Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 12277-12280 [06-2236]
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12277
Rules and Regulations
Federal Register
Vol. 71, No. 47
Friday, March 10, 2006
This section of the FEDERAL REGISTER
contains regulatory documents having general
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are keyed to and codified in the Code of
Federal Regulations, which is published under
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DEPARTMENT OF AGRICULTURE
Food Safety and Inspection Service
9 CFR Part 312
Official Marks, Devices and Certificates
CFR Correction
In Title 9 of the Code of Federal
Regulations, part 200 to end, revised as
of January 1, 2006, the illustration on
page 144 contained in § 312.8(a), should
be interchanged with the illustration on
page 145 contained in § 312.10.
[FR Doc. 06–55508 Filed 3–9–06; 8:45 am]
BILLING CODE 1505–01–D
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24110; Directorate
Identifier 2006–NM–020–AD; Amendment
39–14508; AD 2006–05–11]
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; request for
comments.
rwilkins on PROD1PC63 with RULES
AGENCY:
SUMMARY: The FAA is superseding 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 revising the
airworthiness limitations section of the
Instructions for Continued
Airworthiness of the aircraft
maintenance manual (AMM) by
incorporating procedures for repetitive
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functional tests of the pilot input lever
of the pitch feel simulator (PFS) units.
This AD requires new repetitive
functional tests of the pilot input lever
of the PFS unit, and corrective actions
if necessary. After initiating the new
tests, this AD also requires removal of
the existing procedures for the repetitive
functional tests from the AMM. This AD
results from a report that the shear pin
located in the input lever of two PFS
units failed due to fatigue. We are
issuing this AD to prevent undetected
failure of the shear pin of both PFS units
simultaneously, which could result in
loss of pitch feel forces and consequent
reduced control of the airplane.
DATES: This AD becomes effective
March 27, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of March 27, 2006.
On February 13, 2004 (69 FR 4234,
January 29, 2004), the Director of the
Federal Register approved the
incorporation by reference of
Bombardier Temporary Revision 2B–
1784, dated October 24, 2003, to the CL–
600–2B19 Canadair Regional Jet
Maintenance Requirements Manual,
Part 2, Appendix B, ‘‘Airworthiness
Limitations.’’
We must receive any comments on
this AD by May 9, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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 AD.
You may examine the contents of the
AD docket on the Internet at https://
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dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Room PL–401, on the plaza level
of the Nassif Building, Washington, DC.
This docket number is FAA–2006–
24110; the directorate identifier for this
docket is 2006–NM–020–AD.
FOR FURTHER INFORMATION CONTACT: Dan
Parrillo, Aerospace Engineer, Systems
and Flight Test Branch, ANE–172, New
York Aircraft Certification Office, FAA,
1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone
(516) 228–7305; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
On January 20, 2004, the FAA issued
AD 2004–02–07, amendment 39–13442
(69 FR 4234, January 29, 2004). That AD
applies to certain Bombardier Model
CL–600–2B19 (Regional Jet Series 100 &
440) airplanes. That AD requires
revising the airworthiness limitations
section of the Instructions for Continued
Airworthiness of the aircraft
maintenance manual (AMM) by
incorporating procedures for repetitive
functional tests of the pilot input lever
of the pitch feel simulator (PFS) units.
That AD also requires an initial
functional test of the pilot input lever of
the PFS units, and corrective action if
necessary. That AD resulted from a
report that the shear pin located in the
input lever of two PFS units failed due
to fatigue. The actions specified in that
AD are intended to prevent undetected
failure of the shear pin of both PFS units
simultaneously, which could result in
loss of pitch feel forces and consequent
reduced control of the airplane.
Actions Since AD Was Issued
Since we issued that AD, Transport
Canada Civil Aviation (TCCA), which is
the airworthiness authority for Canada,
has informed us of a delay in
developing a terminating modification.
TCCA advises that Bombardier is
encountering difficulties in developing
a new, improved replacement input
lever for the PFS units. The resulting
delay is increasing the service time on
the existing levers (and resulting risk
exposure) to a level that is higher than
TCCA anticipated when they issued
Canadian Airworthiness Directive CF–
2003–26, dated November 14, 2003. The
delay also results in more airplanes
being delivered with the existing lever
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design. As a consequence, the repetitive
interval of the functional test is being
reduced to help reduce the risk
exposure to a failed input lever and
shear pin. Therefore, TCCA superseded
and cancelled Canadian Airworthiness
Directive CF–2003–26 (which we
referenced in AD 2004–02–07 as the
parallel Canadian Airworthiness
Directive) with Canadian Airworthiness
Directive CF–2005–41, dated December
22, 2005. Canadian Airworthiness
Directive CF–2005–41 expands the
applicability, reduces the repetitive
interval of the functional tests, and adds
repetitive functional tests of the pilot
input lever to determine if the lever is
disconnected, in accordance with new
service information.
Relevant Service Information
Bombardier has issued Alert Service
Bulletin A601R–27–144, Revision A,
dated February 14, 2006, including
Appendix A, dated September 15, 2005.
The alert service bulletin describes
procedures for performing repetitive
functional tests of the pilot input lever
of the PFS units to determine if the lever
is disconnected, and corrective actions
if necessary. The corrective actions
include replacing any defective PFS
unit with a serviceable PFS unit, and
using the data sheet of Appendix A to
submit a test report to Bombardier.
TCCA mandated the service information
to ensure the continued airworthiness of
these airplanes in Canada.
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FAA’s Determination and Requirements
of This 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
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 we need to issue an AD
for products of this type design that are
certificated for operation in the United
States.
Therefore, we are issuing this AD to
supersede AD 2004–02–07. This new
AD retains the repetitive functional tests
of the existing AD. This AD also
requires accomplishing the actions
specified in the alert service bulletin
described previously. Once the new
functional tests are initiated, this AD
also requires removal of the existing
procedures for the repetitive functional
tests from the AMM.
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Clarification Between This AD and the
Canadian Airworthiness Directive
Canadian airworthiness directive CF–
2005–41 references Bombardier Alert
Service Bulletin A601R–27–144,
including Appendix A, dated September
15, 2005, or later revision approved by
TCCA, as the appropriate source of
service information for doing the
required actions. After TCCA issued that
airworthiness directive, Bombardier
issued Revision A of the alert service
bulletin described previously. Revision
A adds an illustration of a cotter pin for
the bolt to Figure 1 of the
Accomplishment Instructions, and
revises two of the steps to include the
cotter pin. TCCA subsequently
approved Revision A of the alert service
bulletin. Therefore, this AD requires
actions in accordance with Revision A
of the alert service bulletin.
Change to Existing AD
This AD would retain the repetitive
functional test requirement of AD 2004–
02–07. Since AD 2004–02–07 was
issued, the AD format has been revised,
and certain paragraphs have been
rearranged. As a result, the
corresponding paragraph identifier has
changed in this AD, as listed in the
following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD 2004–
02–07
paragraph (a) ....................
Corresponding
requirement in
this AD
paragraph (f)
Interim Action
This AD is considered to be interim
action. The reports that are required by
this AD will enable the manufacturer to
obtain better insight into the nature,
cause, and extent of failures of the shear
pins of the PFS units, and eventually to
develop final action to address the
unsafe condition. Once final action has
been identified, we may consider
further rulemaking.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD; therefore, providing notice and
opportunity for public comment before
the AD is issued is impracticable, and
good cause exists to make this AD
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
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however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2006–24110; Directorate Identifier
2006–NM–020–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
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 AD. Using the
search function of that 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
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://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 receives them.
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
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Federal Register / Vol. 71, No. 47 / Friday, March 10, 2006 / Rules and Regulations
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 the 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 AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
airplanes, serial numbers 7003 through 7999
inclusive, and 8000 and subsequent,
certificated in any category.
Unsafe Condition
(d) This AD results from a report that the
shear pin located in the input lever of two
pitch feel stimulator (PFS) units failed due to
fatigue. We are issuing this AD to prevent
undetected failure of the shear pin of both
PFS units simultaneously, which could result
in loss of pitch feel forces and consequent
reduced control of the airplane.
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.
Restatement of Certain Requirements of AD
2004–02–07
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Revise Airworthiness Limitations (AWL)
Section of Aircraft Maintenance Manual
(f) For airplanes having serial numbers
7003 through 7999 inclusive: Within 14 days
after February 13, 2004 (the effective date of
AD 2004–02–07), revise the AWL section of
the Instructions for Continued Airworthiness
of the aircraft maintenance manual by
incorporating the functional check of the PFS
pilot input lever, Task R27–31–A024–01, as
specified in Bombardier Temporary Revision
(TR) 2B–1784, dated October 24, 2003, to the
CL–600–2B19 Canadair Regional Jet
Maintenance Requirements Manual, Part 2,
Appendix B, ‘‘Airworthiness Limitations,’’
into the AWL section.
Adoption of the Amendment
New Requirements
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as
follows:
New Repetitive Functional Tests and
Corrective Actions
(g) Before the accumulation of 4,000 total
flight hours, or within 100 flight hours after
the effective date of this AD, whichever
occurs later: Do a functional test of the pilot
input lever of the PFS units to determine if
the lever is disconnected, in accordance with
the Accomplishment Instructions of
Bombardier Alert Service Bulletin A601R–
27–144, Revision A, dated February 14, 2006,
including Appendix A, dated September 15,
2005. Repeat the test at intervals not to
exceed 100 flight hours. Before further flight,
after performing the initial functional test,
remove the procedures for the functional
tests specified in paragraph (f) of this AD
from the CL–600–2B19 Canadair Regional Jet
Maintenance Requirements Manual.
(h) If any lever is found to be disconnected
during any functional test required by
paragraph (g) of this AD, do the actions
specified in paragraphs (h)(1) and (h)(2) of
this AD in accordance with the
Accomplishment Instructions of Bombardier
Alert Service Bulletin A601R–27–144,
Revision A, dated February 14, 2006,
including Appendix A, dated September 15,
2005.
(1) Before further flight, replace the
defective PFS with a serviceable PFS in
accordance with the Accomplishment
Instructions of the alert service bulletin; and
(2) Within 30 days after removing the
defective PFS, submit a test report to the
manufacturer in accordance with the
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13442 (69
FR 4234, January 29, 2004) and adding
the following new AD:
I
2006–05–11 Bombardier, Inc. (Formerly
Canadair): Docket No. FAA–2006–
24110; Directorate Identifier 2006–NM–
020–AD; Amendment 39–14508.
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Effective Date
(a) This AD becomes effective March 27,
2006.
Affected ADs
(b) This AD supersedes AD 2004–02–07.
Applicability
(c) This AD applies to Bombardier Model
CL–600–2B19 (Regional Jet Series 100 & 440)
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12279
Accomplishment Instructions of the alert
service bulletin. Under the provisions of the
Paperwork Reduction Act (44 U.S.C. 3501 et
seq.), the Office of Management and Budget
(OMB) has approved the information
collection requirements contained in this AD
and has assigned OMB Control Number
2120–0056.
Previously Accomplished Actions
(i) Actions done before the effective date of
this AD in accordance with Bombardier Alert
Service Bulletin A601R–27–144, including
Appendix A, dated September 15, 2005, are
acceptable for compliance with the
requirements of paragraph (g) of this AD.
Alternative Methods of Compliance
(AMOCs)
(j)(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 § 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
(k) Canadian airworthiness directive CF–
2005–41, dated December 22, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Bombardier Alert Service
Bulletin A601R–27–144, Revision A, dated
February 14, 2006, including Appendix A,
dated September 15, 2005; and Bombardier
Temporary Revision 2B–1784, dated October
24, 2003, to the CL–600–2B19 Canadair
Regional Jet Maintenance Requirements
Manual, Part 2, Appendix B, ‘‘Airworthiness
Limitations;’’ as applicable, to perform the
actions that are required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference
Bombardier Alert Service Bulletin A601R–
27–144, Revision A, dated February 14, 2006,
including Appendix A, dated September 15,
2005, in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
(2) On February 13, 2004 (69 FR 4234,
January 29, 2004), the Director of the Federal
Register approved the incorporation by
reference of Bombardier Temporary Revision
2B–1784, dated October 24, 2003, to the CL–
600–2B19 Canadair Regional Jet Maintenance
Requirements Manual, Part 2, Appendix B,
‘‘Airworthiness Limitations.’’
(3) Contact Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087, Station
Centre-ville, Montreal, Quebec H3C 3G9,
Canada, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at 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 https://www.archives.gov/
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Federal Register / Vol. 71, No. 47 / Friday, March 10, 2006 / Rules and Regulations
federal_register/code_of_
federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on February
28, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–2236 Filed 3–9–06; 8:45 am]
§ 162.623 What will BIA do if a tenant
holds over after the expiration or
cancellation of a lease?
DEPARTMENT OF THE INTERIOR
If a tenant remains in possession after
the expiration or cancellation of a lease,
we will treat the unauthorized use as a
trespass. Unless we have reason to
believe that the tenant is engaged in
negotiations with the Indian landowners
to obtain a new lease, we will take
action to recover possession on behalf of
the Indian landowners, and pursue any
additional remedies available under
applicable law.
Bureau of Indian Affairs
[FR Doc. 06–55509 Filed 3–9–06; 8:45 am]
BILLING CODE 4910–13–P
BILLING CODE 1505–01–D
25 CFR Part 162
Leases and Permits
DEPARTMENT OF THE TREASURY
CFR Correction
Internal Revenue Service
In Title 25 of the Code of Federal
Regulations, revised as of April 1, 2005,
on page 435, part 162 is corrected by
reinstating §§ 162.622 and 162.623 to
read as follows:
§ 162.622 Can BIA take emergency action
if the leased premises are threatened with
immediate and significant harm?
If a tenant or any other party causes
or threatens to cause immediate and
significant harm to the leased premises
during the term of a lease, we will take
appropriate emergency action.
Emergency action may include judicial
action seeking immediate cessation of
the activity resulting in or threatening
the harm. Reasonable efforts will be
made to notify the Indian landowners,
either before or after the emergency
action is taken.
26 CFR Part 1
Income Taxes
CFR Correction
In Title 26 of the Code of Federal
Regulations, part 1 (§ 1.1551 to end),
revised as of April 1, 2005, on page 526,
in § 1.6696–1, paragraph (b), the third
sentence is corrected by removing
‘‘rified’’, and adding in its place, ‘‘Thus,
the claim may be prepared by the
preparer’s employer or by other persons.
In all cases, however, the claim for
credit or refund shall contain the
information specified in paragraph (d)
of this section and, as required in that
paragraph, shall be verified’’.
[FR Doc. 06–55511 Filed 3–9–06; 8:45 am]
BILLING CODE 1505–01–D
DEPARTMENT OF DEFENSE
Office of the Secretary
32 CFR Parts 59, 62b, 73, 158, 190, 216,
221, 224, 229, 238, 248, 252, 258, 261,
271, 336, 345, 347, 371, 378, and 388
[DOD–2006–OS–0042]
Removal of Parts
AGENCY:
ACTION:
Department of Defense.
Final rule.
SUMMARY: The Department of Defense is
removing several CFR parts from
Chapter I, Office of the Secretary of
Defense. This administrative action
removes obsolete information from the
Code of Federal Regulations and notifies
readers of the availability of the current
DoD documents that contain the
information being removed.
DATES:
This rule is effective March 10,
2006.
FOR FURTHER INFORMATION CONTACT:
The chart
below identifies the status of the parts
being removed. All documents with a
current date status may be found as a
DoD Directive (D), DoD Instruction (I),
or Administrative Instruction (AI) on
the Washington Headquarters Services
Web site at https://www.dtic.mil/whs/
directives/. Where ‘‘removed’’ is
indicated, the applicable DoD document
has been removed from the DoD
Directives System.
SUPPLEMENTARY INFORMATION:
Part No.
Document No.
59 ...............................
62b .............................
Voluntary Military Pay Allotments ...................................................................................................
Drunk and Drugged Driving by DoD ...............................................................................................
DoD Personnel ................................................................................................................................
Training Simulators and Devices ....................................................................................................
Guidelines for Systematic Declassification Review of Classified Information in Permanently Valuable DoD Records.
Natural Resources Management Program .....................................................................................
Military Recruiting and Reserve Officer Training Corps Program Access to Institutions of Higher
Education.
Participation in the National Practitioner Data Bank (NPDB) .........................................................
DoD Committee Management Program .........................................................................................
Protection of Archaeological Resources: Uniform Regulations ......................................................
Armed Forces Community Relations ..............................................................................................
Department of Defense Periodicals ................................................................................................
Department of Defense Offshore Military Activities Program .........................................................
Cooperation with Allies in Research and Development of Defense Equipment ............................
Armed Services Military Club and Package Stores ........................................................................
Obtaining Information from Financial Institutions ...........................................................................
Publications of Proposed and Adopted Regulations Affecting the Public ......................................
Department of Defense Section 6 Schools ....................................................................................
Department of Defense Dependents Schools ................................................................................
Defense Prisoner of War/Missing in Action Office (DPMO) ...........................................................
Assistant to the Secretary of Defense for Intelligence Oversight ...................................................
Ballistic Missile Defense Organization ............................................................................................
73 ...............................
158 .............................
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190 .............................
216 .............................
221
224
229
238
248
252
258
261
271
336
345
347
371
378
388
.............................
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L.
Bynum 703–696–6970.
Canceled by
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DoDD 7330.1.
DoDD 1010.7.
DoDD 1430.13.
Removed 1/14/04.
Removed 7/20/04.
DoDD 1322.13.
DoDD 6025.13.
DoDD 5105.18.
Removed 6/21/04.
DoDI 5410.19.
Removed 12/15/95.
Removed 1/13/05.
DoDD 2010.6.
DoDD 1015.2.
Duplicate of Part 275.
AI 102.
DoDD 1342.20.
DoDD 1342.20.
DoDD 5110.10.
DoDD 5148.11.
DoDD 5134.09.
Agencies
[Federal Register Volume 71, Number 47 (Friday, March 10, 2006)]
[Rules and Regulations]
[Pages 12277-12280]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-2236]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24110; Directorate Identifier 2006-NM-020-AD;
Amendment 39-14508; AD 2006-05-11]
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; request for comments.
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SUMMARY: The FAA is superseding 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
revising the airworthiness limitations section of the Instructions for
Continued Airworthiness of the aircraft maintenance manual (AMM) by
incorporating procedures for repetitive functional tests of the pilot
input lever of the pitch feel simulator (PFS) units. This AD requires
new repetitive functional tests of the pilot input lever of the PFS
unit, and corrective actions if necessary. After initiating the new
tests, this AD also requires removal of the existing procedures for the
repetitive functional tests from the AMM. This AD results from a report
that the shear pin located in the input lever of two PFS units failed
due to fatigue. We are issuing this AD to prevent undetected failure of
the shear pin of both PFS units simultaneously, which could result in
loss of pitch feel forces and consequent reduced control of the
airplane.
DATES: This AD becomes effective March 27, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of March 27,
2006.
On February 13, 2004 (69 FR 4234, January 29, 2004), the Director
of the Federal Register approved the incorporation by reference of
Bombardier Temporary Revision 2B-1784, dated October 24, 2003, to the
CL-600-2B19 Canadair Regional Jet Maintenance Requirements Manual, Part
2, Appendix B, ``Airworthiness Limitations.''
We must receive any comments on this AD by May 9, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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 AD.
You may examine the contents of the AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2006-24110; the directorate identifier for this docket is
2006-NM-020-AD.
FOR FURTHER INFORMATION CONTACT: Dan Parrillo, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, New York Aircraft
Certification Office, FAA, 1600 Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228-7305; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
On January 20, 2004, the FAA issued AD 2004-02-07, amendment 39-
13442 (69 FR 4234, January 29, 2004). That AD applies to certain
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes.
That AD requires revising the airworthiness limitations section of the
Instructions for Continued Airworthiness of the aircraft maintenance
manual (AMM) by incorporating procedures for repetitive functional
tests of the pilot input lever of the pitch feel simulator (PFS) units.
That AD also requires an initial functional test of the pilot input
lever of the PFS units, and corrective action if necessary. That AD
resulted from a report that the shear pin located in the input lever of
two PFS units failed due to fatigue. The actions specified in that AD
are intended to prevent undetected failure of the shear pin of both PFS
units simultaneously, which could result in loss of pitch feel forces
and consequent reduced control of the airplane.
Actions Since AD Was Issued
Since we issued that AD, Transport Canada Civil Aviation (TCCA),
which is the airworthiness authority for Canada, has informed us of a
delay in developing a terminating modification. TCCA advises that
Bombardier is encountering difficulties in developing a new, improved
replacement input lever for the PFS units. The resulting delay is
increasing the service time on the existing levers (and resulting risk
exposure) to a level that is higher than TCCA anticipated when they
issued Canadian Airworthiness Directive CF-2003-26, dated November 14,
2003. The delay also results in more airplanes being delivered with the
existing lever
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design. As a consequence, the repetitive interval of the functional
test is being reduced to help reduce the risk exposure to a failed
input lever and shear pin. Therefore, TCCA superseded and cancelled
Canadian Airworthiness Directive CF-2003-26 (which we referenced in AD
2004-02-07 as the parallel Canadian Airworthiness Directive) with
Canadian Airworthiness Directive CF-2005-41, dated December 22, 2005.
Canadian Airworthiness Directive CF-2005-41 expands the applicability,
reduces the repetitive interval of the functional tests, and adds
repetitive functional tests of the pilot input lever to determine if
the lever is disconnected, in accordance with new service information.
Relevant Service Information
Bombardier has issued Alert Service Bulletin A601R-27-144, Revision
A, dated February 14, 2006, including Appendix A, dated September 15,
2005. The alert service bulletin describes procedures for performing
repetitive functional tests of the pilot input lever of the PFS units
to determine if the lever is disconnected, and corrective actions if
necessary. The corrective actions include replacing any defective PFS
unit with a serviceable PFS unit, and using the data sheet of Appendix
A to submit a test report to Bombardier. TCCA mandated the service
information to ensure the continued airworthiness of these airplanes in
Canada.
FAA's Determination and Requirements of This 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 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 we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to supersede AD 2004-02-07. This
new AD retains the repetitive functional tests of the existing AD. This
AD also requires accomplishing the actions specified in the alert
service bulletin described previously. Once the new functional tests
are initiated, this AD also requires removal of the existing procedures
for the repetitive functional tests from the AMM.
Clarification Between This AD and the Canadian Airworthiness Directive
Canadian airworthiness directive CF-2005-41 references Bombardier
Alert Service Bulletin A601R-27-144, including Appendix A, dated
September 15, 2005, or later revision approved by TCCA, as the
appropriate source of service information for doing the required
actions. After TCCA issued that airworthiness directive, Bombardier
issued Revision A of the alert service bulletin described previously.
Revision A adds an illustration of a cotter pin for the bolt to Figure
1 of the Accomplishment Instructions, and revises two of the steps to
include the cotter pin. TCCA subsequently approved Revision A of the
alert service bulletin. Therefore, this AD requires actions in
accordance with Revision A of the alert service bulletin.
Change to Existing AD
This AD would retain the repetitive functional test requirement of
AD 2004-02-07. Since AD 2004-02-07 was issued, the AD format has been
revised, and certain paragraphs have been rearranged. As a result, the
corresponding paragraph identifier has changed in this AD, as listed in
the following table:
Revised Paragraph Identifiers
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Corresponding requirement in
Requirement in AD 2004-02-07 this AD
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paragraph (a).......................... paragraph (f)
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Interim Action
This AD is considered to be interim action. The reports that are
required by this AD will enable the manufacturer to obtain better
insight into the nature, cause, and extent of failures of the shear
pins of the PFS units, and eventually to develop final action to
address the unsafe condition. Once final action has been identified, we
may consider further rulemaking.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
24110; Directorate Identifier 2006-NM-020-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
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 AD. Using the search function of that 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
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
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
receives them.
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
[[Page 12279]]
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 the 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 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 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-13442 (69 FR 4234, January 29, 2004) and adding
the following new AD:
2006-05-11 Bombardier, Inc. (Formerly Canadair): Docket No. FAA-
2006-24110; Directorate Identifier 2006-NM-020-AD; Amendment 39-
14508.
Effective Date
(a) This AD becomes effective March 27, 2006.
Affected ADs
(b) This AD supersedes AD 2004-02-07.
Applicability
(c) This AD applies to Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) airplanes, serial numbers 7003 through 7999
inclusive, and 8000 and subsequent, certificated in any category.
Unsafe Condition
(d) This AD results from a report that the shear pin located in
the input lever of two pitch feel stimulator (PFS) units failed due
to fatigue. We are issuing this AD to prevent undetected failure of
the shear pin of both PFS units simultaneously, which could result
in loss of pitch feel forces and consequent reduced control of the
airplane.
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.
Restatement of Certain Requirements of AD 2004-02-07
Revise Airworthiness Limitations (AWL) Section of Aircraft
Maintenance Manual
(f) For airplanes having serial numbers 7003 through 7999
inclusive: Within 14 days after February 13, 2004 (the effective
date of AD 2004-02-07), revise the AWL section of the Instructions
for Continued Airworthiness of the aircraft maintenance manual by
incorporating the functional check of the PFS pilot input lever,
Task R27-31-A024-01, as specified in Bombardier Temporary Revision
(TR) 2B-1784, dated October 24, 2003, to the CL-600-2B19 Canadair
Regional Jet Maintenance Requirements Manual, Part 2, Appendix B,
``Airworthiness Limitations,'' into the AWL section.
New Requirements
New Repetitive Functional Tests and Corrective Actions
(g) Before the accumulation of 4,000 total flight hours, or
within 100 flight hours after the effective date of this AD,
whichever occurs later: Do a functional test of the pilot input
lever of the PFS units to determine if the lever is disconnected, in
accordance with the Accomplishment Instructions of Bombardier Alert
Service Bulletin A601R-27-144, Revision A, dated February 14, 2006,
including Appendix A, dated September 15, 2005. Repeat the test at
intervals not to exceed 100 flight hours. Before further flight,
after performing the initial functional test, remove the procedures
for the functional tests specified in paragraph (f) of this AD from
the CL-600-2B19 Canadair Regional Jet Maintenance Requirements
Manual.
(h) If any lever is found to be disconnected during any
functional test required by paragraph (g) of this AD, do the actions
specified in paragraphs (h)(1) and (h)(2) of this AD in accordance
with the Accomplishment Instructions of Bombardier Alert Service
Bulletin A601R-27-144, Revision A, dated February 14, 2006,
including Appendix A, dated September 15, 2005.
(1) Before further flight, replace the defective PFS with a
serviceable PFS in accordance with the Accomplishment Instructions
of the alert service bulletin; and
(2) Within 30 days after removing the defective PFS, submit a
test report to the manufacturer in accordance with the
Accomplishment Instructions of the alert service bulletin. Under the
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.),
the Office of Management and Budget (OMB) has approved the
information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
Previously Accomplished Actions
(i) Actions done before the effective date of this AD in
accordance with Bombardier Alert Service Bulletin A601R-27-144,
including Appendix A, dated September 15, 2005, are acceptable for
compliance with the requirements of paragraph (g) of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(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
(k) Canadian airworthiness directive CF-2005-41, dated December
22, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Bombardier Alert Service Bulletin A601R-27-144,
Revision A, dated February 14, 2006, including Appendix A, dated
September 15, 2005; and Bombardier Temporary Revision 2B-1784, dated
October 24, 2003, to the CL-600-2B19 Canadair Regional Jet
Maintenance Requirements Manual, Part 2, Appendix B, ``Airworthiness
Limitations;'' as applicable, to perform the actions that are
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference Bombardier Alert Service Bulletin A601R-
27-144, Revision A, dated February 14, 2006, including Appendix A,
dated September 15, 2005, in accordance with 5 U.S.C. 552(a) and 1
CFR part 51.
(2) On February 13, 2004 (69 FR 4234, January 29, 2004), the
Director of the Federal Register approved the incorporation by
reference of Bombardier Temporary Revision 2B-1784, dated October
24, 2003, to the CL-600-2B19 Canadair Regional Jet Maintenance
Requirements Manual, Part 2, Appendix B, ``Airworthiness
Limitations.''
(3) Contact Bombardier, Inc., Canadair, Aerospace Group, P.O.
Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada,
for a copy of this service information. You may review copies at the
Docket Management Facility, U.S. Department of Transportation, 400
Seventh Street SW., Room PL-401, Nassif Building, Washington, DC; on
the Internet at https://dms.dot.gov; or at 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 https://
www.archives.gov/
[[Page 12280]]
federal--register/code--of-- federal--regulations/ ibr--
locations.html.
Issued in Renton, Washington, on February 28, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-2236 Filed 3-9-06; 8:45 am]
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