[Federal Register Volume 71, Number 237 (Monday, December 11, 2006)]
[Proposed Rules]
[Pages 71492-71494]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-20969]


 ========================================================================
 Proposed Rules
                                                 Federal Register
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 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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  Federal Register / Vol. 71, No. 237 / Monday, December 11, 2006 / 
Proposed 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

[[Page 71493]]

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]
BILLING CODE 4910-13-P