Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 68313-68316 [E8-26915]
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Federal Register / Vol. 73, No. 223 / Tuesday, November 18, 2008 / Rules and Regulations
(iii) Certain aircraft arriving from
areas south of the United States. Certain
aircraft arriving from areas south of the
United States (other than Cuba) must
follow the advance notice of arrival
procedures set forth in § 122.23 of this
part.
(iv) Other aircraft. The commander of
an aircraft not otherwise covered by
paragraphs (c)(1)(i), (c)(1)(ii) and
(c)(1)(iii) of this section must give
advance notice of arrival as set forth in
paragraph (d) of this section. Notice
must be given to the port director at the
place of first landing, either:
(A) Directly by radio, telephone, or
other method; or
(B) Through Federal Aviation
Administration flight notification
procedure (see International Flight
Information Manual, Federal Aviation
Administration).
(2) Reliable facilities. When reliable
means for giving notice are not available
(for example, when departure is from a
remote place) a departure must be made
at a place where notice can be sent prior
to coming into the U.S.
(d) Contents of notice. The advance
notice of arrival required by aircraft
covered in paragraph (c)(1)(iv) of this
section must include the following
information:
(1) Type of aircraft and registration
number;
(2) Name (last, first, middle, if
available) of aircraft commander;
(3) Place of last foreign departure;
(4) International airport of intended
landing or other place at which landing
has been authorized by CBP;
(5) Number of alien passengers;
(6) Number of citizen passengers; and
(7) Estimated time of arrival.
(e) Time of notice. Notice of arrival as
required pursuant to paragraph (c)(1)(iv)
of this section must be furnished far
enough in advance to allow inspecting
CBP officers to reach the place of first
landing of the aircraft prior to the
aircraft’s arrival.
(f) Notice of other Federal agencies.
When advance notice is received, the
port director will inform any other
concerned Federal agency.
■ 11. Section 122.32 is revised to read
as follows:
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§ 122.32
Aircraft required to land.
(a) Any aircraft coming into the U.S.,
from an area outside of the U.S., is
required to land, unless it is denied
permission to land in the U.S. by CBP
pursuant to § 122.12(c), or is exempted
from landing by the Federal Aviation
Administration.
(b) Conditional permission to land.
CBP has the authority to limit the
locations where aircraft entering the
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13:43 Nov 17, 2008
Jkt 217001
U.S. from a foreign area may land. As
such, aircraft must land at the airport
designated in their APIS transmission
unless instructed otherwise by CBP or
changes to the airport designation are
required for aircraft and/or airspace
safety as directed by the Federal
Aviation Administration (FAA) flight
services.
■ 12. Section 122.61 is amended by
revising the introductory text of
paragraph (a) to read as follows:
§ 122.61
Aircraft required to clear.
(a) Private aircraft leaving the United
States as defined in § 122.22, for a
foreign area are required to clear as set
forth in § 122.26. All other aircraft,
except for public aircraft leaving the
United States for a foreign area, are
required to clear if:
*
*
*
*
*
■ 13. Section 122.154 is amended by
revising paragraph (a) and adding a new
paragraph (d) to read as follows:
§ 122.154
Notice of arrival.
(a) Application. All aircraft entering
the U.S. from Cuba must give advance
notice of arrival, unless it is an Office
of Foreign Assets Control (OFAC)
approved scheduled commercial aircraft
of a scheduled airline.
*
*
*
*
*
(d) Private Aircraft. In addition to
these requirements, private aircraft must
also give notice of arrival pursuant to
§ 122.22 of this part.
Michael Chertoff,
Secretary.
[FR Doc. E8–26621 Filed 11–17–08; 8:45 am]
BILLING CODE 9111–14–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0265; Directorate
Identifier 2007–NM–349–AD; Amendment
39–15732; AD 2008–23–11]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2B19 (Regional Jet
Series 100 & 440) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Bombardier
Model CL–600–2B19 airplanes. That AD
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currently requires repetitive eddy
current inspections for cracking of the
main landing gear (MLG) main fittings,
and replacement with new or
serviceable MLG main fittings if
necessary. The existing AD also
currently 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. For certain airplanes, this
new AD requires replacement of the
MLG main fittings with new improved
MLG main fittings, which would
terminate the repetitive inspections of
the MLG main fittings and inspection
and servicing of the MLG shock struts.
This AD results from premature failure
of the MLG main fittings. We are issuing
this AD to prevent failure of the MLG
main fittings, which could result in
collapse of the MLG upon landing.
DATES: This AD becomes effective
December 23, 2008.
On February 16, 2007 (72 FR 1430,
January 12, 2007), the Director of the
Federal Register approved the
incorporation by reference of
Bombardier Service Bulletin 601R–32–
093, Revision B, dated July 14, 2005.
On June 13, 2003 (68 FR 31956, May
29, 2003), the Director of the Federal
Register approved the incorporation by
reference of Bombardier Alert Service
Bulletin A601R–32–079, Revision ‘E,’
dated September 12, 2002; including
Appendix 1, Revision ‘D,’ dated
September 12, 2002; including
Appendices 2 and 3, dated September
12, 2002.
ADDRESSES: For service information
identified in this AD, contact
Bombardier, Inc., Canadair, Aerospace
Group, P.O. Box 6087, Station Centreville, Montreal, Quebec H3C 3G9,
Canada.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Pong K. Lee, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
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Federal Register / Vol. 73, No. 223 / Tuesday, November 18, 2008 / Rules and Regulations
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7324; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2003–11–11, amendment
39–13170 (68 FR 31956, May 29, 2003).
The existing AD applies to certain
Bombardier Model CL–600–2B19
airplanes. That NPRM was published in
the Federal Register on March 11, 2008
(73 FR 12901). That NPRM proposed to
require replacement of the main landing
gear (MLG) main fittings with new
improved MLG main fittings, which
would terminate the existing repetitive
inspections of the MLG main fittings
and inspection and servicing of the
MLG shock struts.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Request To Clarify Airplanes on Which
the Replacement Is Required
Bombardier notes that the
applicability in AD 2007–01–07
(specified in the NPRM as ‘‘Other
Related Rulemaking’’) covers the entire
fleet of Model CL–600–2B19 airplanes
(serial number (S/N) 7003 through 7067
and 7069 through 8999 inclusive) since
S/N 7068 is a hull loss and the airplane
series ends at S/N 8999. Bombardier
states that the applicability specified in
the NPRM will not cover additional
Model CL–600–2B19 airplanes.
Bombardier adds that every Model CL–
600–2B19 airplane equipped with a
MLG main fitting having part number
(P/N) 601R85001–3/4 (Messier-Dowty P/
N 17064–101 through 104) will need to
be in compliance with the replacement
required by AD 2007–01–07 by May 16,
2008.
We infer that Bombardier requests
that we clarify which airplanes are
required to do the replacement specified
in paragraph (r) of this AD. We agree
that the airplanes affected by paragraph
(r) of this AD should be further clarified.
As stated by Bombardier, for Model CL–
600–2B19 airplanes having S/N 7003
through 7067 and 7069 through 8999
inclusive, the replacement is already
required in accordance with paragraph
(l) of AD 2007–01–07. Therefore, we
have changed paragraph (r) of this AD
to specify that the replacement be
accomplished only on airplanes having
S/Ns 9000 and subsequent, which
terminates the requirements of
paragraphs (h) through (q) of this AD.
We have also changed paragraph (t) of
this AD to specify that, for the other
airplanes on which the replacement
required by paragraph (l) of AD 2007–
01–07 has been accomplished, it
terminates the requirements of
paragraphs (h) through (q) of this AD.
We disagree with the commenter that
the applicability in AD 2007–01–07
covers the entire fleet. In order to ensure
that any future production airplanes,
S/N 9000 and subsequent, meet the
compliance requirements of this AD, the
replacement specified in paragraph (r)
of this AD is necessary to address the
identified unsafe condition. We have
also revised the Estimated Costs table in
the preamble of this AD by changing the
number of U.S.-registered airplanes
required to do the replacement from 618
to 0.
Request To Change Compliance Time
Bombardier Aerospace asks that we
change the compliance time specified in
the NPRM. Bombardier states that AD
2007–01–07 (under ‘‘Related
Rulemaking’’ in the NPRM) is effective
for the same parts and also mandates
incorporation of Bombardier Service
Bulletin 601R–32–093, Revision B,
dated July 14, 2005. Bombardier notes
that AD 2007–01–07 was effective on
February 16, 2007, and its compliance
date is May 16, 2008. Bombardier adds
that this compliance date is 9 months
later than the date agreed to by MessierDowty, Bombardier Aerospace, and
Transport Canada, based on careful
consideration of fleet safety, MLG
capability/logistics, and operator
overhaul facilities capacity. Bombardier
asks that the compliance time be the
same as the time in AD 2007–01–07 (i.e.,
no later than May 16, 2008). Bombardier
considers that different compliance
dates for the same service bulletin will
create confusion among U.S. operators
and unnecessary burden for all parties
involved.
We do not agree with the commenter.
As stated previously, the new
requirements in this AD apply only to
airplanes having S/Ns 9000 and
subsequent. Therefore, we have made
no change to the AD in this regard.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been received, and determined
that air safety and the public interest
require adopting the AD with the
changes described previously. We have
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
The following table provides the
estimated costs, at an average labor rate
of $80 per work hour, for U.S. operators
to comply with this AD. Due to other
existing ADs, the actions have already
been accomplished on the majority of
affected U.S.-registered airplanes;
therefore, the estimated costs will be
significantly less than those specified in
the table.
ESTIMATED COSTS
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Action
Detailed inspection (required
by AD 2003–11–11).
Eddy current inspection (required by AD 2003–11–11).
Fluorescent penetrant inspection (required by AD 2003–
11–11).
Inspection and servicing of
shock struts (required by AD
2003–11–11).
Replacement (new action) ......
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13:43 Nov 17, 2008
Work
hours
Number of
U.S.-registered
airplanes
Parts
Cost per airplane
1
None ...................
$80, per inspection cycle .......
618
$49,440, per inspection cycle.
1
None ...................
$80, per inspection cycle .......
618
$49,440, per inspection cycle.
1
None ...................
$80, per inspection cycle .......
618
$49,440, per inspection cycle.
2
None ...................
$160, per inspection cycle .....
618
$98,880, per inspection cycle.
56
Up to $35,000 ....
Up to $39,480 .........................
0
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Fleet cost
$0.
Federal Register / Vol. 73, No. 223 / Tuesday, November 18, 2008 / Rules and Regulations
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 Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD 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.
For the reasons discussed above, I
certify that this AD:
(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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13170 (68
FR 31956, May 29, 2003) and by adding
the following new airworthiness
directive (AD):
■
2008–23–11 Bombardier, Inc. (Formerly
Canadair): Amendment 39–15732.
Docket No. FAA–2008–0265; Directorate
Identifier 2007–NM–349–AD.
Effective Date
(a) This AD becomes effective December
23, 2008.
Affected ADs
(b) This AD supersedes AD 2003–11–11.
Applicability
(c) This AD applies to Bombardier Model
CL–600–2B19 (Regional Jet Series 100 & 440)
airplanes, certificated in any category; having
serial numbers (S/Ns) 7003 and subsequent,
equipped with main landing gear (MLG)
main fittings having part numbers (P/Ns)
601R85001–3 and –4 (Messier-Dowty P/Ns
17064–101, –102, –103, and –104).
Unsafe Condition
(d) This AD results from premature failure
of the MLG main fittings. We are issuing this
AD to prevent failure of the MLG main
fittings, which could result in collapse of the
MLG upon landing.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Note 1: Where there are differences
between the referenced service bulletin and
the AD, the AD prevails.
Restatement of Requirements of AD 2003–
11–11
Service Bulletin References
(f) Accomplishment of the inspections and
servicing, as applicable, specified in
paragraphs (h), (l), (m), and (n) of this AD,
per Bombardier Alert Service Bulletin
A601R–32–079, dated December 3, 1999;
Revision ‘A,’ dated January 7, 2000; Revision
‘B,’ dated June 1, 2000; Revision ‘C,’ dated
October 26, 2000; or Revision ‘D,’ dated
December 1, 2000; prior to June 13, 2003 (the
effective date of AD 2003–11–11), is
considered acceptable for compliance with
the requirements of paragraphs (h), (l), (m),
and (n) of this AD.
(g) The term ‘‘service bulletin,’’ as used in
paragraphs (h) through (q) of this AD, means
the Accomplishment Instructions of
Bombardier Alert Service Bulletin A601R–
32–079, Revision ‘E,’ dated September 12,
2002; including Appendix 1, Revision ‘D,’
dated September 12, 2002; including
Appendices 2 and 3, dated September 12,
2002.
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Initial Eddy Current Inspection
(h) Perform an eddy current inspection to
detect cracking of the MLG main fittings, per
PART B of the service bulletin, at the earlier
of the times specified in paragraph (h)(1) or
(h)(2) of this AD.
(1) Prior to the accumulation of 1,500 total
flight cycles on the MLG, or within 150 flight
cycles after December 4, 2001 (the effective
date of AD 2001–22–09, amendment 39–
12488, which was superseded by AD 2003–
11–11), whichever occurs later.
(2) Prior to the accumulation of 1,000 total
flight cycles on the MLG, or within 150 flight
cycles after June 13, 2003, whichever occurs
later.
Repetitive Eddy Current Inspections
(i) Repeat the eddy current inspection
specified in paragraph (h) of this AD at the
time specified in paragraph (i)(1), (i)(2), or
(i)(3), as applicable, except as provided by
paragraph (i)(4) of this AD, per PART B of the
service bulletin.
(1) For airplanes on which the eddy
current inspection required by paragraph (h)
of this AD is accomplished after June 13,
2003: Repeat the inspection at intervals not
to exceed 500 flight cycles.
(2) For airplanes on which the repetitive
eddy current inspection required by AD
2001–22–09 has been accomplished, and on
which the repetitive intervals have been
increased per paragraph (j) of AD 2001–22–
09 before June 13, 2003: Repeat the
inspection within 500 flight cycles after June
13, 2003, or within 1,000 flight cycles since
the last eddy current inspection, whichever
occurs first, and thereafter at intervals not to
exceed 500 flight cycles.
(3) For airplanes on which the repetitive
eddy current inspection required by AD
2001–22–09 has been accomplished, and on
which the repetitive intervals have not been
increased per paragraph (j) of AD 2001–22–
09 before June 13, 2003: Repeat the eddy
current inspection at intervals not to exceed
500 flight cycles.
(4) For airplanes on which an eddy current
inspection has been accomplished to confirm
the detailed inspection required by paragraph
(o) of this AD: The next eddy current
inspection must be done within 500 flight
cycles following the last detailed inspection
required by paragraph (o) of this AD, and
thereafter at intervals not to exceed 500 flight
cycles.
Corrective Actions
(j) If no cracking of the MLG main fittings
is suspected during the next eddy current
inspection required by paragraph (h) or (i) of
this AD, but the paint has been removed:
Prior to further flight, apply a new finish and
install the harness clamp on the brake line
with the bolt, washers, nut, and cotter pin;
per PART B of the service bulletin.
(k) If any cracking of the MLG main fittings
is found during any eddy current inspection
required by paragraph (h) or (i) of this AD:
Prior to further flight, replace any cracked
MLG main fitting with a new or serviceable
part per the service bulletin.
Servicing the Shock Struts
(l) Prior to the accumulation of 1,500 total
flight cycles on the MLG shock struts, or
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Federal Register / Vol. 73, No. 223 / Tuesday, November 18, 2008 / Rules and Regulations
within 500 flight cycles after December 4,
2001, whichever occurs later: Service (Oil
and Nitrogen) the left and right MLG shock
struts per PART C (for airplanes on the
ground) or PART D (for airplanes on jacks)
of the service bulletin.
Other Inspections
(m) Within 500 flight cycles after
completing the actions required by paragraph
(l) of this AD: Inspect the MLG left and right
shock struts for nitrogen pressure, visible
chrome dimension, and oil leakage, in
accordance with PART E of the service
bulletin. Thereafter, repeat the inspection at
intervals not to exceed 500 flight cycles.
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Corrective Actions for Certain Inspections
(n) 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 during any
inspection required by paragraph (m) of this
AD: 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 service bulletin.
Detailed and Follow-On Inspections and
Corrective Action
(o) Prior to the accumulation of 1,000 total
flight cycles on the MLG, or within 250 flight
cycles after June 13, 2003, whichever occurs
later: Accomplish a detailed inspection of the
MLG main fittings to detect signs of cracking
(including linear paint cracks along the
circumference of the main fitting tube, lack
of paint (paint peeling) or other paint
damage, lack of adhesion or paint bulging,
and signs of corrosion), per PART A of the
service bulletin. Repeat the inspection
thereafter at intervals not to exceed 100 flight
cycles.
Note 2: For the purposes of this AD, a
detailed 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.’’
(p) If any linear paint crack along the
circumference of the main fitting tube, lack
of paint (paint peeling) or other paint
damage, evidence of paint bulging due to
lack of adhesion, or evidence of corrosion is
found during any inspection required by
paragraph (o) of this AD: Prior to further
flight, accomplish either an eddy current
inspection to detect cracking, per PART B of
the service bulletin; or a fluorescent
penetrant inspection to detect cracking, per
PART F of the service bulletin.
(1) If no cracking of the MLG main fittings
is found during any inspection required by
paragraph (p) of this AD: Prior to further
flight, repaint and/or repair/rework any paint
damage per PART B of the service bulletin.
(2) If any cracking of the MLG main fittings
is found during any inspection required by
paragraph (p) of this AD: Prior to further
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13:43 Nov 17, 2008
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flight, replace any cracked MLG main fitting
with a new or serviceable part per the service
bulletin.
Reporting Requirement
(q) Within 30 days after each inspection
and servicing required by paragraphs (h), (i),
(l), (m), (o), and (p) of this AD, report all
findings, positive or negative, to: Bombardier
Aerospace, In-Service Engineering, fax
number 514–855–8501. Although the service
bulletin references completion of a ‘‘Service
Bulletin Comment Sheet-Facsimile Reply
Sheet,’’ this AD does not require that action.
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.
New Requirements of This AD
Replacement
(r) For airplanes having serial numbers
9000 and subsequent: Within 6 months after
the effective date of this AD, replace the MLG
main fittings with new improved MLG main
fittings, in accordance with Bombardier
Service Bulletin 601R–32–093, Revision ‘B,’
dated July 14, 2005. Replacing the MLG main
fittings terminates the requirements of
paragraphs (h) through (q) of this AD.
Credit for Actions Done According to
Previous Issues of the Service Bulletin
(s) Replacements done before the effective
date of this AD in accordance with
Bombardier Service Bulletin 601R–32–093,
dated October 17, 2003; or Revision ‘A,’
dated September 21, 2004; are acceptable for
compliance with the requirements of
paragraph (r) of this AD.
Credit for AD 2007–01–07
(t) For airplanes having S/Ns 7003 through
7067 inclusive and S/Ns 7069 through 8999
inclusive, equipped with MLG main fittings
having P/N 601R85001–3 or –4 (MessierDowty P/N 17064–101, –102, –103, or –104):
Accomplishing the replacement required by
paragraph (l) of AD 2007–01–07, amendment
39–14879, terminates the requirements of
paragraphs (h) through (q) of this AD.
Alternative Methods of Compliance
(AMOCs)
(u)(1) The Manager, New York Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Pong
K. Lee, Aerospace Engineer, Airframe and
Propulsion Branch, ANE–171, FAA, New
York ACO, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone (516)
228–7324; fax (516) 794–5531. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) AMOCs issued to allow escalation of
the repetitive intervals for the eddy current
inspections from 500 to 1,000 flight cycles in
accordance with paragraph (e) of AD 2001–
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22–09 are not approved as AMOCs with this
AD.
Note 3: Information concerning the
existence of AMOCs with this AD, if any,
may be obtained from the New York ACO.
Related Information
(v) Canadian airworthiness directive CF–
1999–32R3, dated September 21, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
(w) You must use Bombardier Service
Bulletin 601R–32–093, Revision ‘B,’ dated
July 14, 2005; and Bombardier Alert Service
Bulletin A601R–32–079, Revision ‘E,’ dated
September 12, 2002; including Appendix 1,
Revision ‘D,’ dated September 12, 2002;
including Appendices 2 and 3, dated
September 12, 2002; as applicable; to perform
the actions that are required by this AD,
unless the AD specifies otherwise.
(1) On February 16, 2007 (72 FR 1430,
January 12, 2007), the Director of the Federal
Register approved the incorporation by
reference of Bombardier Service Bulletin
601R–32–093, Revision ‘B,’ dated July 14,
2005.
(2) On June 13, 2003 (68 FR 31956, May
29, 2003), the Director of the Federal Register
approved the incorporation by reference of
Bombardier Alert Service Bulletin A601R–
32–079, Revision ‘E,’ dated September 12,
2002; including Appendix 1, Revision ‘D,’
dated September 12, 2002; including
Appendices 2 and 3, dated September 12,
2002.
ˆ
(3) Contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com for a copy of this
service information. You may review copies
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Renton, Washington, on
November 4, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–26915 Filed 11–17–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2008–0529; Airspace
Docket No. 08–AWP–6]
Establishment and Revocation of
Class E Airspace; Lake Havasu, AZ
Federal Aviation
Administration (FAA), DOT.
AGENCY:
E:\FR\FM\18NOR1.SGM
18NOR1
]]>Agencies
[Federal Register Volume 73, Number 223 (Tuesday, November 18, 2008)]
[Rules and Regulations]
[Pages 68313-68316]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-26915]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0265; Directorate Identifier 2007-NM-349-AD;
Amendment 39-15732; AD 2008-23-11]
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.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Bombardier Model CL-600-2B19 airplanes.
That AD currently requires repetitive eddy current inspections for
cracking of the main landing gear (MLG) main fittings, and replacement
with new or serviceable MLG main fittings if necessary. The existing AD
also currently 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. For
certain airplanes, this new AD requires replacement of the MLG main
fittings with new improved MLG main fittings, which would terminate the
repetitive inspections of the MLG main fittings and inspection and
servicing of the MLG shock struts. This AD results from premature
failure of the MLG main fittings. We are issuing this AD to prevent
failure of the MLG main fittings, which could result in collapse of the
MLG upon landing.
DATES: This AD becomes effective December 23, 2008.
On February 16, 2007 (72 FR 1430, January 12, 2007), the Director
of the Federal Register approved the incorporation by reference of
Bombardier Service Bulletin 601R-32-093, Revision B, dated July 14,
2005.
On June 13, 2003 (68 FR 31956, May 29, 2003), the Director of the
Federal Register approved the incorporation by reference of Bombardier
Alert Service Bulletin A601R-32-079, Revision `E,' dated September 12,
2002; including Appendix 1, Revision `D,' dated September 12, 2002;
including Appendices 2 and 3, dated September 12, 2002.
ADDRESSES: For service information identified in this AD, contact
Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station
Centre-ville, Montreal, Quebec H3C 3G9, Canada.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Pong K. Lee, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-
[[Page 68314]]
171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue,
Suite 410, Westbury, New York 11590; telephone (516) 228-7324; fax
(516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2003-11-11, amendment
39-13170 (68 FR 31956, May 29, 2003). The existing AD applies to
certain Bombardier Model CL-600-2B19 airplanes. That NPRM was published
in the Federal Register on March 11, 2008 (73 FR 12901). That NPRM
proposed to require replacement of the main landing gear (MLG) main
fittings with new improved MLG main fittings, which would terminate the
existing repetitive inspections of the MLG main fittings and inspection
and servicing of the MLG shock struts.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request To Clarify Airplanes on Which the Replacement Is Required
Bombardier notes that the applicability in AD 2007-01-07 (specified
in the NPRM as ``Other Related Rulemaking'') covers the entire fleet of
Model CL-600-2B19 airplanes (serial number (S/N) 7003 through 7067 and
7069 through 8999 inclusive) since S/N 7068 is a hull loss and the
airplane series ends at S/N 8999. Bombardier states that the
applicability specified in the NPRM will not cover additional Model CL-
600-2B19 airplanes. Bombardier adds that every Model CL-600-2B19
airplane equipped with a MLG main fitting having part number (P/N)
601R85001-3/4 (Messier-Dowty P/N 17064-101 through 104) will need to be
in compliance with the replacement required by AD 2007-01-07 by May 16,
2008.
We infer that Bombardier requests that we clarify which airplanes
are required to do the replacement specified in paragraph (r) of this
AD. We agree that the airplanes affected by paragraph (r) of this AD
should be further clarified. As stated by Bombardier, for Model CL-600-
2B19 airplanes having S/N 7003 through 7067 and 7069 through 8999
inclusive, the replacement is already required in accordance with
paragraph (l) of AD 2007-01-07. Therefore, we have changed paragraph
(r) of this AD to specify that the replacement be accomplished only on
airplanes having S/Ns 9000 and subsequent, which terminates the
requirements of paragraphs (h) through (q) of this AD. We have also
changed paragraph (t) of this AD to specify that, for the other
airplanes on which the replacement required by paragraph (l) of AD
2007-01-07 has been accomplished, it terminates the requirements of
paragraphs (h) through (q) of this AD.
We disagree with the commenter that the applicability in AD 2007-
01-07 covers the entire fleet. In order to ensure that any future
production airplanes, S/N 9000 and subsequent, meet the compliance
requirements of this AD, the replacement specified in paragraph (r) of
this AD is necessary to address the identified unsafe condition. We
have also revised the Estimated Costs table in the preamble of this AD
by changing the number of U.S.-registered airplanes required to do the
replacement from 618 to 0.
Request To Change Compliance Time
Bombardier Aerospace asks that we change the compliance time
specified in the NPRM. Bombardier states that AD 2007-01-07 (under
``Related Rulemaking'' in the NPRM) is effective for the same parts and
also mandates incorporation of Bombardier Service Bulletin 601R-32-093,
Revision B, dated July 14, 2005. Bombardier notes that AD 2007-01-07
was effective on February 16, 2007, and its compliance date is May 16,
2008. Bombardier adds that this compliance date is 9 months later than
the date agreed to by Messier-Dowty, Bombardier Aerospace, and
Transport Canada, based on careful consideration of fleet safety, MLG
capability/logistics, and operator overhaul facilities capacity.
Bombardier asks that the compliance time be the same as the time in AD
2007-01-07 (i.e., no later than May 16, 2008). Bombardier considers
that different compliance dates for the same service bulletin will
create confusion among U.S. operators and unnecessary burden for all
parties involved.
We do not agree with the commenter. As stated previously, the new
requirements in this AD apply only to airplanes having S/Ns 9000 and
subsequent. Therefore, we have made no change to the AD in this regard.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
The following table provides the estimated costs, at an average
labor rate of $80 per work hour, for U.S. operators to comply with this
AD. Due to other existing ADs, the actions have already been
accomplished on the majority of affected U.S.-registered airplanes;
therefore, the estimated costs will be significantly less than those
specified in the table.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work Parts Cost per registered Fleet cost
hours airplane airplanes
----------------------------------------------------------------------------------------------------------------
Detailed inspection (required 1 None................. $80, per 618 $49,440, per
by AD 2003-11-11). inspection inspection
cycle. cycle.
Eddy current inspection 1 None................. $80, per 618 $49,440, per
(required by AD 2003-11-11). inspection inspection
cycle. cycle.
Fluorescent penetrant 1 None................. $80, per 618 $49,440, per
inspection (required by AD inspection inspection
2003-11-11). cycle. cycle.
Inspection and servicing of 2 None................. $160, per 618 $98,880, per
shock struts (required by AD inspection inspection
2003-11-11). cycle. cycle.
Replacement (new action)..... 56 Up to $35,000........ Up to $39,480.. 0 $0.
----------------------------------------------------------------------------------------------------------------
[[Page 68315]]
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 Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-13170 (68 FR 31956, May 29, 2003) and by adding
the following new airworthiness directive (AD):
2008-23-11 Bombardier, Inc. (Formerly Canadair): Amendment 39-15732.
Docket No. FAA-2008-0265; Directorate Identifier 2007-NM-349-AD.
Effective Date
(a) This AD becomes effective December 23, 2008.
Affected ADs
(b) This AD supersedes AD 2003-11-11.
Applicability
(c) This AD applies to Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) airplanes, certificated in any category;
having serial numbers (S/Ns) 7003 and subsequent, equipped with main
landing gear (MLG) main fittings having part numbers (P/Ns)
601R85001-3 and -4 (Messier-Dowty P/Ns 17064-101, -102, -103, and -
104).
Unsafe Condition
(d) This AD results from premature failure of the MLG main
fittings. We are issuing this AD to prevent failure of the MLG main
fittings, which could result in collapse of the MLG upon landing.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Note 1: Where there are differences between the referenced
service bulletin and the AD, the AD prevails.
Restatement of Requirements of AD 2003-11-11
Service Bulletin References
(f) Accomplishment of the inspections and servicing, as
applicable, specified in paragraphs (h), (l), (m), and (n) of this
AD, per Bombardier Alert Service Bulletin A601R-32-079, dated
December 3, 1999; Revision `A,' dated January 7, 2000; Revision `B,'
dated June 1, 2000; Revision `C,' dated October 26, 2000; or
Revision `D,' dated December 1, 2000; prior to June 13, 2003 (the
effective date of AD 2003-11-11), is considered acceptable for
compliance with the requirements of paragraphs (h), (l), (m), and
(n) of this AD.
(g) The term ``service bulletin,'' as used in paragraphs (h)
through (q) of this AD, means the Accomplishment Instructions of
Bombardier Alert Service Bulletin A601R-32-079, Revision `E,' dated
September 12, 2002; including Appendix 1, Revision `D,' dated
September 12, 2002; including Appendices 2 and 3, dated September
12, 2002.
Initial Eddy Current Inspection
(h) Perform an eddy current inspection to detect cracking of the
MLG main fittings, per PART B of the service bulletin, at the
earlier of the times specified in paragraph (h)(1) or (h)(2) of this
AD.
(1) Prior to the accumulation of 1,500 total flight cycles on
the MLG, or within 150 flight cycles after December 4, 2001 (the
effective date of AD 2001-22-09, amendment 39-12488, which was
superseded by AD 2003-11-11), whichever occurs later.
(2) Prior to the accumulation of 1,000 total flight cycles on
the MLG, or within 150 flight cycles after June 13, 2003, whichever
occurs later.
Repetitive Eddy Current Inspections
(i) Repeat the eddy current inspection specified in paragraph
(h) of this AD at the time specified in paragraph (i)(1), (i)(2), or
(i)(3), as applicable, except as provided by paragraph (i)(4) of
this AD, per PART B of the service bulletin.
(1) For airplanes on which the eddy current inspection required
by paragraph (h) of this AD is accomplished after June 13, 2003:
Repeat the inspection at intervals not to exceed 500 flight cycles.
(2) For airplanes on which the repetitive eddy current
inspection required by AD 2001-22-09 has been accomplished, and on
which the repetitive intervals have been increased per paragraph (j)
of AD 2001-22-09 before June 13, 2003: Repeat the inspection within
500 flight cycles after June 13, 2003, or within 1,000 flight cycles
since the last eddy current inspection, whichever occurs first, and
thereafter at intervals not to exceed 500 flight cycles.
(3) For airplanes on which the repetitive eddy current
inspection required by AD 2001-22-09 has been accomplished, and on
which the repetitive intervals have not been increased per paragraph
(j) of AD 2001-22-09 before June 13, 2003: Repeat the eddy current
inspection at intervals not to exceed 500 flight cycles.
(4) For airplanes on which an eddy current inspection has been
accomplished to confirm the detailed inspection required by
paragraph (o) of this AD: The next eddy current inspection must be
done within 500 flight cycles following the last detailed inspection
required by paragraph (o) of this AD, and thereafter at intervals
not to exceed 500 flight cycles.
Corrective Actions
(j) If no cracking of the MLG main fittings is suspected during
the next eddy current inspection required by paragraph (h) or (i) of
this AD, but the paint has been removed: Prior to further flight,
apply a new finish and install the harness clamp on the brake line
with the bolt, washers, nut, and cotter pin; per PART B of the
service bulletin.
(k) If any cracking of the MLG main fittings is found during any
eddy current inspection required by paragraph (h) or (i) of this AD:
Prior to further flight, replace any cracked MLG main fitting with a
new or serviceable part per the service bulletin.
Servicing the Shock Struts
(l) Prior to the accumulation of 1,500 total flight cycles on
the MLG shock struts, or
[[Page 68316]]
within 500 flight cycles after December 4, 2001, whichever occurs
later: Service (Oil and Nitrogen) the left and right MLG shock
struts per PART C (for airplanes on the ground) or PART D (for
airplanes on jacks) of the service bulletin.
Other Inspections
(m) Within 500 flight cycles after completing the actions
required by paragraph (l) of this AD: Inspect the MLG left and right
shock struts for nitrogen pressure, visible chrome dimension, and
oil leakage, in accordance with PART E of the service bulletin.
Thereafter, repeat the inspection at intervals not to exceed 500
flight cycles.
Corrective Actions for Certain Inspections
(n) 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 during any inspection required by paragraph (m) of this AD:
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 service bulletin.
Detailed and Follow-On Inspections and Corrective Action
(o) Prior to the accumulation of 1,000 total flight cycles on
the MLG, or within 250 flight cycles after June 13, 2003, whichever
occurs later: Accomplish a detailed inspection of the MLG main
fittings to detect signs of cracking (including linear paint cracks
along the circumference of the main fitting tube, lack of paint
(paint peeling) or other paint damage, lack of adhesion or paint
bulging, and signs of corrosion), per PART A of the service
bulletin. Repeat the inspection thereafter at intervals not to
exceed 100 flight cycles.
Note 2: For the purposes of this AD, a detailed 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.''
(p) If any linear paint crack along the circumference of the
main fitting tube, lack of paint (paint peeling) or other paint
damage, evidence of paint bulging due to lack of adhesion, or
evidence of corrosion is found during any inspection required by
paragraph (o) of this AD: Prior to further flight, accomplish either
an eddy current inspection to detect cracking, per PART B of the
service bulletin; or a fluorescent penetrant inspection to detect
cracking, per PART F of the service bulletin.
(1) If no cracking of the MLG main fittings is found during any
inspection required by paragraph (p) of this AD: Prior to further
flight, repaint and/or repair/rework any paint damage per PART B of
the service bulletin.
(2) If any cracking of the MLG main fittings is found during any
inspection required by paragraph (p) of this AD: Prior to further
flight, replace any cracked MLG main fitting with a new or
serviceable part per the service bulletin.
Reporting Requirement
(q) Within 30 days after each inspection and servicing required
by paragraphs (h), (i), (l), (m), (o), and (p) of this AD, report
all findings, positive or negative, to: Bombardier Aerospace, In-
Service Engineering, fax number 514-855-8501. Although the service
bulletin references completion of a ``Service Bulletin Comment
Sheet-Facsimile Reply Sheet,'' this AD does not require that action.
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.
New Requirements of This AD
Replacement
(r) For airplanes having serial numbers 9000 and subsequent:
Within 6 months after the effective date of this AD, replace the MLG
main fittings with new improved MLG main fittings, in accordance
with Bombardier Service Bulletin 601R-32-093, Revision `B,' dated
July 14, 2005. Replacing the MLG main fittings terminates the
requirements of paragraphs (h) through (q) of this AD.
Credit for Actions Done According to Previous Issues of the Service
Bulletin
(s) Replacements done before the effective date of this AD in
accordance with Bombardier Service Bulletin 601R-32-093, dated
October 17, 2003; or Revision `A,' dated September 21, 2004; are
acceptable for compliance with the requirements of paragraph (r) of
this AD.
Credit for AD 2007-01-07
(t) For airplanes having S/Ns 7003 through 7067 inclusive and S/
Ns 7069 through 8999 inclusive, equipped with MLG main fittings
having P/N 601R85001-3 or -4 (Messier-Dowty P/N 17064-101, -102, -
103, or -104): Accomplishing the replacement required by paragraph
(l) of AD 2007-01-07, amendment 39-14879, terminates the
requirements of paragraphs (h) through (q) of this AD.
Alternative Methods of Compliance (AMOCs)
(u)(1) The Manager, New York Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Pong K. Lee, Aerospace Engineer, Airframe and
Propulsion Branch, ANE-171, FAA, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, New York 11590; telephone (516) 228-7324; fax
(516) 794-5531. Before using any approved AMOC on any airplane to
which the AMOC applies, notify your appropriate principal inspector
(PI) in the FAA Flight Standards District Office (FSDO), or lacking
a PI, your local FSDO.
(2) AMOCs issued to allow escalation of the repetitive intervals
for the eddy current inspections from 500 to 1,000 flight cycles in
accordance with paragraph (e) of AD 2001-22-09 are not approved as
AMOCs with this AD.
Note 3: Information concerning the existence of AMOCs with this
AD, if any, may be obtained from the New York ACO.
Related Information
(v) Canadian airworthiness directive CF-1999-32R3, dated
September 21, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(w) You must use Bombardier Service Bulletin 601R-32-093,
Revision `B,' dated July 14, 2005; and Bombardier Alert Service
Bulletin A601R-32-079, Revision `E,' dated September 12, 2002;
including Appendix 1, Revision `D,' dated September 12, 2002;
including Appendices 2 and 3, dated September 12, 2002; as
applicable; to perform the actions that are required by this AD,
unless the AD specifies otherwise.
(1) On February 16, 2007 (72 FR 1430, January 12, 2007), the
Director of the Federal Register approved the incorporation by
reference of Bombardier Service Bulletin 601R-32-093, Revision `B,'
dated July 14, 2005.
(2) On June 13, 2003 (68 FR 31956, May 29, 2003), the Director
of the Federal Register approved the incorporation by reference of
Bombardier Alert Service Bulletin A601R-32-079, Revision `E,' dated
September 12, 2002; including Appendix 1, Revision `D,' dated
September 12, 2002; including Appendices 2 and 3, dated September
12, 2002.
(3) Contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West,
Dorval, Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax
514-855-7401; e-mail thd.crj@aero.bombardier.com; Internet https://www.bombardier.com for a copy of this service information. You may
review copies at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on November 4, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8-26915 Filed 11-17-08; 8:45 am]
BILLING CODE 4910-13-P
