[Federal Register: July 12, 2006 (Volume 71, Number 133)]
[Proposed Rules]
[Page 39237-39241]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12jy06-22]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22559; Directorate Identifier 2005-NM-076-AD]
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: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Bombardier Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes. The existing AD currently
requires repetitive inspections for cracks, sealant damage, and
corrosion of the main fittings of the main landing gear (MLG), and
corrective actions if necessary. This proposed AD would reduce the
compliance times for inspecting certain low-utilization airplanes, and
provide a terminating action for the repetitive inspections. This
proposed AD results from a report of a cracked main fitting of the MLG.
We are proposing this AD to detect and correct fatigue cracking of the
main fitting of the MLG and consequent failure of the main fitting,
which could result in the collapse of the MLG.
DATES: We must receive comments on this proposed AD by August 11, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Richard Beckwith, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7302; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-22559;
Directorate Identifier 2005-NM-076-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
[[Page 39238]]
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
(DMS) receives them.
Discussion
On September 27, 2004, we issued AD 2004-20-09, amendment 39-13814
(69 FR 59790, October 6, 2004), for certain Bombardier Model CL-600-
2B19 (Regional Jet Series 100 & 440) airplanes. That AD requires
repetitive inspections for cracks, sealant damage, and corrosion of the
main fittings of the main landing gear (MLG), and corrective actions if
necessary. That AD resulted from a report of a cracked main fitting of
the MLG. We issued that AD to detect and correct fatigue cracking of
the main fitting of the MLG and consequent failure of the main fitting,
which could result in the collapse of the MLG.
Actions Since Existing AD Was Issued
Since we issued AD 2004-20-09, Transport Canada Civil Aviation
(TCCA), which is the airworthiness authority for Canada, has revised
its parallel airworthiness directive, and issued Canadian airworthiness
directive CF-2004-18R1, dated September 21, 2005. (Canadian emergency
airworthiness directive CF-2004-18, dated September 16, 2004, was
referenced as the parallel airworthiness directive in AD 2004-20-09.)
This revision to the Canadian airworthiness directive specifies the
revised inspection intervals in Revision B of Bombardier Alert Service
Bulletin A601R-32-099, dated June 16, 2005. (Alert Service Bulletin
A601R-32-099, dated September 15, 2004, was referenced in AD 2004-20-09
as the appropriate source of service information for accomplishing the
required actions.) The revised inspection intervals apply only to
certain low-utilization airplanes, and specify that these airplanes
comply with the actions in AD 2004-20-09 sooner than currently required
by that AD. This revision to the Canadian airworthiness directive also
specifies replacement of the main fittings of the MLG with new
fittings, which terminates the repetitive inspections.
In addition, the preamble to AD 2004-20-09 explains that we
consider the requirements of AD 2004-20-09 to be ``interim action'' and
that we are considering further rulemaking. We now have determined that
further rulemaking is indeed necessary, and this proposed AD follows
from that determination.
Other Relevant Rulemaking
On November 16, 2001, we issued AD 2001-22-09 (amendment 39-12488,
66 FR 58931, November 26, 2001), for certain Bombardier Model CL-600-
2B19 series airplanes. That AD requires repetitive eddy current
inspections for cracking of the MLG main fittings, and replacement with
a new or serviceable MLG if necessary. That AD also requires servicing
the MLG shock struts; inspecting the MLG shock struts for nitrogen
pressure, visible chrome dimension, and oil leakage; and performing
corrective actions if necessary. That AD was prompted by reports of
premature failure of the MLG main fitting. We issued that AD to prevent
failure of the MLG main fitting, which could result in collapse of the
MLG upon landing.
On June 30, 2004, we issued AD 2004-14-16 (amendment 39-13725, 69
FR 41421, July 9, 2004), for certain Bombardier Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes. That AD requires repetitive
detailed and eddy current inspections on the main fittings of the MLGs
to detect discrepancies, and related investigative/corrective actions
if necessary. That AD also requires servicing the shock strut of the
MLGs; inspecting the shock strut of the MLGs for nitrogen pressure,
visible chrome dimension, and oil leakage; and servicing any discrepant
strut. That AD resulted from results of a stress analysis that revealed
that certain main fittings of the MLGs are susceptible to premature
cracking, starting in the radius of the upper lug. We issued that AD to
detect and correct premature cracking of the main fittings of the MLGs,
which could result in failure of the fittings and consequent collapse
of the MLGs during landing.
Relevant Service Information
Bombardier has issued Alert Service Bulletin A601R-32-099, Revision
B, dated June 16, 2005, including Appendices A through D, Revision A,
dated December 13, 2004. The procedures in this service bulletin are
essentially the same as the procedures in the original issue of
Bombardier Alert Service Bulletin A601R-32-099, including Appendices A
through D, dated September 15, 2004, which was cited as the appropriate
source of service information in AD 2004-20-09.
Bombardier has also issued Service Bulletin 601R-32-093, Revision
B, dated July 14, 2005. This service bulletin describes procedures for
replacing the main fitting of the MLG with a new main fitting having a
new part number.
TCCA mandated the service information and issued Canadian
airworthiness directive CF-2004-18R1, dated September 21, 2005, to
ensure the continued airworthiness of these airplanes in Canada. TCCA
considers Bombardier Service Bulletin 601R-32-093 to be terminating
action for the repetitive inspections in Bombardier Alert Service
Bulletin A601R-32-099.
Bombardier Service Bulletin 601R-32-093, Revision B, refers to
Messier-Dowty Service Bulletin M-DT SB17002-32-24, dated October 9,
2003; and Messier-Dowty Service Bulletin M-DT SB17002-32-25, Revision
1, dated October 17, 2003; as additional sources of service information
for replacing the MLG main fitting. Operators should note that P/Ns
601R85001-81/82 (Messier-Dowty P/Ns 17064-105/106), as specified in
Bombardier Service Bulletin 601R-32-093, Revision B, and Messier-Dowty
Service Bulletin M-DT SB17002-32-25, Revision 1, require different
inspections in accordance with AD 2004-14-16. We are considering
additional rulemaking to supersede that AD to require replacement of
the noted part numbers at a different compliance time.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
section 21.29 of the
[[Page 39239]]
Federal Aviation Regulations (14 CFR 21.29) and the applicable
bilateral airworthiness agreement. Pursuant to this bilateral
airworthiness agreement, TCCA has kept the FAA informed of the
situation described above. We have examined TCCA's findings, evaluated
all pertinent information, and determined that AD action is necessary
for airplanes of this type design that are certificated for operation
in the United States.
This proposed AD would supersede AD 2004-20-09. This proposed AD
would continue to require repetitive inspections for cracks, sealant
damage, and corrosion of the main fittings of the MLG, and corrective
actions if necessary. This proposed AD also would reduce the compliance
times for inspecting certain affected airplanes, and require that
operators do the actions in accordance with a new revision of the
service bulletin, described previously, except as discussed under
``Difference Between the Proposed AD and Bombardier Alert Service
Bulletin A601R-32-099.''
Difference Between the Proposed AD and Bombardier Alert Service
Bulletin A601R-32-099
Although the Accomplishment Instructions of the Bombardier Alert
Service Bulletin A601R-32-099, Revision B, describe procedures for
reporting crack indications, returning cracked parts to Messier-Dowty,
and submitting a comment sheet related to service bulletin quality and
a sheet recording compliance with the service bulletin, this AD, like
Canadian airworthiness directive CF-2004-18R1, would not require those
actions.
Difference Between the Proposed AD and the Canadian Airworthiness
Directive
Canadian airworthiness directive CF-2004-18R1, recommends replacing
the main fitting of the MLG with a new main fitting having a new part
number by June 2007, which is 27 months after the effective date of the
Canadian airworthiness directive. We find that a compliance time of
within 15 months after the effective date of this proposed AD would
allow us to come close to the compliance date of June 2007, and
represents an appropriate interval of time for affected airplanes to
continue to operate without compromising safety. This difference has
been coordinated with TCCA.
Clarification of Inspection Language
Bombardier Alert Service Bulletin A601R-32-099, Revision B,
specifies that operators should do a visual inspection for cracks of
the inboard and outboard sides of the main fitting of the MLG; and a
visual inspection for sealant damage or corrosion around the forward
bushing of the left and right main fittings of the MLG. The Canadian
airworthiness directive refers to this inspection as a ``detailed
visual inspection.'' In this proposed AD we refer to this inspection as
a ``detailed inspection.'' Note 1 of this proposed AD defines this
inspection.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD. There are approximately 201 U.S.-
registered airplanes. The average labor rate is $80 per hour.
Estimated Costs
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Work
Action hours Parts Cost per airplane Fleet cost
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Detailed inspection for cracks of 1 N/A $80, per inspection $16,080, per
the main fitting (required by AD cycle. inspection cycle.
2004-20-09).
Detailed inspection for sealant 1 N/A $80, per inspection $16,080, per
damage of the bushing (required by cycle. inspection cycle.
AD 2004-20-09).
Ultrasonic inspection for cracks of 1 N/A $80, per inspection $16,080, per
the main fittings (required by AD cycle. inspection cycle.
2004-20-09).
Replacement (new proposed action)... 56 $105,732 $110,212............... $22,152,612.
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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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed AD. 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 39240]]
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing amendment 39-13814 (69 FR
59790, October 6, 2004) and adding the following new airworthiness
directive (AD):
Bombardier, Inc. (Formerly Canadair): Docket No. FAA-2005-22559;
Directorate Identifier 2005-NM-076-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by August 11, 2006.
Affected ADs
(b) This AD supersedes AD 2004-20-09.
Applicability
(c) This AD applies to Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) airplanes, certificated in any category;
serial numbers 7003 through 7067 inclusive, and 7069 through 8999
inclusive; equipped with main landing gear (MLG) main fittings,
having part number (P/N) 601R85001-3 or -4 (Messier-Dowty P/N 17064-
101, -102, -103, or -104).
Unsafe Condition
(d) This AD results from a report of a cracked main fitting of
the MLG. We are issuing this AD to detect and correct fatigue
cracking of the main fitting of the MLG and consequent failure of
the main fitting, which could result in the collapse of the MLG.
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.
Service Bulletin
(f) Unless otherwise specified in this AD, the term ``service
bulletin,'' as used in this AD, means the Accomplishment
Instructions of Bombardier Alert Service Bulletin A601R-32-099,
including Appendices A, B, and D, and excluding Appendix C, dated
September 15, 2004; or Bombardier Alert Service Bulletin A601R-32-
099, Revision A, including Appendices A, B, and D, and excluding
Appendix C, dated December 13, 2004; or Bombardier Alert Service
Bulletin A601R-32-099, Revision B, dated June 16, 2005, including
Appendices A, B, and D, and excluding Appendix C, Revision A, dated
December 13, 2004.
(1) After the effective date of this AD, only Revision B of the
service bulletin may be used.
(2) Although the service bulletin specifies to submit certain
information to the airplane manufacturer and to return cracked main
fittings to the supplier, this AD does not include those
requirements.
Restatement of the Requirements of AD 2004-20-09
Initial Inspections at New Reduced Compliance Times
(g) Do the actions in Table 1 of this AD.
Table 1.--Initial Inspection Thresholds at New Reduced Compliance Times
------------------------------------------------------------------------
Do the following in Column At the earlier of the times specified in
1-- Column 2 or Column 3--
------------------------------------------------------------------------
Column 2--The latest Column 3--The latest
Column 1-- of-- of--
------------------------------------------------------------------------
(1) A detailed inspection (i)(A) Before the (ii)(A) Within 48
for cracks of the inboard accumulation of months since the
and outboard sides of the 8,000 total flight main fitting of the
main fitting of the MLG cycles since the MLG was new.
between the pintle pin main fitting of the (B) Within 48 months
trunnion and the radius of MLG was new. since the last
the shock strut lug, in (B) Within 8,000 overhaul of the MLG
accordance with Part A of flight cycles since done before the
the service bulletin. the last overhaul effective date of
of the MLG done this AD.
before the (C) Within 50 flight
effective date of cycles after the
this AD. effective date of
(C) Within 50 flight this AD.
cycles after
October 21, 2004
(the effective date
of AD 2004-20-09).
(2) A detailed inspection (i)(A) Before the (ii)(A) Within 48
for sealant damage or accumulation of months since the
corrosion around the 8,000 total flight main fitting of the
forward bushing of the left cycles since the MLG was new.
and right main fittings of main fitting of the (B) Within 48 months
the MLG, in accordance with MLG was new. since the last
Part B of the service (B) Within 8,000 overhaul of the MLG
bulletin. flight cycles since done before the
the last overhaul effective date of
of the MLG done this AD.
before the (C) Within 500
effective date of flight cycles or 6
this AD. months after the
(C) Within 500 effective date of
flight cycles after this AD, whichever
October 21, 2004. occurs first.
(3) An ultrasonic inspection (i)(A) Before the (ii)(A) Within 48
for cracks of the left and accumulation of months since the
right main fittings of the 8,000 total flight main fitting of the
MLG, in accordance with cycles since the MLG was new.
Part C of the service main fitting of the (B) Within 48 months
bulletin. MLG was new. since the last
(B) Within 8,000 overhaul of the MLG
flight cycles, done before the
since the last effective date of
overhaul of the MLG this AD.
done before the (C) Within 500
effective date of flight cycles or 6
this AD. months after the
(C) Within 500 effective date of
flight cycles after this AD, whichever
October 21, 2004. occurs first.
------------------------------------------------------------------------
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repetitive Inspections
(h) Repeat the inspections in paragraph (g) of this AD
thereafter at the applicable interval in paragraph (h)(1) or (h)(2)
of this AD, until the terminating action required by paragraph (l)
of this AD is accomplished.
(1) For airplanes on which the applicable initial inspection in
paragraph (g) of this AD has been done before the effective date of
this AD, do the next inspection at the applicable interval in Table
2 of this AD.
(2) For airplanes on which the applicable initial inspection in
paragraph (g) of this AD has not been done before the effective date
of this AD, repeat the inspection at the applicable interval in
Table 2 of this AD.
[[Page 39241]]
Table 2.--Repetitive Inspections at New Intervals
------------------------------------------------------------------------
For the inspection required Repeat at intervals Until the action
by-- not to exceed-- required by--
------------------------------------------------------------------------
(3) Paragraph (g)(1) of this 5 days.............. Paragraph (g)(3) of
AD. this AD is done,
unless required by
paragraph (j) of
this AD.
(4) Paragraph (g)(2) of this 500 flight cycles or Paragraph (j)(2) of
AD. 6 months, whichever this AD is done.
occurs first.
(5) Paragraph (g)(3) of this 5,000 flight cycles (None).
AD. or 30 months,
whichever occurs
first, except as
required by
paragraph (j)(2) of
this AD.
------------------------------------------------------------------------
Corrective Actions
(i) If there is an indication of a crack during any inspection
required by paragraph (g)(1), (h)(3), or (j)(1) of this AD, before
further flight, do the actions specified in paragraph (i)(1) or
(i)(2) of this AD in accordance with Part A of the service bulletin;
or do the terminating action required by paragraph (l) of this AD.
(1) Replace the cracked main fitting of the MLG with a new or
serviceable main fitting.
(2) Do an eddy current inspection to verify whether there is a
crack. If there is a crack, replace the cracked main fitting of the
MLG with a new or serviceable main fitting.
(j) If any sealant damage or corrosion is found during any
inspection required by either paragraph (g)(2) or (h)(4) of this AD,
do the actions specified in Table 3 of this AD in accordance with
Part B of the service bulletin, until the terminating action
required by paragraph (l) of this AD is accomplished.
Table 3.--Corrective Actions for Sealant Damage or Corrosion
----------------------------------------------------------------------------------------------------------------
Repeat at intervals not Until the action
Do the inspection specified in-- Within-- to exceed-- specified in--
----------------------------------------------------------------------------------------------------------------
(1) Paragraph (g)(1) of this AD.. 5 days after doing the 5 days.................. Paragraph (j)(2) or (l)
inspection required by of this AD is done.
(g)(2) or (h)(4) of this
AD, as applicable.
(2) Paragraph (g)(3) of this AD.. 500 flight cycles after 500 flight cycles....... Paragraph (l) of this AD
doing the inspection is done.
required by paragraph
(g)(2) or (h)(4) of this
AD, as applicable.
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(k) If there is an indication of a crack during any inspection
required by paragraph (g)(3) or (h)(5) of this AD, before further
flight, replace the cracked main fitting of the MLG with a new or
serviceable main fitting in accordance with Part C of the service
bulletin; or do the terminating action required by paragraph (l) of
this AD.
New Requirement of This AD
Terminating Action--Replacement
(l) Within 15 months after the effective date of this AD,
replace both main fittings of the MLG with new main fittings having
new part numbers, in accordance with the Accomplishment Instructions
of Bombardier Service Bulletin 601R-32-093, Revision B, dated July
14, 2005. Doing this replacement terminates all requirements of
paragraphs (g), (h), (i), (j), and (k) of this AD.
Note 2: Bombardier Service Bulletin 601R-32-093, Revision B,
refers to Messier-Dowty Service Bulletin M-DT SB17002-32-24, dated
October 9, 2003; and Messier-Dowty Service Bulletin M-DT SB17002-32-
25, Revision 1, dated October 17, 2003; as additional sources of
service information for replacing the MLG main fitting.
Actions Accomplished in Accordance With Earlier Issues of Service
Bulletin
(m) Actions done before the effective date of this AD in
accordance with the service bulletins listed in Table 4 of this AD
are acceptable for compliance with the corresponding action
specified in this AD.
Table 4.--Earlier Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Bombardier Service Bulletin 601R-32-093 Original................... October 17, 2003.
Bombardier Service Bulletin 601R-32-093 A.......................... September 21, 2004.
----------------------------------------------------------------------------------------------------------------
Parts Installation
(n) As of the effective date of this AD, no person may install a
main fitting of the MLG, Bombardier P/N 601R85001-3 or 601R85001-4;
also referred to as Messier-Dowty P/N 17064-101, 17064-102, 17064-
103, or 17064-104; on any airplane.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, New York Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested in accordance with the procedures found in 14 CFR 39.19.
(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.
Related Information
(p) Canadian airworthiness directive CF-2004-18R1, dated
September 21, 2005, also addresses the subject of this AD.
Issued in Renton, Washington, on July 6, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-10913 Filed 7-11-06; 8:45 am]
BILLING CODE 4910-13-P