considers that this rule 
is necessary to ensure that the unsafe condition is addressed in the 
event that any of these subject airplanes are imported and placed on 
the U.S. Register in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 2 work hours to 
accomplish the required inspection actions, at an average labor charge 
of $60 per work hour. Based on these figures, the total cost impact of 
this AD would be $120 per airplane per inspection.
    If a cracked axle is found and replaced, that action would require 
8 work hours per airplane to accomplish, at an average labor charge of 
$60 per work hour. Required parts are estimated to cost $13,000 per 
assembly. Based on these figures, the total cost impact of necessary 
replacement required by this AD would be $13,480 per airplane.
    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
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 under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 95-NM-173-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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. 

[[Page 54423]]


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:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-22-04 Canadair: Amendment 39-9411. Docket 95-NM-173-AD.

    Applicability: Model CL-215-1A10 (piston) and CL-215-6B11 
(turboprop) series airplanes, having serial numbers 1011 through 
1125 inclusive, certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must use the authority 
provided in paragraph (f) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent cracking in the inner bearing surface of the main 
landing gear (MLG) axle, which can result in failure of the axle, 
separation of the wheel from the aircraft, and consequent reduced 
controllability of the airplane during takeoff or landing, 
accomplish the following:
    (a) Within 60 days after the effective date of this AD, 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.
    (b) If the inner bearing surface of the MLG axle has not been 
reworked using chromium plating, no further action is required by 
this AD for that axle.
    (c) 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.
    (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.
    (d) Within 5 days after completing each ultrasonic inspection 
required by paragraph (c) of this AD, submit a report of inspection 
findings, both positive and negative, to Canadair, Amphibious 
Aircraft Division, Customer Support, Dept. 645, Attention: Manager 
of Technical Support, P.O. Box 6087, Station A, Montreal, Quebec H3C 
3G9, Canada; fax (514) 856-0152. Information collection requirements 
contained in this regulation have been approved by the Office of 
Management and Budget (OMB) under the provisions of the Paperwork 
Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.
    (e) Installation of an MLG axle that does not have an inner 
bearing surface that has been reworked using chromium plating, in 
accordance with Canadair Alert Service Bulletin 215-A462, dated June 
2, 1993, constitutes terminating action for the inspections required 
by this AD for that axle.
    (f) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, New York Aircraft Certification 
Office (ACO), FAA, Engine and Propeller Directorate. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, New York ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York ACO.

    (g) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.
    (h) The inspections and replacement shall be done in accordance 
with Canadair Alert Service Bulletin 215-A462, dated June 2, 1993. 
This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Bombardier, Inc., Canadair Aerospace 
Group, P.O. Box 6087, Station Centre-ville, 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, Engine and Propeller Directorate, 10 
Fifth Street, Third Floor, , Valley Stream, New York; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (i) This amendment becomes effective on November 8, 1995.

    Issued in Renton, Washington, on October 16, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-25990 Filed 10-23-95; 8:45 am]
BILLING CODE 4910-13-U