[Federal Register Volume 75, Number 86 (Wednesday, May 5, 2010)]
[Rules and Regulations]
[Pages 24389-24392]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-10472]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0435; Directorate Identifier 2010-NM-084-AD;
Amendment 39-16283; AD 2010-10-04]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
Operators of DHC-8 400 Series aeroplanes have been reporting
chafing of wires in the AC wire harnesses located along the lower
wing shroud on either wing resulting in a loss of various system
services. Chafed wires may lead to arcing, local overheating and AC
generator failure. The AC generators provide power to the anti-icing
heaters, including pitot/static heater, engine adapter heater, and
propeller heater. Failure of both AC generators would result in the
loss of these systems and poses a safety concern.
* * * * *
Loss of both AC generators could lead to unannunciated loss of heat
to both engine inlets, which could lead to loss of power in both
engines during icing conditions. This AD requires actions that are
intended to address the unsafe condition described in the MCAI.
DATES: This AD becomes effective May 20, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of May 20, 2010.
We must receive comments on this AD by June 21, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Craig Yates, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury,
[[Page 24390]]
New York 11590; telephone (516) 228-7355; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2010-08, dated March 16, 2010 (referred to after this as ``the MCAI''),
to correct an unsafe condition for the specified products. The MCAI
states:
Operators of DHC-8 400 Series aeroplanes have been reporting
chafing of wires in the AC wire harnesses located along the lower
wing shroud on either wing resulting in a loss of various system
services. Chafed wires may lead to arcing, local overheating and AC
generator failure. The AC generators provide power to the anti-icing
heaters, including pitot/static heater, engine adapter heater, and
propeller heater. Failure of both AC generators would result in the
loss of these systems and poses a safety concern.
Investigation has revealed that at four wiring harness tie down
mount locations, the blind fasteners used to attach the tie down
mount base were found to have protruding stems which chafed through
the wire insulation leading to arcing damage. In addition, the wire
chafing along the wing rear spar lower shroud has been attributed to
sagging wire bundles resting on the structure and insufficient
support in low clearance areas.
This directive mandates the replacement of the blind fasteners
with solid rivets, and to inspect for and rectify damaged wiring
along the wing lower shroud.
Loss of both AC generators could lead to unannunciated loss of heat to
both engine inlets, which could lead to loss of power in both engines
during icing conditions. The required actions also include a detailed
inspection for damage and chafing of the wires in the wiring harness
installation, and the Teflon tubing if necessary. The corrective
actions (rectifying) include replacement or repair of the chafed or
damaged wire or Teflon tubing. You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Bombardier has issued Alert Service Bulletin A84-24-44, Revision A,
dated February 2, 2010; and Repair Drawing 8/4-24-011, Issue 2, dated
January 21, 2010. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between the AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the AD.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because the
chafing of a wire bundle could result in an electrical short and
potential loss of several functions essential for safe flight,
including both AC generators. Therefore, we determined that notice and
opportunity for public comment before issuing this AD are impracticable
and that good cause exists for making this amendment effective in fewer
than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2010-0435; Directorate
Identifier 2010-NM-084-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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 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 this AD:
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 AD and placed it in the AD docket.
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:
[[Page 24391]]
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 AD:
2010-10-04 Bombardier, Inc.: Amendment 39-16283. Docket No. FAA-
2010-0435; Directorate Identifier 2010-NM-084-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 20,
2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier, Inc. Model DHC-8-400, -401,
and -402 airplanes, serial numbers 4001 through 4169 inclusive,
certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 24:
Electrical Power.
Reason
(e) The mandatory continued airworthiness information (MCAI)
states:
Operators of DHC-8 400 Series aeroplanes have been reporting
chafing of wires in the AC wire harnesses located along the lower
wing shroud on either wing resulting in a loss of various system
services. Chafed wires may lead to arcing, local overheating and AC
generator failure. The AC generators provide power to the anti-icing
heaters, including pitot/static heater, engine adapter heater, and
propeller heater. Failure of both AC generators would result in the
loss of these systems and poses a safety concern.
Investigation has revealed that at four wiring harness tie down
mount locations, the blind fasteners used to attach the tie down
mount base were found to have protruding stems which chafed through
the wire insulation leading to arcing damage. In addition, the wire
chafing along the wing rear spar lower shroud has been attributed to
sagging wire bundles resting on the structure and insufficient
support in low clearance areas.
This directive mandates the replacement of the blind fasteners
with solid rivets, and to inspect for and rectify damaged wiring
along the wing lower shroud.
Loss of both AC generators could lead to unannunciated loss of heat
to both engine inlets, which could lead to loss of power in both
engines during icing conditions. The required actions also include a
detailed inspection for damage and chafing of the wires in the
wiring harness installation, and the Teflon tubing if necessary. The
corrective actions (rectifying) include replacement or repair of the
chafed or damaged wire or Teflon tubing.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Replacement of Blind Fasteners, Inspection for Chafing at Four Wiring
Harness Tie Down Mount Locations and Corrective Action
(g) Within 200 flight hours after the effective date of this AD:
Replace the blind fasteners installed at the four wiring harness tie
down mount locations with solid rivets; and do a detailed inspection
for chafing and damage of the wires and, as applicable, of any
Teflon tubing and do all applicable corrective actions; in
accordance with paragraph B.(6) of the Accomplishment Instructions
of Bombardier Alert Service Bulletin A84-24-44, Revision A, dated
February 2, 2010. Do all applicable corrective actions before
further flight.
Inspection of AC Feeder Cables Along Lower Wing Shroud and Corrective
Action
(h) At the applicable time in paragraph (h)(1) or (h)(2) of this
AD: Do a detailed inspection of the wiring harness installation
along the wing rear spar lower shroud for any chafing and damage,
and do all applicable corrective actions, in accordance with the
Accomplishment Instructions of Bombardier Alert Service Bulletin
A84-24-44, Revision A, dated February 2, 2010. Do all applicable
corrective actions before further flight.
(1) For airplanes with AC feeder cables not covered with
protective Teflon tubing (Modsum Number IS4Q2450001 or production
Modsum 4Q109946 not incorporated): Within 600 flight hours after the
effective date of this AD.
(2) For airplanes with AC feeder cables covered with protective
Teflon tubing (Modsum Number IS4Q2450001 or production Modsum
4Q109946 incorporated): Within 4,000 flight hours after the
effective date of this AD.
(i) For airplanes on which the temporary repair specified in
Bombardier Repair Drawing 8/4-24-011, Issue 2, dated January 21,
2010, has been done: Within 600 flight hours after accomplishing the
temporary repair or 60 flight hours after the effective date of this
AD, whichever occurs later, do the permanent repair or replace the
wiring, in accordance with Bombardier Repair Drawing 8/4-24-011,
Issue 2, dated January 21, 2010.
Actions According to Previous Issue of Service Information
(j) Actions done before the effective date of this AD in
accordance with Bombardier Alert Service Bulletin A84-24-44, dated
January 27, 2010, are acceptable for compliance with the
corresponding requirements of paragraphs (g) and (h) of this AD.
(k) Actions done before the effective date of this AD in
accordance with any modification summary identified in Table 1 of
this AD are acceptable for compliance with the corresponding
requirements of paragraph (g) of this AD.
Table 1--Modification Summaries
----------------------------------------------------------------------------------------------------------------
Bombardier modification summary-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
IS4Q5700013.............................. A January 12, 2010.
IS4Q5700013.............................. B January 20, 2010.
IS4Q5700013.............................. C January 27, 2010.
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Reporting Requirement
(l) Submit a report of the findings (both positive and negative)
of the inspection required by paragraph (h) of this AD to Bombardier
Technical Help Desk; telephone 416-375-4000; e-mail
[email protected]; at the applicable time specified in
paragraph (l)(1) or (l)(2) of this AD. Use Figures 1 and 2 (Feedback
Form) of Bombardier Alert Service Bulletin A84-24-44, Revision A,
dated February 2, 2010, to submit the report. The report must
include the inspection results, a description of any discrepancies
found, the airplane serial number, and the number of landings and
flight hours on the airplane.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 14 days after the inspection.
(2) If the inspection was accomplished prior to the effective
date of this AD: Submit the report within 14 days after the
effective date of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: The MCAI does not specify a compliance time for doing a
permanent repair or replacement for airplanes on which a temporary
repair is done. This AD requires that the temporary repair is
replaced by a permanent repair or replacement of the wiring. We have
coordinated this difference with Transport Canada Civil Aviation
(TCCA).
Other FAA AD Provisions
(m) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANE-
170, New York Aircraft Certification Office, FAA, has the authority
to approve AMOCs for this AD, if requested using the procedures
found in 14
[[Page 24392]]
CFR 39.19. Send information to Attn: Program Manager, Continuing
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite
410, Westbury, New York, 11590; telephone 516-228-7300; fax 516-794-
5531. Before using any approved AMOC on any airplane to which the
AMOC applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(n) Refer to MCAI Canadian Airworthiness Directive CF-2010-08,
dated March 16, 2010; Bombardier Alert Service Bulletin A84-24-44,
Revision A, dated February 2, 2010; and Bombardier Repair Drawing 8/
4-24-011, Issue 2, dated January 21, 2010; for related information.
Material Incorporated by Reference
(o) You must use Bombardier Alert Service Bulletin A84-24-44,
Revision A, dated February 2, 2010; and Bombardier Repair Drawing 8/
4-24-011, Issue 2, dated January 21, 2010; as applicable; to do the
actions required by this AD, unless the AD specifies otherwise.
Bombardier Repair Drawing 8/4-24-011, Issue 2, dated January 21,
2010, contains the following effective pages:
------------------------------------------------------------------------
Revision
Page No. level shown Date shown on page
on page
------------------------------------------------------------------------
1, 3......................... 2 January 21, 2010.*
2, 4-7....................... 1 January 18, 2010.*
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* Only the first page of this repair drawing contains the issue dates.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; e-mail [email protected]; Internet http://www.bombardier.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on April 27, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-10472 Filed 5-4-10; 8:45 am]
BILLING CODE 4910-13-P