Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 75727-75729 [05-24245]
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Federal Register / Vol. 70, No. 244 / Wednesday, December 21, 2005 / Rules and Regulations
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.’’
Reporting
(h) If any gimbal pin is found migrated:
Submit a report of the findings (migrated
pins only) of the measurement and
inspections required by paragraph (g) of this
AD to Bombardier, Attention: Dept. Customer
Support Program Office (CSPO), fax (514)
855–8798. Submit the report at the applicable
time specified in paragraph (h)(1) or (h)(2) of
this AD. The report must include the airplane
serial number, the HSTA part number and
serial number, the results of the inspection,
and the action taken. Submitting the Service
Bulletin Feedback Form of the service
bulletin is an acceptable means of complying
with this requirement. Under the provisions
of the Paperwork Reduction Act of 1980 (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.
(1) If the measurement was done after the
effective date of this AD: Submit the report
within 30 days after the inspection.
(2) If the measurement was done prior to
the effective date of this AD: Submit the
report within 30 days after the effective date
of this AD.
Parts Installation
(i) As of the effective date of this AD, no
person may install an HSTA on any airplane
unless the actions required by paragraph (g)
of this AD are accomplished on it.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, New York Aircraft
Certification Office, 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 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
rmajette on PROD1PC67 with RULES
Related Information
(k) Canadian airworthiness directive CF–
2005–20, dated June 23, 2005, also addresses
the subject of this AD.
Material Incorporated by Reference
(l) You must use Bombardier Service
Bulletin 600–0720, dated January 31, 2005; or
Bombardier Service Bulletin 601–0555, dated
January 31, 2005; as applicable, to perform
the actions that are required by this AD,
unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. 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
VerDate Aug<31>2005
14:47 Dec 20, 2005
Jkt 208001
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/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
December 13, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–24244 Filed 12–20–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22403; Directorate
Identifier 2005–NM–144–AD; Amendment
39–14426; AD 2005–26–05]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier Model DHC–8–400 series
airplanes. This AD requires an
inspection of the laminated shims for
cracks, damage, or extrusion between
the forward attachment fittings of the
horizontal stabilizer and the top rib of
the vertical stabilizer; a torque check of
the attachment bolts in the attachment
fittings of the front, middle, and rear
spars; and corrective actions if
necessary. This AD results from a report
indicating that delaminated shims
extruded from the interface between the
forward attaching fittings of the
horizontal stabilizer and the top rib of
the vertical stabilizer, and that
inadequate torque values of some bolts
were found. We are issuing this AD to
prevent reduced structural integrity of
the horizontal stabilizer, and
consequent loss of controllability of the
airplane.
DATES: This AD becomes effective
January 25, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of January 25, 2006.
PO 00000
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Fmt 4700
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75727
You may examine 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., Nassif Building, Room PL–401,
Washington, DC.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT:
George Duckett, 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) 228–7325; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
Examining the Docket
You may examine the airworthiness
directive (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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Bombardier Model
DHC–8–400 series airplanes. That
NPRM was published in the Federal
Register on September 14, 2005 (70 FR
54316). (An NPRM correction was
published in the Federal Register on
September 30, 2005 (70 FR 57221).)
That NPRM proposed to require an
inspection of the laminated shims for
cracks, damage, or extrusion between
the forward attachment fittings of the
horizontal stabilizer and the top rib of
the vertical stabilizer; a torque check of
the attachment bolts in the attachment
fittings of the front, middle, and rear
spars; and corrective actions if
necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received.
Request for Credit for Doing
Bombardier All Operator Message
(AOM)
One commenter requests that
operators be given credit for doing the
procedures in accordance with
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Federal Register / Vol. 70, No. 244 / Wednesday, December 21, 2005 / Rules and Regulations
Bombardier AOM 096B, dated June 12,
2003, before the effective date of the AD,
as an alternative method of compliance
(AMOC) with the requirements of
paragraphs (i)(1) and (i)(2) of the NPRM.
We agree with the commenter that
accomplishing the actions specified in
Bombardier AOM 096B before the
effective date of this AD is acceptable
for compliance with the detailed
inspection and torque check required by
paragraphs (i)(1) and (i)(2) of the AD.
We also have determined that those
actions are also acceptable for the
replacement requirements of the AD.
We have revised paragraph (g) of the
final rule accordingly and reidentified
subsequent paragraphs.
Explanation of Change to Identified
Repair Drawings
We have revised paragraph (h) of the
final rule to refer to the correct revisions
and dates of Bombardier Repair Drawing
RD 8/4–55–090 and RD 8/4–55–094.
Clarification of AMOC Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We have carefully reviewed the
available data, including the comment
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 for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Action
Work hours
Detailed inspection and torque check ......................
Replacement .............................................................
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.
rmajette on PROD1PC67 with RULES
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;
14:47 Dec 20, 2005
2
30
$65
$65
Cost per
airplane
Parts
None .................
Free of charge ..
(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.
$130
$1,950
Number of
U.S.-registered airplanes
19
19
Fleet cost
$2,470
37,050
Effective Date
(a) This AD becomes effective January 25,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–400 series airplanes, certificated in
any category; serial numbers 4001, and 4003
through 4081 inclusive.
Jkt 208001
I
Unsafe Condition
(d) This AD results from a report indicating
that laminated shims were delaminated and
extruded from the interface between the
forward attaching fittings of horizontal
stabilizer and the top rib of the vertical
stabilizer, and that inadequate torque values
of some bolts were found. We are issuing this
AD to prevent reduced structural integrity of
the horizontal stabilizer, and consequent loss
of controllability of the airplane.
PART 39—AIRWORTHINESS
DIRECTIVES
Regulatory Findings
VerDate Aug<31>2005
Average
labor rate
per hour
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.
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:
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 adding the following new
airworthiness directive (AD):
I
2005–26–05 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–14426.
Docket No. FAA–2005–22403;
Directorate Identifier 2005–NM–144–AD.
PO 00000
Frm 00016
Fmt 4700
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Service Information
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Bombardier Service Bulletin
84–55–02, Revision ‘‘A,’’ dated January 12,
2005.
(g) Accomplishing a detailed inspection, a
breakaway torque check, and corrective
actions if necessary before the effective date
of this AD in accordance with Bombardier
Service Bulletin 84–55–02, dated December
11, 2003; or Bombardier All Operator
Message 096B, dated June 12, 2003; is
acceptable for compliance with the
corresponding requirements of this AD.
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Federal Register / Vol. 70, No. 244 / Wednesday, December 21, 2005 / Rules and Regulations
(h) Accomplishing the repair before the
effective date of this AD in accordance with
the applicable Bombardier repair drawings in
Table 1 of this AD is acceptable for
compliance with the requirements of this AD.
TABLE 1.—REPAIR DRAWINGS
Bombardier repair drawing
RD
RD
RD
RD
RD
RD
RD
RD
RD
8/4–55–083
8/4–55–084
8/4–55–089
8/4–55–090
8/4–55–093
8/4–55–094
8/4–55–106
8/4–55–110
8/4–55–138
.........................................................................................................................................................
.........................................................................................................................................................
.........................................................................................................................................................
.........................................................................................................................................................
.........................................................................................................................................................
.........................................................................................................................................................
.........................................................................................................................................................
.........................................................................................................................................................
.........................................................................................................................................................
Detailed Inspection and Torque Check
(i) Within 4,000 flight hours after the
effective date of this AD, do the actions
specified in paragraphs (i)(1) and (i)(2) of this
AD in accordance with Part A of the service
bulletin.
(1) Do a detailed inspection of the
laminated shims for cracks, damage, or
extrusion between the forward attachment
fittings of the horizontal stabilizer and the
top rib of the vertical stabilizer.
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.’’
(2) Do a breakaway torque check of the six
attachment bolts in the attachment fittings of
the front, middle, and rear spars.
rmajette on PROD1PC67 with RULES
Corrective Actions
(j) If, during the inspection required by
paragraph (i)(1) of this AD, any cracked,
damaged, or extruded laminated shim is
found, before further flight, replace the
discrepant laminated shim with a solid shim,
and replace the attachment bolts, barrel nuts,
and retainers of both front spars with new
parts, in accordance with Parts A and B of
the service bulletin.
(k) If, during the torque check required by
paragraph (i)(2) of this AD, any attachment
bolt is found with a breakaway torque value
outside the limits specified in the service
bulletin, before further flight, replace the
attachment bolt and its corresponding barrel
nut and retainer with new parts, in
accordance Part A of the service bulletin.
Replacement of Laminated Shims
(1) Within 8,000 flight hours after the
effective date of this AD, unless previously
accomplished in accordance with paragraph
(j) of this AD, replace the laminated shims,
between the forward attachment fittings of
the horizontal stabilizer and the top rib of the
vertical stabilizer, with solid shims and
replace the corresponding barrel nut and
retainer with new parts, in accordance with
Part B of the service bulletin.
VerDate Aug<31>2005
RD issue
14:47 Dec 20, 2005
Jkt 208001
No Reporting
3
1
2
8
2
4
2
3
1
Dated
April 16, 2003.
May 5, 2003.
June 6, 2003.
October 9, 2003.
June 20, 2003.
October 20, 2003.
July 31, 2003.
October 1, 2003.
October 29, 2003.
(m) Although the service bulletin
referenced in this AD specifies to submit
certain information to the manufacturer, this
AD does not include that requirement.
Alternative Methods of Compliance
(AMOCs)
Issued in Renton, Washington, on
December 13, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–24245 Filed 12–20–05; 8:45 am]
BILLING CODE 4910–13–P
(n)(1) The Manager, New York Aircraft
Certification Office, 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
DEPARTMENT OF COMMERCE
Office of the Secretary
15 CFR Part 4
[Docket No. 051215336–5336–01]
RIN 0605–AA21
Disclosure of Government Information;
Addition of Designated Official
Office of the Secretary;
Department of Commerce.
ACTION: Final rule.
(o) Canadian airworthiness directive CF–
2005–07, issued March 21, 2005, also
addresses the subject of this AD.
AGENCY:
Material Incorporated by Reference
SUMMARY: This final rule amends the
Department of Commerce’s Freedom of
Information Act regulations (15 CFR
part 4) by adding an official authorized
To deny requests for records under the
Freedom of Information Act, and
requests for correction or amendment
under the Privacy Act, for the
Technology Administration.
DATES: Effective December 16, 2005.
FOR FURTHER INFORMATION CONTACT:
Philip Greene, Freedom of Information
Officer, Office of the Chief Counsel,
Technology Administration, 202–482–
1984.
SUPPLEMENTARY INFORMATION: Appendix
B to 15 CFR part 4 designates the
officials authorized to deny requests for
records under the Freedom of
Information Act (FOIA), and requests for
records and requests for correction or
amendment under the Privacy Act (PA).
The Department of Commerce
(Department) amends its regulations to
add the Deputy Assistant Secretary for
Technology Policy as a designated
(p) You must use Bombardier Service
Bulletin 84–55–02, Revision ‘A,’ dated
January 12, 2005, to perform the actions that
are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register approved the incorporation
by reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5,
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/
federal_register/code_of_federal_regulations/
ibr_locations.html.
PO 00000
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Fmt 4700
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21DER1
]]>Agencies
[Federal Register Volume 70, Number 244 (Wednesday, December 21, 2005)]
[Rules and Regulations]
[Pages 75727-75729]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-24245]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22403; Directorate Identifier 2005-NM-144-AD;
Amendment 39-14426; AD 2005-26-05]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier Model DHC-8-400 series airplanes. This AD requires
an inspection of the laminated shims for cracks, damage, or extrusion
between the forward attachment fittings of the horizontal stabilizer
and the top rib of the vertical stabilizer; a torque check of the
attachment bolts in the attachment fittings of the front, middle, and
rear spars; and corrective actions if necessary. This AD results from a
report indicating that delaminated shims extruded from the interface
between the forward attaching fittings of the horizontal stabilizer and
the top rib of the vertical stabilizer, and that inadequate torque
values of some bolts were found. We are issuing this AD to prevent
reduced structural integrity of the horizontal stabilizer, and
consequent loss of controllability of the airplane.
DATES: This AD becomes effective January 25, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of January 25,
2006.
ADDRESSES: You may examine 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., Nassif Building,
Room PL-401, Washington, DC.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: George Duckett, 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) 228-7325; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Bombardier
Model DHC-8-400 series airplanes. That NPRM was published in the
Federal Register on September 14, 2005 (70 FR 54316). (An NPRM
correction was published in the Federal Register on September 30, 2005
(70 FR 57221).) That NPRM proposed to require an inspection of the
laminated shims for cracks, damage, or extrusion between the forward
attachment fittings of the horizontal stabilizer and the top rib of the
vertical stabilizer; a torque check of the attachment bolts in the
attachment fittings of the front, middle, and rear spars; and
corrective actions if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received.
Request for Credit for Doing Bombardier All Operator Message (AOM)
One commenter requests that operators be given credit for doing the
procedures in accordance with
[[Page 75728]]
Bombardier AOM 096B, dated June 12, 2003, before the effective date of
the AD, as an alternative method of compliance (AMOC) with the
requirements of paragraphs (i)(1) and (i)(2) of the NPRM.
We agree with the commenter that accomplishing the actions
specified in Bombardier AOM 096B before the effective date of this AD
is acceptable for compliance with the detailed inspection and torque
check required by paragraphs (i)(1) and (i)(2) of the AD. We also have
determined that those actions are also acceptable for the replacement
requirements of the AD. We have revised paragraph (g) of the final rule
accordingly and reidentified subsequent paragraphs.
Explanation of Change to Identified Repair Drawings
We have revised paragraph (h) of the final rule to refer to the
correct revisions and dates of Bombardier Repair Drawing RD 8/4-55-090
and RD 8/4-55-094.
Clarification of AMOC Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
We have carefully reviewed the available data, including the
comment 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 for U.S. operators
to comply with this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average Cost per U.S.-
Action Work hours labor rate Parts airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed inspection and torque check........... 2 $65 None.................................. $130 19 $2,470
Replacement.................................... 30 $65 Free of charge........................ $1,950 19 37,050
--------------------------------------------------------------------------------------------------------------------------------------------------------
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
adding the following new airworthiness directive (AD):
2005-26-05 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-14426. Docket No. FAA-2005-22403; Directorate Identifier 2005-NM-
144-AD.
Effective Date
(a) This AD becomes effective January 25, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400 series
airplanes, certificated in any category; serial numbers 4001, and
4003 through 4081 inclusive.
Unsafe Condition
(d) This AD results from a report indicating that laminated
shims were delaminated and extruded from the interface between the
forward attaching fittings of horizontal stabilizer and the top rib
of the vertical stabilizer, and that inadequate torque values of
some bolts were found. We are issuing this AD to prevent reduced
structural integrity of the horizontal stabilizer, and consequent
loss of controllability 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.
Service Information
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Bombardier Service Bulletin 84-55-02,
Revision ``A,'' dated January 12, 2005.
(g) Accomplishing a detailed inspection, a breakaway torque
check, and corrective actions if necessary before the effective date
of this AD in accordance with Bombardier Service Bulletin 84-55-02,
dated December 11, 2003; or Bombardier All Operator Message 096B,
dated June 12, 2003; is acceptable for compliance with the
corresponding requirements of this AD.
[[Page 75729]]
(h) Accomplishing the repair before the effective date of this
AD in accordance with the applicable Bombardier repair drawings in
Table 1 of this AD is acceptable for compliance with the
requirements of this AD.
Table 1.--Repair Drawings
------------------------------------------------------------------------
Bombardier repair drawing RD issue Dated
------------------------------------------------------------------------
RD 8/4-55-083.................... 3 April 16, 2003.
RD 8/4-55-084.................... 1 May 5, 2003.
RD 8/4-55-089.................... 2 June 6, 2003.
RD 8/4-55-090.................... 8 October 9, 2003.
RD 8/4-55-093.................... 2 June 20, 2003.
RD 8/4-55-094.................... 4 October 20, 2003.
RD 8/4-55-106.................... 2 July 31, 2003.
RD 8/4-55-110.................... 3 October 1, 2003.
RD 8/4-55-138.................... 1 October 29, 2003.
------------------------------------------------------------------------
Detailed Inspection and Torque Check
(i) Within 4,000 flight hours after the effective date of this
AD, do the actions specified in paragraphs (i)(1) and (i)(2) of this
AD in accordance with Part A of the service bulletin.
(1) Do a detailed inspection of the laminated shims for cracks,
damage, or extrusion between the forward attachment fittings of the
horizontal stabilizer and the top rib of the vertical stabilizer.
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.''
(2) Do a breakaway torque check of the six attachment bolts in
the attachment fittings of the front, middle, and rear spars.
Corrective Actions
(j) If, during the inspection required by paragraph (i)(1) of
this AD, any cracked, damaged, or extruded laminated shim is found,
before further flight, replace the discrepant laminated shim with a
solid shim, and replace the attachment bolts, barrel nuts, and
retainers of both front spars with new parts, in accordance with
Parts A and B of the service bulletin.
(k) If, during the torque check required by paragraph (i)(2) of
this AD, any attachment bolt is found with a breakaway torque value
outside the limits specified in the service bulletin, before further
flight, replace the attachment bolt and its corresponding barrel nut
and retainer with new parts, in accordance Part A of the service
bulletin.
Replacement of Laminated Shims
(1) Within 8,000 flight hours after the effective date of this
AD, unless previously accomplished in accordance with paragraph (j)
of this AD, replace the laminated shims, between the forward
attachment fittings of the horizontal stabilizer and the top rib of
the vertical stabilizer, with solid shims and replace the
corresponding barrel nut and retainer with new parts, in accordance
with Part B of the service bulletin.
No Reporting
(m) Although the service bulletin referenced in this AD
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, New York Aircraft Certification Office, 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
(o) Canadian airworthiness directive CF-2005-07, issued March
21, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(p) You must use Bombardier Service Bulletin 84-55-02, Revision
`A,' dated January 12, 2005, to perform the actions that are
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register approved the incorporation by reference of
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123
Garratt Boulevard, Downsview, Ontario M3K 1Y5, 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/federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on December 13, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-24245 Filed 12-20-05; 8:45 am]
BILLING CODE 4910-13-P
