[Federal Register Volume 78, Number 231 (Monday, December 2, 2013)]
[Rules and Regulations]
[Pages 71998-72001]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-28104]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0700; Directorate Identifier 2013-NM-102-AD;
Amendment 39-17676; AD 2013-24-02]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes. This AD was prompted by reports of fractured rudder pedal
tubes installed on the pilot-side rudder bar assembly. This AD requires
repetitive inspections for cracking and damage of both pilot-side
rudder pedal tubes, and replacement of affected pilot-side rudder bar
assemblies if necessary. We are issuing this AD to detect and correct
cracking of both pilot-side rudder pedal tubes, which could result in
loss of pilot rudder pedal input causing reduced yaw controllability or
a runway excursion.
DATES: This AD becomes effective January 6, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 6,
2014.
ADDRESSES: You may examine the AD on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0700 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., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9,
Canada; telephone 514-855-5000; fax 514-855-7401; email
[email protected]; Internet http://www.bombardier.com. You
may view this referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
FOR FURTHER INFORMATION CONTACT: Ricardo Garcia, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7331; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
The NPRM was published in the Federal Register on August 26, 2013 (78
FR 52712). The NPRM proposed to correct an unsafe condition for the
specified products. Transport Canada Civil Aviation (TCCA), which is
the aviation authority for Canada, has issued Canadian Airworthiness
Directive CF-2013-12, dated May 14, 2013 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for the specified products. The MCAI
states:
[[Page 71999]]
There have been two in-service reports of fracture of rudder
pedal tubes installed on the pilot-side rudder bar assembly.
Laboratory examination of the fractured rudder pedal tubes found
that in both cases, the fatigue cracks initiated at the aft taper
pin holes where the connecting rod fitting is attached. Fatigue
testing of the rudder pedal tubes confirmed that the fatigue
cracking is due to loads induced during parking brake application.
Therefore, only the rudder pedal tubes on the pilot's side are
vulnerable to fatigue cracking as the parking brake is primarily
applied by the pilot.
Loss of pilot rudder pedal input during flight would result in
reduced yaw controllability of the aeroplane. Loss of pilot rudder
pedal input during takeoff or landing may lead to a runway
excursion.
This [Canadian] AD mandates initial and repetitive [detailed or
eddy current] inspections [for cracking and damage and replacement
if necessary] of the pilot-side rudder * * * [bar assembly], until
the terminating action is accomplished.
Required actions also include repairing damage. The terminating
action is replacement of both pilot-side rudder bar assemblies. You may
obtain further information by examining the MCAI in the AD docket on
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-
0700-0002.
Comments
We gave the public the opportunity to participate in developing
this AD.
We received no comments on the NPRM (78 FR 52712, August 26, 2013)
or on the determination of the cost to the public.
Conclusion
We reviewed the available data 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 (78 FR 52712, August 26, 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 52712, August 26, 2013).
Costs of Compliance
We estimate that this AD affects 529 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection...................... 3 work-hours x $85 per $0 $255 per inspection $134,895 per
hour = $255 per cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacement
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need this
repair:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement................................... 6 work-hours x $85 per hour = $510.... $2,850 $3,360
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
a cost estimate for the repair specified in this AD.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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 http://www.regulations.gov/#!docketDetail;D=FAA-2013-0700; or in person at the
Docket Operations office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone (800)
647-5527) is in the ADDRESSES section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 72000]]
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:
2013-24-02 Bombardier, Inc.: Amendment 39-17676. Docket No. FAA-
2013-0700; Directorate Identifier 2013-NM-102-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective January 6,
2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model CL-600-2B19 (Regional
Jet Series 100 & 440) airplanes, certificated in any category,
serial numbers 7003 and subsequent.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by reports of fractured rudder pedal tubes
installed on the pilot-side rudder bar assembly. We are issuing this
AD to detect and correct cracking of both pilot-side rudder pedal
tubes, which could result in loss of pilot rudder pedal input
causing reduced yaw controllability or a 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) Initial Inspections
At the applicable time specified in paragraphs (g)(1) through
(g)(6) of this AD, do a detailed or eddy current inspection for
cracking and damage (i.e., corrosion or cracking) of both pilot-side
rudder pedal tubes having part number (P/N) 600-90204-3, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 601R-27-162, including Appendix A, dated April 5,
2013.
(1) For airplanes that have accumulated less than 20,000 total
flight cycles as of the effective date of this AD: Do the inspection
before the accumulation of 23,000 total flight cycles.
(2) For airplanes that have accumulated 20,000 total flight
cycles or more, but less than 25,000 total flight cycles as of the
effective date of this AD: Do the inspection within 3,000 flight
cycles after the effective date of this AD, but not to exceed 26,300
total flight cycles.
(3) For airplanes that have accumulated 25,000 total flight
cycles or more, but less than 30,000 total flight cycles as of the
effective date of this AD: Do the inspection within 1,300 flight
cycles after the effective date of this AD, but not to exceed 30,800
total flight cycles.
(4) For airplanes that have accumulated 30,000 total flight
cycles or more, but less than 33,000 total flight cycles as of the
effective date of this AD: Do the inspection within 800 flight
cycles after the effective date of this AD, but not to exceed 33,500
total flight cycles.
(5) For airplanes that have accumulated 33,000 total flight
cycles or more, but less than 37,000 total flight cycles as of the
effective date of this AD: Do the inspection within 500 flight
cycles after the effective of this AD, but not to exceed 37,300
total flight cycles.
(6) For airplanes that have accumulated 37,000 total flight
cycles or more as of the effective date of this AD: Do the
inspection within 300 flight cycles after the effective date of this
AD.
(h) Inspection Definition
For the purposes of this AD, a detailed inspection is an
intensive examination of a specific item, installation, or assembly
to detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at an
intensity deemed appropriate. Inspection aids such as a mirror,
magnifying lenses, etc., may be necessary. Surface cleaning and
elaborate procedures may be required.
(i) Repetitive Inspections
For any tube on which no cracking and no damage is found during
any inspection required by paragraph (g) of this AD: At the
applicable time specified in paragraph (i)(1) or (i)(2) of this AD,
repeat the detailed or eddy current inspection for cracking of the
pilot-side rudder pedal tubes, specified in paragraph (g) of this
AD, until the terminating action specified in paragraph (k) of this
AD has been accomplished.
(1) If the most recent inspection was a detailed inspection:
Repeat the inspection within 600 flight cycles thereafter.
(2) If the most recent inspection was an eddy current
inspection: Repeat the inspection within 1,000 flight cycles
thereafter.
(j) Corrective Actions
(1) If any cracking is found around the aft tapered holes during
any inspection required by paragraph (g) or (i) of this AD, before
further flight, replace the affected rudder bar assemblies, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 601R-27-162, including Appendix A, dated April 5,
2013.
(2) If any other damage (i.e., corrosion or cracking), other
than that specified in paragraph (j)(1) of this AD, is found during
any inspection required by paragraph (g) or (i) of this AD, before
further flight, repair using a method approved by either the
Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA;
or Transport Canada Civil Aviation (TCCA) (or its delegated agent).
(k) Optional Terminating Action
Replacement of both pilot-side rudder bar assemblies, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 601R-27-162, including Appendix A, dated April 5,
2013, terminates the inspections required by paragraphs (g) and (i)
of this AD.
(l) 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, NY 11590; telephone 516-228-7300; fax 516-794-5531.
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office. The AMOC approval letter must specifically reference this
AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer 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.
(m) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
Canadian Airworthiness Directive CF-2013-12, dated May 14, 2013, for
related information, which can be found in the AD docket on the
internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-
0700-0002.
(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 the AD specifies otherwise.
(i) Bombardier Service Bulletin 601R-27-162, including Appendix
A, dated April 5, 2013.
(ii) Reserved.
(3) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email [email protected]; Internet http://www.bombardier.com.
(4) You may view this service information at the FAA, Transport
Airplane Directorate,
[[Page 72001]]
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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on November 15, 2013.
John Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-28104 Filed 11-29-13; 8:45 am]
BILLING CODE 4910-13-P