AD Amdt-39-10321

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-3262]


-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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