[Federal Register Volume 63, Number 31 (Tuesday, February 17, 1998)]
[Rules and Regulations]
[Pages 7640-7642]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3262]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-332-AD; Amendment 39-10321; AD 98-04-08]
RIN 2120-AA64
Airworthiness Directives; Bombardier 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 Bombardier Model CL-215-1A10 and CL-215-6B11
series airplanes. This action 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 amendment is
prompted by issuance of mandatory continuing airworthiness information
by a foreign civil airworthiness authority. The actions specified in
this AD are intended 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: Effective March 4, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 4, 1998.
Comments for inclusion in the Rules Docket must be received on or
before March 19, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-332-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
Bombardier, nc., Canadair, Aerospace Group, P.O. Box 6087, Station
Centre-ville, Montreal, 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, Engine and Propeller
Directorate, New York Aircraft Certification Office, 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: Serge Napoleon, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, Engine and Propeller
Directorate, New York Aircraft Certification Office, 10 Fifth Street,
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7512;
fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: Transport Canada Aviation (TCA), which is
the airworthiness authority for Canada, notified the FAA that an unsafe
condition may exist on certain Bombardier Model CL-215-1A10 and CL-215-
6B11 series airplanes. The TCA advises that fatigue cracks have been
found in the lower caps of the wing front spar and rear spar at wing
station 51 of several in-service airplanes. This condition, if not
detected and corrected in a timely manner, could result in reduced
structural integrity of the airplane.
Explanation of Relevant Service Information
Transport Canada Aviation issued Canadian airworthiness directives
CF-92-26, dated December 23, 1992, and CF-93-07, dated March 26, 1993,
in order to assure the continued airworthiness of these airplanes in
Canada. Those Canadian airworthiness directives cite Bombardier Inc.
Canadair Alert Wires 215-A454, dated December 23, 1992, and 215-A463,
dated March 26, 1993, respectively, which provide procedures for
ultrasonic inspection to detect cracking of the rear and front spar
lower cap at the left and right wing station 51, and repair, if
necessary.
Subsequently, the manufacturer issued 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, which
describe procedures for repetitive ultrasonic inspections to detect
fatigue cracking of the lower caps of the wing front and rear spars at
wing station 51. For airplanes on which any discrepancy is found, the
alert service bulletins also describe procedures for rework of the
lower caps, and follow-on visual inspection of the front or rear spar
web area and the lower skin area from inside the wing box.
FAA's Conclusions
These airplane models are manufactured in Canada and are 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, TCA has kept
[[Page 7641]]
the FAA informed of the situation described above. The FAA has examined
the findings of TCA, 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.
Explanation of Requirements of the Rule
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 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. This AD
requires accomplishment of the actions specified in the service
bulletins described previously, except as discussed below.
Differences Between This Rule and the Alert Service Bulletins
Operators should note that, although the alert service bulletins
specify that the manufacturer may be contacted for disposition of
certain repair conditions, this AD requires that repair of those
conditions be accomplished in accordance with a method approved by the
FAA.
Cost Impact
None of the airplanes affected by this action are 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 16 work hours to
accomplish the required inspections, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of this AD would
be $960 per airplane, per inspection cycle.
Determination of Rule's Effective Date
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, prior 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 97-NM-332-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
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.
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), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
98-04-08 Bombardier, Inc. (Formerly Canadair): Amendment 39-10321.
Docket 97-NM-332-AD.
Applicability: Model CL-215-1A10 and CL-215-6B11 series
airplanes, serial numbers 1001 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
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 request approval for an
alternative method of compliance in accordance with paragraph (b) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
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, accomplish the following:
(a) Prior to the accumulation of 3,000 total flight hours, or
within 25 flight hours after the effective date of this AD,
whichever occurs later: Perform an ultrasonic inspection to detect
cracking of the lower cap of the wing front and rear spars at wing
station 51,
[[Page 7642]]
in accordance with the Accomplishment Instructions of Canadair Alert
Service Bulletin 215-A463, Revision 1, dated May 25, 1995 (for the
front spar); and Canadair Alert Service Bulletin 215-A454, Revision
1, dated May 25, 1995 (for the rear spar). Thereafter, repeat the
ultrasonic inspection at intervals not to exceed 600 flight hours.
If any cracking is detected, prior to further flight, accomplish
paragraphs (a)(1) and (a)(2) of this AD.
(1) Rework the lower cap of the front or rear spar, as
applicable, in accordance with the alert service bulletin. And
(2) Visually inspect, from inside the wing box, the front spar
web or the rear spar web, as applicable, and the lower skin area to
detect cracks. If any cracking is detected, prior to further flight,
repair in accordance with a method approved by the Manager, New York
Aircraft Certification Office (ACO), FAA, Engine and Propeller
Directorate.
(b) 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 ACO. 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.
(c) 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.
(d) The actions shall be done in accordance with 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. 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, 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, Engine and Propeller Directorate, New
York Aircraft Certification Office, 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.
Note 3: The subject of this AD is addressed in Canadian
airworthiness directives CF-92-26, dated December 23, 1992, and CF-
93-07, dated March 26, 1993.
(e) This amendment becomes effective on March 4, 1998.
Issued in Renton, Washington, on February 4, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-3262 Filed 2-13-98; 8:45 am]
BILLING CODE 4910-13-U
