[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 [www.gpo.gov]
[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:
[[Page 41776]]
(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]
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