Airworthiness Directives; Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 Series Airplanes, 30959-30961 [E7-10670]
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30959
Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations
Issued in Burlington, Massachusetts, on
May 24, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E7–10588 Filed 6–4–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27713; Directorate
Identifier 2006–NM–240–AD; Amendment
39–15079; AD 2007–12–01]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–100, DHC–8–200, and
DHC–8–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier Model DHC–8–100, DHC–
8–200, and DHC–8–300 series airplanes.
This AD requires, for certain airplanes,
modification of the upper bearing of the
main landing gear (MLG) shock strut.
This AD also requires, for certain
airplanes, revising the de Havilland
DHC–8 Maintenance Program Manual to
include the MLG shock strut servicing
task. This AD results from reports of
over-extension of the MLG shock strut
piston, which allows the torque links to
go over-center and rest on the piston.
We are issuing this AD to prevent loss
in shock absorption during touchdown
and failure of the shock strut housing,
which could result in a subsequent loss
of directional control.
SUMMARY:
This AD becomes effective July
10, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of July 10, 2007.
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:
Mazdak Hobbi, 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) 228–7330; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
March 29, 2007 (72 FR 14721). That
NPRM proposed to require, for certain
airplanes, modification of the upper
bearing of the main landing gear (MLG)
shock strut. That NPRM proposed to
also require, for certain airplanes,
revising the de Havilland DHC–8
Maintenance Program Manual to
include the MLG shock strut servicing
task.
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.
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.
DATES:
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–8–100, DHC–8–200, and DHC–8–
300 series airplanes. That NPRM was
published in the Federal Register on
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the NPRM or on the
determination of the cost to the public.
Clarification of Part Number
We have revised paragraph (i)(2) of
this final rule to correct a typographical
error, which resulted in an incorrect
part number. Paragraph (i)(2) should
have read ‘‘* * * 10129–5 or 10129–
553.’’
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
Conclusion
We have carefully reviewed the
available data 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
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Modification ........................................................
Manual Revision ................................................
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.
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15:27 Jun 04, 2007
Jkt 211001
Average
labor rate
per hour
4
1
$80
80
Parts
$274
0
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
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Fmt 4700
Sfmt 4700
Number of U.S.registered
airplanes
Cost per
airplane
$594
80
Up to 135 .........
135 ...................
Fleet cost
Up to $80,190.
$10,800.
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.
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30960
Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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
2007–12–01 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–15079.
Docket No. FAA–2007–27713;
Directorate Identifier 2006–NM–240–AD.
Effective Date
(a) This AD becomes effective July 10,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–101, –102, –103, –106, –201, –202,
–301, –311, –314, and –315 airplanes,
certificated in any category; serial numbers
003 through 618 inclusive.
Unsafe Condition
(d) This AD results from reports of overextension of the main landing gear (MLG)
shock strut piston, which allows the torque
links to go over-center and rest on the piston.
We are issuing this AD to prevent loss in
shock absorption during touchdown and
failure of the shock strut housing, which
could result in a subsequent loss of
directional control.
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.
PART 39—AIRWORTHINESS
DIRECTIVES
Modification of the Upper Bearing
(f) For Model DHC–8–311, –314, and –315
airplanes, serial numbers 202 through 516
inclusive, with MLG shock struts having any
1. The authority citation for part 39
continues to read as follows:
I
serial number DCL3501/90 through
DCL3768/97 inclusive installed: Within
3,000 flight hours after the effective date of
this AD, modify the upper bearing in each
MLG (including doing inspections of the
upper bearing and cylinder bore for wear and
damage, and doing all applicable corrective
actions) in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–32–144, Revision ‘A,’
dated April 29, 2002, which includes
Messier-Dowty Service Bulletin M–DT
SBDHC8–32–82, Revision 1, dated July 5,
2001, except if wear exceeds the maximum
diameter specified in the service bulletin for
the cylinder bore or if damage is found on
the cylinder bore, before further flight, repair
using a method approved by either the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or
Transport Canada Civil Aviation (TCCA) (or
its delegated agent). Do all applicable
corrective actions before further flight.
Revision of the Maintenance Program
Manual
(g) For Model DHC–8–101, –102, –103,
–106, –201, –202, –301, –311, –314, and –315
airplanes, serial numbers 003 through 614
inclusive: Within 30 days after the effective
date of this AD, revise Part 1 of the
applicable de Havilland DHC–8 Maintenance
Program Manual by incorporating the
applicable MLG shock strut servicing Task
3210/15 specified in Table 1 of this AD.
Note 1: This may be done by inserting
copies of the applicable task into the
applicable maintenance program manual.
When these tasks have been included in the
general revisions of the applicable
maintenance program manual, the general
revisions may be inserted in the applicable
maintenance program manual and the copy
of the task may be removed from the
maintenance program manual.
TABLE 1.—TASKS
To the de
Havilland Program Support
Manual
(PSM)—
Task—
Dated—
de Havilland Dash 8 Series 100 Maintenance Task Card
3210/15.
de Havilland Dash 8 Series 200 Maintenance Task Card
3210/15.
de Havilland Dash 8 Series 300 Maintenance Task Card
3210/15.
June 22, 2005 ..........................
1–8–7
DHC–8–100 series airplanes.
June 22, 2005 ..........................
1–82–7
DHC–8–200 series airplanes.
November 29, 2005 .................
1–83–7
DHC–8–300 series airplanes.
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Parts Installation
(h) After the effective date of this AD, no
person may install a part identified in
paragraphs (h)(1) and (h)(2) of this AD, as a
replacement during the repair or overhaul of
any shock strut assembly, on any airplane.
(1) Upper bearing, part number 10130–3 or
10130–551.
(2) Damper ring, part number 10129–3 or
10129–551.
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15:27 Jun 04, 2007
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(i) After the effective date of this AD, only
the parts identified in paragraphs (i)(1) and
(i)(2) of this AD may be installed on any
airplane as replacement upper bearings and
damper rings during the repair or overhaul of
any shock strut assembly, except as provided
by paragraph (j) of this AD.
(1) Upper bearing, part number 10130–5.
(2) Damper ring, part number 10129–5 or
10129–553.
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Fmt 4700
Sfmt 4700
For model—
(j) After the effective date of this AD, only
MLGs with a reworked, oversize cylinder
bore (part number identified in the
applicable component maintenance manual
(CMM)) that have parts identified in
paragraphs (j)(1), (j)(2), and (j)(3) of this AD
used in accordance with the applicable CMM
may be installed on any airplane.
(1) Upper bearing, part number CRS85–
167–11.
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05JNR1
Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations
(2) Damper ring, part number CRS85–167–
31 or CRS85–167–33.
(3) Seal carrier, part number CRS85–167–
21.
Credit for Actions Done Using Previous
Service Information
(k) Modifications accomplished before the
effective date of this AD in accordance with
Bombardier Service Bulletin 8–32–144, dated
August 10, 1998, which includes MessierDowty Service Bulletin M–DT SBDHC8–32–
82, dated March 9, 1998, are considered
acceptable for compliance with the
corresponding actions specified in this AD.
Alternative Methods of Compliance
(AMOCs)
accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(m) Canadian airworthiness directive CF–
2006–14, dated June 14, 2006, also addresses
the subject of this AD.
Material Incorporated by Reference
(l)(1) The Manager, New York Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
(n) You must use Bombardier Service
Bulletin 8–32–144, Revision ‘A,’ dated April
29, 2002, which includes Messier-Dowty
30961
Service Bulletin M–DT SBDHC8–32–82,
Revision 1, dated July 5, 2001; and the task
cards identified in Table 2 of this AD; 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., 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 FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
TABLE 2.—TASK CARDS INCORPORATED BY REFERENCE
Task card—
Dated—
de Havilland Dash 8 Series 100 Maintenance Task Card 3210/15 ......................................................
de Havilland Dash 8 Series 200 Maintenance Task Card 3210/15 ......................................................
de Havilland Dash 8 Series 300 Maintenance Task Card 3210/15 ......................................................
June 22, 2005 .................
June 22, 2005 .................
November 29, 2005 ........
Issued in Renton, Washington, on May 25,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10670 Filed 6–4–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–26856; Directorate
Identifier 2006–NM–125–AD; Amendment
39–15082; AD 2007–12–04]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B4–600, B4–600R, and F4–600R
Series Airplanes, and Model C4–605R
Variant F Airplanes (Collectively Called
A300–600 Series Airplanes)
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to all Airbus Model A300–
600 series airplanes. That AD currently
requires inspections of the lower door
surrounding structure to detect cracks
and corrosion; inspections to detect
cracking of the holes of the corner
VerDate Aug<31>2005
15:27 Jun 04, 2007
Jkt 211001
doublers, the fail-safe ring, and the door
frames of the door structures; and repair
if necessary. That AD also provides for
optional terminating action for certain
inspections. This new AD retains all
requirements of the existing AD,
mandates the previously optional
terminating action, reduces the
applicability of the existing AD, and
adds repetitive inspections behind scuff
plates for certain affected airplanes.
This AD results from a determination
that further rulemaking is necessary to
improve the fatigue behavior of the
cabin door surroundings. We are issuing
this AD to prevent corrosion between
the scuff plates at exit and cargo doors
and fatigue cracks originating from
certain fastener holes located in
adjacent structure, which could result in
reduced structural integrity of the door
surroundings.
DATES: This AD becomes effective July
10, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of July 10, 2007.
On September 4, 1998 (63 FR 40812,
July 31, 1998), the Director of the
Federal Register approved the
incorporation by reference of certain
other publications listed in the AD.
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
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
To the de
Havilland program support
manual—
1–8–7.
1–82–7.
1–83–7.
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
fax (425) 227–1149.
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
supersedes AD 98–16–05, amendment
39–10680 (63 FR 40812, July 31, 1998).
The existing AD applies to all Airbus
Model A300–600 series airplanes. That
E:\FR\FM\05JNR1.SGM
05JNR1
]]>Agencies
[Federal Register Volume 72, Number 107 (Tuesday, June 5, 2007)]
[Rules and Regulations]
[Pages 30959-30961]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10670]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27713; Directorate Identifier 2006-NM-240-AD;
Amendment 39-15079; AD 2007-12-01]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-100, DHC-8-200,
and DHC-8-300 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-8-100, DHC-8-200, and DHC-8-300 series
airplanes. This AD requires, for certain airplanes, modification of the
upper bearing of the main landing gear (MLG) shock strut. This AD also
requires, for certain airplanes, revising the de Havilland DHC-8
Maintenance Program Manual to include the MLG shock strut servicing
task. This AD results from reports of over-extension of the MLG shock
strut piston, which allows the torque links to go over-center and rest
on the piston. We are issuing this AD to prevent loss in shock
absorption during touchdown and failure of the shock strut housing,
which could result in a subsequent loss of directional control.
DATES: This AD becomes effective July 10, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of July 10, 2007.
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: Mazdak Hobbi, 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) 228-7330; 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-8-100, DHC-8-200, and DHC-8-300 series airplanes. That NPRM
was published in the Federal Register on March 29, 2007 (72 FR 14721).
That NPRM proposed to require, for certain airplanes, modification of
the upper bearing of the main landing gear (MLG) shock strut. That NPRM
proposed to also require, for certain airplanes, revising the de
Havilland DHC-8 Maintenance Program Manual to include the MLG shock
strut servicing task.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the NPRM or on the
determination of the cost to the public.
Clarification of Part Number
We have revised paragraph (i)(2) of this final rule to correct a
typographical error, which resulted in an incorrect part number.
Paragraph (i)(2) should have read ``* * * 10129-5 or 10129-553.''
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
We have carefully reviewed the available data 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
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average
Action Work hours labor rate Parts Cost per Number of U.S.-registered Fleet cost
per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification.......................... 4 $80 $274 $594 Up to 135.................... Up to $80,190.
Manual Revision....................... 1 80 0 80 135.......................... $10,800.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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.
[[Page 30960]]
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):
2007-12-01 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-15079. Docket No. FAA-2007-27713; Directorate Identifier 2006-NM-
240-AD.
Effective Date
(a) This AD becomes effective July 10, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-101, -102, -103, -
106, -201, -202, -301, -311, -314, and -315 airplanes, certificated
in any category; serial numbers 003 through 618 inclusive.
Unsafe Condition
(d) This AD results from reports of over-extension of the main
landing gear (MLG) shock strut piston, which allows the torque links
to go over-center and rest on the piston. We are issuing this AD to
prevent loss in shock absorption during touchdown and failure of the
shock strut housing, which could result in a subsequent loss of
directional control.
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.
Modification of the Upper Bearing
(f) For Model DHC-8-311, -314, and -315 airplanes, serial
numbers 202 through 516 inclusive, with MLG shock struts having any
serial number DCL3501/90 through DCL3768/97 inclusive installed:
Within 3,000 flight hours after the effective date of this AD,
modify the upper bearing in each MLG (including doing inspections of
the upper bearing and cylinder bore for wear and damage, and doing
all applicable corrective actions) in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-32-144,
Revision `A,' dated April 29, 2002, which includes Messier-Dowty
Service Bulletin M-DT SBDHC8-32-82, Revision 1, dated July 5, 2001,
except if wear exceeds the maximum diameter specified in the service
bulletin for the cylinder bore or if damage is found on the cylinder
bore, before further flight, repair using a method approved by
either the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or Transport Canada Civil Aviation (TCCA)
(or its delegated agent). Do all applicable corrective actions
before further flight.
Revision of the Maintenance Program Manual
(g) For Model DHC-8-101, -102, -103, -106, -201, -202, -301, -
311, -314, and -315 airplanes, serial numbers 003 through 614
inclusive: Within 30 days after the effective date of this AD,
revise Part 1 of the applicable de Havilland DHC-8 Maintenance
Program Manual by incorporating the applicable MLG shock strut
servicing Task 3210/15 specified in Table 1 of this AD.
Note 1: This may be done by inserting copies of the applicable
task into the applicable maintenance program manual. When these
tasks have been included in the general revisions of the applicable
maintenance program manual, the general revisions may be inserted in
the applicable maintenance program manual and the copy of the task
may be removed from the maintenance program manual.
Table 1.--Tasks
----------------------------------------------------------------------------------------------------------------
To the de
Havilland
Task-- Dated-- Program For model--
Support Manual
(PSM)--
----------------------------------------------------------------------------------------------------------------
de Havilland Dash 8 Series 100 June 22, 2005............. 1-8-7 DHC-8-100 series
Maintenance Task Card 3210/15. airplanes.
de Havilland Dash 8 Series 200 June 22, 2005............. 1-82-7 DHC-8-200 series
Maintenance Task Card 3210/15. airplanes.
de Havilland Dash 8 Series 300 November 29, 2005......... 1-83-7 DHC-8-300 series
Maintenance Task Card 3210/15. airplanes.
----------------------------------------------------------------------------------------------------------------
Parts Installation
(h) After the effective date of this AD, no person may install a
part identified in paragraphs (h)(1) and (h)(2) of this AD, as a
replacement during the repair or overhaul of any shock strut
assembly, on any airplane.
(1) Upper bearing, part number 10130-3 or 10130-551.
(2) Damper ring, part number 10129-3 or 10129-551.
(i) After the effective date of this AD, only the parts
identified in paragraphs (i)(1) and (i)(2) of this AD may be
installed on any airplane as replacement upper bearings and damper
rings during the repair or overhaul of any shock strut assembly,
except as provided by paragraph (j) of this AD.
(1) Upper bearing, part number 10130-5.
(2) Damper ring, part number 10129-5 or 10129-553.
(j) After the effective date of this AD, only MLGs with a
reworked, oversize cylinder bore (part number identified in the
applicable component maintenance manual (CMM)) that have parts
identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD used
in accordance with the applicable CMM may be installed on any
airplane.
(1) Upper bearing, part number CRS85-167-11.
[[Page 30961]]
(2) Damper ring, part number CRS85-167-31 or CRS85-167-33.
(3) Seal carrier, part number CRS85-167-21.
Credit for Actions Done Using Previous Service Information
(k) Modifications accomplished before the effective date of this
AD in accordance with Bombardier Service Bulletin 8-32-144, dated
August 10, 1998, which includes Messier-Dowty Service Bulletin M-DT
SBDHC8-32-82, dated March 9, 1998, are considered acceptable for
compliance with the corresponding actions specified in this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(m) Canadian airworthiness directive CF-2006-14, dated June 14,
2006, also addresses the subject of this AD.
Material Incorporated by Reference
(n) You must use Bombardier Service Bulletin 8-32-144, Revision
`A,' dated April 29, 2002, which includes Messier-Dowty Service
Bulletin M-DT SBDHC8-32-82, Revision 1, dated July 5, 2001; and the
task cards identified in Table 2 of this AD; 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., 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 FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.
Table 2.--Task Cards Incorporated by Reference
------------------------------------------------------------------------
To the de
Havilland
Task card-- Dated-- program
support
manual--
------------------------------------------------------------------------
de Havilland Dash 8 Series 100 June 22, 2005....... 1-8-7.
Maintenance Task Card 3210/15.
de Havilland Dash 8 Series 200 June 22, 2005....... 1-82-7.
Maintenance Task Card 3210/15.
de Havilland Dash 8 Series 300 November 29, 2005... 1-83-7.
Maintenance Task Card 3210/15.
------------------------------------------------------------------------
Issued in Renton, Washington, on May 25, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-10670 Filed 6-4-07; 8:45 am]
BILLING CODE 4910-13-P
