[Federal Register: December 11, 2006 (Volume 71, Number 237)]
[Proposed Rules]
[Page 71492-71494]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11de06-9]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26558; Directorate Identifier 2006-NM-206-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -
106 Airplanes; and Model DHC-8-200 and DHC-8-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Bombardier Model DHC-8-100 (as described above), DHC-8-200,
and DHC-8-300 series airplanes. This proposed AD would require doing a
one-time inspection for damage of the electrical cable harness assembly
located on the left and right wing root to fuselage aft seal, and
repair if necessary; and reworking the fuselage aft seal assembly (left
and right) to create a clearance between the electrical cable
assemblies and the edge of the fairing panel. This proposed AD results
from a report that an airplane encountered an uncommanded propeller
feathering during climb, which resulted in an emergency landing. We are
proposing this AD to prevent chafing or grounding of the wiring against
the aft seal assemblies, which, if not corrected, could interrupt the
operation of various systems, including the propeller feather control,
alternating current (AC) electrical power, and standby hydraulic power,
and result in reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by January 10,
2007.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Douglas Wagner, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New
York 11590; telephone (516) 228-7306; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
26558; Directorate Identifier 2006-NM-206-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
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 may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, notified us that an unsafe condition may exist on
certain Bombardier Model DHC-8-102, -103, and -106 airplanes, and Model
DHC-8-200 and DHC-8-300 series airplanes. TCCA advises that a Model
DHC-8 airplane encountered an uncommanded propeller feathering during
climb, which resulted in an emergency landing. Investigation showed
that the wing-to-fuselage aft seal assembly had chafed through the
wires associated with the auto-feather control system. Chafing or
grounding of the wiring against the aft seal assemblies, if not
corrected, could interrupt the operation of various systems, including
the propeller feather control, alternating current (AC) electrical
power, and standby hydraulic power, and result in reduced
controllability of the airplane.
Relevant Service Information
Bombardier has issued Service Bulletin 8-24-83, Revision A, dated
August 2, 2005. The service bulletin describes procedures for
inspecting for damage of the electrical cable harness assembly located
at the left and right wing root to fuselage aft seal, and repair if
necessary. The service bulletin also describes procedures for reworking
the fuselage aft seal assembly (left and right) to create a clearance
between the electrical cable assemblies and the edge of the fairing
panel. The rework described in Service Bulletin 8-24-83, Revision A,
contains the instructions for
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incorporating Bombardier Modification Summary Package 8Y122031,
Revision B, dated December 2, 2004. (The technical content of
Bombardier Modification Summary Package IS8Q2400005, Revision C, dated
January 7, 2005, is equivalent to Modification Summary Package
8Y122031, Revision B.) The rework includes removing a rivet and
installing a new rivet, installing new anchor nuts with a clamp, and
winding a protective layer of ``spiral wrap'' around the affected
electrical cable assemblies. Accomplishing the actions specified in the
service information is intended to adequately address the unsafe
condition. TCCA mandated the service information and issued Canadian
airworthiness directive CF-2006-15, dated June 14, 2006, to ensure the
continued airworthiness of these airplanes in Canada.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in Canada and are 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 airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously.
Clarification of Inspection Terminology
Where the TCCA airworthiness directive specifies to ``visually
inspect'' and the service bulletin specifies to ``inspect'' the
electrical cable harness assembly, this proposed AD refers to the
inspection as a general visual inspection. We have included the
definition for a general visual inspection in a note in the proposed
AD.
Costs of Compliance
This proposed AD would affect about 136 airplanes of U.S. registry.
The proposed actions would take about 4 work hours per airplane, at an
average labor rate of $80 per work hour. Required parts would cost
about $75 per airplane. Based on these figures, the estimated cost of
the proposed AD for U.S. operators is $53,720, or $395 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2006-
26558; Directorate Identifier 2006-NM-206-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by January
10, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-102, -103, and -
106 airplanes, and Model DHC-8-200 and DHC-8-300 series airplanes,
certificated in any category; serial numbers 003 through 606,
inclusive.
Unsafe Condition
(d) This AD results from a report that an airplane encountered
an uncommanded propeller feathering during climb, which resulted in
an emergency landing. We are issuing this AD to prevent chafing or
grounding of the wiring against the aft seal assemblies, which, if
not corrected, could interrupt the operation of various systems,
including the propeller feather control, alternating current (AC)
electrical power, and standby hydraulic power, and result in reduced
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.
Inspection and Rework
(f) Within 6,000 flight hours after the effective date of this
AD, do the actions in paragraphs (f)(1) and (f)(2) of this AD. Do
all actions in accordance with Bombardier Service Bulletin 8-24-83,
Revision A, dated August 2, 2005. The actions in paragraph (f)(1) of
this AD must be done before the rework in paragraph (f)(2) of this
AD.
Note 1: Bombardier Service Bulletin 8-24-83, Revision A,
contains the instructions for incorporating Bombardier Modification
Summary Package 8Y122031, Revision B, dated December 2, 2004. (The
technical content of Bombardier Modification Summary Package
IS8Q2400005, Revision C, dated January 7, 2004, is equivalent to
Bombardier Modification Summary Package 8Y122031, Revision B.)
(1) Do a general visual inspection for damage of the electrical
cable harness assembly located on the left and right wing root-to-
fuselage aft seal. If any damage is found, repair the damage before
further flight.
(2) Rework the fuselage aft seal assembly (left and right) to
create a clearance between the electrical cable assemblies and the
edge of the fairing panel.
Note 2: For the purposes of this AD, a general visual inspection
is: ``A visual
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examination of an interior or exterior area, installation, or
assembly to detect obvious damage, failure, or irregularity. This
level of inspection is made from within touching distance unless
otherwise specified. A mirror may be necessary to ensure visual
access to all surfaces in the inspection area. This level of
inspection is made under normally available lighting conditions such
as daylight, hangar lighting, flashlight, or droplight and may
require removal or opening of access panels or doors. Stands,
ladders, or platforms may be required to gain proximity to the area
being checked.''
Actions Accomplished in Accordance With Previous Revision of Service
Bulletin
(g) Actions done before the effective date of this AD in
accordance with Bombardier Service Bulletin 8-24-83, dated December
23, 2004, are acceptable for compliance with the corresponding
requirements in paragraph (f) of this AD.
Alternative Methods of Compliance (AMOCs)
(h)(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
(i) Canadian airworthiness directive CF-2006-15, dated June 14,
2006, also addresses the subject of this AD.
Issued in Renton, Washington, on December 1, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-20969 Filed 12-8-06; 8:45 am]
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