[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

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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.

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    (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,

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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]
BILLING CODE 4910-13-P