[Federal Register Volume 66, Number 227 (Monday, November 26, 2001)]
[Rules and Regulations]
[Pages 58931-58932]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-29322]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-68-AD; Amendment 39-12488; AD 2001-22-09]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document corrects information in an existing 
airworthiness directive (AD) that applies to certain Bombardier Model 
CL-600-2B19 series airplanes. That AD currently requires repetitive 
eddy current inspections for cracking of the main landing gear (MLG) 
main fittings, and replacement with a new or serviceable MLG, if 
necessary. That AD also requires servicing the MLG shock struts; 
inspecting the MLG shock struts for nitrogen pressure, visible chrome 
dimension, and oil leakage; and performing corrective actions, if 
necessary. This document corrects a typographical error existing in the 
``Applicability'' section of the AD. This correction is necessary to 
ensure that the correct airplane model is specified.

DATES: Effective December 4, 2001.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of December 4, 2001, (66 FR 54658, October 30, 2001).

FOR FURTHER INFORMATION CONTACT: Serge Napoleon, Aerospace Engineer, 
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: On October 22, 2001, the Federal Aviation 
Administration (FAA) issued AD 2001-22-09, amendment 39-12488 (66 FR 
54658, October 30, 2001), which applies to certain Bombardier Model CL-
600-2B19 series airplanes. That AD requires repetitive eddy current 
inspections for cracking of the main landing gear (MLG) main fittings, 
and replacement with a new or serviceable MLG, if necessary. That AD 
also requires servicing the MLG shock struts; inspecting the MLG shock 
struts for nitrogen pressure, visible chrome dimension, and oil 
leakage; and performing corrective actions, if necessary. The actions 
specified by that AD are intended to prevent failure of the MLG main 
fitting, which could result in collapse of the MLG upon landing. The 
actions are intended to address the identified unsafe condition.

Need for the Correction

    The FAA notes that a typographical error occurred in the 
``Applicability'' section of AD 2001-22-09. Although the airplane model 
was referred to correctly as ``CL-600-2B19'' in all other areas of that 
AD, the ``Applicability'' section incorrectly identified the applicable 
airplane model as ``CL-200-2B19.'' We have corrected the 
``Applicability'' section of this AD to specify ``CL-600-2B19.''
    The FAA has determined that a correction to AD 2001-22-09 is 
necessary. The correction will correctly identify the applicable 
airplane model in the ``applicability'' section of the AD.

[[Page 58932]]

Correction of Publication

    This document corrects the error and correctly adds the AD as an 
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 
39.13).
    The AD is reprinted in its entirety for the convenience of affected 
operators. The effective date of the AD remains December 4, 2001.
    Since this action only corrected a typographical error, it has no 
adverse economic impact and imposes no additional burden on any person. 
Therefore, the FAA has determined that notice and public procedures are 
unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Correction

    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  [Corrected]

    2. Section 39.13 is amended by correctly adding the following 
airworthiness directive (AD):

Bombardier:   Amendment 39-. Docket 2000-NM-68-AD.

    Applicability: Model CL-600-2B19 series airplanes, certificated 
in any category, having serial numbers 7003 and subsequent, and 
equipped with a main landing gear (MLG) main fitting having part 
number (P/N) 17064-101, 17064-102, 17064-103, or 17064-104.

    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 prevent failure of MLG main fitting, which could result in 
collapse of the MLG upon landing, accomplish the following:

Inspection and Replacement

    (a) Prior to the accumulation of 1,500 total flight cycles, or 
within 150 flight cycles after December 4, 2001, the effective date 
of this AD, whichever occurs later: Perform an eddy current 
inspection to detect cracking of the MLG main fittings, in 
accordance with Part B of the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A601R-32-079, Revision D, dated 
December 1, 2000. If any cracking is found, prior to further flight, 
replace the cracked fitting with a new or serviceable fitting in 
accordance with the alert service bulletin. Repeat the inspection 
thereafter at intervals not to exceed 500 flight cycles.

Servicing the Shock Struts

    (b) Prior to the accumulation of 1,500 total flight cycles since 
the date of manufacture, or within 500 flight cycles after the 
effective date of this AD, whichever occurs later: Perform a 
servicing (Oil and Nitrogen) of the MLG shock struts (left and right 
main landing shock struts), in accordance with Part C (for airplanes 
on the ground) or Part D (for airplanes on jacks) of the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
A601R-32-079, Revision D, dated December 1, 2000.

Other Inspections

    (c) Within 500 flight cycles after completing the actions 
required by paragraph (b) of this AD: Perform an inspection of the 
MLG left and right shock struts for nitrogen pressure, visible 
chrome dimension, and oil leakage, in accordance with Part E of the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
A601R-32-079, Revision D, dated December 1, 2000. Thereafter, repeat 
the inspection at intervals not to exceed 500 flight cycles.

Corrective Actions for Certain Inspections

    (d) If the chrome extension dimension of the shock strut 
pressure reading is outside the limits specified in the Airplane 
Maintenance Manual, Task 32-11-05-220-801, or any oil leakage is 
found: Prior to further flight, service the MLG shock strut in 
accordance with Part C (for airplanes on the ground) or Part D (for 
airplanes on jacks) of the Accomplishment Instructions of Bombardier 
Alert Service Bulletin A601R-32-079, Revision D, dated December 1, 
2000.

Extension of the Repetitive Interval

    (e) After the effective date of this AD: After a total of five 
consecutive inspections of the MLG shock struts that verify that the 
shock struts are serviced properly, and a total of five consecutive 
eddy current inspections of the MLG main fitting has been 
accomplished that verify there is no cracking of the main fitting, 
in accordance with Bombardier Alert Service Bulletin A601R-32-079, 
Revision D, dated December 1, 2000, the repetitive interval for the 
eddy current inspections required by paragraph (a) of this AD may be 
extended from every 500 flight cycles to every 1,000 flight cycles.

Reporting Requirement

    (f) Within 30 days after each inspection and servicing required 
by paragraphs (a), (b), and (c) of this AD, report all findings, 
positive or negative, to: Bombardier Aerospace, Regional Aircraft, 
CRJ Action Desk, fax number 514-855-8501. Information collection 
requirements contained in this regulation 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 Aircraft Certification 
Office (ACO), FAA. 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 2: 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 
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

    (i) The actions shall be done in accordance with Bombardier 
Alert Service Bulletin A601R-32-079, Revision D, dated December 1, 
2000. This incorporation by reference was approved previously by the 
Director of the Federal Register as of December 4, 2001 (66 FR 
54658, October 30, 2001). 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, 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 3: The subject of this AD is addressed in Canadian 
airworthiness directive CF-1999-32R1, dated January 22, 2001.

Effective Date

    (j) The effective date of this amendment remains December 4, 
2001.

    Issued in Renton, Washington, on November 16, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-29322 Filed 11-23-01; 8:45 am]
BILLING CODE 4910-13-U