Airworthiness Directives; Bombardier, Inc. Airplanes, 49434-49439 [2014-17549]
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49434
Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations
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.
(k) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2012–0233, dated November 7,
2012, for related information. This MCAI
may be found in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0124-0002.
(l) Material Incorporated by Reference
None.
Issued in Renton, Washington, on August
4, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–19549 Filed 8–20–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–1065; Directorate
Identifier 2011–NM–230–AD; Amendment
39–17915; AD 2014—15–13]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2005–15–
04 for certain Bombardier, Inc. Model
CL–600–1A11 (CL–600), CL–600–2A12
(CL–601), and CL–600–2B16 (CL–601–
3A, CL–601–3R, and CL–604 Variants)
airplanes. AD 2005–15–04 required
operators to assign serial numbers or
part numbers to certain landing gear
parts; establish the number of landings
on the parts, if necessary; and revise the
Airworthiness Limitations Section
(ALS) of the Instructions for Continued
Airworthiness (ICA) to reflect the new
life limits of the landing gear parts. This
new AD adds airplanes to the
applicability, requires operators to
assign serial numbers or part numbers to
certain additional landing gear parts to
establish the number of landings on the
parts if necessary, and requires
operators to record in all required
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SUMMARY:
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airplane technical records and manuals
the new part numbers, serial numbers,
and landings assigned to these parts.
This AD was prompted by reports that
landing gear parts that have safe-life
limits but do not have serial numbers or
part numbers can be removed from one
landing gear and re-installed on another,
making tracking difficult. We are issuing
this AD to prevent life-limited landing
gear parts from being used beyond their
safe-life limits, which could lead to
collapse of the landing gear.
DATES: This AD becomes effective
September 25, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 25, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of August 30, 2005 (70 FR
43032, July 26, 2005).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-1065; 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 Bombardier, Inc./Canadair service
information identified in this AD,
ˆ
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. For
Messier-Dowty service information
identified in this AD, contact Messier
Services Americas, Customer Support
Center, 45360 Severn Way, Sterling, VA
20166–8910; phone: 703–450–8233; fax:
703–404–1621; Internet: https://
techpubs.services/messier-dowty.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:
Andreas Rambalakos, 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) 228–7345;
fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
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part 39 to supersede AD 2005–15–04,
Amendment 39–14193 (70 FR 43032,
July 26, 2005). AD 2005–15–04 applied
to certain Bombardier, Inc. Model CL–
600–1A11 (CL–600), CL–600–2A12 (CL–
601), and CL–600–2B16 (CL–601–3A,
CL–601–3R, and CL–604 Variants)
airplanes. The NPRM published in the
Federal Register on December 30, 2013
(78 FR 79329). The NPRM was
prompted by reports that landing gear
parts that have safe-life limits but do not
have serial numbers or part numbers
can be removed from one landing gear
and re-installed on another, making
tracking difficult. The NPRM proposed
to add airplanes to the applicability,
require operators to assign serial
numbers or part numbers to certain
additional landing gear parts to
establish the number of landings on the
parts if necessary, and requires
operators to record in all required
airplane technical records and manuals
the new part numbers, serial numbers,
and landings assigned to these parts. We
are issuing this AD to prevent lifelimited landing gear parts from being
used beyond their safe-life limits, which
could lead to collapse of the landing
gear.
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, has issued
Canadian Airworthiness Directives CF–
2003–18R2, dated September 28, 2011;
CF–2003–20R1, dated September 28,
2011; and CF–2003–21R2, dated
September 28, 2011 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’); to correct an unsafe condition
for certain Bombardier, Inc. Model CL–
600–1A11 (CL–600), CL–600–2A12 (CL–
601), and CL–600–2B16 (CL–601–3A,
CL–601–3R, and CL–604 Variants)
airplanes. The MCAI states:
Certain landing gear parts that are listed in
the aeroplane model Airworthiness
Limitations Section, as safe life items with
structural life limits, could be rotable and
may not have been serialized, making
tracking difficult. This [Canadian
airworthiness] directive mandates that such
parts be serialized. This [Canadian
airworthiness] directive also provides the
procedure to determine the number of
landings for those parts where the service
history cannot be established.
*
*
*
*
*
[T]his [Canadian Airworthiness] directive
* * * mandate[s] serialization of * * *
additional landing gear parts.
This AD also adds airplanes to the
applicability. The unsafe condition is
using life-limited landing gear parts
beyond their safe-life limits, which
could lead to collapse of the landing
gear. You may examine the MCAI in the
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Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2013-10650002.
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Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (78
FR 79329, December 30, 2013) 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.
We have become 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 ADmandated 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 actions must be
accomplished using a method approved
by the FAA, Transport Canada Civil
Aviation (TCCA), or Bombardier’s TCCA
Design Approval Organization (DAO).
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DAO, the approval must include
the DAO-authorized signature. The DAO
signature indicates that the data and
information contained in the document
are TCCA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DAO-authorized signature approval are
not TCCA-approved, unless TCCA
directly approves the manufacturer’s
message or other information.
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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.
We also have decided not to include
a generic reference to either the
‘‘delegated agent’’ or ‘‘design approval
holder (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 available 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 (78 FR
79329, December 30, 2013) for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 79329,
December 30, 2013).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 419
airplanes of U.S. registry.
The actions that were required by AD
2005–15–04, Amendment 39–14193 (70
FR 43032, July 26, 2005), that are
retained in this AD take up to 13 workhours per product, at an average labor
rate of $85 per work hour. Based on
these figures, the estimated cost of the
currently required actions is up to
$1,105 per product.
We estimate that it would take about
9 work-hours per product to comply
with the new basic requirements of this
AD. The average labor rate is $85 per
work-hour. Based on these figures, we
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49435
estimate the cost of this AD on U.S.
operators to be $320,535, or $765 per
product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-1065; 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.
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Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations
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
removing Airworthiness Directive (AD)
2005–15–04, Amendment 39–14193 (70
FR 43032, July 26, 2005), and adding the
following new AD:
■
2014–15–13 Bombardier, Inc.: Amendment
39–17915. Docket No. FAA–2013–1065;
Directorate Identifier 2011–NM–230–AD.
(a) Effective Date
This AD becomes effective September 25,
2014.
(b) Affected ADs
This AD replaces AD 2005–15–04,
Amendment 39–14193 (70 FR 43032, July 26,
2005).
(c) Applicability
This AD applies to Bombardier, Inc.
airplanes, certificated in any category, as
identified in paragraphs (c)(1) through (c)(4)
of this AD.
(1) Model CL–600–1A11 (CL–600)
airplanes, serial numbers 1004 through 1085
inclusive.
(2) Model CL–600–2A12 (CL–601)
airplanes, serial numbers 3001 through 3066
inclusive;
(3) Model CL–600–2B16 (CL–601–3A and
CL–601–3R Variants) airplanes, serial
numbers 5001 through 5194 inclusive.
(4) Model CL–600–2B16 (CL–604 Variant)
airplanes, serial numbers 5301 through 5573
inclusive, 5579, and 5595.
(5) This AD requires revisions to certain
operator maintenance documents to include
new actions (e.g., inspections). Compliance
with these actions is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by this AD, the operator
may not be able to accomplish the actions
described in the revisions. In this situation,
to comply with 14 CFR 91.403(c), the
operator must request approval for an
alternative method of compliance according
to paragraph (r) of this AD. The request
should include a description of changes to
the required actions that will ensure the
continued damage tolerance of the affected
structure.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Reason
This AD was prompted by reports that
landing gear parts that have safe-life limits
but do not have serial numbers (S/Ns) or part
numbers (P/Ns) can be removed from one
landing gear and re-installed on another,
making tracking difficult. We are issuing this
AD to prevent life-limited landing gear parts
from being used beyond their safe-life limits,
which could lead to collapse of the landing
gear.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Requirement To Add S/Ns or
P/Ns
This paragraph restates the actions
required by paragraph (f) of AD 2005–15–04,
Amendment 39–14193 (70 FR 43032, July 26,
2005), with revised affected airplanes. Except
for Model CL–600–2B16 airplanes having S/
Ns 5514 through 5595 inclusive: At the
applicable compliance time specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD,
add serial numbers and part numbers, as
applicable, to the parts identified in the
applicable service bulletin specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
Do all actions in accordance with the
applicable service bulletin specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) For parts identified in Bombardier
Service Bulletin 600–0710, Revision 01,
dated December 15, 2003; and Bombardier
Service Bulletin 601–0546, Revision 01,
dated December 15, 2003; as having a
compliance time of ‘‘five years for the parts
listed in Part A’’: Within 60 months after
August 30, 2005 (the effective date of AD
2005–15–04, Amendment 39–14193 (70 FR
43032, July 26, 2005)).
(2) For parts identified in Bombardier
Service Bulletin 600–0710, Revision 01,
dated December 15, 2003; and Bombardier
Service Bulletin 601–0546, Revision 01,
dated December 15, 2003; as having a
compliance time of ‘‘ten years for the parts
listed in Part B’’: Within 120 months after
August 30, 2005 (the effective date of AD
2005–15–04, Amendment 39–14193 (70 FR
43032, July 26, 2005)).
(3) For parts identified in Bombardier
Service Bulletin 604–32–014, dated May 31,
2002, as having a compliance time of ‘‘no
later than a calendar time of 8 years’’: Within
96 months after August 30, 2005 (the
effective date of AD 2005–15–04,
Amendment 39–14193 (70 FR 43032, July 26,
2005)).
Note 1 to paragraph (g) of this AD: The
Bombardier service bulletins identified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD
refer to the Messier-Dowty service bulletins
identified in table 1 to paragraph (g) of this
AD as additional sources of guidance for
adding part numbers or serial numbers by
vibro-peening the numbers on main landing
gear (MLG) and nose landing gear (NLG)
components that do not have them; and for
determining the number of landings for parts
without a part number or serial number on
which the time since new (TSN) and cycles
since new (CSN) have not been tracked.
TABLE 1 TO PARAGRAPH (g) OF THIS AD—MESSIER-DOWTY SERVICE BULLETINS
Landing gear component—
Corresponding bombardier service bulletin(s)—
Messier–Dowty service bulletin—
CL–600–1A11 (CL–600), CL–600–2A12 (CL–
601) and CL–600–2B16 (CL–601–3A and
CL–601–3R) airplanes.
CL–600–2B16 (CL–604) airplanes ...................
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Model—
MLG side strut retraction actuator eye
bolt.
MLG shock strut .........
600–0710 and 601–
0546.
M–DT SB104467009/010–32–1, dated March
19, 2001.
604–32–014 ...............
CL–600–2B16 (CL–604) airplanes ...................
CL–600–1A11 (CL–600), CL–600–2A12 (CL–
601) and CL–600–2B16 (CL–601–3A and
CL–601–3R) airplanes.
CL–600–1A11 (CL–600) airplanes ...................
NLG shock strut .........
NLG drag brace hinge
pin.
604–32–014 ...............
600–0710 and 601–
0546.
M–DT SB19090–32–4, dated March 19,
2001.
M–DT SB20020–32–5, dated July 12, 2001.
M–DT SB200814001–32–3, dated March 19,
2001.
MLG shock strut .........
600–0710 ...................
CL–600–1A11 (CL–600) airplanes ...................
NLG shock strut .........
600–0710 ...................
CL–600–2A12 (CL–601) and CL–600–2B16
(CL–601–3A and CL–601–3R) airplanes.
MLG shock strut pin ...
601–0546 ...................
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M–DT SB200922001/2–32–6, dated March
19, 2001.
M–DT SB200924003/004–32–16, dated July
12, 2001.
M–DT SB6100–32–10, dated March 19,
2001.
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Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations
49437
TABLE 1 TO PARAGRAPH (g) OF THIS AD—MESSIER-DOWTY SERVICE BULLETINS—Continued
Model—
Landing gear component—
Corresponding bombardier service bulletin(s)—
Messier–Dowty service bulletin—
CL–600–1A11 (CL–600), CL–600–2A12 (CL–
601) and CL–600–2B16 (CL–601–3A and
CL–601–3R) airplanes.
CL–600–1A11 (CL–600), CL–600–2A12 (CL–
601) and CL–600–2B16 (CL–601–3A and
CL–601–3R) airplanes.
CL–600–2A12 (CL–601) and CL–600–2B16
(CL–601–3A and CL–601–3R) airplanes.
MLG side strut retraction actuator.
600–0710 and 601–
0546.
M–DT SB6500–32–1, dated March 19, 2001.
NLG drag brace hinge
pin.
600–0710 and 601–
0546.
M–DT SB7200–32–6, dated March 19, 2001.
NLG shock strut .........
601–0546 ...................
M–DT SB7300–32–16, dated July 12, 2001.
(h) Retained Requirement—Establishment of
the Number of Landings
table 1 to paragraph (g) of this AD to establish
the TSN or CSN, and record the newly
calculated TSN or CSN in the airplane log
books.
This paragraph restates the actions
required by paragraph (g) of AD 2005–15–04,
Amendment 39–14193 (70 FR 43032, July 26,
2005), with revised affected airplanes. Except
for Model CL–600–2B16 airplanes having S/
Ns 5314 through 5595 inclusive: At the
applicable time specified in paragraph (g) of
this AD, if a component does not have a
serial number and the CSN or TSN were not
tracked, use the formula in the applicable
Messier-Dowty service bulletin specified in
(i) Retained Requirement To Revise the
Airworthiness Limitations Section (ALS)
This paragraph restates the revision
required by paragraph (h) of AD 2005–15–04,
Amendment 39–14193 (70 FR 43032, July 26,
2005), with revised affected airplanes. Except
for Model CL–600–2B16 airplanes having S/
Ns 5514 through 5595 inclusive: Within 30
days after August 30, 2005 (the effective date
of AD 2005–15–04), revise the ALS of the
applicable Instructions for Continued
Airworthiness to reflect the new life limits of
the landing gear parts by inserting copies of
the Canadair temporary revisions (TR)
specified in table 2 to paragraph (i) of this AD
into the ALS of the applicable Canadair
Time-Limits/Maintenance Check Manual.
When the contents of the TRs are included
in the general revisions of the ALS, these TRs
may be removed provided the relevant
information in the ALS is identical to that in
the TRs.
TABLE 2 TO PARAGRAPH (i) OF THIS AD—CANADAIR TEMPORARY REVISIONS
Applicable canadair time–
limits/maintenance check
manual—
Canadair temporary revision—
Manual section—
CL–600–1A11 (CL–600) airplanes ............................................
CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and
CL–601–3R) airplanes.
CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and
CL–601–3R) airplanes.
CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and
CL–601–3R) airplanes.
CL–600–2B16 (CL–604) airplanes ............................................
CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and
CL–601–3R) airplanes.
CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and
CL–601–3R) airplanes.
CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A and
CL–601–3R) airplanes.
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Model—
5–116, dated April 11, 2002 ...
5–190, dated April 11, 2002 ...
5–10–10
5–10–10
PSP 605.
PSP 601–5.
5–191, dated April 11, 2002 ...
5–10–11
PSP 601–5.
5–192, dated April 11, 2002 ...
5–10–12
PSP 601–5.
5–2–6, dated April 11, 2002 ...
5–204, dated April 11, 2002 ...
5–10–10
5–10–10
CL–604.
PSP 601A–5.
5–205, dated April 11, 2002 ...
5–10–11
PSP 601A–5.
5–206, dated April 11, 2002 ...
5–10–12
PSP 601A–5.
(j) Retained Parts Installation Limitation
This paragraph restates the limitations
specified in paragraph (i) of AD 2005–15–04,
Amendment 39–14193 (70 FR 43032, July 26,
2005), with revised affected airplanes. Except
for Model CL–600–2B16 airplanes having
serial numbers 5514 through 5595 inclusive:
As of August 30, 2005 (the effective date of
AD 2005–15–04), no person may install on
any airplane a landing gear part, unless it has
had the applicable part number or serial
number added in accordance with paragraph
(g) of this AD; and has had the number of
landings established in accordance with
paragraph (h) of this AD.
(k) Retained Stipulation of Information of
No Reporting
This paragraph restates the stipulation
specified in paragraph (j) of AD 2005–15–04,
Amendment 39–14193 (70 FR 43032, July 26,
2005). Although the service bulletins
VerDate Mar<15>2010
18:53 Aug 20, 2014
Jkt 232001
identified in paragraph (g) of this AD specify
that operators should submit incorporation
notices to Bombardier after each new part
number or serial number and landings
assigned to these parts is added, this AD does
not include that action.
(l) New Requirement of this AD: Add Serial
Numbers and Part Numbers
(1) For Model CL–600–2B16 (CL–604
Variant) airplanes: Within 96 months after
the effective date of this AD, add serial
numbers and part numbers, as applicable, to
the parts identified in paragraphs (l)(1)(i) and
(l)(1)(ii) of this AD, as applicable, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
604–32–014, Revision 02, dated May 9, 2011,
including Appendix 1, dated May 9, 2011,
and Service Bulletin Information Sheet,
dated July 6, 2010.
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
(i) For airplanes having S/Ns 5301 through
5513 inclusive: Main fitting/drag stay pin of
the NLG having P/N 200811721.
(ii) For airplanes having S/Ns 5301 through
5573 inclusive, 5579, and 5595: NLG
crossbeam pins having P/N 200814601 and
NLG center hinge pins having P/N
200814624.
(2) For Bombardier Model CL–600–2A12
(CL–601) airplanes and Model CL–600–2B16
(CL–601–3A and CL–601–3R Variants)
airplanes: Within 60 months after the
effective date of this AD, add serial numbers
and part numbers, as applicable, to left and
right MLG side strut pins having P/N 6318–
1 or 6318–3; and to left and right MLG hinge
pins having P/N 6329–3; in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 601–0546,
Revision 03, dated May 9, 2011, including
Appendix 1, dated May 9, 2011, and Service
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49438
Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations
Bulletin Information Sheet, dated July 6,
2010.
(3) For Bombardier Model CL–600–2A12
(CL–601) airplanes and Model CL–600–2B16
(CL–601–3A and CL–601–3R Variants)
airplanes: Within 120 months after the
effective date of this AD, add serial numbers
and part numbers, as applicable, to NLG
main fitting/drag stay pins having P/N
200811721; NLG drag brace pivot pins having
P/N 200814601; and left and right MLG
pintle pins having P/N 6324–1; in accordance
with the Accomplishment Instructions of
Bombardier Service Bulletin 601–0546,
Revision 03, dated May 9, 2011, including
Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6,
2010.
(4) For Bombardier Model CL–600–1A11
(CL–600) airplanes: Within 120 months after
the effective date of this AD, add serial
numbers and part numbers, as applicable, to
NLG main fitting/drag stay pins having P/N
200811721 and NLG drag brace pivot pins
having P/N 200814601, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 600–0710,
Revision 03, dated May 9, 2011, including
Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6,
2010.
(m) New Requirement of This AD: Establish
the Number of Landings (CSN)
At the applicable times specified in
paragraph (l) of this AD: If a component does
not have a serial number and the CSN were
not tracked, use Appendix 1, dated May 9,
2011, of the applicable service bulletin
specified in paragraph (m)(1), (m)(2), or
(m)(3) of this AD to establish the number of
landings (CSN).
(1) Bombardier Service Bulletin 604–32–
014, Revision 02, dated May 9, 2011,
including Service Bulletin Information Sheet,
dated July 6, 2010 (for Bombardier Model
CL–600–2B16 (CL–604 Variant) airplanes).
(2) Bombardier Service Bulletin 601–0546,
Revision 03, dated May 9, 2011, including
Service Bulletin Information Sheet, dated
July 6, 2010 (for Model CL–600–2A12 (CL–
601) airplanes and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes).
(3) Bombardier Service Bulletin 600–0710,
Revision 03, dated May 9, 2011, including
Service Bulletin Information Sheet, dated
July 6, 2010 (for Bombardier Model CL–600–
1A11 (CL–600) airplanes).
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(n) New Requirement of This AD: Records
Update
Concurrently with the actions specified in
paragraphs (l) and (m) of this AD: Record any
newly calculated CSN, new part numbers,
and new serial numbers in the airplane
technical records and manuals.
(o) New Requirement of This AD: Parts
Installation Limitation
As of the effective date of this AD, no
person may install on any airplane a landing
gear part identified in paragraph (l) of this
AD, unless it has had the applicable part
number or serial number added as required
by paragraph (l) of this AD, and had the CSN
established as required by paragraph (m) of
this AD.
VerDate Mar<15>2010
18:53 Aug 20, 2014
Jkt 232001
(p) New Action of This AD: Optional Method
of Compliance
Accomplishing the action required by
paragraph (g) of this AD, in accordance with
the Accomplishment Instructions of the
applicable service bulletin specified in
paragraph (p)(1), (p)(2), or (p)(3) of this AD,
is acceptable for compliance with the
requirements of paragraph (g) of this AD.
(1) Bombardier Service Bulletin 601–0546,
Revision 03, dated May 9, 2011, including
Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6,
2010 (for Model CL–600–2A12 (CL–601)
airplanes and Model CL–600–2B16 (CL–601–
3A and CL–601–3R Variants) airplanes).
(2) Bombardier Service Bulletin 604–32–
014, Revision 02, dated May 9, 2011,
including Appendix 1, dated May 9, 2011,
and Service Bulletin Information Sheet,
dated July 6, 2010 (for Model CL–600–2B16
(CL–604 Variant) airplanes).
(3) Bombardier Service Bulletin 600–0710,
Revision 03, dated May 9, 2011, including
Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6,
2010 (for Model CL–600–1A11 (CL–600)
airplanes).
(q) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before
August 30, 2005 (the effective date of AD
2005–15–04, Amendment 39–14193 (70 FR
43032, July 26, 2005)), using the applicable
service bulletin specified in paragraph
(q)(1)(i), (q)(1)(ii), or (q)(1)(iii) of this AD,
which are not incorporated by reference in
this AD.
(i) Bombardier Service Bulletin 601–0546,
dated May 31, 2002 (for Model CL–600–2A12
(CL–601) airplanes and Model CL–600–2B16
(CL–601–3A and CL–601–3R Variants)
airplanes).
(ii) Bombardier Service Bulletin 600–0710,
dated May 31, 2002 (for ModelCL–600–1A11
(CL–600) airplanes).
(iii) Bombardier Service Bulletin 604–32–
014, dated May 31, 2002 (for Model CL–600–
2B16 (CL–604 Variant) airplanes).
(2) This paragraph provides credit for the
addition of serial numbers and part numbers
required by paragraph (l) of this AD, if those
actions were performed before the effective
date of this AD using the applicable service
bulletin specified in paragraph (q)(2)(i),
(q)(2)(ii), or (q)(2)(iii) of this AD, which are
not incorporated by reference in this AD.
(i) Bombardier Service Bulletin 604–32–
014, Revision 01, dated October 29, 2007 (for
Bombardier Model CL–600–2B16 (CL–604
Variant) airplanes).
(ii) Bombardier Service Bulletin 601–0546,
Revision 02, dated October 29, 2007 (for
Model CL–600–2A12 (CL–601) airplanes and
Model CL–600–2B16 (CL–601–3A and CL–
601–3R Variants) airplanes).
(iii) Bombardier Service Bulletin 600–0710,
Revision 02, dated October 29, 2007 (for
Bombardier Model CL–600–1A11 (CL–600)
airplanes).
(3) This paragraph provides credit for the
establishment of the CSN required by
paragraph (m) of this AD, if those actions
were performed before the effective date of
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
this AD using the applicable service bulletin
information sheet specified in paragraph
(q)(3)(i), (q)(3)(ii), or (q)(3)(iii) of this AD.
(i) Service Bulletin Information Sheet,
dated July 6, 2010, of Bombardier Service
Bulletin 604–32–014, Revision 01, dated
October 29, 2007 (for Bombardier Model CL–
600–2B16 (CL–604 Variant) airplanes).
(ii) Service Bulletin Information Sheet,
dated July 6, 2010, of Bombardier Service
Bulletin 601–0546, Revision 02, dated
October 29, 2007 (for Bombardier Model CL–
600–2A12 (CL–601) and Model CL–600–2B16
(CL–601–3A and CL–601–3R Variants)
airplanes).
(iii) Service Bulletin Information Sheet,
dated July 6, 2010, of Bombardier Service
Bulletin 600–0710, Revision 02, dated
October 29, 2007 (for Bombardier Model CL–
600–1A11 (CL–600) airplanes).
(r) 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. AMOCs approved previously in
accordance with AD 2005–15–04,
Amendment 39–14193 (70 FR 43032, July 26,
2005), are approved as AMOCs for the
corresponding provisions of 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.
(s) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directives specified in
paragraphs (s)(1)(i), (s)(1)(ii), and (s)(1)(iii) of
this AD for related information. You may
examine the MCAI in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2013-1065-0002.
(i) Canadian Airworthiness Directive CF–
2003–18R2, dated September 28, 2011.
(ii) Canadian Airworthiness Directive CF–
2003–20R1, dated September 28, 2011.
(iii) Canadian Airworthiness Directive CF–
2003–21R2, dated September 28, 2011.
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tkelley on DSK3SPTVN1PROD with RULES
(2) Service information identified in this
AD that is not incorporated by reference in
this AD may be obtained at the addresses
specified in paragraphs (t)(5) and (t)(6) of this
AD.
(t) 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.
(3) The following service information was
approved for IBR on September 25, 2014.
(i) Bombardier Service Bulletin 600–0710,
Revision 03, dated May 9, 2011, including
Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6,
2010.
(ii) Bombardier Service Bulletin 601–0546,
Revision 03, dated May 9, 2011, including
Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6,
2010.
(iii) Bombardier Service Bulletin 604–32–
014, Revision 02, dated May 9, 2011,
including Appendix 1, dated May 9, 2011,
and Service Bulletin Information Sheet,
dated July 6, 2010.
(4) The following service information was
approved for IBR on August 30, 2005 (70 FR
43032, July 26, 2005).
(i) Bombardier Service Bulletin 600–0710,
Revision 01, dated December 15, 2003.
(ii) Bombardier Service Bulletin 601–0546,
Revision 01, dated December 15, 2003.
(iii) Bombardier Service Bulletin 604–32–
014, dated May 31, 2002.
(iv) Canadair Temporary Revision 5–116,
dated April 11, 2002.
(v) Canadair Temporary Revision 5–190,
dated April 11, 2002.
(vi) Canadair Temporary Revision 5–191,
dated April 11, 2002.
(vii) Canadair Temporary Revision 5–192,
dated April 11, 2002.
(viii) Canadair Temporary Revision 5–2–6,
dated April 11, 2002.
(ix) Canadair Temporary Revision 5–204,
dated April 11, 2002.
(x) Canadair Temporary Revision 5–205,
dated April 11, 2002.
(xi) Canadair Temporary Revision 5–206,
dated April 11, 2002.
(xii) Messier-Dowty Service Bulletin M–DT
SB104467009/010–32–1, dated March 19,
2001.
(xiii) Messier-Dowty Service Bulletin M–
DT SB19090–32–4, dated March 19, 2001.
(xiv) Messier-Dowty Service Bulletin M–
DT SB20020–32–5, dated July 12, 2001.
(xv) Messier-Dowty Service Bulletin M–DT
SB200814001–32–3, dated March 19, 2001.
(xvi) Messier-Dowty Service Bulletin M–
DT SB200922001/2–32–6, dated March 19,
2001.
(xvii) Messier-Dowty Service Bulletin M–
DT SB200924003/004–32–16, dated July 12,
2001.
(xviii) Messier-Dowty Service Bulletin M–
DT SB6100–32–10, dated March 19, 2001.
(xix) Messier-Dowty Service Bulletin M–
DT SB6500–32–1, dated March 19, 2001.
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18:53 Aug 20, 2014
Jkt 232001
(xx) Messier-Dowty Service Bulletin M–DT
SB7200–32–6, dated March 19, 2001.
(xxi) Messier-Dowty Service Bulletin M–
DT SB7300–32–16, dated July 12, 2001.
(5) For Bombardier, Inc./Canadair service
information identified in this AD, contact
ˆ
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. For MessierDowty service information identified in this
AD, contact Messier Services Americas,
Customer Support Center, 45360 Severn
Way, Sterling, VA 20166–8910.
(6) 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.
(7) 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. 2014–17549 Filed 8–20–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0511; Directorate
Identifier 2014–CE–023–AD; Amendment
39–17953; AD 2014–15–51]
RIN 2120–AA64
Airworthiness Directives; Embraer S.A.
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
49439
the unsafe condition as cracking of the
barrel nuts at the horizontal stabilizer to
vertical stabilizer attachment joint. We
are issuing this AD to correct the unsafe
condition on these products.
DATES: This AD is effective August 21,
2014 to all persons except those persons
to whom it was made immediately
effective by Emergency AD 2014–15–51,
issued on July 25, 2014, which
contained the requirements of this
amendment.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication identified in this
AD as of August 21, 2014.
We must receive comments on this
AD by October 6, 2014.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Maill: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this AD, contact: EMBRAER S.A.,
Phenom Maintenance Support, Avenida
Brigadeiro Faria Lima, 2170, Putim,
CEP: 12227–901, Sao Jose dos Campos,
Sao Paulo, Brasil; phone: (+55 12) 3927–
1000; Fax: (+55 12) 3927–6600, Ext.
1448; email: phenom.reliability@
embraer.com.br: Internet: https://www.
embraerexecutivejets.com/en-US/
customer-support/Pages/Service-CenterNetwork.aspxt.
AGENCY:
Examining the AD Docket
We are adopting a new
airworthiness directive (AD) for certain
Embraer S.A. Model EMB–500
airplanes. This AD was sent previously
to all known U.S. owners and operators
of these airplanes as an emergency AD.
This AD requires an inspection and
replacement as necessary of the barrel
nuts at the horizontal stabilizer to
vertical stabilizer attachment joint. This
AD was prompted by mandatory
continuing airworthiness information
(MCAI) issued by the aviation authority
of another country to identify and
correct an unsafe condition on an
aviation product. The MCAI describes
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0511; or in person at the Docket
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations Office (phone:
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Jim
Rutherford, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
SUMMARY:
PO 00000
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]]>Agencies
[Federal Register Volume 79, Number 162 (Thursday, August 21, 2014)]
[Rules and Regulations]
[Pages 49434-49439]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-17549]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-1065; Directorate Identifier 2011-NM-230-AD;
Amendment 39-17915; AD 2014--15-13]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2005-15-04 for
certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-
601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants)
airplanes. AD 2005-15-04 required operators to assign serial numbers or
part numbers to certain landing gear parts; establish the number of
landings on the parts, if necessary; and revise the Airworthiness
Limitations Section (ALS) of the Instructions for Continued
Airworthiness (ICA) to reflect the new life limits of the landing gear
parts. This new AD adds airplanes to the applicability, requires
operators to assign serial numbers or part numbers to certain
additional landing gear parts to establish the number of landings on
the parts if necessary, and requires operators to record in all
required airplane technical records and manuals the new part numbers,
serial numbers, and landings assigned to these parts. This AD was
prompted by reports that landing gear parts that have safe-life limits
but do not have serial numbers or part numbers can be removed from one
landing gear and re-installed on another, making tracking difficult. We
are issuing this AD to prevent life-limited landing gear parts from
being used beyond their safe-life limits, which could lead to collapse
of the landing gear.
DATES: This AD becomes effective September 25, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 25,
2014.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of August
30, 2005 (70 FR 43032, July 26, 2005).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-1065; 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 Bombardier, Inc./Canadair 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. For Messier-Dowty service information identified in
this AD, contact Messier Services Americas, Customer Support Center,
45360 Severn Way, Sterling, VA 20166-8910; phone: 703-450-8233; fax:
703-404-1621; Internet: https://techpubs.services/messier-dowty.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: Andreas Rambalakos, 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) 228-7345; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2005-15-04, Amendment 39-14193 (70 FR 43032,
July 26, 2005). AD 2005-15-04 applied to certain Bombardier, Inc. Model
CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A,
CL-601-3R, and CL-604 Variants) airplanes. The NPRM published in the
Federal Register on December 30, 2013 (78 FR 79329). The NPRM was
prompted by reports that landing gear parts that have safe-life limits
but do not have serial numbers or part numbers can be removed from one
landing gear and re-installed on another, making tracking difficult.
The NPRM proposed to add airplanes to the applicability, require
operators to assign serial numbers or part numbers to certain
additional landing gear parts to establish the number of landings on
the parts if necessary, and requires operators to record in all
required airplane technical records and manuals the new part numbers,
serial numbers, and landings assigned to these parts. We are issuing
this AD to prevent life-limited landing gear parts from being used
beyond their safe-life limits, which could lead to collapse of the
landing gear.
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, has issued Canadian Airworthiness Directives CF-
2003-18R2, dated September 28, 2011; CF-2003-20R1, dated September 28,
2011; and CF-2003-21R2, dated September 28, 2011 (referred to after
this as the Mandatory Continuing Airworthiness Information, or ``the
MCAI''); to correct an unsafe condition for certain Bombardier, Inc.
Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-
601-3A, CL-601-3R, and CL-604 Variants) airplanes. The MCAI states:
Certain landing gear parts that are listed in the aeroplane
model Airworthiness Limitations Section, as safe life items with
structural life limits, could be rotable and may not have been
serialized, making tracking difficult. This [Canadian airworthiness]
directive mandates that such parts be serialized. This [Canadian
airworthiness] directive also provides the procedure to determine
the number of landings for those parts where the service history
cannot be established.
* * * * *
[T]his [Canadian Airworthiness] directive * * * mandate[s]
serialization of * * * additional landing gear parts.
This AD also adds airplanes to the applicability. The unsafe condition
is using life-limited landing gear parts beyond their safe-life limits,
which could lead to collapse of the landing gear. You may examine the
MCAI in the
[[Page 49435]]
AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-1065-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (78 FR 79329, December 30,
2013) 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.
We have become 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 actions must be accomplished using a method approved
by the FAA, Transport Canada Civil Aviation (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.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``design approval holder (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 available 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 (78 FR 79329, December 30, 2013) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 79329, December 30, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 419 airplanes of U.S. registry.
The actions that were required by AD 2005-15-04, Amendment 39-14193
(70 FR 43032, July 26, 2005), that are retained in this AD take up to
13 work-hours per product, at an average labor rate of $85 per work
hour. Based on these figures, the estimated cost of the currently
required actions is up to $1,105 per product.
We estimate that it would take about 9 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $320,535, or $765 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-1065; 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.
[[Page 49436]]
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 removing Airworthiness Directive (AD)
2005-15-04, Amendment 39-14193 (70 FR 43032, July 26, 2005), and adding
the following new AD:
2014-15-13 Bombardier, Inc.: Amendment 39-17915. Docket No. FAA-
2013-1065; Directorate Identifier 2011-NM-230-AD.
(a) Effective Date
This AD becomes effective September 25, 2014.
(b) Affected ADs
This AD replaces AD 2005-15-04, Amendment 39-14193 (70 FR 43032,
July 26, 2005).
(c) Applicability
This AD applies to Bombardier, Inc. airplanes, certificated in
any category, as identified in paragraphs (c)(1) through (c)(4) of
this AD.
(1) Model CL-600-1A11 (CL-600) airplanes, serial numbers 1004
through 1085 inclusive.
(2) Model CL-600-2A12 (CL-601) airplanes, serial numbers 3001
through 3066 inclusive;
(3) Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants)
airplanes, serial numbers 5001 through 5194 inclusive.
(4) Model CL-600-2B16 (CL-604 Variant) airplanes, serial numbers
5301 through 5573 inclusive, 5579, and 5595.
(5) This AD requires revisions to certain operator maintenance
documents to include new actions (e.g., inspections). Compliance
with these actions is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by this AD, the operator may not be able to
accomplish the actions described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (r) of this AD. The request should include a
description of changes to the required actions that will ensure the
continued damage tolerance of the affected structure.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports that landing gear parts that
have safe-life limits but do not have serial numbers (S/Ns) or part
numbers (P/Ns) can be removed from one landing gear and re-installed
on another, making tracking difficult. We are issuing this AD to
prevent life-limited landing gear parts from being used beyond their
safe-life limits, which could lead to collapse of the landing gear.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Requirement To Add S/Ns or P/Ns
This paragraph restates the actions required by paragraph (f) of
AD 2005-15-04, Amendment 39-14193 (70 FR 43032, July 26, 2005), with
revised affected airplanes. Except for Model CL-600-2B16 airplanes
having S/Ns 5514 through 5595 inclusive: At the applicable
compliance time specified in paragraph (g)(1), (g)(2), or (g)(3) of
this AD, add serial numbers and part numbers, as applicable, to the
parts identified in the applicable service bulletin specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD. Do all actions in
accordance with the applicable service bulletin specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) For parts identified in Bombardier Service Bulletin 600-
0710, Revision 01, dated December 15, 2003; and Bombardier Service
Bulletin 601-0546, Revision 01, dated December 15, 2003; as having a
compliance time of ``five years for the parts listed in Part A'':
Within 60 months after August 30, 2005 (the effective date of AD
2005-15-04, Amendment 39-14193 (70 FR 43032, July 26, 2005)).
(2) For parts identified in Bombardier Service Bulletin 600-
0710, Revision 01, dated December 15, 2003; and Bombardier Service
Bulletin 601-0546, Revision 01, dated December 15, 2003; as having a
compliance time of ``ten years for the parts listed in Part B'':
Within 120 months after August 30, 2005 (the effective date of AD
2005-15-04, Amendment 39-14193 (70 FR 43032, July 26, 2005)).
(3) For parts identified in Bombardier Service Bulletin 604-32-
014, dated May 31, 2002, as having a compliance time of ``no later
than a calendar time of 8 years'': Within 96 months after August 30,
2005 (the effective date of AD 2005-15-04, Amendment 39-14193 (70 FR
43032, July 26, 2005)).
Note 1 to paragraph (g) of this AD: The Bombardier service
bulletins identified in paragraphs (g)(1), (g)(2), and (g)(3) of
this AD refer to the Messier-Dowty service bulletins identified in
table 1 to paragraph (g) of this AD as additional sources of
guidance for adding part numbers or serial numbers by vibro-peening
the numbers on main landing gear (MLG) and nose landing gear (NLG)
components that do not have them; and for determining the number of
landings for parts without a part number or serial number on which
the time since new (TSN) and cycles since new (CSN) have not been
tracked.
Table 1 to Paragraph (g) of This AD--Messier-Dowty Service Bulletins
----------------------------------------------------------------------------------------------------------------
Corresponding
Model-- Landing gear bombardier service Messier-Dowty service
component-- bulletin(s)-- bulletin--
----------------------------------------------------------------------------------------------------------------
CL-600-1A11 (CL-600), CL-600-2A12 MLG side strut 600-0710 and 601-0546. M-DT SB104467009/010-32-1,
(CL-601) and CL-600-2B16 (CL-601- retraction actuator dated March 19, 2001.
3A and CL-601-3R) airplanes. eye bolt.
CL-600-2B16 (CL-604) airplanes..... MLG shock strut....... 604-32-014............ M-DT SB19090-32-4, dated
March 19, 2001.
CL-600-2B16 (CL-604) airplanes..... NLG shock strut....... 604-32-014............ M-DT SB20020-32-5, dated
July 12, 2001.
CL-600-1A11 (CL-600), CL-600-2A12 NLG drag brace hinge 600-0710 and 601-0546. M-DT SB200814001-32-3,
(CL-601) and CL-600-2B16 (CL-601- pin. dated March 19, 2001.
3A and CL-601-3R) airplanes.
CL-600-1A11 (CL-600) airplanes..... MLG shock strut....... 600-0710.............. M-DT SB200922001/2-32-6,
dated March 19, 2001.
CL-600-1A11 (CL-600) airplanes..... NLG shock strut....... 600-0710.............. M-DT SB200924003/004-32-16,
dated July 12, 2001.
CL-600-2A12 (CL-601) and CL-600- MLG shock strut pin... 601-0546.............. M-DT SB6100-32-10, dated
2B16 (CL-601-3A and CL-601-3R) March 19, 2001.
airplanes.
[[Page 49437]]
CL-600-1A11 (CL-600), CL-600-2A12 MLG side strut 600-0710 and 601-0546. M-DT SB6500-32-1, dated
(CL-601) and CL-600-2B16 (CL-601- retraction actuator. March 19, 2001.
3A and CL-601-3R) airplanes.
CL-600-1A11 (CL-600), CL-600-2A12 NLG drag brace hinge 600-0710 and 601-0546. M-DT SB7200-32-6, dated
(CL-601) and CL-600-2B16 (CL-601- pin. March 19, 2001.
3A and CL-601-3R) airplanes.
CL-600-2A12 (CL-601) and CL-600- NLG shock strut....... 601-0546.............. M-DT SB7300-32-16, dated
2B16 (CL-601-3A and CL-601-3R) July 12, 2001.
airplanes.
----------------------------------------------------------------------------------------------------------------
(h) Retained Requirement--Establishment of the Number of Landings
This paragraph restates the actions required by paragraph (g) of
AD 2005-15-04, Amendment 39-14193 (70 FR 43032, July 26, 2005), with
revised affected airplanes. Except for Model CL-600-2B16 airplanes
having S/Ns 5314 through 5595 inclusive: At the applicable time
specified in paragraph (g) of this AD, if a component does not have
a serial number and the CSN or TSN were not tracked, use the formula
in the applicable Messier-Dowty service bulletin specified in table
1 to paragraph (g) of this AD to establish the TSN or CSN, and
record the newly calculated TSN or CSN in the airplane log books.
(i) Retained Requirement To Revise the Airworthiness Limitations
Section (ALS)
This paragraph restates the revision required by paragraph (h)
of AD 2005-15-04, Amendment 39-14193 (70 FR 43032, July 26, 2005),
with revised affected airplanes. Except for Model CL-600-2B16
airplanes having S/Ns 5514 through 5595 inclusive: Within 30 days
after August 30, 2005 (the effective date of AD 2005-15-04), revise
the ALS of the applicable Instructions for Continued Airworthiness
to reflect the new life limits of the landing gear parts by
inserting copies of the Canadair temporary revisions (TR) specified
in table 2 to paragraph (i) of this AD into the ALS of the
applicable Canadair Time-Limits/Maintenance Check Manual. When the
contents of the TRs are included in the general revisions of the
ALS, these TRs may be removed provided the relevant information in
the ALS is identical to that in the TRs.
Table 2 to Paragraph (i) of This AD--Canadair Temporary Revisions
----------------------------------------------------------------------------------------------------------------
Canadair temporary Manual section-- Applicable canadair time-limits/
Model-- revision-- maintenance check manual--
----------------------------------------------------------------------------------------------------------------
CL-600-1A11 (CL-600) airplanes... 5-116, dated April 5-10-10 PSP 605.
11, 2002.
CL-600-2A12 (CL-601) and CL-600- 5-190, dated April 5-10-10 PSP 601-5.
2B16 (CL-601-3A and CL-601-3R) 11, 2002.
airplanes.
CL-600-2A12 (CL-601) and CL-600- 5-191, dated April 5-10-11 PSP 601-5.
2B16 (CL-601-3A and CL-601-3R) 11, 2002.
airplanes.
CL-600-2A12 (CL-601) and CL-600- 5-192, dated April 5-10-12 PSP 601-5.
2B16 (CL-601-3A and CL-601-3R) 11, 2002.
airplanes.
CL-600-2B16 (CL-604) airplanes... 5-2-6, dated April 5-10-10 CL-604.
11, 2002.
CL-600-2A12 (CL-601) and CL-600- 5-204, dated April 5-10-10 PSP 601A-5.
2B16 (CL-601-3A and CL-601-3R) 11, 2002.
airplanes.
CL-600-2A12 (CL-601) and CL-600- 5-205, dated April 5-10-11 PSP 601A-5.
2B16 (CL-601-3A and CL-601-3R) 11, 2002.
airplanes.
CL-600-2A12 (CL-601) and CL-600- 5-206, dated April 5-10-12 PSP 601A-5.
2B16 (CL-601-3A and CL-601-3R) 11, 2002.
airplanes.
----------------------------------------------------------------------------------------------------------------
(j) Retained Parts Installation Limitation
This paragraph restates the limitations specified in paragraph
(i) of AD 2005-15-04, Amendment 39-14193 (70 FR 43032, July 26,
2005), with revised affected airplanes. Except for Model CL-600-2B16
airplanes having serial numbers 5514 through 5595 inclusive: As of
August 30, 2005 (the effective date of AD 2005-15-04), no person may
install on any airplane a landing gear part, unless it has had the
applicable part number or serial number added in accordance with
paragraph (g) of this AD; and has had the number of landings
established in accordance with paragraph (h) of this AD.
(k) Retained Stipulation of Information of No Reporting
This paragraph restates the stipulation specified in paragraph
(j) of AD 2005-15-04, Amendment 39-14193 (70 FR 43032, July 26,
2005). Although the service bulletins identified in paragraph (g) of
this AD specify that operators should submit incorporation notices
to Bombardier after each new part number or serial number and
landings assigned to these parts is added, this AD does not include
that action.
(l) New Requirement of this AD: Add Serial Numbers and Part Numbers
(1) For Model CL-600-2B16 (CL-604 Variant) airplanes: Within 96
months after the effective date of this AD, add serial numbers and
part numbers, as applicable, to the parts identified in paragraphs
(l)(1)(i) and (l)(1)(ii) of this AD, as applicable, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
604-32-014, Revision 02, dated May 9, 2011, including Appendix 1,
dated May 9, 2011, and Service Bulletin Information Sheet, dated
July 6, 2010.
(i) For airplanes having S/Ns 5301 through 5513 inclusive: Main
fitting/drag stay pin of the NLG having P/N 200811721.
(ii) For airplanes having S/Ns 5301 through 5573 inclusive,
5579, and 5595: NLG crossbeam pins having P/N 200814601 and NLG
center hinge pins having P/N 200814624.
(2) For Bombardier Model CL-600-2A12 (CL-601) airplanes and
Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes:
Within 60 months after the effective date of this AD, add serial
numbers and part numbers, as applicable, to left and right MLG side
strut pins having P/N 6318-1 or 6318-3; and to left and right MLG
hinge pins having P/N 6329-3; in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 601-0546, Revision 03,
dated May 9, 2011, including Appendix 1, dated May 9, 2011, and
Service
[[Page 49438]]
Bulletin Information Sheet, dated July 6, 2010.
(3) For Bombardier Model CL-600-2A12 (CL-601) airplanes and
Model CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes:
Within 120 months after the effective date of this AD, add serial
numbers and part numbers, as applicable, to NLG main fitting/drag
stay pins having P/N 200811721; NLG drag brace pivot pins having P/N
200814601; and left and right MLG pintle pins having P/N 6324-1; in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 601-0546, Revision 03, dated May 9, 2011, including
Appendix 1, dated May 9, 2011, and Service Bulletin Information
Sheet, dated July 6, 2010.
(4) For Bombardier Model CL-600-1A11 (CL-600) airplanes: Within
120 months after the effective date of this AD, add serial numbers
and part numbers, as applicable, to NLG main fitting/drag stay pins
having P/N 200811721 and NLG drag brace pivot pins having P/N
200814601, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 600-0710, Revision 03, dated May 9,
2011, including Appendix 1, dated May 9, 2011, and Service Bulletin
Information Sheet, dated July 6, 2010.
(m) New Requirement of This AD: Establish the Number of Landings (CSN)
At the applicable times specified in paragraph (l) of this AD:
If a component does not have a serial number and the CSN were not
tracked, use Appendix 1, dated May 9, 2011, of the applicable
service bulletin specified in paragraph (m)(1), (m)(2), or (m)(3) of
this AD to establish the number of landings (CSN).
(1) Bombardier Service Bulletin 604-32-014, Revision 02, dated
May 9, 2011, including Service Bulletin Information Sheet, dated
July 6, 2010 (for Bombardier Model CL-600-2B16 (CL-604 Variant)
airplanes).
(2) Bombardier Service Bulletin 601-0546, Revision 03, dated May
9, 2011, including Service Bulletin Information Sheet, dated July 6,
2010 (for Model CL-600-2A12 (CL-601) airplanes and Model CL-600-2B16
(CL-601-3A and CL-601-3R Variants) airplanes).
(3) Bombardier Service Bulletin 600-0710, Revision 03, dated May
9, 2011, including Service Bulletin Information Sheet, dated July 6,
2010 (for Bombardier Model CL-600-1A11 (CL-600) airplanes).
(n) New Requirement of This AD: Records Update
Concurrently with the actions specified in paragraphs (l) and
(m) of this AD: Record any newly calculated CSN, new part numbers,
and new serial numbers in the airplane technical records and
manuals.
(o) New Requirement of This AD: Parts Installation Limitation
As of the effective date of this AD, no person may install on
any airplane a landing gear part identified in paragraph (l) of this
AD, unless it has had the applicable part number or serial number
added as required by paragraph (l) of this AD, and had the CSN
established as required by paragraph (m) of this AD.
(p) New Action of This AD: Optional Method of Compliance
Accomplishing the action required by paragraph (g) of this AD,
in accordance with the Accomplishment Instructions of the applicable
service bulletin specified in paragraph (p)(1), (p)(2), or (p)(3) of
this AD, is acceptable for compliance with the requirements of
paragraph (g) of this AD.
(1) Bombardier Service Bulletin 601-0546, Revision 03, dated May
9, 2011, including Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6, 2010 (for Model CL-600-
2A12 (CL-601) airplanes and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes).
(2) Bombardier Service Bulletin 604-32-014, Revision 02, dated
May 9, 2011, including Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6, 2010 (for Model CL-600-
2B16 (CL-604 Variant) airplanes).
(3) Bombardier Service Bulletin 600-0710, Revision 03, dated May
9, 2011, including Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6, 2010 (for Model CL-600-
1A11 (CL-600) airplanes).
(q) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before
August 30, 2005 (the effective date of AD 2005-15-04, Amendment 39-
14193 (70 FR 43032, July 26, 2005)), using the applicable service
bulletin specified in paragraph (q)(1)(i), (q)(1)(ii), or
(q)(1)(iii) of this AD, which are not incorporated by reference in
this AD.
(i) Bombardier Service Bulletin 601-0546, dated May 31, 2002
(for Model CL-600-2A12 (CL-601) airplanes and Model CL-600-2B16 (CL-
601-3A and CL-601-3R Variants) airplanes).
(ii) Bombardier Service Bulletin 600-0710, dated May 31, 2002
(for ModelCL-600-1A11 (CL-600) airplanes).
(iii) Bombardier Service Bulletin 604-32-014, dated May 31, 2002
(for Model CL-600-2B16 (CL-604 Variant) airplanes).
(2) This paragraph provides credit for the addition of serial
numbers and part numbers required by paragraph (l) of this AD, if
those actions were performed before the effective date of this AD
using the applicable service bulletin specified in paragraph
(q)(2)(i), (q)(2)(ii), or (q)(2)(iii) of this AD, which are not
incorporated by reference in this AD.
(i) Bombardier Service Bulletin 604-32-014, Revision 01, dated
October 29, 2007 (for Bombardier Model CL-600-2B16 (CL-604 Variant)
airplanes).
(ii) Bombardier Service Bulletin 601-0546, Revision 02, dated
October 29, 2007 (for Model CL-600-2A12 (CL-601) airplanes and Model
CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes).
(iii) Bombardier Service Bulletin 600-0710, Revision 02, dated
October 29, 2007 (for Bombardier Model CL-600-1A11 (CL-600)
airplanes).
(3) This paragraph provides credit for the establishment of the
CSN required by paragraph (m) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service bulletin information sheet specified in paragraph (q)(3)(i),
(q)(3)(ii), or (q)(3)(iii) of this AD.
(i) Service Bulletin Information Sheet, dated July 6, 2010, of
Bombardier Service Bulletin 604-32-014, Revision 01, dated October
29, 2007 (for Bombardier Model CL-600-2B16 (CL-604 Variant)
airplanes).
(ii) Service Bulletin Information Sheet, dated July 6, 2010, of
Bombardier Service Bulletin 601-0546, Revision 02, dated October 29,
2007 (for Bombardier Model CL-600-2A12 (CL-601) and Model CL-600-
2B16 (CL-601-3A and CL-601-3R Variants) airplanes).
(iii) Service Bulletin Information Sheet, dated July 6, 2010, of
Bombardier Service Bulletin 600-0710, Revision 02, dated October 29,
2007 (for Bombardier Model CL-600-1A11 (CL-600) airplanes).
(r) 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. AMOCs approved previously in accordance with AD 2005-15-04,
Amendment 39-14193 (70 FR 43032, July 26, 2005), are approved as
AMOCs for the corresponding provisions of 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.
(s) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directives specified in paragraphs
(s)(1)(i), (s)(1)(ii), and (s)(1)(iii) of this AD for related
information. You may examine the MCAI in the AD docket on the
Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-
1065-0002.
(i) Canadian Airworthiness Directive CF-2003-18R2, dated
September 28, 2011.
(ii) Canadian Airworthiness Directive CF-2003-20R1, dated
September 28, 2011.
(iii) Canadian Airworthiness Directive CF-2003-21R2, dated
September 28, 2011.
[[Page 49439]]
(2) Service information identified in this AD that is not
incorporated by reference in this AD may be obtained at the
addresses specified in paragraphs (t)(5) and (t)(6) of this AD.
(t) 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.
(3) The following service information was approved for IBR on
September 25, 2014.
(i) Bombardier Service Bulletin 600-0710, Revision 03, dated May
9, 2011, including Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6, 2010.
(ii) Bombardier Service Bulletin 601-0546, Revision 03, dated
May 9, 2011, including Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6, 2010.
(iii) Bombardier Service Bulletin 604-32-014, Revision 02, dated
May 9, 2011, including Appendix 1, dated May 9, 2011, and Service
Bulletin Information Sheet, dated July 6, 2010.
(4) The following service information was approved for IBR on
August 30, 2005 (70 FR 43032, July 26, 2005).
(i) Bombardier Service Bulletin 600-0710, Revision 01, dated
December 15, 2003.
(ii) Bombardier Service Bulletin 601-0546, Revision 01, dated
December 15, 2003.
(iii) Bombardier Service Bulletin 604-32-014, dated May 31,
2002.
(iv) Canadair Temporary Revision 5-116, dated April 11, 2002.
(v) Canadair Temporary Revision 5-190, dated April 11, 2002.
(vi) Canadair Temporary Revision 5-191, dated April 11, 2002.
(vii) Canadair Temporary Revision 5-192, dated April 11, 2002.
(viii) Canadair Temporary Revision 5-2-6, dated April 11, 2002.
(ix) Canadair Temporary Revision 5-204, dated April 11, 2002.
(x) Canadair Temporary Revision 5-205, dated April 11, 2002.
(xi) Canadair Temporary Revision 5-206, dated April 11, 2002.
(xii) Messier-Dowty Service Bulletin M-DT SB104467009/010-32-1,
dated March 19, 2001.
(xiii) Messier-Dowty Service Bulletin M-DT SB19090-32-4, dated
March 19, 2001.
(xiv) Messier-Dowty Service Bulletin M-DT SB20020-32-5, dated
July 12, 2001.
(xv) Messier-Dowty Service Bulletin M-DT SB200814001-32-3, dated
March 19, 2001.
(xvi) Messier-Dowty Service Bulletin M-DT SB200922001/2-32-6,
dated March 19, 2001.
(xvii) Messier-Dowty Service Bulletin M-DT SB200924003/004-32-
16, dated July 12, 2001.
(xviii) Messier-Dowty Service Bulletin M-DT SB6100-32-10, dated
March 19, 2001.
(xix) Messier-Dowty Service Bulletin M-DT SB6500-32-1, dated
March 19, 2001.
(xx) Messier-Dowty Service Bulletin M-DT SB7200-32-6, dated
March 19, 2001.
(xxi) Messier-Dowty Service Bulletin M-DT SB7300-32-16, dated
July 12, 2001.
(5) For Bombardier, Inc./Canadair 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. For Messier-Dowty service information
identified in this AD, contact Messier Services Americas, Customer
Support Center, 45360 Severn Way, Sterling, VA 20166-8910.
(6) 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.
(7) 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. 2014-17549 Filed 8-20-14; 8:45 am]
BILLING CODE 4910-13-P
