[Federal Register: September 6, 2005 (Volume 70, Number 171)]
[Rules and Regulations]
[Page 52902-52903]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06se05-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-163-AD; Amendment 39-14244; AD 2005-18-04]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (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& 440) airplanes, that requires performing an inspection of the
electrical harnesses of the spoiler and the brake pressure sensor unit
on both sides of the wing root to detect any chafing or wire damage,
and repairing or replacing any damaged or chafed harness or wire with a
new harness, as applicable. This action also provides/requires a
terminating modification for the one-time inspection. The actions
specified by this AD are intended to detect and correct chafing of the
electrical cables of the spoiler and brake pressure sensor unit on both
sides of the wing root, which could result in loss of the flight
control system and consequent reduced controllability of the airplane.
This action is intended to address the identified unsafe condition.
DATES: Effective October 11, 2005.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of October 11, 2005.
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, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Wing Chan, Aerospace Engineer, Systems
and Flight Test Branch, ANE-172, FAA, New York Aircraft Certification
Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590;
telephone (516) 228-7311; fax (516) 794-5531.
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 (Regional Jet Series 100 & 440) airplanes was published as a
supplemental notice of proposed rulemaking (NPRM) in the Federal
Register on June 27, 2005 (70 FR 36862). That action proposed to
require performing an inspection of the electrical harnesses of the
spoiler and the brake pressure sensor unit on both sides of the wing
root to detect any chafing or wire damage, and repairing or replacing
any damaged or chafed harness or wire with a new harness, as
applicable. The action also proposed to require performing a
terminating modification for the one-time inspection.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. We received no comments on the
proposed AD or on the determination of the cost to the public.
Conclusion
After careful review of the available data, the FAA has determined
that air safety and the public interest require the adoption of the
rule as proposed.
Cost Impact
The FAA estimates that 709 airplanes of U.S. registry will be
affected by this AD.
It will take approximately 1 work hour per airplane to accomplish
the required inspection, at the average labor rate of $65 per work
hour. Based on these figures, the cost impact of the inspection
required by this AD on U.S. operators is estimated to be $46,085, or
$65 per airplane.
It will take approximately 5 work hours per airplane to accomplish
the required modification, at the average labor rate of $65 per work
hour. Required parts will be supplied by the airplane manufacturer at
no cost to operators. Based on these figures, the cost impact of the
modification required by this AD on U.S. operators is estimated to be
$230,425, or $325 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 thisAD 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.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.''Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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
[[Page 52903]]
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:
2005-18-04 Bombardier, Inc. (Formerly Canadair): Amendment 39-14244.
Docket 2003-NM-163-AD.
Applicability: Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes, serial numbers 7003 through 7067 inclusive, and 7069
through 7947 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct chafing of the electrical cables of the
spoiler and brake pressure sensor unit (BPSU) on both sides of the
wing root, which could result in loss of the flight control system
and consequent reduced controllability of the airplane, accomplish
the following:
Initial Inspections
(a) Within 500 flight hours after the effective date of this AD,
do a general visual inspection for chafing or wire damage of the
electrical harnesses of the spoiler and the BPSU on both sides of
the wing root, in accordance with Part A of the Accomplishment
Instructions of Bombardier Alert Service Bulletin A601R-27-133,
Revision `A,' dated September 16, 2004.
Note 1: 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 from within
touching distance unless otherwise specified. A mirror may be
necessary to enhance visual access to all exposed surfaces in the
inspection area. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or droplight 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.''
Corrective Actions
(b) If any damaged or chafed electrical harness or wire is found
during any inspection required by paragraph (a) of this AD, before
further flight, do either paragraph (b)(1) or (b)(2) of this AD.
(1) Replace any damaged or chafed harness or wire with a new
harness, in accordance with Part C or Part D of the Accomplishment
Instructions of Bombardier Alert Service Bulletin A601R-27-133,
Revision `A', dated September 16, 2004, as applicable.
(2) Repair any damaged or chafed electrical harness in
accordance with Part B of the Accomplishment Instructions of
Bombardier Alert ServiceBulletin A601R-27-133, Revision `A', dated
September 16, 2004. Within 3,500 flight hours after the repair is
done, do paragraph (b)(1) of this AD.
Credit for Earlier Service Bulletins
(c) Inspections, replacements, and repairs accomplished before
the effective date of this AD in accordance with Bombardier Alert
ServiceBulletin A601R-27-101, dated April 17, 2000; or Revision `A,'
dated October 26, 2001; or Bombardier Alert Service Bulletin A601R-
27-133, dated July 12, 2004; are acceptable for compliance with the
corresponding requirements of this AD.
Terminating Modification
(d) Within 4,000 flight hours after the effective date of this
AD, modify the routing and support of the electrical harnesses of
the spoiler and the BPSU on both sides of the wing root by
accomplishing all the actions specified in Part E or F, as
applicable, of the AccomplishmentInstructions of Bombardier Alert
Service Bulletin A601R-27-133, Revision `A', dated September 16,
2004. Accomplishing the modification constitutes compliance with the
requirements of this AD.
Exception to Service Bulletin
(e) Although Bombardier Alert Service Bulletin A601R-27-133,
Revision`A', dated September 16, 2004, specifies to submit certain
information to the manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance
(f) In accordance with 14 CFR 39.19, the Manager, New York
AircraftCertification Office, FAA, is authorized to approve
alternative methods of compliance for this AD.
Note 2: The subject of this AD is addressed in Canadiar
airworthiness directive CF-2003-14R1, effective February 26, 2005.
Incorporation by Reference
(g) Unless otherwise specified in this AD, the actions must be
done in accordance with Bombardier Alert Service Bulletin A601R-27-
133, Revision `A', dated September 16, 2004. 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. To get copies of
this service information, contact Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal,
Quebec H3C 3G9, Canada. To inspect copies of this service
information, go to the FAA, TransportAirplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or to the FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; or to the National Archives and RecordsAdministration
(NARA). For information on the availability of this material at the
NARA, call (202) 741-6030, or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html
.
Effective Date
(h) This amendment becomes effective on October 11, 2005.
Issued in Renton, Washington, on August 24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-17405 Filed 9-2-05; 8:45 am]
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