[Federal Register: June 20, 2002 (Volume 67, Number 119)]
[Rules and Regulations]               
[Page 41818-41819]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20jn02-5]                         


[[Page 41818]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-398-AD; Amendment 39-12784; AD 2002-12-12]
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 decreases the compliance time for 
the initial inspection to detect cracking on certain wing-to-fuselage 
frame angles and decreases the interval between repetitive inspections. 
This amendment is prompted by issuance of mandatory continuing 
airworthiness information by a foreign civil airworthiness authority. 
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 July 25, 2002.
    The incorporation by reference of Bombardier Alert Service Bulletin 
215-A476, Revision 4, dated August 18, 2000, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
July 25, 2002.
    The incorporation by reference of Bombardier Alert Service Bulletin 
215-A476, Revision 3, dated August 21, 1998, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as September 7, 1999 (64 FR 41775, August 2, 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, 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: Serge Napoleon, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 99-16-04, 
amendment 39-11239 (64 FR 41775, August 2, 1999), which is applicable 
to certain Bombardier Model CL-215-1A10 and CL-215-6B11 series 
airplanes, was published in the Federal Register on February 8, 2002 
(67 FR 5958). The action proposed to continue to require repetitive 
inspections to detect cracking on certain wing-to-fuselage frame 
angles, and repair, if necessary. The action also proposed to decrease 
the compliance time for the initial inspection to detect cracking on 
certain wing-to-fuselage frame angles and to decrease the interval 
between repetitive inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There is one airplane of U.S. registry that will be affected by 
this AD.
    The inspections that are currently required by AD 99-16-04 take 
approximately 2 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the previously required actions on U.S. operators is 
estimated to be $120 per airplane, per inspection cycle.
    The new inspections that are required by this new AD will take 
approximately 3 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the new requirements of this AD on U.S. operators is 
estimated to be $180 per airplane, per inspection cycle.
    The cost impact figures discussed above are 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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 39-11239 (64 FR 
41775, August 2, 1999), and by adding a new airworthiness directive 
(AD), amendment 39-12784, to read as follows:


[[Page 41819]]


2002-12-12  Bombardier, Inc.: Amendment 39-12784. Docket 2000-NM-
398-AD. Supersedes AD 99-16-04, Amendment 39-11239.
    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 (g) 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:

Restatement of Requirements of AD 99-16-04

    (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 September 7, 1999 
(the effective date of AD 99-16-04, amendment 39-11239), 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 215-A476, Revision 1, dated 
January 14, 1997, or Bombardier Alert Service Bulletin 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 215-A476, Revision 3, dated August 
21, 1998, or Bombardier Alert Service Bulletin 215-A476, Revision 4, 
dated August 18, 2000: Prior to further flight, repair in accordance 
with a method approved by the Manager, New York Aircraft 
Certification Office (ACO), FAA.

New Actions Required by This AD

Initial Inspection

    (c) Unless paragraph (a) of this AD has been accomplished, 
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 
(c)(1) and (c)(2) of this AD, in accordance with Bombardier Alert 
Service Bulletin 215-A476, Revision 4, dated August 18, 2000.
    (1) Prior to the accumulation of 2,300 total flight hours or 
7,500 total water drops, whichever occurs first.
    (2) Within 60 days after the effective date of this AD.

Repetitive Inspection

    (d) Perform an eddy current inspection to detect cracking of the 
fuselage frame angles at the wing front and rear spar attachment to 
the fuselage, in accordance with Bombardier Alert Service Bulletin 
215-A476, Revision 4, dated August 18, 2000, at intervals not to 
exceed 415 flight hours or 1,500 water drops, whichever occurs 
first.

Corrective Action

    (e) If the results of any inspection required by paragraph (c) 
or (d) of this AD are outside the limits specified in paragraph 
2.C.(7) of Bombardier Alert Service Bulletin 215-A476, Revision 4, 
dated August 18, 2000: Prior to further flight, repair in accordance 
with a method approved by the Manager, New York ACO, FAA.

Reporting

    (f) Within 10 days after performing any inspection required by 
paragraph (a), (c), or (d) of this AD: Report the findings, positive 
or negative, to Bombardier Inc., Amphibious Aircraft Division, 
Customer Support, Department 645, Attention: Manager of Technical 
Support, Fax Number (514) 855-7602. Information collection 
requirements contained in this AD 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.

Alternative Methods of Compliance

    (g) 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

    (h) Special flight permits may be issued in accordance with 
Secs. 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

    (i) Except as provided by paragraphs (b) and (e) of this AD, the 
actions shall be done in accordance with Bombardier Alert Service 
Bulletin 215-A476, Revision 3, dated August 21, 1998; and Bombardier 
Alert Service Bulletin 215-A476, Revision 4, dated August 18, 2000; 
as applicable.
    (1) The incorporation by reference of Bombardier Alert Service 
Bulletin 215-A476, Revision 4, dated August 18, 2000, is approved by 
the Director of the Federal Register, in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Bombardier Alert Service 
Bulletin 215-A476, Revision 3, dated August 21, 1998, was approved 
previously by the Director of the Federal Register as of September 
7, 1999 (64 FR 41775, August 2, 1999).
    (3) 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 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-1997-07R2, dated August 17, 2000.

Effective Date

    (j) This amendment becomes effective on July 25, 2002.

    Issued in Renton, Washington, on June 11, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-15242 Filed 6-19-02; 8:45 am]
BILLING CODE 4910-13-P