[Federal Register Volume 78, Number 235 (Friday, December 6, 2013)]
[Proposed Rules]
[Pages 73462-73465]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-29134]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-1024; Directorate Identifier 2013-NM-140-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301,
-311, and -315 airplanes. This proposed AD was prompted by reports of a
fractured wing-to-fuselage strut attachment joint bolt. This proposed
AD would require doing a torque check of all wing-to-fuselage strut
attachment joint bolts, and repairing or replacing if necessary. For
certain airplanes this proposed AD would require a detailed inspection
for corrosion, damage, and wear of each wing-to-fuselage strut
attachment joint bolt and associated hardware, and replacing if
necessary; and a borescope inspection for corrosion and damage of the
bore hole and barrel nut threads, and repairing or replacing if
necessary. We are proposing this AD to detect and correct fractured
bolts, which could result in reduced structural integrity of the wing-
to-fuselage strut attachment joint and subsequent loss of the wing.
DATES: We must receive comments on this proposed AD by January 21,
2014.
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 W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; email
[[Page 73463]]
[email protected]; Internet http://www.bombardier.com.
You may view this referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket 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: Jeffrey Zimmer, 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) 228-7306; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-1024;
Directorate Identifier 2013-NM-140-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on 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 proposed AD.
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2013-17R1, dated June 27, 2013 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for the specified products. The MCAI states:
There have been two in-service reports of a wing-to-fuselage
strut attachment joint bolt found fractured during routine
maintenance. Laboratory examination of one fractured bolt revealed
that the fracture was attributed to stress corrosion cracking.
Failure of the bolts could compromise the structural integrity
of the wing-to-fuselage strut attachment joint and could lead to a
subsequent loss of the wing.
This [Canadian] AD mandates the inspection and rectification, as
required, of the wing-to-fuselage strut attachment joint bolts and
associated hardware.
* * * * *
Required actions include doing a torque check of wing-to-fuselage strut
attachment joint bolts, and repairing or replacing if necessary. For
certain airplanes, required actions include a detailed inspection for
corrosion, damage (including but not limited to scratching, cracking,
pitting, cross threads, etc.), and wear of each wing-to-fuselage strut
attachment joint bolt and associated hardware, and replacement if
necessary; and a borescope inspection for corrosion and damage of the
bore hole and barrel nut threads, and repair or replacement if
necessary. You may examine the MCAI in the AD docket on the Internet at
http://www.regulations.gov by searching for and locating it in Docket
No. FAA-2013-1024.
Relevant Service Information
Bombardier has issued Service Bulletin 8-57-47, Revision A, dated
May 29, 2013. 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 Proposed 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 proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This Proposed AD and the MCAI or Service
Information
In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the AD a requirement
to accomplish the action using a method approved by either the FAA or
the State of Design Authority (or its delegated agent).
We have recently been notified that certain laws in other countries
do not allow such delegation of authority, but some countries do
recognize design approval organizations. In addition, we have become
aware that some U.S. operators have used repair instructions that were
previously approved by a State of Design Authority or a Design Approval
Holder (DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or the DAH repair
approval statements that were not specifically developed to address the
unsafe condition corrected by the AD. Using repair instructions that
were not specifically approved for a particular AD creates the
potential for doing repairs that were not developed to address the
unsafe condition identified by the MCAI AD, the FAA AD, or the
applicable service information, which could result in the unsafe
condition not being fully corrected.
To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, this proposed AD would require that
the repair approval specifically refer to the FAA AD. This change is
intended to clarify the method of compliance and to provide operators
with better visibility of repairs that are specifically developed and
approved to correct the unsafe condition. In addition, we use the
phrase ``its delegated agent, or by the DAH with State of Design
Authority design organization approval, as applicable'' in this
proposed AD to refer to a DAH authorized to approve required repairs
for this proposed AD.
Costs of Compliance
We estimate that this proposed AD affects 94 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD.
We also estimate that it would take about 107 work-hours per
product to comply with the basic requirements of this proposed AD. The
average labor rate is $85 per work-hour. Required parts would cost
about $5,476 per product. Based on these figures, we estimate the cost
of this proposed AD on U.S. operators to be $1,369,674, or $14,571 per
product.
We have received no definitive data that would enable us to provide
a cost estimate for the repairs or replacements specified in this
proposed AD.
[[Page 73464]]
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 proposed 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 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 this 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);
3. Will not affect intrastate aviation in Alaska; and
4. 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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
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:
Bombardier, Inc.: Docket No. FAA-2013-1024; Directorate Identifier
2013-NM-140-AD.
(a) Comments Due Date
We must receive comments by January 21, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model DHC-8-102, -103, -106,
-201, -202, -301, -311, and -315 airplanes; certificated in any
category; serial numbers 003 through 672 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of a fractured wing-to-fuselage
strut attachment joint bolt. We are issuing this AD to detect and
correct fractured bolts, which could result in reduced structural
integrity of the wing-to-fuselage strut attachment joint and
subsequent loss of the wing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Torque Check
At the applicable time specified in paragraph (g)(1) or (g)(2)
of this AD: Do a torque check of the wing-to-fuselage strut
attachment joint bolts, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 8-57-47, Revision A,
dated May 29, 2013.
(1) For airplanes that have accumulated fewer than 40,000 total
flight cycles, and have less than 15 years in service since new, as
of the effective date of this AD: Do the torque check before the
accumulation of 42,000 total flight cycles, or within 16 years in
service since new, whichever occurs first.
(2) For airplanes that have accumulated 40,000 total flight
cycles or more, or have 15 years or more in service since new, as of
the effective date of this AD: Do the torque check within 2,000
flight cycles or 12 months after the effective date of this AD,
whichever occurs first.
(h) Inspection and Corrective Actions
(1) If only one bolt fails the torque check, before further
flight, replace the bolt, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 8-57-47, Revision A,
dated May 29, 2013; and before further flight do the actions
specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.
(2) If more than one bolt fails the torque check, before further
flight, repair, using a method approved by the Manager, New York
Aircraft Certification Office (ACO), FAA; or Transport Canada Civil
Aviation (TCCA) (or its delegated agent or by the Design Approval
Holder with the TCCA design organization approval). For a repair
method to be approved, the repair approval must specifically refer
to this AD.
(3) If all bolts pass the torque check, before further flight,
do the actions specified in paragraphs (h)(3)(i) and (h)(3)(ii) of
this AD, as applicable.
(i) Do a detailed inspection for corrosion, damage (including
but not limited to scratching, cracking, pitting, and cross threads,
etc.), and wear, of each wing-to-fuselage strut attachment joint
bolt and associated hardware, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 8-57-47, Revision A,
dated May 29, 2013. If any bolt or hardware has corrosion, damage,
or wear, before further flight, replace the affected part, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-57-47, Revision A, dated May 29, 2013.
(ii) Do a borescope inspection for corrosion and damage
(including but not limited to scratching, cracking, pitting, and
cross threads, etc.) of the bore hole and barrel nut threads, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-57-47, Revision A, dated May 29, 2013, except as
provided by paragraph (i) of this AD.
(A) If any corrosion or damage is found in the barrel nut
threads, before further flight, replace the barrel nut, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-57-47, Revision A, dated May 29, 2013, except as
provided by paragraph (i) of this AD.
(B) If any corrosion or damage is found in the bore of the hole,
before further flight, repair, using a method approved by the
Manager, New York ACO, FAA; or Transport Canada Civil Aviation
(TCCA) (or its delegated agent or by the Design Approval Holder with
the TCCA design organization approval). For a repair method to be
approved, the repair approval must specifically refer to this AD.
(i) Exception to Service Information
Where Bombardier Service Bulletin 8-57-47, Revision A, dated May
29, 2013, specifies to contact the manufacturer for repair
information, this AD requires repairing before further flight using
a method approved by the Manager, New York ACO, FAA; or TCCA (or its
delegated agent, or by the Design Approval Holder with TCCA design
organization approval). For a repair method to be approved, the
repair approval must specifically refer to this AD.
(j) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Bombardier Service
Bulletin 8-57-47, dated March 16, 2012.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York ACO, ANE-170, FAA, has the authority to approve
[[Page 73465]]
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the ACO, send it to
ATTN: Program Manager, Continuing Operational Safety, FAA, New York
ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone
516-228-7300; fax 516-794-5531. Before using any approved AMOC,
notify your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding 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, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or by the Design Approval Holder with a State of
Design Authority's design organization approval). For a repair
method to be approved, the repair approval must specifically refer
to this AD. You are required to ensure the product is airworthy
before it is returned to service.
(l) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2013-17R1, dated June 27,
2013, for related information, which can be found in the AD docket
on the Internet at http://www.regulations.gov by searching for and
locating it in Docket No. FAA-2013-1024.
(2) For service information identified in this AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000;
fax 416-375-4539; email [email protected]; Internet
http://www.bombardier.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on November 29, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-29134 Filed 12-5-13; 8:45 am]
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