Airworthiness Directives; Bombardier, Inc. Airplanes, 44666-44669 [2014-17467]
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Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations
(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) Repetitive Operational Tests
(1) At the time specified in paragraph (g)(2)
of this AD: Accomplish an operational test of
the hydraulic locking function on each SSC
(any type), when fitted on the Blue or Yellow
hydraulic circuits, in accordance with the
Accomplishment Instructions of the
applicable service information identified in
paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of
this AD. Repeat the operational test thereafter
at intervals not to exceed 48 months.
(i) Airbus Service Bulletin A330–27–3195,
Revision 01, dated February 6, 2014 (for
Model A330–200 Freighter, A330–200 and
–300 series airplanes).
(ii) Airbus Service Bulletin A340–27–4188,
Revision 01, dated February 6, 2014 (for
Model A340–200, and –300 series airplanes).
(iii) Airbus Service Bulletin A340–27–
5059, Revision 01, dated February 6, 2014
(for Model A340–500 and –600 series
airplanes).
(2) At the latest of the times specified in
paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of
this AD, do the operational test specified in
paragraph (g)(1) of this AD.
(i) Within 48 months since first flight of the
airplane.
(ii) Within 48 months since accomplishing
the most recent operational test, as specified
in the applicable Airbus All Operators Telex
(AOT) A330–27A3185; or AOT A340–
27A4181; both dated January 4, 2012. These
AOTs were incorporated by reference in AD
2012–25–10, Amendment 39–17291 (77 FR
76228, December 27, 2012).
(iii) Within 24 months after the effective
date of this AD.
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(h) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using the applicable
service information identified in paragraph
(h)(1), (h)(2), or (h)(3) of this AD, which is
not incorporated by reference in this AD.
(i) Airbus Service Bulletin A330–27–3195,
dated December 7, 2012.
(ii) Airbus Service Bulletin A340–27–4188,
dated December 7, 2012.
(iii) Airbus Service Bulletin A340–27–
5059, dated April 10, 2013.
(i) Replacement of Affected SSCs
If, during any operational test required by
paragraph (g)(1) of this AD, the hydraulic
locking function of an SSC fails the test,
before further flight, replace the affected SSC
with a serviceable part, in accordance with
the Accomplishment Instructions of the
applicable service bulletin specified in
paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of
this AD.
(j) No Terminating Action
Doing the replacement required by
paragraph (i) of this AD is not terminating
action for the repetitive operational tests
required by paragraph (g)(1) of this AD.
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(k) 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
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA 1601 Lind Avenue
SW., Renton, WA 98057–3356; telephone
425–227–1138; 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 European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2013–0251 dated October 15, 2013;
Correction dated October 16, 2013, for related
information. This MCAI may be found in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-0228-0002.
(2) Service information identified in this
AD that is not incorporated by reference may
be viewed 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 this AD specifies otherwise.
(i) Airbus Service Bulletin A330–27–3195,
Revision 01, dated February 6, 2014.
(ii) Airbus Service Bulletin A340–27–4188,
Revision 01, dated February 6, 2014.
(iii) Airbus Service Bulletin A340–27–
5059, Revision 01, dated February 6, 2014.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
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(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 17,
2014.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–17468 Filed 7–31–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0196; Directorate
Identifier 2014–NM–015–AD; Amendment
39–17913; AD 2014–15–11]
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 CL–600–2C10
(Regional Jet Series 700, 701, & 702)
airplanes, Model CL–600–2D15
(Regional Jet Series 705) airplanes,
Model CL–600–2D24 (Regional Jet
Series 900) airplanes, and Model CL–
600–2E25 (Regional Jet Series 1000)
airplanes. This AD was prompted by
two in-service reports of fracture of the
rudder pedal tubes installed on the
pilot-side rudder bar assembly. This AD
requires repetitive inspections for
cracking and damage of the pilot-side
rudder pedal tubes, and corrective
action if necessary. This AD also
provides optional terminating action for
the repetitive inspections. We are
issuing this AD to detect and correct
cracked and damaged pilot-side rudder
pedal tubes, which could result in loss
of function of the pilot’s rudder pedal
during flight, takeoff, or landing, and
could result in reduced controllability
of the airplane.
DATES: This AD becomes effective
September 5, 2014.
The Director of the Federal Register
approved the incorporation by reference
SUMMARY:
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of a certain publication listed in this AD
as of September 5, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA–2014–0196 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., 400
ˆ
´
Cote-Vertu Road West, Dorval, Quebec
H4S 1Y9, Canada; telephone 514–855–
5000; fax 514–855–7401; email thd.crj@
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:
Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7318; 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
CL–600–2C10 (Regional Jet Series 700,
701, & 702) airplanes, Model CL–600–
2D15 (Regional Jet Series 705) airplanes,
Model CL–600–2D24 (Regional Jet
Series 900) airplanes, and Model CL–
600–2E25 (Regional Jet Series 1000)
airplanes. The NPRM published in the
Federal Register on April 14, 2014 (79
FR 20829).
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, has issued
Canadian Airworthiness Directive CF–
2014–02, dated January 8, 2014 (referred
to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’). The MCAI states:
There have been two in-service reports of
fracture of the rudder pedal tubes installed
on the pilot-side rudder bar assembly on CL–
600–2B19 model aeroplanes.
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
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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.
Although there have been no reported
failures to date on any CL–600–2C10, –2D15,
–2D24, and –2D25 model aeroplanes, the
same torque tubes part number (P/N) 600–
90204–3 are installed, which may be prone
to premature fatigue cracking.
This [Canadian] AD mandates initial and
repetitive [detailed and eddy current]
inspections [for cracking and damage] of the
pilot-side rudder pedal tubes, P/N 600–
90204–3, until the terminating action
[replacement of both pilot-side rudder bar
assemblies] is accomplished [and corrective
actions if necessary].
Corrective actions include replacement
of the rudder bar assembly and repair.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-01960002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
FR 20829, April 14, 2014) or on the
determination of the cost to the public.
‘‘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 (79 FR 20829, April 14,
2014), 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, we proposed to
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44667
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
proposed AD.
No comments were provided to the
NPRM (79 FR 20829, April 14, 2014)
about these proposed changes. However,
a comment was provided for a similar
NPRM, 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.
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
that 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, Inc.’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
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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
discussed previously, 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 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.
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Conclusion
Regulatory Findings
We reviewed the relevant data 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 (79 FR
20829, April 14, 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 20829,
April 14, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
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.
Costs of Compliance
We estimate that this AD affects 400
airplanes of U.S. registry.
We also estimate that it takes about 3
work-hours per product to comply with
the basic inspection requirements of this
AD. The average labor rate is $85 per
work-hour. Based on these figures, we
estimate the cost of this AD on U.S.
operators to be $102,000, or $255 per
airplane, per inspection cycle.
In addition, we estimate that any
necessary replacement of the rudder
pedal tubes takes about 6 work-hours
and require parts costing $2,850, for a
cost of $3,360 per product. We have no
way of determining the number of
aircraft that might need this action.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition repairs
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.
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/#!docketDetail;D=
FAA-2014-0196; 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.
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):
■
2014–15–11 Bombardier, Inc.: Amendment
39–17913. Docket No. FAA–2014–0196;
Directorate Identifier 2014–NM–015–AD.
(a) Effective Date
This AD becomes effective September 5,
2014.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1), (c)(2), and (c)(3) of this
AD, certificated in any category.
(1) Bombardier, Inc. Model CL–600–2C10
(Regional Jet Series 700, 701, & 702)
airplanes, serial numbers 10002 through
10342 inclusive.
(2) Bombardier, Inc. Model CL–600–2D15
(Regional Jet Series 705), and Model CL–600–
2D24 (Regional Jet Series 900) airplanes,
serial numbers 15001 through 15337
inclusive.
(3) Bombardier, Inc. Model CL–600–2E25
(Regional Jet Series 1000) airplanes, serial
numbers 19001 through 19040 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Reason
This AD was prompted by two in-service
reports of fracture of the rudder pedal tubes
installed on the pilot-side rudder bar
assembly. We are issuing this AD to detect
and correct cracked and damaged pilot-side
rudder pedal tubes, which could result in
loss of function of the pilot’s rudder pedal
during flight, takeoff, or landing, and could
result in reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Repetitive Inspections
Before the accumulation of 26,000 total
flight cycles or within 3 months after the
effective date of this AD, whichever occurs
later: Perform a detailed or eddy current
inspection for cracking around the aft tapered
holes of both pilot-side rudder pedal tubes,
and for damage of the rudder pedal tubes in
locations other than around the aft tapered
holes, in accordance with Part A of the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–27–065, including
Appendix A, dated November 15, 2013.
Repeat the inspection thereafter at the
applicable intervals specified in paragraph
(g)(1) or (g)(2) of this AD, until the
terminating action specified in paragraph (i)
of this AD is done.
(1) If the most recent inspection was a
detailed inspection: Within 750 flight cycles
after doing the detailed inspection.
(2) If the most recent inspection was an
eddy current inspection: Within 1,250 flight
cycles after doing the eddy current
inspection.
(h) Corrective Actions
(1) If any crack is found around the aft
tapered holes during any inspection required
by paragraph (g) of this AD, before further
flight, replace the rudder bar assembly, in
accordance with Part B of the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–27–065, including
Appendix A, dated November 15, 2013.
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(2) If any damage is found during any
inspection required by paragraph (g) of this
AD in a location other than around the aft
tapered holes: 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 DAOauthorized signature.
(i) Optional Terminating Action
Replacement of both pilot-side rudder bar
assemblies, in accordance with Part B of the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–27–065, including
Appendix A, dated November 15, 2013,
constitutes terminating action for the
repetitive inspections required by paragraph
(g) of this AD.
(j) 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. Send information 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 Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(k) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2014–02, dated
January 8, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0196-0002.
(l) 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) Bombardier Service Bulletin 670BA–27–
065, including Appendix A, dated November
15, 2013.
(ii) Reserved.
PO 00000
Frm 00035
Fmt 4700
Sfmt 4700
44669
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
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 17,
2014.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–17467 Filed 7–31–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0254; Directorate
Identifier 2013–NM–047–AD; Amendment
39–17910; AD 2014–15–08]
RIN 2120–AA64
Airworthiness Directives; Beechcraft
Corporation (Type Certificate
Previously Held by Hawker Beechcraft
Corporation; Raytheon Aircraft
Company) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Beechcraft Corporation (Type Certificate
Previously Held by Hawker Beechcraft
Corporation; Raytheon Aircraft
Company) Model Hawker 800XP,
850XP, and 900XP airplanes. This AD
was prompted by a design review that
revealed there were no instructions to
apply sealant to structural components
in the fuel tank during the winglet
installation process. This AD requires
an inspection for the presence of sealant
on doubler plate edges, doubler plate
rivets, and adjacent skin in the fuel vent
surge tanks; and corrective actions if
necessary. We are issuing this AD to
detect and correct missing sealant,
which, during a lightning strike, could
result in a potential source of ignition in
a fuel tank and consequent explosion or
SUMMARY:
E:\FR\FM\01AUR1.SGM
01AUR1
]]>Agencies
[Federal Register Volume 79, Number 148 (Friday, August 1, 2014)]
[Rules and Regulations]
[Pages 44666-44669]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-17467]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0196; Directorate Identifier 2014-NM-015-AD;
Amendment 39-17913; AD 2014-15-11]
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 CL-600-2C10 (Regional Jet Series 700, 701, &
702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes,
Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL-
600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by
two in-service reports of fracture of the rudder pedal tubes installed
on the pilot-side rudder bar assembly. This AD requires repetitive
inspections for cracking and damage of the pilot-side rudder pedal
tubes, and corrective action if necessary. This AD also provides
optional terminating action for the repetitive inspections. We are
issuing this AD to detect and correct cracked and damaged pilot-side
rudder pedal tubes, which could result in loss of function of the
pilot's rudder pedal during flight, takeoff, or landing, and could
result in reduced controllability of the airplane.
DATES: This AD becomes effective September 5, 2014.
The Director of the Federal Register approved the incorporation by
reference
[[Page 44667]]
of a certain publication listed in this AD as of September 5, 2014.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0196 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., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9,
Canada; telephone 514-855-5000; fax 514-855-7401; email
thd.crj@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: Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7318; 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 CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes,
Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-
2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25
(Regional Jet Series 1000) airplanes. The NPRM published in the Federal
Register on April 14, 2014 (79 FR 20829).
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, has issued Canadian Airworthiness Directive CF-
2014-02, dated January 8, 2014 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''). The MCAI
states:
There have been two in-service reports of fracture of the rudder
pedal tubes installed on the pilot-side rudder bar assembly on CL-
600-2B19 model aeroplanes.
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.
Although there have been no reported failures to date on any CL-
600-2C10, -2D15, -2D24, and -2D25 model aeroplanes, the same torque
tubes part number (P/N) 600-90204-3 are installed, which may be
prone to premature fatigue cracking.
This [Canadian] AD mandates initial and repetitive [detailed and
eddy current] inspections [for cracking and damage] of the pilot-
side rudder pedal tubes, P/N 600-90204-3, until the terminating
action [replacement of both pilot-side rudder bar assemblies] is
accomplished [and corrective actions if necessary].
Corrective actions include replacement of the rudder bar assembly and
repair. You may examine the MCAI in the AD docket on the Internet at
https://www.regulations.gov/#!documentDetail;D=FAA-2014-0196-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 20829, April 14,
2014) or on the determination of the cost to the public.
``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 (79 FR 20829, April 14, 2014), 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, we 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
proposed AD.
No comments were provided to the NPRM (79 FR 20829, April 14, 2014)
about these proposed changes. However, a comment was provided for a
similar NPRM, 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. 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 that 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, Inc.'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
[[Page 44668]]
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 discussed previously, 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 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 (79 FR 20829, April 14, 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 20829, April 14, 2014).
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 400 airplanes of U.S. registry.
We also estimate that it takes about 3 work-hours per product to
comply with the basic inspection requirements of this AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this AD on U.S. operators to be $102,000, or $255 per
airplane, per inspection cycle.
In addition, we estimate that any necessary replacement of the
rudder pedal tubes takes about 6 work-hours and require parts costing
$2,850, for a cost of $3,360 per product. We have no way of determining
the number of aircraft that might need this action.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs 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-2014-0196; 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.
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):
2014-15-11 Bombardier, Inc.: Amendment 39-17913. Docket No. FAA-
2014-0196; Directorate Identifier 2014-NM-015-AD.
(a) Effective Date
This AD becomes effective September 5, 2014.
[[Page 44669]]
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
(1) Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700,
701, & 702) airplanes, serial numbers 10002 through 10342 inclusive.
(2) Bombardier, Inc. Model CL-600-2D15 (Regional Jet Series
705), and Model CL-600-2D24 (Regional Jet Series 900) airplanes,
serial numbers 15001 through 15337 inclusive.
(3) Bombardier, Inc. Model CL-600-2E25 (Regional Jet Series
1000) airplanes, serial numbers 19001 through 19040 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by two in-service reports of fracture of
the rudder pedal tubes installed on the pilot-side rudder bar
assembly. We are issuing this AD to detect and correct cracked and
damaged pilot-side rudder pedal tubes, which could result in loss of
function of the pilot's rudder pedal during flight, takeoff, or
landing, and could result in reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Before the accumulation of 26,000 total flight cycles or within
3 months after the effective date of this AD, whichever occurs
later: Perform a detailed or eddy current inspection for cracking
around the aft tapered holes of both pilot-side rudder pedal tubes,
and for damage of the rudder pedal tubes in locations other than
around the aft tapered holes, in accordance with Part A of the
Accomplishment Instructions of Bombardier Service Bulletin 670BA-27-
065, including Appendix A, dated November 15, 2013. Repeat the
inspection thereafter at the applicable intervals specified in
paragraph (g)(1) or (g)(2) of this AD, until the terminating action
specified in paragraph (i) of this AD is done.
(1) If the most recent inspection was a detailed inspection:
Within 750 flight cycles after doing the detailed inspection.
(2) If the most recent inspection was an eddy current
inspection: Within 1,250 flight cycles after doing the eddy current
inspection.
(h) Corrective Actions
(1) If any crack is found around the aft tapered holes during
any inspection required by paragraph (g) of this AD, before further
flight, replace the rudder bar assembly, in accordance with Part B
of the Accomplishment Instructions of Bombardier Service Bulletin
670BA-27-065, including Appendix A, dated November 15, 2013.
(2) If any damage is found during any inspection required by
paragraph (g) of this AD in a location other than around the aft
tapered holes: 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.
(i) Optional Terminating Action
Replacement of both pilot-side rudder bar assemblies, in
accordance with Part B of the Accomplishment Instructions of
Bombardier Service Bulletin 670BA-27-065, including Appendix A,
dated November 15, 2013, constitutes terminating action for the
repetitive inspections required by paragraph (g) of this AD.
(j) 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. Send information 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 Design Approval Organization (DAO). If
approved by the DAO, the approval must include the DAO-authorized
signature.
(k) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
Canadian Airworthiness Directive CF-2014-02, dated January 8, 2014,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-
2014-0196-0002.
(l) 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) Bombardier Service Bulletin 670BA-27-065, including Appendix
A, dated November 15, 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 thd.crj@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 17, 2014.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-17467 Filed 7-31-14; 8:45 am]
BILLING CODE 4910-13-P
