AD Amdt-39-11239

[Federal Register Volume 64, Number 147 (Monday, August 2, 1999)]
[Rules and Regulations]
[Pages 41775-41776]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-19453]



[[Page 41775]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-370-AD; Amendment 39-11239; AD 99-16-04]
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 on certain wing to fuselage frame-angles, and 
repair, if necessary. This amendment would continue to require the same 
inspections. This amendment is prompted by an adverse comment received 
in response to the existing amendment. The actions specified by this AD 
are intended to detect and correct cracking in the wing to fuselage 
frame-angles, which could result in reduced structural integrity of the 
airframe.

DATES: Effective September 7, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 7, 1999.

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, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Franco Pieri, 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) 256-7526; 
fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding amendment 39-10458 
(63 FR 17672, April 10, 1998). [A correction of the direct final rule 
was published in the Federal Register on May 4, 1998 (63 FR 24389)]. 
That amendment is applicable to certain Bombardier Model CL-215-1A10 
and CL-215-6B11 series airplanes, and was published in the Federal 
Register on April 5, 1999 (64 FR 16366). The action proposed to require 
repetitive inspections to detect cracking on certain wing to fuselage 
frame-angles, and repair, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that 1 airplane of U.S. registry will be affected 
by this AD.
    It will take approximately 2 work hours per airplane to accomplish 
the required actions, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of this AD on U.S. operators is 
estimated to be $120 per airplane, per inspection cycle.
    The cost impact figure discussed above is 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.

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 removing amendment 39-10458 (63 FR 
34389, May 4, 1998), and by adding a new airworthiness directive (AD), 
amendment 39-11239, to read as follows:

99-16-04 Bombardier Inc. (Formerly Canadair): Amendment 39-11239. 
Docket 98-NM-370-AD. Supersedes Amendment 39-10458.

    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 (c) 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 in the wing to fuselage frame-
angles, which could result in reduced structural integrity of the 
airframe, accomplish the following:

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    (a) Perform an eddy current inspection to detect cracking of the 
fuselage frame angles at the wing front and rear spar attachment to 
the fuselage at the later of the times specified in paragraphs 
(a)(1) and (a)(2) of this AD; in accordance with Bombardier Alert 
Service Bulletin 215-A476, Revision 3, dated August 21, 1998. 
Thereafter, repeat the inspection at intervals not to exceed 415 
flight hours.
    (1) Prior to the accumulation of 2,300 total flight hours.
    (2) Within 150 flight hours or 4 months after the effective date 
of this AD, whichever occurs first.
    Note 2: Accomplishment of the eddy current inspections of the 
lower surfaces of the frame angles conducted in accordance with 
Bombardier Alert Service Bulletin ASB 215-A476, Revision 1, dated 
January 14, 1997, or ASB 215-A476, Revision 2, dated June 15, 1998, 
prior to the effective date of this AD is considered to be 
acceptable for compliance with the requirements of paragraph (a) of 
this AD for that area only.

    (b) If the results of any inspection required by paragraph (a) 
of this AD are outside the limits specified in paragraph 2.C.(7) of 
Bombardier Alert Service Bulletin ASB 215-A476, Revision 3, dated 
August 21, 1998: 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.

Alternative Methods of Compliance

    (c) 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York ACO.

Special Flight Permits

    (d) 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.

Incorporation by Reference

    (e) The inspections shall be done in accordance with Bombardier 
Alert Service Bulletin 215-A476, Revision 3, dated August 21, 1998. 
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 4: The subject of this AD is addressed in Canadian 
airworthiness directive CF-97-07R1, dated September 30, 1998.
    (f) This amendment becomes effective on September 7, 1999.

    Issued in Renton, Washington, on July 23, 1999.
D. L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-19453 Filed 7-30-99; 8:45 am]
BILLING CODE 4910-13-U