[Federal Register Volume 65, Number 9 (Thursday, January 13, 2000)]
[Rules and Regulations]
[Pages 2019-2022]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-720]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-192-AD; Amendment 39-11510; AD 2000-01-12]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional
Jet Series 100) 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-600-2B19 (Regional Jet
Series 100 and 200) series airplanes, that currently requires
repetitive inspections to detect cracks of a certain bulkhead web of
the fuselage at certain locations, and repair, if necessary. This
amendment revises the repetitive inspection intervals for certain
airplanes, and requires modification or repair, as applicable. This
amendment is prompted by the development of a modification that will
adequately address the identified unsafe condition. The actions
specified by this AD are intended to detect and correct fatigue
cracking, which could result in uncontrolled depressurization of the
airplane and/or reduced structural integrity of the fuselage.
DATES: Effective February 17, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 17, 2000.
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; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: George Duckett, 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
[[Page 2020]]
11581; telephone (516) 256-7525; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 97-14-11,
amendment 39-10082 (62 FR 38206, July 17, 1997), which is applicable to
certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200)
series airplanes, was published in the Federal Register on November 9,
1999 (64 FR 61039). The action proposed to continue to require
repetitive inspections to detect cracks of a certain bulkhead web of
the fuselage at certain locations, and repair, if necessary. The action
also proposed to revise the repetitive inspection intervals for certain
airplanes, and require modification or repair, as applicable.
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.
Change to Service Bulletin Citation
The FAA has revised paragraphs (a) and (b) and NOTE 4 of the final
rule to correctly specify that Appendix 2 is included in Canadair
Regional Jet Service Bulletin 601R-53-047. This appendix was
incorrectly associated with Canadair Regional Jet Alert Service
Bulletin A601R-53-045 in 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 with the change described
previously. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 77 airplanes of U.S. registry that will be
affected by this AD.
The inspection that is currently required by AD 97-14-11 takes
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 currently required inspection on U.S. operators is
estimated to be $9,960, or $120 per airplane, per inspection cycle.
The repair that is required by this AD will take approximately 300
work hours per airplane to accomplish, at an average labor rate of $60
per work hour. Required parts will cost approximately $1,828. Based on
these figures, the cost impact of the repair on U.S. operators is
estimated to be $19,828 per airplane.
The modification that is required by this AD will take
approximately 212 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will cost approximately
$935. Based on these figures, the cost impact of the modification on
U.S. operators is estimated to be $13,655 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
AD, and that no operator would accomplish those actions in the future
if this AD were not adopted. However, the FAA has been advised that the
manufacturer has committed previously to its customers that it will
bear the labor costs associated with the repair and modification
associated with accomplishing the actions required by this AD.
Additionally, the manufacturer has indicated that warranty remedies may
be available to defer the cost of the replacement parts also associated
with accomplishing the actions required by this AD.
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 39-10082 (62 FR
38206, July 17, 1997), and by adding a new airworthiness directive
(AD), amendment 39-11510, to read as follows:
2000-01-12 Bombardier, Inc. (Formerly Canadair): Amendment 39-
11510. Docket No.98-NM-192-AD. Supersedes AD 97-14-11, Amendment 39-
10082.
Applicability: Model CL-600-2B19 (Regional Jet Series 100)
series airplanes, serial numbers 7003 through 7185 inclusive;
certificated in any category; except those airplanes on which
Canadair Regional Jet Service Bulletin 601R-53-046, Revision `B,'
dated December 22, 1997, or Canadair Regional Jet Service Bulletin
601R-53-047, Revision `D,' including Appendix 1 and Appendix 2,
dated December 22, 1997, has been accomplished.
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 (d)(1)
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 fatigue cracking in the underfloor
pressure bulkhead of the fuselage, which could result in
uncontrolled depressurization of the airplane and/or reduced
structural integrity of the fuselage, accomplish the following:
Detailed Visual Inspections
(a) Perform a detailed visual inspection to detect cracks at
FS409+128 of the bulkhead web drawing number 601R32208-123 of the
fuselage, in accordance withCanadair Regional Jet Alert Service
Bulletin A601R-53-045, Revision `D,' includingAppendix 1, dated
December 22, 1997, at the time specified in paragraph (a)(1) or
(a)(2) of this AD, as applicable, until accomplishment of paragraph
(b) or (c) of this AD, as applicable.
[[Page 2021]]
(1) For airplanes that have accomplished a detailed visual
inspection in accordance with AD 97-14-11 prior to the effective
date of this AD: Perform a subsequent detailed visual inspection
prior to the accumulation of 1,000 total flight hours, or within 100
flight hours after the immediately preceding inspection accomplished
in accordance with AD 97-14-11, whichever occurs later. Thereafter,
repeat the inspection at intervals not to exceed 100 flight hours.
(2) For airplanes that have not accomplished a detailed visual
inspection in accordance with AD 97-14-11 prior to the effective
date of this AD: Perform a detailed visual inspection within 20
flight hours after the effective date of this AD. Perform a
subsequent detailed visual inspection prior to the accumulation of
1,000 total flight hours, or within 100 flight hours after
accomplishment of the immediately preceding inspection, whichever
occurs later. Thereafter, repeat the inspection at intervals not to
exceed 100 flight hours.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc. may be used. Surface cleaning and
elaborate access procedures may be required.''
Note 3: Accomplishment of the inspection required by paragraph
(a) of thisAD, prior to the effective date of this AD in accordance
with Canadair Regional Jet AlertService Bulletin A601R-53-045, dated
June 25, 1997; Revision `A,' includingAppendix 1, dated June 26,
1997; Revision `B,' including Appendix 1, dated June 27,1997; or
Revision `C,' including Appendix 1, dated July 2, 1997; is
considered acceptable for compliance with the applicable action
specified by this AD.
Modification
(b) For any airplane on which no cracking has been detected
during any inspection required by paragraph (a) of this AD: Within 9
months after the effective date of this AD, modify FS409+128 of the
bulkhead web drawing number 601R32208-123 of the fuselage in
accordance with Canadair Regional Jet Service Bulletin 601R-53-047,
Revision `D,' including Appendix 1 and Appendix 2, dated December
22, 1997. Accomplishment of this modification terminates the
requirements of this AD.
Note 4: Any modification accomplished prior to the effective
date of this AD in accordance with Canadair Regional Jet Service
Bulletin 601R-53-047, including Appendix 1 and Appendix 2, dated
July 18, 1997; Revision `A,' including Appendix 1 and Appendix 2,
dated July 31, 1997; Revision `B,' including Appendix 1 and Appendix
2, dated August 22, 1997; or Revision `C,' including Appendix 1 and
Appendix 2, dated October 7, 1997; is considered acceptable for
compliance with the applicable actions required by this AD.
Repair
(c) For any airplane on which any cracking is detected during
any inspection required by paragraph (a) of this AD: Prior to
further flight, determine the extent of the cracking as specified in
Part A of paragraph 2.B. of the Accomplishment Instructions of
Canadair Regional Jet Alert Service Bulletin A601R-53-045, Revision
`D,' including Appendix 1, dated December 22, 1997, and accomplish
the requirements of paragraph (c)(1) or (c)(2), as applicable.
(1) If the cracking is within the limits specified by Part A of
paragraph 2.B. of the Accomplishment Instructions of the alert
service bulletin, accomplish the requirements of paragraphs
(c)(1)(i) and (c)(1)(ii) of this AD at the time specified in those
paragraphs.
(i) Repeat the detailed visual inspection required by paragraph
(a) of this AD thereafter at intervals not to exceed 100 flight
hours; and
(ii) Within 6 months after the effective date of this AD, or
within 3 months after the initial date the crack was detected,
whichever occurs later: Repair the affected area in accordance with
Canadair Regional Jet Service Bulletin 601R-53-046, Revision `B,'
dated December 22, 1997. Accomplishment of this repair terminates
the requirements of this AD.
Note 5: Any repair accomplished prior to the effective date of
this AD in accordance with Canadair Regional Jet Service Bulletin
601R-53-046, dated June 27, 1997, or Revision `A,' dated July 2,
1997, is considered acceptable for compliance with the applicable
actions specified by this AD.
(2) If the cracking is outside the limits specified by Part A of
the Accomplishment Instructions of the alert service bulletin, prior
to further flight, perform a high frequency eddy current (HFEC)
inspection to detect cracks of the forward side of the web of
fuselage FS409+128 bulkhead web drawing number 601R32208-123, along
the upper edge of the horizontal angle part number 601R32208-73, in
accordance with Part B of paragraph 2.B. of the Accomplishment
Instructions of the alert service bulletin.
(i) If, during any HFEC inspection required by paragraph (c)(2)
of this AD, any cracking is detected that is within the limits
specified by Part B of paragraph 2.B. of the Accomplishment
Instructions of the alert service bulletin, accomplish the
requirements of paragraphs (c)(2)(i)(A) and (c)(2)(i)(B) of this AD
at the times specified in those paragraphs.
(A) Repeat the HFEC inspection required by paragraph (c)(2) of
this AD thereafter at intervals not to exceed 50 flight hours, and
repeat the detailed visual inspection required by paragraph (a) of
this AD thereafter at interval not to exceed 100 flight hours; and
(B) Within 6 months after the effective date of this AD, or
within 3 months after the initial date the crack was detected,
whichever occurs later: Repair the affected area in accordance with
Canadair Regional Jet Service Bulletin 601R-53-046, Revision `B,'
dated December 22, 1997. Accomplishment of this repair terminates
the requirements of this AD.
(ii) If, during any HFEC inspection required by paragraph (c)(2)
of this AD, any cracking is detected that is outside the limits
specified by Part B of paragraph 2.B. of the Accomplishment
Instructions of the alert service bulletin, prior to further flight,
determine the extent of the cracking as specified in paragraph 1.D.
(``Compliance'') of Canadair Regional Jet Service Bulletin 601R-53-
046, Revision `B,' dated December 22, 1997, and accomplish the
requirements of paragraph (c)(2)(ii)(A) or (c)(2)(ii)(B) of this AD,
as applicable.
(A) If the cracking is within the limits specified by paragraph
1.D. (``Compliance'') of the service bulletin, prior to further
flight, repair in accordance with the service bulletin.
Accomplishment of this repair terminates the requirements of this
AD.
(B) If the cracking is outside the limits specified by paragraph
1.D. (``Compliance'') of the service bulletin, prior to further
flight, repair in accordance with a method approved by the Manager,
New York Aircraft Certification Office (ACO).
Alternative Methods of Compliance
(d)(1) 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.
(2) Alternative methods of compliance, approved previously in
accordance with AD 97-14-11, amendment 39-10082, are approved as
alternative methods of compliance for this AD.
Note 6: 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
(e) Special flight permits may be issued in accordance with
sections 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
(f) Except as provided by paragraph (c)(2)(ii)(B) of this AD,
the actions shall be done in accordance with Canadair Regional Jet
Alert Service Bulletin A601R-53-045, Revision `D,' including
Appendix 1, dated December 22, 1997; Canadair Regional Jet Service
Bulletin 601R-53-047, Revision `D,' including Appendix 1 and
Appendix 2, dated December 22, 1997; and Canadair Regional Jet
Service Bulletin 601R-53-046, Revision `B,' dated December 22, 1997;
as applicable. 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,
[[Page 2022]]
Third Floor, Valley Stream, New York; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
Note 7: The subject of this AD is addressed in Canadian
airworthiness directive CF-97-11R2, dated December 22, 1997.
(g) This amendment becomes effective on February 17, 2000.
Issued in Renton, Washington, on January 6, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-720 Filed 1-12-00; 8:45 am]
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