[Federal Register: December 5, 2005 (Volume 70, Number 232)]
[Rules and Regulations]
[Page 72361-72363]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05de05-7]
[[Page 72361]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-46-AD; Amendment 39-14392; AD 2005-24-12]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2C10 (Regional
Jet Series 700, 701, & 702) 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-600-2C10 (Regional Jet Series
700, 701, & 702) airplanes, that requires an inspection of the thrust
reverser cascades for correct installation; removing and reinstalling
the cascade in the correct location, if necessary; and reworking the
thrust reverser cascades to add locating spigots (metal protrusions) to
each cascade; as applicable. This action is necessary to prevent
asymmetric reverse thrust and consequent loss of control of the
airplane during reverse thrust operation. This action is intended to
address the identified unsafe condition.
DATES: Effective January 9, 2006.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 9, 2006.
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, New York Aircraft Certification
Office, 1600 Stewart Avenue, suite 410, Westbury, New York.
FOR FURTHER INFORMATION CONTACT: Rocco Viselli or James Delisio,
Aerospace Engineers, New York Aircraft Certification Office, FAA,
Engine and Propeller Directorate, 1600 Stewart Avenue, suite 410,
Westbury, New York 11590; telephone (516) 228-7331; 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 Bombardier Model CL-600-2C10
(Regional Jet Series 700, & 701) series airplanes was published in the
Federal Register on May 19, 2004 (69 FR 28865). That action proposed to
require an inspection of the thrust reverser cascades for correct
installation; removing and reinstalling the cascade in the correct
location, if necessary; and reworking the thrust reverser cascades to
add locating spigots (metal protrusions) to each cascade; 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 comments received.
Request To Clarify Intent of Paragraph (b) of the Proposed AD
The commenter requests clarification on the inspection of the
cascades upon the reinstallation of a cascade. The commenter wonders:
``In the event only one cascade is removed and reinstalled, does this
paragraph require performance of the entire service bulletin
([Bombardier Alert Service Bulletin] A670BA-78-001) meaning both
[engine] nacelles, on the corresponding nacelle, or for the individual
cascade?'
We agree that clarification may be needed. We intended only for the
corresponding nacelle or for the individual cascade to be inspected for
correct installation when a cascade is removed and reinstalled. We have
not changed the AD in this regard.
Request To Change the Applicability of Paragraph (b)
The commenter requests that the applicability of paragraph (b) of
the proposed AD be changed since the applicability of paragraph (a) is
limited to airplanes with serial numbers (S/N) 10005 through 10040. The
commenter suggests revising paragraph (b) to be applicable only to
cascades that have been removed and reinstalled.
We agree that the reasoning for the applicability of paragraph (b)
of this AD needs to be clarified. However, we disagree that paragraph
(b) needs to be revised. Airplanes with S/N 10005 through 10040
inclusive may have been delivered to customers with incorrectly
installed cascades (before awareness of the incorrect cascade
installation occurred). Airplanes with S/N 10003, 10004, and 10041
through 10116 were subject to a pre-delivery inspection to ensure that
the airplanes were delivered with correctly configured cascades.
However, those airplanes were delivered with cascades that could be
mis-installed during maintenance actions. Airplanes with S/N 10117 and
subsequent were delivered with cascades that were modified to help
prevent mis-installation of the cascades. We have not changed the AD in
this regard.
Request To Revise Cost Impact Statement
The commenter states that the cost impact statements do not reflect
those in the referenced service bulletins. We infer that the commenter
requests that the cost estimates be revised.
We partially agree to revise the cost impact statement. We
erroneously stated the per nacelle cost to perform the modification as
the per airplane cost. We have revised the statement to state the
correct per airplane cost for the modification. However, we do not
agree to revise the cost estimate for the inspection. We only include
costs directly related to the required action. While the service
bulletin includes an estimate on the cost to access and close-up the
inspection area and other actions not directly a part of the
inspection, we do not include those costs in our estimate. Those
actions can be used in combination with other ADs, service bulletins,
or maintenance actions that use the same access points.
Request To Delete Paragraph (e) of This AD
The commenter states that due to the amount of work hours involved
in modifying the cascades, the applicability of paragraph (e) of the
proposed AD should be modified to be limited only to cascades that have
been removed and reinstalled or replaced per the inspection criteria in
paragraph (b) of the proposed AD.
We do not agree to eliminate or modify paragraph (e) of this AD.
The actions of paragraphs (b) and (e) of this AD are intended to
differentiate between installation and reinstallation situations. For
instance, a situation where an operator removes a cascade to gain
access to an engine component may be considered a ``reinstallation''
situation, and the operator would be required to inspect the cascade
installation to ensure that the removed cascade was reinstalled
correctly. In that case, paragraph (b) would apply and the operator
would not need to modify the cascade per paragraph (e). In contrast, if
an operator was removing a cascade to do an action on it or to replace
the cascade with another cascade, then the operator would be required
to ensure that the cascade being installed has been modified in
accordance with paragraph (e) and would not be permitted to only
[[Page 72362]]
inspect for proper installation. The modification in paragraph (e) is
intended as a terminating action for the inspections required by this
AD. We have not changed the AD in this regard.
Parts Availability
The commenter also states that spares are not readily available.
The commenter adds that the lead time (order to delivery) for kits to
modify the thrust reverser cascades is 10 to 12 weeks. We infer that
the commenter wants the compliance time for the modified parts required
in paragraph (e) of this AD to be extended.
We agree to extend the compliance time of paragraph (e) of this AD
and have modified paragraph (e) to have a compliance time of 90 days
after the effective date of this AD. We have evaluated the level of
risk and have determined that extending the compliance time for
paragraph (e) of this AD will not adversely affect safety. Should it be
necessary, paragraph (g) of this AD provides operators the opportunity
to request an additional extension of the compliance time if data (such
as proof that parts have been ordered) are presented to justify such an
extension.
Request To Revise Reference in Note 2
The commenter notes that the Bombardier service bulletin reference
in Note 2 is missing a ``B'' from the service bulletin number.
We agree. We have changed the reference in Note 2 to correctly
reference the Bombardier service bulletin.
Explanation of Change to Applicability
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Clarification of Previous Difference With the Canadian Airworthiness
Directive
In the NPRM, we differed from the Canadian airworthiness directive
available at that time (CF-2002-30, dated May 22, 2002) and proposed
requiring the modification actions in paragraph (d) of this AD. We also
noted that Transport Canada Civil Aviation (TCCA) was considering
superseding their airworthiness directive to mandate the same actions
we specified in paragraph (d). On June 22, 2004, the TCCA issued a
revised Canadian airworthiness directive (CF-2002-30R1) that added a
requirement for the modification that is the same as the actions of
paragraph (d). We no longer differ from the Canadian airworthiness
directive. We have revised Note 3 of this AD to refer to the revised
Canadian airworthiness directive.
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.
Cost Impact
The FAA estimates that 102 airplanes of U.S. registry will be
affected by this AD. The average labor rate is $65 per work hour.
It will take approximately 1 work hour per airplane to accomplish
the inspection. Based on these figures, the cost impact of the
inspection on U.S. operators is estimated to be $6,630, or $65 per
airplane, per inspection cycle.
It will take approximately 6 work hours per airplane to accomplish
the modification. Based on these figures, the cost impact of the rework
on U.S. operators is estimated to be $39,780, or $390 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.
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 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:
[[Page 72363]]
2005-24-12 Bombardier, Inc (Formerly Canadair): Amendment 39-14392.
Docket No. 2003-NM-46-AD.
Applicability: Model CL-600-2C10 (Regional Jet Series 700, 701,
& 702) airplanes, serial numbers 10003 through 10116 inclusive,
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent asymmetric reverse thrust and consequent loss of
control of the airplane during reverse thrust operation, accomplish
the following:
Inspection
(a) For airplanes with serial numbers 10005 through 10040
inclusive: Within 72 flight hours or 30 days from the effective date
of the AD, whichever occurs first, perform a general visual
inspection of the thrust reverser cascades for correct installation,
per the Accomplishment Instructions of Bombardier Alert Service
Bulletin A670BA-78-001, Revision A, dated April 23, 2002.
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.''
Repetitive Inspections for Certain Airplanes
(b) For airplanes with serial numbers 10003 through 10116
inclusive: Each time the thrust reverser cascade is removed and
reinstalled, perform the action specified in paragraph (a) of this
AD.
Corrective Action
(c) If any thrust reverser cascade is found to be incorrectly
installed during any inspection required by paragraph (a) or (b) of
this AD, before further flight, remove and reinstall the cascade in
the correct location, per the Accomplishment Instructions of
Bombardier Alert Service Bulletin A670BA-78-001, Revision A, dated
April 23, 2002.
Terminating Action
(d) Within 6,000 flight hours from the effective date of the AD,
rework the thrust reverser cascades by accomplishing all the actions
in the Accomplishment Instructions of Bombardier Service Bulletin
670BA-78-003, dated January 22, 2004. Accomplishment of the rework
terminates the requirements of paragraphs (a) and (b) of this AD.
Note 2: Bombardier Service Bulletin 670BA-78-003, references GE
Aircraft Engines Service Bulletin 670GE-78-008, dated December 17,
2003, as an additional source of service information for the
accomplishment of the rework.
Parts Installation
(e) Except as provided by paragraphs (b) and (c) of this AD,
within 90 days after the effective date of this AD, no person may
install on any airplane a thrust reverser cascade with powerplant
system, serial numbers PS0003 through PS0116 inclusive, left- and
right-hand, unless it has been reworked per Bombardier Service
Bulletin 670BA-78-003, dated January 22, 2004.
Previous Actions
(f) Inspections accomplished before the effective date of this
AD per Bombardier Alert Service Bulletin A670BA-78-001, dated April
19, 2002, are considered acceptable for compliance with paragraphs
(a) and (b) of this AD.
Alternative Methods of Compliance (AMOCs)
(g)(1) In accordance with 14 CFR 39.19, the Manager, New York
Aircraft Certification Office, FAA, is authorized to approve AMOCs
for this AD.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Incorporation by Reference
(h) Unless otherwise specified in this AD, the actions must be
done in accordance with Bombardier Alert Service Bulletin A670BA-78-
001, Revision A, dated April 23, 2002; and Bombardier Service
Bulletin 670BA-78-003, dated January 22, 2004; 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. 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, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or to the FAA, New York
Aircraft Certification Office, 1600 Stewart Avenue, suite 410,
Westbury, New York; or to the National Archives and Records
Administration (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/code-- of--federal--regulations/
ibr--locations.html.
Note 3: The subject of this AD is addressed in Canadian
airworthiness directive CF-2002-30R1, dated June 22, 2004.
Effective Date
(i) This amendment becomes effective on January 9, 2006.
Issued in Renton, Washington, on November 18, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-23511 Filed 12-2-05; 8:45 am]
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