Airworthiness Directives; Bombardier, Inc. Airplanes, 43607-43611 [2014-17316]
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Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations
(i) Modification Prior to CFRP Door
Installation
At the applicable time specified in
paragraph (i)(1) or (i)(2) of this AD: Modify
the CFRP MLG outboard doors and
attachment to the MLG, in accordance with
Part 2 of the Accomplishment Instructions of
Fokker Service Bulletin SBF100–52–090,
dated November 17, 2011, including Fokker
Manual Change Notification F100–147, dated
October 28, 2011, as revised by Fokker
Service Bulletin Change Notification
SBF100–52–090/01, dated January 24, 2012.
Accomplishing the modification in this
paragraph terminates the inspection required
by paragraph (g) of this AD.
(1) For airplanes on which a CFRP MLG
outboard door is installed as of the effective
date of this AD: Do the modification within
24 months after the effective date of this AD.
(2) For airplanes on which an aluminum
door is installed as of the effective date of
this AD: Do the modification prior to the
installation of the CFRP MLG outboard door.
Note 1 to paragraph (i) of this AD: The
aluminum MLG outboard doors and the
CFRP MLG outboard doors are two-way
interchangeable.
(j) Parts Installation Prohibition
As of the effective date of this AD, do not
install on any airplane an MLG outboard
door having part number (P/N) D13310–401
through –418, or any MLG outboard door
assembly having P/N D13312–401 through
–410.
Note 2 to paragraph (j) of this AD: Civil
Aviation Authority-Netherlands (CAA–NL)
AD NL–2006–001, dated January 5, 2006
(European Aviation Safety Agency (EASA)
approval 2006–002), contains guidance for
modifying spare MLG outboard door
assemblies having P/N D13312–401 through
–410, to P/N D13312–7XX standard, as
specified in the Accomplishment
Instructions of Fokker Component Service
Bulletin D13312–52–09, December 12, 2005,
which is not incorporated by reference in this
AD.
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(k) Parts Installation Limitation
As of the effective date of this AD, do not
install on any airplane a P/N D13310–701
through –708 MLG outboard door, or a P/N
D13312–702 through –711 MLG outboard
door assembly, unless the part has been
inspected for cracks in the recessed bolt
heads, all applicable corrective actions have
been done, and the CFRP MLG outboard door
has been modified, in accordance with the
Accomplishment Instructions of Fokker
Component Service Bulletin D13312–52–015,
dated November 17, 2011.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve 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
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Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Fokker Services B.V.’s EASA
Design Organization Approval (DOA). If
approved by the DOA, the approval must
include the DOA-authorized signature.
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information EASA
Airworthiness Directive 2012–0023, dated
February 6, 2012, for related information.
This MCAI may be found in the AD docket
on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-0007-0002.
(2) Service information identified in this
AD that is not incorporated by reference may
be viewed at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
RIN 2120–AA64
(n) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Fokker Component Service Bulletin
D13312–52–015, dated November 17, 2011.
(ii) Fokker Service Bulletin SBF100–52–
090, dated November 17, 2011, including
Fokker Manual Change Notification F100–
147, dated October 28, 2011.
(iii) Fokker Service Bulletin Change
Notification SBF100–52–090/01, dated
January 24, 2012. The page number shown on
the first page of this document should read
‘‘Page 1 of 2.’’
(3) For service information identified in
this AD, contact Fokker Services B.V.,
Technical Services Dept., P.O. Box 1357,
2130 EL Hoofddorp, the Netherlands;
telephone +31 (0)88–6280–350; fax +31
(0)88–6280–111; email technicalservices@
fokker.com; Internet https://
www.myfokkerfleet.com.
(4) You may view this 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.
(5) You may view this service information
that is incorporated by reference at the
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Issued in Renton, Washington, on June 25,
2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–17297 Filed 7–25–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–1024; Directorate
Identifier 2013–NM–140–AD; Amendment
39–17909; AD 2014–15–07]
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–102,
–103, –106, –201, –202, –301, –311, and
–315 airplanes. This AD was prompted
by reports of a fractured wing-tofuselage strut attachment joint bolt. This
AD requires a torque check of all wingto-fuselage strut attachment joint bolts,
and repair or replacement if necessary.
For certain airplanes, this AD also
requires a detailed inspection for
corrosion, damage, 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. We are issuing this AD to
detect and correct fractured strut
attachment joint bolts, which could
result in reduced structural integrity of
the wing-to-fuselage strut attachment
joint and subsequent loss of the wing.
DATES: This AD becomes effective
September 2, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 2, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2013-1024SUMMARY:
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Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations
0002 or in person at the Docket
Management Facility, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC.
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
thd.qseries@aero.bombardier.com;
Internet https://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.
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, NY
11590; telephone (516) 228–7306; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Bombardier, Inc. Model
DHC–8–102, –103, –106, –201, –202,
–301, –311, and –315 airplanes. The
NPRM published in the Federal
Register on December 6, 2013 (78 FR
73462).
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 certain Bombardier, Inc. Model
DHC–8–102, –103, –106, –201, –202,
–301, –311, and –315 airplanes. 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 a torque check
of wing-to-fuselage strut attachment
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joint bolts, and repair or replacement if
necessary. For certain airplanes,
required actions include a detailed
inspection for corrosion, damage
(including but not limited to scratching,
cracking, pitting, cross threads), 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 https://www.regulations.gov/
#!documentDetail;D=FAA-2013-10240002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (78 FR 73462,
December 6, 2013) and the FAA’s
response to each comment.
Request To Extend Compliance Time
An anonymous commenter requested
that we extend the compliance times
from 2,000 flight cycles or 12 months,
to 4,000 flight cycles or 24 months, after
the effective date of the AD, in order to
coincide with their scheduled ‘‘C’’
checks.
We do not agree with the commenter’s
request to extend the compliance time.
We have determined that the
compliance time, as proposed,
represents the maximum interval of
time allowable for the affected airplanes
to continue to safely operate before the
modification is done. We have not
changed this AD in this regard.
Request To Give Credit for Previous
Compliance
An anonymous commenter requested
that we allow credit for actions
accomplished using deHavilland Dash 8
Series 100 Task Card Number 5730/04B,
dated February 6, 2012, if the actions
were done before the date the final rule
becomes effective.
We agree with the request. We have
redesignated paragraph (j) of the
proposed AD (78 FR 73462, December 6,
2013) as paragraph (j)(1) of this AD, and
have added new paragraph (j)(2) to this
AD to allow credit for actions
accomplished prior to the effective date
of this AD using deHavilland Dash 8
Series 100 Task Card Number 5730/04B,
dated February 6, 2012.
‘‘Contacting the Manufacturer’’
Paragraph in This AD
Since late 2006, we have included a
standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
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FAA develops an AD based on a foreign
authority’s AD.
The MCAI or referenced service
information in an FAA AD often directs
the owner/operator to contact the
manufacturer for corrective actions,
such as a repair. Briefly, the Airworthy
Product paragraph allowed owners/
operators to use corrective actions
provided by the manufacturer if those
actions were FAA-approved. In
addition, the paragraph stated that any
actions approved by the State of Design
Authority (or its delegated agent) are
considered to be FAA-approved.
In the NPRM (78 FR 73462, December
6, 2013), we proposed to prevent the use
of repairs that were not specifically
developed to correct the unsafe
condition, by requiring that the repair
approval provided by the State of
Design Authority or its delegated agent
specifically refer to this FAA AD. This
change was 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, proposed to
change the phrase ‘‘its delegated agent’’
to include a design approval holder
(DAH) with State of Design Authority
design organization approval (DOA), as
applicable, to refer to a DAH authorized
to approve required repairs for the
NPRM.
No comments were provided to the
NPRM (78 FR 73462, December 6, 2013)
about these proposed changes. However,
a comment was provided for an NPRM
having Directorate Identifier 2012–NM–
101–AD (78 FR 78285, December 26,
2013). The commenter stated the
following: ‘‘The proposed wording,
being specific to repairs, eliminates the
interpretation that Airbus messages are
acceptable for approving minor
deviations (corrective actions) needed
during accomplishment of an AD
mandated Airbus service bulletin.’’
This comment has made the FAA
aware that some operators have
misunderstood or misinterpreted the
Airworthy Product paragraph to allow
the owner/operator to use messages
provided by the manufacturer as
approval of deviations during the
accomplishment of an AD-mandated
action. The Airworthy Product
paragraph does not approve messages or
other information provided by the
manufacturer for deviations to the
requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
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However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
for an alternative method of compliance
to the AD-required actions using the
procedures found in 14 CFR 39.19.
To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed the
paragraph and retitled it ‘‘Contacting the
Manufacturer.’’ This paragraph now
clarifies that for any requirement in this
AD to obtain corrective actions from a
manufacturer, the action must be
accomplished using a method approved
by the FAA, TCCA, or Bombardier’s
TCCA Design Approval Organization
(DAO).
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DAO, the approval must include
the DAO-authorized signature. The DAO
signature indicates that the data and
information contained in the document
are TCCA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DAO-authorized signature approval are
not TCCA-approved, unless TCCA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility previously afforded by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
recommendation of the Airworthiness
Directive Implementation Aviation
Rulemaking Committee to increase
flexibility in complying with ADs by
identifying those actions in
manufacturers’ service instructions that
are ‘‘Required for Compliance’’ with
ADs. We continue to work with
manufacturers to implement this
recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an alternative method of
compliance.
Other commenters to the NPRM
having Directorate Identifier 2012–NM–
101–AD (78 FR 78285, December 26,
2013) pointed out that in many cases the
foreign manufacturer’s service bulletin
and the foreign authority’s MCAI might
have been issued some time before the
FAA AD. Therefore, the DOA might
have provided U.S. operators with an
approved repair, developed with full
awareness of the unsafe condition,
before the FAA AD is issued. Under
these circumstances, to comply with the
FAA AD, the operator would be
required to go back to the
manufacturer’s DOA and obtain a new
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approval document, adding time and
expense to the compliance process with
no safety benefit.
Based on these comments, we
removed the requirement that the DAHprovided repair specifically refer to this
AD. Before adopting such a
requirement, the FAA will coordinate
with affected DAHs and verify they are
prepared to implement means to ensure
that their repair approvals consider the
unsafe condition addressed in this AD.
Any such requirements will be adopted
through the normal AD rulemaking
process, including notice-and-comment
procedures, when appropriate. We also
have decided not to include a generic
reference to either the ‘‘delegated agent’’
or ‘‘DAH with State of Design Authority
design organization approval,’’ but
instead we have provided the specific
delegation approval granted by the State
of Design Authority for the DAH
throughout this AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
73462, December 6, 2013) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 73462,
December 6, 2013).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 94
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD.
We also estimate that it would take
about 107 work-hours per product to
comply with the basic requirements of
this 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 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 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,
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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 that 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);
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-1024; 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
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2014–15–07 Bombardier, Inc.: Amendment
39–17909. Docket No. FAA–2013–1024;
Directorate Identifier 2013–NM–140–AD.
(a) Effective Date
This AD becomes effective September 2,
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 strut attachment joint
bolts, which could result in reduced
structural integrity of the wing-to-fuselage
strut attachment joint and subsequent loss of
the wing.
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(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
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the effective date of this AD, whichever
occurs first.
(h) Inspection and Corrective Actions
(1) If only one bolt fails the torque check
required by paragraph (g) of this AD, 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 required by paragraph (g) of this AD,
before further flight, repair using a method
approved by the Manager, New York ACO,
ANE–170, Engine and Propeller Directorate,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(3) If all bolts pass the torque check
required by paragraph (g) of this AD, 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-tofuselage 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, ANE–170, Engine
and Propeller Directorate, FAA; or TCCA; or
Bombardier, Inc.’s TCCA DAO. If approved
by the DAO, the approval must include the
DAO-authorized signature.
(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, ANE–170,
Engine and Propeller Directorate, FAA; or
TCCA; or Bombardier, Inc.’s TCCA DAO;
and, if approved by the DAO, the approval
must include the DAO-authorized signature.
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
(j) Credit for Previous Actions
(1) 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, which is not incorporated by
reference in this AD.
(2) 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 de
Havilland Inc. Dash 8 Series 100
Maintenance Task Card Number 5730/04B,
dated February 6, 2012, which is not
incorporated by reference in this AD.
(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
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) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
Engine and Propeller Directorate, FAA; or
TCCA; or Bombardier, Inc.’s TCCA DAO. If
approved by the DAO, the approval must
include the DAO-authorized signature.
(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.
This MCAI may be found in the AD docket
on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2013-1024-0002.
(2) Service information identified in this
AD that is not incorporated by reference may
be viewed at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
E:\FR\FM\28JYR1.SGM
28JYR1
Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 8–57–47,
Revision A, dated May 29, 2013.
(ii) Reserved.
(3) 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 thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com.
(4) You may view this 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.
(5) You may view this 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 15,
2014.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–17316 Filed 7–25–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0253; Directorate
Identifier 2013–NM–257–AD; Amendment
39–17908; AD 2014–15–06]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 747–100B
SUD, 747–200B, 747–300, 747–400, and
747–400D series airplanes. This AD was
prompted by an evaluation by the
design approval holder (DAH)
indicating that the upper deck tension
ties are subject to widespread fatigue
damage (WFD). This AD requires
repetitive inspections for cracking in the
pmangrum on DSK3VPTVN1PROD with RULES
SUMMARY:
upper deck tension ties, and related
investigative and corrective actions if
necessary; tension tie replacement; and
post-replacement repetitive inspections
for cracking in the upper deck tension
ties, and related investigative and
corrective actions if necessary. We are
issuing this AD to detect and correct
fatigue cracking of the upper deck
tension ties. Severed or disconnected
tension ties at multiple locations could
result in rapid decompression and loss
of structural integrity of the airplane.
DATES: This AD is effective September 2,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 2, 2014.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0253; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6428; fax:
425–917–6590; email:
nathan.p.weigand@faa.gov.
43611
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 747–100B SUD, 747–200B, 747–
300, 747–400, 747–400D series
airplanes. The NPRM published in the
Federal Register on April 23, 2014 (79
FR 22596). The NPRM was prompted by
an evaluation by the DAH indicating
that the upper deck tension ties are
subject to WFD. The NPRM proposed to
require repetitive inspections for
cracking in the upper deck tension ties,
and related investigative and corrective
actions if necessary; tension tie
replacement; and post-replacement
repetitive inspections for cracking in the
upper deck tension ties, and related
investigative and corrective actions if
necessary. We are issuing this AD to
detect and correct fatigue cracking of the
upper deck tension ties. Severed or
disconnected tension ties at multiple
locations could result in rapid
decompression and loss of structural
integrity of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
The Boeing Company supported the
NPRM (79 FR 22596, April 23, 2014).
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
22596, April 23, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 22596,
April 23, 2014).
Costs of Compliance
We estimate that this AD affects 76
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Inspections (pre-modification
and post-modification).
VerDate Mar<15>2010
14:46 Jul 25, 2014
Labor cost
Parts cost
Up to 164 work-hours × $85
per hour = $13,940 per inspection cycle.
Jkt 232001
PO 00000
Frm 00019
Cost per product
$0
Fmt 4700
Sfmt 4700
Cost on U.S. operators
Up to $13,940 per inspection
cycle.
Up to $1,059,440 per inspection cycle.
E:\FR\FM\28JYR1.SGM
28JYR1
]]>Agencies
[Federal Register Volume 79, Number 144 (Monday, July 28, 2014)]
[Rules and Regulations]
[Pages 43607-43611]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-17316]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-1024; Directorate Identifier 2013-NM-140-AD;
Amendment 39-17909; AD 2014-15-07]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311,
and -315 airplanes. This AD was prompted by reports of a fractured
wing-to-fuselage strut attachment joint bolt. This AD requires a torque
check of all wing-to-fuselage strut attachment joint bolts, and repair
or replacement if necessary. For certain airplanes, this AD also
requires a detailed inspection for corrosion, damage, 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. We are issuing this AD to detect and correct
fractured strut attachment joint bolts, which could result in reduced
structural integrity of the wing-to-fuselage strut attachment joint and
subsequent loss of the wing.
DATES: This AD becomes effective September 2, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September 2,
2014.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-1024-
[[Page 43608]]
0002 or in person at the Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
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 thd.qseries@aero.bombardier.com; Internet https://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.
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, NY
11590; telephone (516) 228-7306; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Bombardier, Inc.
Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315
airplanes. The NPRM published in the Federal Register on December 6,
2013 (78 FR 73462).
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 certain Bombardier, Inc. Model DHC-8-102, -103, -
106, -201, -202, -301, -311, and -315 airplanes. 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 a torque check of wing-to-fuselage strut
attachment joint bolts, and repair or replacement if necessary. For
certain airplanes, required actions include a detailed inspection for
corrosion, damage (including but not limited to scratching, cracking,
pitting, cross threads), 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
https://www.regulations.gov/#!documentDetail;D=FAA-2013-1024-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (78
FR 73462, December 6, 2013) and the FAA's response to each comment.
Request To Extend Compliance Time
An anonymous commenter requested that we extend the compliance
times from 2,000 flight cycles or 12 months, to 4,000 flight cycles or
24 months, after the effective date of the AD, in order to coincide
with their scheduled ``C'' checks.
We do not agree with the commenter's request to extend the
compliance time. We have determined that the compliance time, as
proposed, represents the maximum interval of time allowable for the
affected airplanes to continue to safely operate before the
modification is done. We have not changed this AD in this regard.
Request To Give Credit for Previous Compliance
An anonymous commenter requested that we allow credit for actions
accomplished using deHavilland Dash 8 Series 100 Task Card Number 5730/
04B, dated February 6, 2012, if the actions were done before the date
the final rule becomes effective.
We agree with the request. We have redesignated paragraph (j) of
the proposed AD (78 FR 73462, December 6, 2013) as paragraph (j)(1) of
this AD, and have added new paragraph (j)(2) to this AD to allow credit
for actions accomplished prior to the effective date of this AD using
deHavilland Dash 8 Series 100 Task Card Number 5730/04B, dated February
6, 2012.
``Contacting the Manufacturer'' Paragraph in This AD
Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
The MCAI or referenced service information in an FAA AD often
directs the owner/operator to contact the manufacturer for corrective
actions, such as a repair. Briefly, the Airworthy Product paragraph
allowed owners/operators to use corrective actions provided by the
manufacturer if those actions were FAA-approved. In addition, the
paragraph stated that any actions approved by the State of Design
Authority (or its delegated agent) are considered to be FAA-approved.
In the NPRM (78 FR 73462, December 6, 2013), we proposed to prevent
the use of repairs that were not specifically developed to correct the
unsafe condition, by requiring that the repair approval provided by the
State of Design Authority or its delegated agent specifically refer to
this FAA AD. This change was 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, proposed to change the phrase ``its delegated
agent'' to include a design approval holder (DAH) with State of Design
Authority design organization approval (DOA), as applicable, to refer
to a DAH authorized to approve required repairs for the NPRM.
No comments were provided to the NPRM (78 FR 73462, December 6,
2013) about these proposed changes. However, a comment was provided for
an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR 78285,
December 26, 2013). The commenter stated the following: ``The proposed
wording, being specific to repairs, eliminates the interpretation that
Airbus messages are acceptable for approving minor deviations
(corrective actions) needed during accomplishment of an AD mandated
Airbus service bulletin.''
This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements.
[[Page 43609]]
However, deviations to AD-required actions are addressed in 14 CFR
39.17, and anyone may request the approval for an alternative method of
compliance to the AD-required actions using the procedures found in 14
CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this AD to obtain corrective actions from a
manufacturer, the action must be accomplished using a method approved
by the FAA, TCCA, or Bombardier's TCCA Design Approval Organization
(DAO).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DAO, the approval must include the DAO-authorized
signature. The DAO signature indicates that the data and information
contained in the document are TCCA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DAO-authorized signature approval are not TCCA-
approved, unless TCCA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that in many cases
the foreign manufacturer's service bulletin and the foreign authority's
MCAI might have been issued some time before the FAA AD. Therefore, the
DOA might have provided U.S. operators with an approved repair,
developed with full awareness of the unsafe condition, before the FAA
AD is issued. Under these circumstances, to comply with the FAA AD, the
operator would be required to go back to the manufacturer's DOA and
obtain a new approval document, adding time and expense to the
compliance process with no safety benefit.
Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this AD. Before adopting such a
requirement, the FAA will coordinate with affected DAHs and verify they
are prepared to implement means to ensure that their repair approvals
consider the unsafe condition addressed in this AD. Any such
requirements will be adopted through the normal AD rulemaking process,
including notice-and-comment procedures, when appropriate. We also have
decided not to include a generic reference to either the ``delegated
agent'' or ``DAH with State of Design Authority design organization
approval,'' but instead we have provided the specific delegation
approval granted by the State of Design Authority for the DAH
throughout this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 73462, December 6, 2013) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 73462, December 6, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 94 airplanes of U.S. registry. We
estimate the following costs to comply with this AD.
We also estimate that it would take about 107 work-hours per
product to comply with the basic requirements of this 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 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 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 that 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);
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-1024; 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 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 43610]]
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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 airworthiness
directive (AD):
2014-15-07 Bombardier, Inc.: Amendment 39-17909. Docket No. FAA-
2013-1024; Directorate Identifier 2013-NM-140-AD.
(a) Effective Date
This AD becomes effective September 2, 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 strut attachment joint 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 required by
paragraph (g) of this AD, 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 required by
paragraph (g) of this AD, before further flight, repair using a
method approved by the Manager, New York ACO, ANE-170, Engine and
Propeller Directorate, FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization
(DAO). If approved by the DAO, the approval must include the DAO-
authorized signature.
(3) If all bolts pass the torque check required by paragraph (g)
of this AD, 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, ANE-170, Engine and Propeller Directorate,
FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by the
DAO, the approval must include the DAO-authorized signature.
(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, ANE-170, Engine and
Propeller Directorate, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO;
and, if approved by the DAO, the approval must include the DAO-
authorized signature.
(j) Credit for Previous Actions
(1) 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, which is not incorporated by
reference in this AD.
(2) 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 de Havilland Inc. Dash 8
Series 100 Maintenance Task Card Number 5730/04B, dated February 6,
2012, which is not incorporated by reference in this AD.
(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 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) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, New York ACO,
ANE-170, Engine and Propeller Directorate, FAA; or TCCA; or
Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
(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. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-1024-0002.
(2) Service information identified in this AD that is not
incorporated by reference may be viewed at the addresses specified
in paragraphs (n)(3) and (n)(4) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
[[Page 43611]]
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 8-57-47, Revision A, dated May
29, 2013.
(ii) Reserved.
(3) 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 thd.qseries@aero.bombardier.com; Internet
https://www.bombardier.com.
(4) You may view this 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.
(5) You may view this 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on July 15, 2014.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-17316 Filed 7-25-14; 8:45 am]
BILLING CODE 4910-13-P
