Airworthiness Directives; Bombardier, Inc. Airplanes, 48954-48957 [2014-18863]
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48954
Federal Register / Vol. 79, No. 160 / Tuesday, August 19, 2014 / Rules and Regulations
TABLE 1 TO PARAGRAPH (h) OF THIS AD—LOW-PRESSURE OXYGEN HOSES (P/N)—Continued
Boeing specification No.
Hydroflow
10–60174–35 .............................................................
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for The Boeing
Company Model 707 airplanes, Model 720
and 720B series airplanes, Model 727
airplanes, and Model 737–100, –200, and
–200C series airplanes, covered by 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (j)(1) or (j)(2) of this AD, as
applicable. Information may be emailed to: 9ANM-LAACO-AMOC-REQUESTS@faa.gov.
(2) 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.
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(j) Related Information
For more information about this AD,
contact the applicable person identified in
paragraph (j)(1) or (j)(2) of this AD.
(1) For Model 707 airplanes, Model 720
and 720B series airplanes, and Model 727
airplanes, contact Patrick Farina, Aerospace
Engineer, Cabin Safety, Mechanical and
Environmental Systems Branch, ANM–150L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5344; fax: 562–627–5210; email:
Patrick.Farina@faa.gov.
(2) For Model 737–100, –200, and –200C
series airplanes, contact Tracy Ton,
Aerospace Engineer, Cabin Safety,
Mechanical and Environmental Systems
Branch, ANM–150L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, CA
90712–4137; phone: 562–627–5352; fax: 562–
627–5210; email: Tracy.Ton@faa.gov.
(k) 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) Boeing 707 Alert Service Bulletin
A3538, dated October 2, 2013.
(ii) Boeing Alert Service Bulletin 727–
35A0031, dated July 18, 2013.
(iii) Boeing Alert Service Bulletin 737–
35A1140, dated August 28, 2013.
(3) For service information identified in
this AD, contact Boeing Commercial
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Jkt 232001
37001–35
37001–36
173470–35 .................................................................
173470–36
ZH833–35
ZH833–36
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(4) You may view this service information
at 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 30,
2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–18860 Filed 8–18–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0120; Directorate
Identifier 2013–NM–056–AD; Amendment
39–17932; AD 2014–16–08]
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–215–6B11
(CL–215T Variant), and CL–215–6B11
(CL–415 Variant) airplanes. This AD
was prompted by several reports
indicating that shorter nacelle strut
bushings were inadvertently installed
on certain airplanes. This AD requires a
general visual inspection of the left and
right nacelle upper strut bushings;
installation of the bolts and preload
indicating (PLI) washers, if necessary;
and replacement of the bushing or
repair of the bushing installation, if
SUMMARY:
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(aka REDAR)
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40830–505–018
necessary. We are issuing this AD to
detect and correct inadequate nacelle
strut bushings, which provide
insufficient engagement in the strut fork
end, and could deform under the
bearing load and lead to the failure of
the joint.
DATES: This AD becomes effective
September 23, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 23, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0120; 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:
Ricardo Garcia, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; phone 516–228–7331; 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–215–6B11 (CL–215T Variant), and
CL–215–6B11 (CL–415 Variant)
airplanes. The NPRM published in the
Federal Register on February 27, 2014
(79 FR 11022).
Transport Canada Civil Aviation,
which is the aviation authority for
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Canada, has issued Canadian
Airworthiness Directive CF–2013–06,
dated February 27, 2013 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
certain Bombardier, Inc. Model CL–215–
6B11 (CL–215T Variant), and CL–215–
6B11 (CL–415 Variant) airplanes. The
MCAI states:
It was discovered in several cases that
nacelle strut bushings with part number (P/
N), 85410265–105, have been inadvertently
installed in lieu of P/N 85410265–103.
Bushing P/N 85410265–105 is shorter than
bushing P/N 85410265–103 and provides for
less engagement in the strut fork end, P/N
215T16534–12/–13, which may deform
under the bearing load leading to the failure
of the joint.
The actions for this AD include a
general visual inspection of the left and
right nacelle upper strut bushings;
installation of the bolts and PLI
washers, if necessary; and replacement
of the bushing or repair of the bushing
installation, if necessary. You may
examine the MCAI in the AD docket on
the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-01200002.
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Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
FR 11022, February 27, 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 11022, February
27, 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
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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 11022, February 27, 2014)
about these proposed changes. However,
a comment was provided for another
NPRM having Directorate Identifier
2012–NM–101–AD (78 FR 78285,
December 26, 2013). The commenter
stated the following: ‘‘The proposed
wording, being specific to repairs,
eliminates the interpretation that Airbus
messages are acceptable for approving
minor deviations (corrective actions)
needed during accomplishment of an
AD mandated Airbus service bulletin.’’
This comment has made the FAA
aware that some operators have
misunderstood or misinterpreted the
Airworthy Product paragraph to allow
the owner/operator to use messages
provided by the manufacturer as
approval of deviations during the
accomplishment of an AD-mandated
action. The Airworthy Product
paragraph does not approve messages or
other information provided by the
manufacturer for deviations to the
requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
for an alternative method of compliance
to the AD-required actions using the
procedures found in 14 CFR 39.19.
To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed the
paragraph and retitled it ‘‘Contacting the
Manufacturer.’’ This paragraph now
clarifies that for any requirement in this
AD to obtain corrective actions from a
manufacturer, the action must be
accomplished using a method approved
by the FAA, TCCA, or Bombardier’s
TCCA Design Approval Organization
(DAO).
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DAO, the approval must include
the DAO-authorized signature. The DAO
signature indicates that the data and
information contained in the document
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48955
are TCCA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DAO-authorized signature approval are
not TCCA-approved, unless TCCA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility previously afforded by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
recommendation of the Airworthiness
Directive Implementation Aviation
Rulemaking Committee to increase
flexibility in complying with ADs by
identifying those actions in
manufacturers’ service instructions that
are ‘‘Required for Compliance’’ with
ADs. We continue to work with
manufacturers to implement this
recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an alternative method of
compliance.
Other commenters to the NPRM
having Directorate Identifier 2012–NM–
101–AD (78 FR 78285, December 26,
2013) pointed out that in many cases the
foreign manufacturer’s service bulletin
and the foreign authority’s MCAI might
have been issued some time before the
FAA AD. Therefore, the DOA might
have provided U.S. operators with an
approved repair, developed with full
awareness of the unsafe condition,
before the FAA AD is issued. Under
these circumstances, to comply with the
FAA AD, the operator would be
required to go back to the
manufacturer’s DOA and obtain a new
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
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Authority for the DAH in the Contacting
the Manufacturer paragraph of 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
11022, February 27, 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 11022,
February 27, 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 5
airplanes of U.S. registry.
We also estimate that it will take
about 4 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Required parts will cost
about $0 per product. Based on these
figures, we estimate the cost of this AD
on U.S. operators to be $1,700, or $340
per product.
In addition, we estimate that any
necessary follow-on actions will take
about 4 work-hours and require parts
costing $0, for a cost of $340 per
product. We have no way of
determining the number of aircraft that
might need these actions.
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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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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-2014-0120; 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):
■
2014–16–08 Bombardier, Inc.: Amendment
39–17932. Docket No. FAA–2014–0120;
Directorate Identifier 2013–NM–056–AD.
(a) Effective Date
This AD becomes effective September 23,
2014.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to the Bombardier, Inc.
airplanes, certificated in any category,
identified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) Model CL–215–6B11 (CL–215T Variant)
airplanes, serial numbers 1056, 1057, 1061,
1080, 1109, 1113, 1114, 1115, 1116, 1117,
1118, 1119, 1120, 1121, 1122, and 1125.
(2) Model CL–215–6B11 (CL–415 Variant)
airplanes, serial numbers 2001 through 2067
inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/Pylons.
(e) Reason
This AD was prompted by several reports
indicating that shorter nacelle strut bushings
were inadvertently installed on certain
airplanes. We are issuing this AD to detect
and correct inadequate nacelle strut
bushings, which provide insufficient
engagement in the strut fork end, and could
deform under the bearing load and lead to
the failure of the joint.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection of the Bushing
Within 3 months after the effective date of
this AD: Do a general visual inspection to
determine the part number of the left and
right nacelle upper strut bushings, in
accordance with the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 215–A3173, dated April 11, 2012
(for Model CL–215–6B11 (CL–215T Variant)
airplanes); or Bombardier Alert Service
Bulletin 215–A4453, dated April 10, 2012
(for Model CL–215–6B11 (CL–415 Variant)
airplanes).
(1) If any bushing with part number (P/N)
85410265–103 is installed: Before further
flight, install the bolts and preload indicating
(PLI) washers, in accordance with paragraph
2.G. of the Accomplishment Instructions of
Bombardier Alert Service Bulletin 215–
A3173, dated April 11, 2012 (for Model CL–
215–6B11 (CL–215T Variant) airplanes); or
Bombardier Alert Service Bulletin 215–
A4453, dated April 10, 2012 (for Model CL–
215–6B11 (CL–415 Variant) airplanes).
(2) If any bushing with P/N 85410265–105
is installed in either the left or right nacelle:
Do the actions in paragraph (h) of this AD.
(h) Replacement or Repair of the Bushing
If any bushing with P/N 85410265–105 is
found installed during the inspection
required by paragraph (g) of this AD: Before
further flight, do the actions specified in
paragraph (h)(1) or (h)(2) of this AD.
(1) Replace the bushing in accordance with
paragraph 2.E. of the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 215–A3173, dated April 11, 2012
(for Model CL–215–6B11 (CL–215T Variant)
airplanes); or Bombardier Alert Service
Bulletin 215–A4453, dated April 10, 2012
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(for Model CL–215–6B11 (CL–415 Variant)
airplanes); and continue with the installation
of the bolt and PLI washer, in accordance
with paragraph 2.G. of the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 215–A3173, dated April 11, 2012
(for Model CL–215–6B11 (CL–215T Variant)
airplanes); or Bombardier Alert Service
Bulletin 215–A4453, dated April 10, 2012
(for Model CL–215–6B11 (CL–415 Variant)
airplanes).
(2) Repair the bushing in accordance with
paragraph 2.F. of the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 215–A3173, dated April 11, 2012
(for Model CL–215–6B11 (CL–215T Variant)
airplanes); or Bombardier Alert Service
Bulletin 215–A4453, dated April 10, 2012
(for Model CL–215–6B11 (CL–415 Variant)
airplanes); and continue with the installation
of the bolt and PLI washer, in accordance
with paragraph 2.G. of the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 215–A3173, dated April 11, 2012
(for Model CL–215–6B11 (CL–215T Variant)
airplanes); or Bombardier Alert Service
Bulletin 215–A4453, dated April 10, 2012
(for Model CL–215–6B11 (CL–415 Variant)
airplanes).
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(i) Replacement of Repaired Bushing
For any bushing that has been repaired as
specified in paragraph (h)(2) of this AD:
Within 5,000 flight hours after accomplishing
the repair or at the next engine removal,
whichever occurs first, replace the bushing
with P/N 85410265–103, in accordance with
paragraph 2.E. of the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 215–A3173, dated April 11, 2012
(for Model CL–215–6B11 (CL–215T Variant)
airplanes); or Bombardier Alert Service
Bulletin 215–A4453, dated April 10, 2012
(for Model CL–215–6B11 (CL–415 Variant)
airplanes); and continue with the installation
of the bolt and PLI washer, in accordance
with paragraph 2.G. of the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 215–A3173, dated April 11, 2012
(for Model CL–215–6B11 (CL–215T Variant)
airplanes); or Bombardier Alert Service
Bulletin 215–A4453, dated April 10, 2012
(for Model CL–215–6B11 (CL–415 Variant)
airplanes).
(j) Airplanes for Which No Further Action Is
Required
(1) For airplanes on which a general visual
inspection specified in paragraph (g) of this
AD is done and it is determined that nacelle
strut bushings having P/N 85410265–103 are
installed in the airplane: No further actions
are required by this AD, provided the actions
specified in paragraph (g)(1) of this AD have
been done.
(2) For airplanes on which nacelle strut
bushings having P/N 85410265–103 are
installed as specified in paragraph (h)(1) or
(i) of this AD: No further actions are required
by this AD.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, FAA,
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has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the ACO, send it to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7300; fax 516–794–5531.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
Engine and Propeller Directorate, FAA; or
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.
(l) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2013–06, dated
February 27, 2013, for related information.
This MCAI may be found in the AD docket
on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-0120-0002.
(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) Bombardier Alert Service Bulletin 215–
A3173, dated April 11, 2012.
(ii) Bombardier Alert Service Bulletin 215–
A4453, dated April 10, 2012.
(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.
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
48957
Issued in Renton, Washington, on July 30,
2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–18863 Filed 8–18–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1158; Directorate
Identifier 2011–NM–232–AD; Amendment
39–17501; AD 2013–13–13]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A310 series airplanes;
and Model A300 B4–600, B4–600R, and
F4–600R series airplanes, and Model
A300 C4–605R Variant F airplanes
(collectively called A300–600 series
airplanes). This AD was prompted by
the revision of certain airworthiness
limitation items (ALI) documents,
which require more restrictive
maintenance requirements and
airworthiness limitations. This AD
requires revising the maintenance or
inspection program to incorporate the
limitations section. We are issuing this
AD to prevent fatigue cracking, damage,
or corrosion in principal structural
elements, which could result in reduced
structural integrity of the airplane.
DATES: This AD becomes effective
September 23, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 23, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2012-1158 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 Airbus SAS,
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
SUMMARY:
E:\FR\FM\19AUR1.SGM
19AUR1
]]>Agencies
[Federal Register Volume 79, Number 160 (Tuesday, August 19, 2014)]
[Rules and Regulations]
[Pages 48954-48957]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-18863]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0120; Directorate Identifier 2013-NM-056-AD;
Amendment 39-17932; AD 2014-16-08]
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-215-6B11 (CL-215T Variant), and CL-215-6B11
(CL-415 Variant) airplanes. This AD was prompted by several reports
indicating that shorter nacelle strut bushings were inadvertently
installed on certain airplanes. This AD requires a general visual
inspection of the left and right nacelle upper strut bushings;
installation of the bolts and preload indicating (PLI) washers, if
necessary; and replacement of the bushing or repair of the bushing
installation, if necessary. We are issuing this AD to detect and
correct inadequate nacelle strut bushings, which provide insufficient
engagement in the strut fork end, and could deform under the bearing
load and lead to the failure of the joint.
DATES: This AD becomes effective September 23, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 23,
2014.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0120; 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: Ricardo Garcia, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; phone 516-228-7331; 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-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant)
airplanes. The NPRM published in the Federal Register on February 27,
2014 (79 FR 11022).
Transport Canada Civil Aviation, which is the aviation authority
for
[[Page 48955]]
Canada, has issued Canadian Airworthiness Directive CF-2013-06, dated
February 27, 2013 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition certain Bombardier, Inc. Model CL-215-6B11 (CL-215T Variant),
and CL-215-6B11 (CL-415 Variant) airplanes. The MCAI states:
It was discovered in several cases that nacelle strut bushings
with part number (P/N), 85410265-105, have been inadvertently
installed in lieu of P/N 85410265-103. Bushing P/N 85410265-105 is
shorter than bushing P/N 85410265-103 and provides for less
engagement in the strut fork end, P/N 215T16534-12/-13, which may
deform under the bearing load leading to the failure of the joint.
The actions for this AD include a general visual inspection of the
left and right nacelle upper strut bushings; installation of the bolts
and PLI washers, if necessary; and replacement of the bushing or repair
of the bushing installation, if necessary. You may examine the MCAI in
the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0120-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 11022, February 27,
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 11022, February 27, 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 11022, February 27,
2014) about these proposed changes. However, a comment was provided for
another NPRM having Directorate Identifier 2012-NM-101-AD (78 FR 78285,
December 26, 2013). The commenter stated the following: ``The proposed
wording, being specific to repairs, eliminates the interpretation that
Airbus messages are acceptable for approving minor deviations
(corrective actions) needed during accomplishment of an AD mandated
Airbus service bulletin.''
This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this AD to obtain corrective actions from a
manufacturer, the action must be accomplished using a method approved
by the FAA, TCCA, or Bombardier's TCCA Design Approval Organization
(DAO).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DAO, the approval must include the DAO-authorized
signature. The DAO signature indicates that the data and information
contained in the document are TCCA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DAO-authorized signature approval are not TCCA-
approved, unless TCCA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that in many cases
the foreign manufacturer's service bulletin and the foreign authority's
MCAI might have been issued some time before the FAA AD. Therefore, the
DOA might have provided U.S. operators with an approved repair,
developed with full awareness of the unsafe condition, before the FAA
AD is issued. Under these circumstances, to comply with the FAA AD, the
operator would be required to go back to the manufacturer's DOA and
obtain a new approval document, adding time and expense to the
compliance process with no safety benefit.
Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this AD. Before adopting such a
requirement, the FAA will coordinate with affected DAHs and verify they
are prepared to implement means to ensure that their repair approvals
consider the unsafe condition addressed in this AD. Any such
requirements will be adopted through the normal AD rulemaking process,
including notice-and-comment procedures, when appropriate.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``DAH with State of Design Authority design
organization approval,'' but instead we have provided the specific
delegation approval granted by the State of Design
[[Page 48956]]
Authority for the DAH in the Contacting the Manufacturer paragraph of
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 11022, February 27, 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 11022, February 27, 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 5 airplanes of U.S. registry.
We also estimate that it will take about 4 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $0 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $1,700, or $340 per product.
In addition, we estimate that any necessary follow-on actions will
take about 4 work-hours and require parts costing $0, for a cost of
$340 per product. We have no way of determining the number of aircraft
that might 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0120; 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):
2014-16-08 Bombardier, Inc.: Amendment 39-17932. Docket No. FAA-
2014-0120; Directorate Identifier 2013-NM-056-AD.
(a) Effective Date
This AD becomes effective September 23, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Bombardier, Inc. airplanes, certificated
in any category, identified in paragraphs (c)(1) and (c)(2) of this
AD.
(1) Model CL-215-6B11 (CL-215T Variant) airplanes, serial
numbers 1056, 1057, 1061, 1080, 1109, 1113, 1114, 1115, 1116, 1117,
1118, 1119, 1120, 1121, 1122, and 1125.
(2) Model CL-215-6B11 (CL-415 Variant) airplanes, serial numbers
2001 through 2067 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.
(e) Reason
This AD was prompted by several reports indicating that shorter
nacelle strut bushings were inadvertently installed on certain
airplanes. We are issuing this AD to detect and correct inadequate
nacelle strut bushings, which provide insufficient engagement in the
strut fork end, and could deform under the bearing load and lead to
the failure of the joint.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection of the Bushing
Within 3 months after the effective date of this AD: Do a
general visual inspection to determine the part number of the left
and right nacelle upper strut bushings, in accordance with the
Accomplishment Instructions of Bombardier Alert Service Bulletin
215-A3173, dated April 11, 2012 (for Model CL-215-6B11 (CL-215T
Variant) airplanes); or Bombardier Alert Service Bulletin 215-A4453,
dated April 10, 2012 (for Model CL-215-6B11 (CL-415 Variant)
airplanes).
(1) If any bushing with part number (P/N) 85410265-103 is
installed: Before further flight, install the bolts and preload
indicating (PLI) washers, in accordance with paragraph 2.G. of the
Accomplishment Instructions of Bombardier Alert Service Bulletin
215-A3173, dated April 11, 2012 (for Model CL-215-6B11 (CL-215T
Variant) airplanes); or Bombardier Alert Service Bulletin 215-A4453,
dated April 10, 2012 (for Model CL-215-6B11 (CL-415 Variant)
airplanes).
(2) If any bushing with P/N 85410265-105 is installed in either
the left or right nacelle: Do the actions in paragraph (h) of this
AD.
(h) Replacement or Repair of the Bushing
If any bushing with P/N 85410265-105 is found installed during
the inspection required by paragraph (g) of this AD: Before further
flight, do the actions specified in paragraph (h)(1) or (h)(2) of
this AD.
(1) Replace the bushing in accordance with paragraph 2.E. of the
Accomplishment Instructions of Bombardier Alert Service Bulletin
215-A3173, dated April 11, 2012 (for Model CL-215-6B11 (CL-215T
Variant) airplanes); or Bombardier Alert Service Bulletin 215-A4453,
dated April 10, 2012
[[Page 48957]]
(for Model CL-215-6B11 (CL-415 Variant) airplanes); and continue
with the installation of the bolt and PLI washer, in accordance with
paragraph 2.G. of the Accomplishment Instructions of Bombardier
Alert Service Bulletin 215-A3173, dated April 11, 2012 (for Model
CL-215-6B11 (CL-215T Variant) airplanes); or Bombardier Alert
Service Bulletin 215-A4453, dated April 10, 2012 (for Model CL-215-
6B11 (CL-415 Variant) airplanes).
(2) Repair the bushing in accordance with paragraph 2.F. of the
Accomplishment Instructions of Bombardier Alert Service Bulletin
215-A3173, dated April 11, 2012 (for Model CL-215-6B11 (CL-215T
Variant) airplanes); or Bombardier Alert Service Bulletin 215-A4453,
dated April 10, 2012 (for Model CL-215-6B11 (CL-415 Variant)
airplanes); and continue with the installation of the bolt and PLI
washer, in accordance with paragraph 2.G. of the Accomplishment
Instructions of Bombardier Alert Service Bulletin 215-A3173, dated
April 11, 2012 (for Model CL-215-6B11 (CL-215T Variant) airplanes);
or Bombardier Alert Service Bulletin 215-A4453, dated April 10, 2012
(for Model CL-215-6B11 (CL-415 Variant) airplanes).
(i) Replacement of Repaired Bushing
For any bushing that has been repaired as specified in paragraph
(h)(2) of this AD: Within 5,000 flight hours after accomplishing the
repair or at the next engine removal, whichever occurs first,
replace the bushing with P/N 85410265-103, in accordance with
paragraph 2.E. of the Accomplishment Instructions of Bombardier
Alert Service Bulletin 215-A3173, dated April 11, 2012 (for Model
CL-215-6B11 (CL-215T Variant) airplanes); or Bombardier Alert
Service Bulletin 215-A4453, dated April 10, 2012 (for Model CL-215-
6B11 (CL-415 Variant) airplanes); and continue with the installation
of the bolt and PLI washer, in accordance with paragraph 2.G. of the
Accomplishment Instructions of Bombardier Alert Service Bulletin
215-A3173, dated April 11, 2012 (for Model CL-215-6B11 (CL-215T
Variant) airplanes); or Bombardier Alert Service Bulletin 215-A4453,
dated April 10, 2012 (for Model CL-215-6B11 (CL-415 Variant)
airplanes).
(j) Airplanes for Which No Further Action Is Required
(1) For airplanes on which a general visual inspection specified
in paragraph (g) of this AD is done and it is determined that
nacelle strut bushings having P/N 85410265-103 are installed in the
airplane: No further actions are required by this AD, provided the
actions specified in paragraph (g)(1) of this AD have been done.
(2) For airplanes on which nacelle strut bushings having P/N
85410265-103 are installed as specified in paragraph (h)(1) or (i)
of this AD: No further actions are required by this AD.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York 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) 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 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.
(l) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
Canadian Airworthiness Directive CF-2013-06, dated February 27,
2013, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0120-0002.
(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) Bombardier Alert Service Bulletin 215-A3173, dated April 11,
2012.
(ii) Bombardier Alert Service Bulletin 215-A4453, dated April
10, 2012.
(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 30, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-18863 Filed 8-18-14; 8:45 am]
BILLING CODE 4910-13-P
