[Federal Register: February 8, 2006 (Volume 71, Number 26)]
[Proposed Rules]
[Page 6408-6411]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08fe06-26]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23820; Directorate Identifier 2005-NM-249-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -
106 Airplanes; and Model DHC-8-200 and -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 revise an existing airworthiness directive
(AD) that applies to certain Bombardier Model DHC-8-102, -103, and -106
airplanes; and Model DHC-8-200 and -300 series airplanes. The existing
AD currently requires performing a one-time inspection to detect
chafing of electrical wires in the cable trough below the cabin floor;
repairing, if necessary; installing additional tie-mounts and tie-
wraps; applying sealant to rivet heads; and modifying electrical wires
in certain sections. This proposed AD would, for certain airplanes,
eliminate the requirement to modify electrical wires in certain
sections. This proposed AD results from a report indicating that the
modification of electrical wires does not need to be done on certain
airplanes subject to the existing AD. We are proposing this AD to
prevent chafing of electrical wires, which could result in an
uncommanded shutdown of an engine during flight.
DATES: We must receive comments on this proposed AD by March 10, 2006.
[[Page 6409]]
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 G. Wagner, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, New York Aircraft
Certification Office, FAA, 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 ``Docket No.
FAA-2006-23820; Directorate Identifier 2005-NM-249-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 a docket,
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
On January 29, 2004, we issued AD 2004-03-15, amendment 39-13459
(69 FR 7111, February 13, 2004), for certain Bombardier Model DHC-8-
102, -103, -106, -201, -202, -301, -311, and -315 airplanes. That AD
requires a one-time inspection to detect chafing of electrical wires in
the cable trough below the cabin floor; repair, if necessary;
installation of additional tie-mounts and tie-wraps; application of
sealant to rivet heads; and modification of the electrical wires in
certain sections. That AD resulted from a report of an uncommanded
engine shutdown during flight. We issued that AD to prevent chafing of
electrical wires, which could result in an uncommanded shutdown of an
engine during flight.
Actions Since Existing AD Was Issued
Paragraph (b) of AD 2004-03-15 requires all airplanes subject to
the AD to modify the electrical wires in the cable trough below the
cabin floor at Sections X510.00 to X580.50, in accordance with
Bombardier Service Bulletin 8-53-80, Revision `A,' dated July 25, 2000.
Since we issued AD 2004-03-15, we have received a report indicating
that Bombardier Model DHC-8-300 series airplanes should not be required
to do this modification.
We have reviewed Canadian airworthiness directive CF-1998-08R2,
dated July 12, 2000, which AD 2004-03-15 refers to as the parallel
Canadian airworthiness directive. Canadian airworthiness directive CF-
1998-08R2 identifies Model DHC-8-300 series airplanes as being subject
only to Bombardier Service Bulletin S.B. 8-53-66, dated March 27, 1998,
not to Bombardier Service Bulletin 8-53-80, Revision `A.' (Paragraph
(a) of AD 2004-03-15 refers to Bombardier Service Bulletin S.B. 8-53-66
as the appropriate source of service information for the actions
required by that paragraph.)
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, Transport Canada Civil Aviation
(TCCA), which is the airworthiness authority for Canada, 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.
This proposed AD would revise AD 2004-03-15 and would retain the
requirements of the existing AD. This proposed AD would eliminate the
requirement to modify electrical wires in certain sections on Model
DHC-8-300 series airplanes. The actions would be required to be done in
accordance with the service information specified in the existing AD,
except as discussed under ``Difference Between This Proposed AD and
Service Bulletin'' in the notice of proposed rulemaking for AD 2004-03-
15.
Changes to Existing AD
This proposed AD would retain all requirements of AD 2004-03-15.
Since AD 2004-03-15 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
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Corresponding requirement in
Requirement in AD 2004-03-15 this proposed AD
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paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
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Also, we have revised the range of airplane serial numbers (S/Ns)
stated in paragraphs (f)(1) and (f)(2) of this proposed AD. Paragraphs
(a)(1) and (a)(2) of AD 2004-03-15 specify the compliance times for
inspections in accordance with Bombardier Service Bulletin 8-53-66, as
required by paragraph (a) of that AD. Paragraph (a)(1) of AD 2004-03-15
states the compliance time for S/Ns 3 through 519 inclusive (excluding
S/N 462). Paragraph (a)(2) states the compliance
[[Page 6410]]
time for S/Ns 520 through 540 inclusive. We have determined that the
airplane having S/N 519 was incorrectly included in paragraph (a)(1) of
AD 2004-03-15. That airplane is a Model DHC-8-300 series airplane and
should be subject to the compliance time in paragraph (a)(2) of AD
2004-03-15. Therefore, we have revised paragraphs (f)(1) and (f)(2) of
this proposed AD to move S/N 519 into paragraph (f)(2) of this proposed
AD. (This change results in a slight extension of the compliance time
for the airplane having S/N 519.)
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.
Costs of Compliance
This new AD adds no new costs to affected operators; in fact, it
reduces the costs for some airplanes that are not subject to the
modification of certain wiring.
We estimate that 173 airplanes of U.S. registry will be subject to
the inspection, installation of additional tie-mounts and tie-wraps,
and application of sealant to rivet heads that are currently required
by AD 2004-03-15. These actions take between 80 and 100 work hours per
airplane, at an average labor rate of $65 per work hour. Required parts
are provided by the manufacturer at no cost to the operator. Based on
these figures, the estimated cost of these actions on U.S. operators is
between $899,600 and $1,124,500, or between $5,200 and $6,500 per
airplane.
We estimate that 103 airplanes of U.S. registry are subject to the
modification of certain wiring that is currently required by AD 2004-
03-15. This action takes approximately 10 work hours per airplane, at
an average labor rate of $65 per work hour. Required parts are provided
by the manufacturer at no cost to the operator. Based on these figures,
the estimated cost of the modification on U.S. operators is $66,950, or
$650 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
removing amendment 39-13459 (69 FR 7111, February 13, 2004) and adding
the following new airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2006-
23820; Directorate Identifier 2005-NM-249-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by March 10,
2006.
Affected ADs
(b) This AD revises AD 2004-03-15.
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 3 through 540 inclusive,
excluding serial number 462.
Unsafe Condition
(d) This AD results from a report indicating that the
modification of electrical wires does not need to be done on certain
airplanes subject to the existing AD. We are issuing this AD to
prevent chafing of electrical wires, which could result in an
uncommanded shutdown of an engine during flight.
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.
Requirements of AD 2004-03-15
One-Time Inspection, Corrective Action, and Modification
(f) Perform a one-time general visual inspection to detect
chafing of electrical wires in the cable trough below the cabin
floor; install additional tie-mounts and tie-wraps; and apply
sealant to rivet heads (reference Bombardier Modification 8/2705);
in accordance with Bombardier Service Bulletin S.B. 8-53-66, dated
March 27, 1998, at the time specified in paragraph (f)(1) or (f)(2)
of this AD, as applicable. If any chafing is detected during the
inspection required by this paragraph, prior to further flight,
repair in accordance with the service bulletin.
Note 1: For the purposes of this AD, a general visual inspection
is defined as: ``A visual 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 enhance visual access to all exposed 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.''
(1) For airplanes having serial numbers 3 through 518 inclusive,
excluding serial number 462: Inspect within 36 months after October
27, 1998 (the effective date of AD 98-20-14, amendment 39-10781).
(2) For airplanes having serial numbers 519 through 540
inclusive: Inspect within 36 months after November 10, 1999 (the
effective date of AD 99-21-09, amendment 39-11352, which superseded
AD 98-20-14), or at the next ``C'' check, whichever occurs first.
[[Page 6411]]
Modification
(g) For Model DHC-8-102, -103, and -106 airplanes; and Model
DHC-8-200 series airplanes: Within 36 months after March 19, 2004
(the effective date of AD 2004-03-15), modify the electrical wires
in the cable trough below the cabin floor at Sections X510.00 to
X580.50 (including performing a general visual inspection and any
applicable repair), in accordance with Part III, paragraphs 1
through 9 and 12 through 20, of the Accomplishment Instructions of
Bombardier Service Bulletin 8-53-80, Revision ``A,'' dated July 25,
2000. Any applicable repair must be done before further flight.
Accomplishment of these actions before March 19, 2004, in accordance
with Bombardier Service Bulletin 8-53-80, dated December 22, 1999,
is considered acceptable for compliance with the actions required by
this paragraph.
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-1998-08R2, dated July
10, 2000, also addresses the subject of this AD.
Issued in Renton, Washington, on January 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-1683 Filed 2-7-06; 8:45 am]
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