[Federal Register Volume 68, Number 183 (Monday, September 22, 2003)]
[Rules and Regulations]
[Pages 54994-54996]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-23671]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-176-AD; Amendment 39-13307; AD 2003-19-04]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional
Jet Series 100 and 440) Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series
100 and 440) airplanes, that requires, for certain airplanes, a one-
time inspection to detect chafing or other damage of the integrated
drive generator (IDG) cables and the firewall separators of the pylon,
and corrective action if necessary. For other airplanes, this AD
requires identification of the part number of the clamps, and
replacement with new clamps if necessary. The actions specified by this
AD are intended to prevent electrical arcing between the IDG cables and
the firewall separators due to chafing, which could result in an in-
flight fire and/or loss of electrical power. This action is intended to
address the identified unsafe condition.
DATES: Effective October 27, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 27, 2003.
ADDRESSES: The service information referenced in this AD may be
obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box
6087, Station Centreville, 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; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Luciano L. Castracane, Aerospace
Engineer, Systems and Flight Test Branch, ANE-172, FAA, New York
Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley
Stream, New York 11581; telephone (516) 256-7535; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Bombardier Model CL-600-
2B19 series airplanes was published in the Federal Register on June 18,
2002 (67 FR 41357). That action proposed to require, for certain
affected airplanes, a one-time inspection to detect chafing or other
damage of the integrated drive generator (IDG) cables and the firewall
separators of the pylon, and corrective action if necessary. For other
affected airplanes, that action proposed to require identification of
the part number of the clamps, and replacement with new clamps 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 comments received.
Request To Revise Service Information Citation
One commenter requests that the FAA revise paragraph (a) of the
proposed AD
[[Page 54995]]
to cite only Bombardier Alert Service Bulletin A601R-24-091, dated
March 9, 2000; and Revision A, dated May 10, 2000; as the appropriate
sources of service information for reinspecting for proper clamp part
numbers. The commenter notes that Revision B of the alert service
bulletin, dated September 14, 2000, was issued to, among other things,
specify the proper clamp installations. The commenter agrees, however,
that use of Revision B was correctly addressed in Note 2 of the
proposed AD.
The FAA agrees. Paragraph (a) has been revised accordingly in this
final rule.
Request To Remove ``Spares'' Paragraph
This same commenter requests that paragraph (c) of the proposed AD
be removed. Paragraph (c) of the proposed AD stated that only those IDG
cable clamps having part number TA121010R14-04 (P/N ``-R'') may be
installed on affected airplanes. The commenter describes other
legitimate installations for another part number, TA121010L14-04 (P/N
``-L''), for securing IDG cables elsewhere on the airplane. The
commenter suggests revising the proposed AD to prohibit installation of
P/N ``-L'' during accomplishment of Bombardier Alert Service Bulletin
A601R-24-091, but to specify that P/N ``-R'' must be used to obtain the
proper IDG cable orientation/clearance from the pylon separator panel.
The FAA concurs. Paragraph (c) has been revised in this final rule
to prohibit installation of P/N ``-L'' during incorporation of Revision
``C'' of Bombardier Alert Service Bulletin A601R-24-091.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Changes to Proposed AD
The identity of affected airplanes has been changed in this final
rule to ``Bombardier Model CL-600-2B19 (Regional Jet series 100 and
440) airplanes'' to match the type certificate data sheet for these
airplanes.
Paragraph (a)(2) has been revised in this final rule to identify
the source of service information to clarify the required method for
the clamp replacement.
Changes to 14 CFR Part 39/Effect on the AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance. However, for clarity and consistency in this final rule, we
have retained the language of the NPRM regarding that material.
Revised Labor Rate
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
Cost Impact
The FAA estimates that 160 airplanes of U.S. registry will be
affected by this AD.
It will take approximately 7 work hours per airplane to accomplish
the inspection, at an average labor rate of $65 per work hour. Based on
these figures, the cost impact of this action is estimated to be $455
per airplane.
It will take approximately 1 work hour per airplane to determine
the part number of the clamp, at an average labor rate of $65 per work
hour. Based on these figures, the cost impact of this action is
estimated to be $65 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 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
0
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
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2003-19-04 Bombardier, Inc. (Formerly Canadair): Amendment 39-13307.
Docket 2001-NM-176-AD.
Applicability: Model CL-600-2B19 (Regional Jet series 100 and
440) airplanes, serial numbers 7003 through 7269 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 (e) 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.
[[Page 54996]]
Compliance: Required as indicated, unless accomplished
previously.
To prevent electrical arcing between the integrated drive
generator (IDG) cables and the firewall separators due to IDG cable
chafing, which could result in an in-flight fire and/or loss of
electrical power, accomplish the following:
Part Number Identification
(a) For airplanes that have been repaired or modified before the
effective date of this AD in accordance with Bombardier Alert
Service Bulletin A601R-24-091, dated March 9, 2000; or Revision
``A,'' dated May 10, 2000: Within 550 flight hours or 2 months after
the effective date of this AD, whichever occurs first, determine the
part numbers (P/Ns) of the clamps that hold the IDG cables on the
left and right pylons.
(1) If the P/N of all clamps is TA121010R14-04: No further
action is required by this paragraph.
(2) If the P/N of any clamp is NOT TA121010R14-04: Before
further flight, replace the discrepant clamp with a clamp having P/N
TA121010R14-04, in accordance with Bombardier Alert Service Bulletin
A601R-24-091, Revision `C,' dated February 1, 2001.
Inspection
(b) For airplanes not identified in paragraph (a) of this AD:
Within 550 flight hours or 2 months after the effective date of this
AD, whichever occurs first, perform a one-time general visual
inspection to detect chafing and other damage of the IDG cables and
the firewall separators of the pylon, in accordance with Bombardier
Alert Service Bulletin A601R-24-091, Revision `C,' dated February 1,
2001. Prior to further flight thereafter, perform all applicable
corrective actions and install a clamp, a conduit, and Teflon
strips, in accordance with the alert service bulletin. If a
temporary repair is performed, replace the harnesses with new parts
within 4,000 flight hours after the repair, in accordance with the
alert service bulletin.
(c) Accomplishment of an inspection and applicable corrective
actions before the effective date of this AD in accordance with
Bombardier Alert Service Bulletin A601R-24-091, Revision `B,' dated
September 14, 2000, is acceptable for compliance with the
requirements of paragraph (b) of this AD.
Note 2:
For the purposes of this AD, a general visual inspection is
defined as: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or drop-light, and may require removal or opening of
access panels or doors. Stands, ladders, or platforms may be
required to gain proximity to the area being checked.''
Part Installation
(d) As of the effective date of this AD, no person may install
an IDG cable clamp, P/N TA121010L14-04, during incorporation of
Revision `C' of Bombardier Alert Service Bulletin A601R-24-091.
Alternative Methods of Compliance
(e) 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 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
(f) 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
(g) Unless otherwise specified in this AD, the actions must be
done in accordance with Bombardier Alert Service Bulletin A601R-24-
091, Revision `C,' dated February 1, 2001. 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 Centreville, 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-2000-17R1, dated October 30, 2000.
Effective Date
(h) This amendment becomes effective on October 27, 2003.
Issued in Renton, Washington, on September 11, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-23671 Filed 9-18-03; 12:01 pm]
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