[Federal Register: June 15, 2005 (Volume 70, Number 114)]
[Rules and Regulations]
[Page 34641-34642]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15jn05-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20860; Directorate Identifier 2005-NM-043-AD;
Amendment 39-14131; AD 2005-12-15]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier Model DHC-8-400 series airplanes. This AD requires
revising the Airworthiness Limitation section of the Instructions for
Continued Airworthiness of the Dash 8 400 Series (Bombardier)
Maintenance Requirements Manual to reduce the life limits of the main
landing gear (MLG) orifice support tube, upper bearing, and piston
plug; and to reduce the threshold for initiating repetitive detailed
inspections for cracking of the engine isolator brackets. This AD is
prompted by the discovery of fatigue failures, during type
certification fatigue testing, at the engine isolator bracket and at
the orifice support tube, upper bearing, and piston plug in the shock
strut assembly of the MLG, which are principal structural elements. We
are issuing this AD to prevent the development of cracks in these
principal structural elements, which could reduce the structural
integrity of the engine installation and the MLG. Reduced structural
integrity of the engine installation could result in separation of the
engine from the airplane, and reduced structural integrity of the MLG
could result in collapse of the MLG.
DATES: This AD becomes effective July 20, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of July
20, 2005.
ADDRESSES: For service information identified in this AD, contact
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Washington, DC. This docket number is FAA-2005-20860; the directorate
identifier for this docket is 2005-NM-043-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: The FAA proposed to amend 14 CFR part 39
with an AD for certain Bombardier Model DHC-8-400 series airplanes.
That action, published in the Federal Register on April 6, 2005 (70 FR
17354), proposed to require revising the Airworthiness Limitation
section of the Instructions for Continued Airworthiness of the Dash 8
400 Series (Bombardier) Maintenance Requirements Manual to reduce the
life limits of the main landing gear (MLG) orifice support tube, upper
bearing, and piston plug; and to reduce the threshold for initiating
repetitive detailed inspections for cracking of the engine isolator
brackets.
Explanation of Change to Applicability
We have revised the applicability of the proposed AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been submitted on the proposed
AD or on the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD with the
change described previously. We have determined that this change will
neither increase the economic burden on any operator nor increase the
scope of the AD.
Costs of Compliance
There are about 93 airplanes of the affected design in the
worldwide fleet. This AD will affect about 21 airplanes of U.S.
registry. The actions will take about 1 work hour per airplane, at an
average labor rate of $65 per work hour. Based on these figures, the
estimated cost of the AD for U.S. operators is $1,365, or $65 per
airplane.
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;
[[Page 34642]]
(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. 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 FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-12-15 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-14131. Docket No. FAA-2005-20860; Directorate Identifier 2005-NM-
043-AD.
Effective Date
(a) This AD becomes effective July 20, 2005.
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 4094 inclusive.
Note 1: This AD requires revision to a certain operator
maintenance document to include a new replacement time. Compliance
with this replacement time is required by 14 CFR 91.403(c). For
airplanes that have been previously modified, altered, or repaired
in the areas addressed by this replacement time, the operator may
not be able to accomplish the replacement described in the revision.
In this situation, to comply with 14 CFR 91.403(c), the operator
must request approval for an alternative method of compliance
according to paragraph (g) of this AD. The request should include a
description of changes to the required replacement time that will
ensure the continued damage tolerance of the affected structure. The
FAA has provided guidance for this determination in Advisory
Circular (AC) 25-1529.
Unsafe Condition
(d) This AD was prompted by the discovery of fatigue failures,
during type certification fatigue testing, at the engine isolator
bracket and at the orifice support tube, upper bearing, and piston
plug in the shock strut assembly of the main landing gear (MLG),
which are principal structural elements. We are issuing this AD to
prevent the development of cracks in these principal structural
elements, which could reduce the structural integrity of the engine
installation and MLG. Reduced structural integrity of the engine
installation could result in separation of the engine from the
airplane, and reduced structural integrity of the MLG could result
in collapse of the MLG.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Revisions to Airworthiness Limitation (AWL) Section
(f) Within 30 days after the effective date of this AD, revise
the AWL section of the Instructions for Continued Airworthiness of
the Dash 8 400 Series (Bombardier) Maintenance Requirements Manual,
PSM 1-84-7, by doing the actions specified in paragraphs (f)(1) and
(f)(2) of this AD.
(1) Reduce the life limits of the MLG orifice support tube
having part number (P/N) 46117-1, upper bearing having P/N 46114-1,
and piston plug having P/N 46137-1, by inserting Dash 8 400 Series
(Bombardier) Temporary Revision ALI-28, dated December 11, 2003,
into the AWL section. Thereafter, except as provided in paragraph
(g) of this AD, no alternative life limits may be approved for the
MLG orifice support tube, upper bearing, or piston plug.
(2) Incorporate structural inspection tasks 712001F102 and
712003F102 to reduce the threshold for initiating repetitive
detailed inspections for cracking of the engine isolator brackets by
inserting Dash 8 400 Series (Bombardier) Temporary Revision ALI-37,
dated March 30, 2004, into the AWL section. Thereafter, except as
provided in paragraph (g) of this AD, no alternative structural
inspection threshold may be approved.
Alternative Methods of Compliance (AMOCs)
(g) 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.
Related Information
(h) Canadian airworthiness directive CF-2004-19, dated September
21, 2004, also addresses the subject of this AD.
Material Incorporated by Reference
(i) You must use Dash 8 400 Series (Bombardier) Temporary
Revision ALI-28, dated December 11, 2003; and Dash 8 400 Series
(Bombardier) Temporary Revision ALI-37, dated March 30, 2004; to the
Dash 8 400 Series (Bombardier) Maintenance Requirements Manual, to
perform the actions that are required by this AD, unless the AD
specifies otherwise. The Director of the Federal Register approves
the incorporation by reference of these documents in accordance with
5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service
information, contact Bombardier, Inc., Bombardier Regional Aircraft
Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada.
To view the AD docket, go to the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Nassif Building, Washington, DC. To review copies of the service
information, go to 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 http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Issued in Renton, Washington, on June 7, 2005.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-11695 Filed 6-14-05; 8:45 am]
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