Airworthiness Directives; Bombardier, Inc. Airplanes, 65176-65178 [2013-25305]
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65176
Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Luke Walker, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7363; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1311; Directorate
Identifier 2011–NM–204–AD; Amendment
39–17636; AD 2013–22–04]
RIN 2120–AA64
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, and –106 airplanes; and Model
DHC–8–200, –300, and –400 series
airplanes. This AD was prompted by
reports of excessive wear found in the
clevis (bolt) hole where the rod
assembly attaches to the rudder/brake
pedal bellcrank, due to prolonged
fretting. This AD requires measuring the
bellcrank clevis holes, inspecting for
cracking of the bellcrank, and reworking the clevis holes with steel
bushings, or replacing the bellcrank. We
are issuing this AD to detect and correct
a worn or cracked clevis hole, which
could cause failure of the bellcrank on
one side, with subsequent asymmetric
braking and consequent runway
excursion.
SUMMARY:
This AD becomes effective
December 5, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 5, 2013.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2012-1311; or in
person at the 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., QSeries 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.
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DATES:
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FOR FURTHER INFORMATION CONTACT:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to the specified products. The
NPRM was published in the Federal
Register on December 26, 2012 (77 FR
75906). The NPRM proposed to correct
an unsafe condition for the specified
products. Transport Canada Civil
Aviation (TCCA), which is the aviation
authority for Canada, issued Canadian
Airworthiness Directive CF–2011–32,
dated August 15, 2011 (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 several in-service reports
of excessive wear found in the bolt [clevis]
hole where the rod assembly, Part Numbers
(P/N) 82710795–001 or 82710024–003, is
attached to the rudder/brake pedal bellcrank.
An investigation revealed that the wear was
attributed to prolonged fretting.
Failure of the bellcrank on one side could
lead to asymmetric braking and may lead to
runway excursion.
This [Canadian] directive mandates
[measuring clevis holes for length, and, for
certain bellcranks, doing a liquid penetrant
inspection for cracking, and] the re-work [by
installing steel bushings] or replacement of
each bellcrank, P/N 82710022–001/–002,
82710029–001/–002, 82710813–001/–002
and 82710814–001/–002, found with a worn
[or cracked] bolt hole.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2012-13110002.
Revised Service Information
Bombardier, Inc. has issued Service
Bulletin 84–27–55, Revision A, dated
February 22, 2012. The NPRM (77 FR
75906, December 26, 2012) referred to
Bombardier Service Bulletin 84–27–55,
dated June 15, 2011, in paragraphs (h)
and (i) of the NPRM. In this final rule,
we have revised the service bulletin
references in those paragraphs
accordingly, and have added new
paragraph (j) to this final rule to give
credit for actions done before the
effective date of this AD in accordance
with Bombardier Service Bulletin 84–
27–55, dated June 15, 2011 (and
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redesignated subsequent paragraphs
accordingly).
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comments received.
Request To Allow Use of Serviceable
Parts
An anonymous commenter requested
that the references to ‘‘new bellcrank’’
in the NPRM (77 FR 75906, December
26, 2012) be changed to allow operators
to install ‘‘serviceable’’ bellcranks (new
bellcranks or ones that have been
modified according to the applicable
service information), thus giving equal
safety, yet providing more flexibility
and less recordkeeping for operators.
We agree with the commenter’s
request for the reasons given. We have
revised paragraphs (g)(2), (h)(2), (h)(3),
(h)(4), (i)(2), (i)(3), and (i)(4) of this AD
by specifying to replace the bellcrank
with a new bellcrank ‘‘or with a
serviceable bellcrank with bushings
having part number 82710297–101
installed.’’ We have also clarified
paragraphs (h)(1) and (i)(1) of this final
rule by specifying to replace the
bellcrank ‘‘with a new or with a
serviceable bellcrank with bushings
having part number 82710297–101
installed.’’
Request To Add Eddy Current
Inspection Option
The same anonymous commenter
requested that we include an eddy
current inspection option in this final
rule to agree with parallel actions
specified in Bombardier Service
Bulletin 84–27–55, Revision A, dated
February 22, 2012.
We agree with the commenter’s
request because Bombardier added that
inspection option in Bombardier Service
Bulletin 84–27–55, Revision A, dated
February 22, 2012. Accordingly, we
have added the option in paragraphs (h)
and (i) of this final rule.
Request To Clarify Compliance Times
The same anonymous commenter, in
an incomplete request, stated that the
replacement times in paragraph (h) of
the NPRM (77 FR 75906, December 26,
2012) do not sufficiently remove the
identified unsafe condition. From the
truncated statement, we cannot infer
what part of paragraph (h) the
commenter requested that we change.
We have made no change to this final
rule in this regard.
Conclusion
We reviewed the available data,
including the comments received, and
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Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations
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 changes:
• Are consistent with the intent that
was proposed in the NPRM (77 FR
75906, December 26, 2012) for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (77 FR 75906,
December 26, 2012).
wreier-aviles on DSK5TPTVN1PROD with RULES
Costs of Compliance
We estimate that this AD will affect
178 products of U.S. registry. We also
estimate that it will take 5 work-hours
per product to comply with the basic
requirements of this AD. The average
labor rate is $85 per work-hour. Based
on these figures, we estimate the cost of
this AD to the U.S. operators to be
$75,650, or $425 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 16 work-hours and require parts
costing up to $2,532, for a cost of $3,892
per product. Where the service
information lists required parts costs
that are covered under warranty, we
have assumed that there will be no
charge for these parts. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. We have no
way of determining the number of
products that may need these actions.
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
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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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2012-13110002; 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 MCAI, 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.
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 AD:
■
2013–22–04 Bombardier, Inc.: Amendment
39–17636. Docket No. FAA–2012–1311;
Directorate Identifier 2011–NM–204–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective December 5, 2013.
(b) Affected ADs
None.
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65177
(c) Applicability
This AD applies to Bombardier, Inc.
airplanes, certificated in any category, as
specified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) Model DHC–8–102, –103, –106, –201,
–202, –301, –311, and –315 airplanes: Serial
numbers 003 through 672 inclusive.
(2) Model DHC–8–400, –401, and –402
airplanes: Serial numbers 4003 through 4372
inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 27: Flight controls.
(e) Reason
This AD was prompted by reports of
excessive wear found in the clevis (bolt) hole
where the rod assembly attaches to the
rudder/brake pedal bellcrank, due to
prolonged fretting. We are issuing this AD to
detect and correct a worn or cracked clevis
hole, which could cause failure of the
bellcrank on one side, with subsequent
asymmetric braking and consequent runway
excursion.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Actions for Model DHC–8–100, –200, and
–300 Series Airplanes
For Model DHC–8–102, –103, –106, –201,
–202, –301, –311, and –315 airplanes: Within
6,000 flight hours or 24 months after the
effective date of this AD, whichever occurs
first, inspect each bellcrank for cracking
using liquid penetrant, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 8–27–111, dated
June 15, 2011.
(1) If no cracking is found: Before further
flight, rework the bellcrank, in accordance
with the Accomplishment Instructions of
Bombardier Service Bulletin 8–27–111, dated
June 15, 2011.
(2) If any clevis hole is greater than 0.218
inch (measured edge-to-edge), or if any
cracking is found: Before further flight,
replace the bellcrank with a new bellcrank,
or with a serviceable bellcrank with bushings
having part number 82710297–101 installed,
in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–27–111, dated June 15, 2011.
(h) Actions for Certain Model DHC–8–400
Series Airplanes
For Model DHC–8–400, –401, and –402
airplanes that have accumulated less than or
equal to 15,000 total flight hours as of the
effective date of this AD: Within 6,000 flight
hours after the effective date of this AD, but
not to exceed 15,600 total flight hours,
measure the edge-to-edge length of the clevis
holes of each bellcrank, and inspect each
bellcrank for cracking using liquid penetrant
or eddy current inspection method; in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–55, Revision A, dated February 22,
2012.
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(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than
or equal to 0.218 inch: Within 6,000 flight
hours after the effective date of this AD, but
not to exceed 15,600 total flight hours,
rework the bellcrank, or replace the bellcrank
with a new bellcrank or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(2) If no cracking is found, and any clevis
hole edge-to-edge length is greater than 0.218
inch, but is less than or equal to 0.248 inch:
Within 6,000 flight hours after the effective
date of this AD, replace the bellcrank with a
new bellcrank, or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(3) If no cracking is found, and any clevis
hole edge-to-edge length is greater than 0.248
inch, but is less than or equal to 0.278 inch:
Within 1,200 flight hours after doing the
measurement/inspection required by
paragraph (h) of this AD, replace the
bellcrank with a new bellcrank, or with a
serviceable bellcrank with bushings having
part number 82710297–101 installed, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–55, Revision A, dated February 22,
2012.
(4) If any cracking is found, or if any clevis
hole edge-to-edge length exceeds 0.278 inch:
Before further flight, replace the bellcrank
with a new bellcrank, or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(i) Actions for Certain Other Model DHC–8–
400 Series Airplanes
For Model DHC–8–400, –401, and –402
airplanes that have accumulated more than
15,000 total flight hours as of the effective
date of this AD: Within 600 flight hours after
the effective date of this AD, measure the
edge-to-edge length of the clevis holes of
each bellcrank, and inspect each bellcrank
for cracking using liquid penetrant or eddy
current inspection method; in accordance
with the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than
or equal to 0.218 inch: Within 1,200 flight
hours after the effective date of this AD,
rework the bellcrank, or replace the bellcrank
with a new bellcrank or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(2) If no cracking is found, and any clevis
hole edge-to-edge length is greater than
0.218, inch but is less than or equal to 0.248
inch: Within 6,000 flight hours after the
effective date of this AD, replace the
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bellcrank with a new bellcrank, or with a
serviceable bellcrank with bushings having
part number 82710297–101 installed, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
84–27–55, Revision A, dated February 22,
2012.
(3) If no cracking is found, and any clevis
hole edge-to-edge length is greater than 0.248
inch, but is less than or equal to 0.278 inch:
Within 1,200 flight hours after the effective
date of this AD, replace the bellcrank with a
new bellcrank, or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(4) If any cracking is found, or any clevis
hole edge-to-edge length exceeds 0.278 inch:
Before further flight, replace the bellcrank
with a new bellcrank, or with a serviceable
bellcrank with bushings having part number
82710297–101 installed, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(j) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraphs (h) and (i) of
this AD, if those actions were performed
before the effective date of this AD using the
Accomplishment Instructions of Bombardier
Service Bulletin 84–27–55, dated June 15,
2011.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (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, New York
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 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.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2011–32, dated
August 15, 2011, for related information. The
MCAI can be found in the AD docket on the
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Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2012-1311-0002.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(m) 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 the AD specifies otherwise.
(i) Bombardier Service Bulletin 8–27–111,
dated June 15, 2011.
(ii) Bombardier Service Bulletin 84–27–55,
Revision A, dated February 22, 2012.
(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 review copies of the 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
September 30, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–25305 Filed 10–30–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0526; Directorate
Identifier 2008–SW–14–AD; Amendment
39–17633; AD 2013–22–01]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada (Bell)
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Bell
Model 206L–4 and 407 helicopters. This
AD requires replacing or reworking
certain aft bearing caps. This AD was
SUMMARY:
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]]>Agencies
[Federal Register Volume 78, Number 211 (Thursday, October 31, 2013)]
[Rules and Regulations]
[Pages 65176-65178]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25305]
[[Page 65176]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1311; Directorate Identifier 2011-NM-204-AD;
Amendment 39-17636; AD 2013-22-04]
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, and -106 airplanes; and Model
DHC-8-200, -300, and -400 series airplanes. This AD was prompted by
reports of excessive wear found in the clevis (bolt) hole where the rod
assembly attaches to the rudder/brake pedal bellcrank, due to prolonged
fretting. This AD requires measuring the bellcrank clevis holes,
inspecting for cracking of the bellcrank, and re-working the clevis
holes with steel bushings, or replacing the bellcrank. We are issuing
this AD to detect and correct a worn or cracked clevis hole, which
could cause failure of the bellcrank on one side, with subsequent
asymmetric braking and consequent runway excursion.
DATES: This AD becomes effective December 5, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 5,
2013.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2012-1311; or in person at the
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: Luke Walker, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7363; 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 the specified products. The
NPRM was published in the Federal Register on December 26, 2012 (77 FR
75906). The NPRM proposed to correct an unsafe condition for the
specified products. Transport Canada Civil Aviation (TCCA), which is
the aviation authority for Canada, issued Canadian Airworthiness
Directive CF-2011-32, dated August 15, 2011 (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 several in-service reports of excessive wear
found in the bolt [clevis] hole where the rod assembly, Part Numbers
(P/N) 82710795-001 or 82710024-003, is attached to the rudder/brake
pedal bellcrank. An investigation revealed that the wear was
attributed to prolonged fretting.
Failure of the bellcrank on one side could lead to asymmetric
braking and may lead to runway excursion.
This [Canadian] directive mandates [measuring clevis holes for
length, and, for certain bellcranks, doing a liquid penetrant
inspection for cracking, and] the re-work [by installing steel
bushings] or replacement of each bellcrank, P/N 82710022-001/-002,
82710029-001/-002, 82710813-001/-002 and 82710814-001/-002, found
with a worn [or cracked] bolt hole.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2012-1311-0002.
Revised Service Information
Bombardier, Inc. has issued Service Bulletin 84-27-55, Revision A,
dated February 22, 2012. The NPRM (77 FR 75906, December 26, 2012)
referred to Bombardier Service Bulletin 84-27-55, dated June 15, 2011,
in paragraphs (h) and (i) of the NPRM. In this final rule, we have
revised the service bulletin references in those paragraphs
accordingly, and have added new paragraph (j) to this final rule to
give credit for actions done before the effective date of this AD in
accordance with Bombardier Service Bulletin 84-27-55, dated June 15,
2011 (and redesignated subsequent paragraphs accordingly).
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comments received.
Request To Allow Use of Serviceable Parts
An anonymous commenter requested that the references to ``new
bellcrank'' in the NPRM (77 FR 75906, December 26, 2012) be changed to
allow operators to install ``serviceable'' bellcranks (new bellcranks
or ones that have been modified according to the applicable service
information), thus giving equal safety, yet providing more flexibility
and less recordkeeping for operators.
We agree with the commenter's request for the reasons given. We
have revised paragraphs (g)(2), (h)(2), (h)(3), (h)(4), (i)(2), (i)(3),
and (i)(4) of this AD by specifying to replace the bellcrank with a new
bellcrank ``or with a serviceable bellcrank with bushings having part
number 82710297-101 installed.'' We have also clarified paragraphs
(h)(1) and (i)(1) of this final rule by specifying to replace the
bellcrank ``with a new or with a serviceable bellcrank with bushings
having part number 82710297-101 installed.''
Request To Add Eddy Current Inspection Option
The same anonymous commenter requested that we include an eddy
current inspection option in this final rule to agree with parallel
actions specified in Bombardier Service Bulletin 84-27-55, Revision A,
dated February 22, 2012.
We agree with the commenter's request because Bombardier added that
inspection option in Bombardier Service Bulletin 84-27-55, Revision A,
dated February 22, 2012. Accordingly, we have added the option in
paragraphs (h) and (i) of this final rule.
Request To Clarify Compliance Times
The same anonymous commenter, in an incomplete request, stated that
the replacement times in paragraph (h) of the NPRM (77 FR 75906,
December 26, 2012) do not sufficiently remove the identified unsafe
condition. From the truncated statement, we cannot infer what part of
paragraph (h) the commenter requested that we change. We have made no
change to this final rule in this regard.
Conclusion
We reviewed the available data, including the comments received,
and
[[Page 65177]]
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 changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 75906, December 26, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 75906, December 26, 2012).
Costs of Compliance
We estimate that this AD will affect 178 products of U.S. registry.
We also estimate that it will take 5 work-hours per product to comply
with the basic requirements of this AD. The average labor rate is $85
per work-hour. Based on these figures, we estimate the cost of this AD
to the U.S. operators to be $75,650, or $425 per product.
In addition, we estimate that any necessary follow-on actions would
take about 16 work-hours and require parts costing up to $2,532, for a
cost of $3,892 per product. Where the service information lists
required parts costs that are covered under warranty, we have assumed
that there will be no charge for these parts. As we do not control
warranty coverage for affected parties, some parties may incur costs
higher than estimated here. We have no way of determining the number of
products that may need these actions.
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2012-1311-0002; 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 MCAI, 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.
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 AD:
2013-22-04 Bombardier, Inc.: Amendment 39-17636. Docket No. FAA-
2012-1311; Directorate Identifier 2011-NM-204-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective December 5,
2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. airplanes, certificated in
any category, as specified in paragraphs (c)(1) and (c)(2) of this
AD.
(1) Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -
315 airplanes: Serial numbers 003 through 672 inclusive.
(2) Model DHC-8-400, -401, and -402 airplanes: Serial numbers
4003 through 4372 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 27: Flight
controls.
(e) Reason
This AD was prompted by reports of excessive wear found in the
clevis (bolt) hole where the rod assembly attaches to the rudder/
brake pedal bellcrank, due to prolonged fretting. We are issuing
this AD to detect and correct a worn or cracked clevis hole, which
could cause failure of the bellcrank on one side, with subsequent
asymmetric braking and consequent runway excursion.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Actions for Model DHC-8-100, -200, and -300 Series Airplanes
For Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -
315 airplanes: Within 6,000 flight hours or 24 months after the
effective date of this AD, whichever occurs first, inspect each
bellcrank for cracking using liquid penetrant, in accordance with
the Accomplishment Instructions of Bombardier Service Bulletin 8-27-
111, dated June 15, 2011.
(1) If no cracking is found: Before further flight, rework the
bellcrank, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 8-27-111, dated June 15, 2011.
(2) If any clevis hole is greater than 0.218 inch (measured
edge-to-edge), or if any cracking is found: Before further flight,
replace the bellcrank with a new bellcrank, or with a serviceable
bellcrank with bushings having part number 82710297-101 installed,
in accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-27-111, dated June 15, 2011.
(h) Actions for Certain Model DHC-8-400 Series Airplanes
For Model DHC-8-400, -401, and -402 airplanes that have
accumulated less than or equal to 15,000 total flight hours as of
the effective date of this AD: Within 6,000 flight hours after the
effective date of this AD, but not to exceed 15,600 total flight
hours, measure the edge-to-edge length of the clevis holes of each
bellcrank, and inspect each bellcrank for cracking using liquid
penetrant or eddy current inspection method; in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55,
Revision A, dated February 22, 2012.
[[Page 65178]]
(1) If no cracking is found, and the edge-to-edge length of all
clevis holes is less than or equal to 0.218 inch: Within 6,000
flight hours after the effective date of this AD, but not to exceed
15,600 total flight hours, rework the bellcrank, or replace the
bellcrank with a new bellcrank or with a serviceable bellcrank with
bushings having part number 82710297-101 installed, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
84-27-55, Revision A, dated February 22, 2012.
(2) If no cracking is found, and any clevis hole edge-to-edge
length is greater than 0.218 inch, but is less than or equal to
0.248 inch: Within 6,000 flight hours after the effective date of
this AD, replace the bellcrank with a new bellcrank, or with a
serviceable bellcrank with bushings having part number 82710297-101
installed, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 84-27-55, Revision A, dated February 22,
2012.
(3) If no cracking is found, and any clevis hole edge-to-edge
length is greater than 0.248 inch, but is less than or equal to
0.278 inch: Within 1,200 flight hours after doing the measurement/
inspection required by paragraph (h) of this AD, replace the
bellcrank with a new bellcrank, or with a serviceable bellcrank with
bushings having part number 82710297-101 installed, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
84-27-55, Revision A, dated February 22, 2012.
(4) If any cracking is found, or if any clevis hole edge-to-edge
length exceeds 0.278 inch: Before further flight, replace the
bellcrank with a new bellcrank, or with a serviceable bellcrank with
bushings having part number 82710297-101 installed, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
84-27-55, Revision A, dated February 22, 2012.
(i) Actions for Certain Other Model DHC-8-400 Series Airplanes
For Model DHC-8-400, -401, and -402 airplanes that have
accumulated more than 15,000 total flight hours as of the effective
date of this AD: Within 600 flight hours after the effective date of
this AD, measure the edge-to-edge length of the clevis holes of each
bellcrank, and inspect each bellcrank for cracking using liquid
penetrant or eddy current inspection method; in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55,
Revision A, dated February 22, 2012.
(1) If no cracking is found, and the edge-to-edge length of all
clevis holes is less than or equal to 0.218 inch: Within 1,200
flight hours after the effective date of this AD, rework the
bellcrank, or replace the bellcrank with a new bellcrank or with a
serviceable bellcrank with bushings having part number 82710297-101
installed, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 84-27-55, Revision A, dated February 22,
2012.
(2) If no cracking is found, and any clevis hole edge-to-edge
length is greater than 0.218, inch but is less than or equal to
0.248 inch: Within 6,000 flight hours after the effective date of
this AD, replace the bellcrank with a new bellcrank, or with a
serviceable bellcrank with bushings having part number 82710297-101
installed, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 84-27-55, Revision A, dated February 22,
2012.
(3) If no cracking is found, and any clevis hole edge-to-edge
length is greater than 0.248 inch, but is less than or equal to
0.278 inch: Within 1,200 flight hours after the effective date of
this AD, replace the bellcrank with a new bellcrank, or with a
serviceable bellcrank with bushings having part number 82710297-101
installed, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 84-27-55, Revision A, dated February 22,
2012.
(4) If any cracking is found, or any clevis hole edge-to-edge
length exceeds 0.278 inch: Before further flight, replace the
bellcrank with a new bellcrank, or with a serviceable bellcrank with
bushings having part number 82710297-101 installed, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
84-27-55, Revision A, dated February 22, 2012.
(j) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraphs (h) and (i) of this AD, if those actions were performed
before the effective date of this AD using the Accomplishment
Instructions of Bombardier Service Bulletin 84-27-55, dated June 15,
2011.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (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, New York 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 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.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2011-32, dated August 15,
2011, for related information. The MCAI can be found in the AD
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2012-1311-0002.
(2) Service information identified in this AD that is not
incorporated by reference may be obtained at the addresses specified
in paragraphs (m)(3) and (m)(4) of this AD.
(m) 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 the AD specifies otherwise.
(i) Bombardier Service Bulletin 8-27-111, dated June 15, 2011.
(ii) Bombardier Service Bulletin 84-27-55, Revision A, dated
February 22, 2012.
(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 review copies of the 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 September 30, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-25305 Filed 10-30-13; 8:45 am]
BILLING CODE 4910-13-P
