Airworthiness Directives; Bombardier, Inc. Model CL-600-2A12 (CL-601) and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) Airplanes, 41653-41657 [2011-17402]
Download as PDF
<![CDATA[
Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations
and could lead to the loss of the vertical
stabilizer.
Compliance
(f) Comply with this AD within the
compliance times specified, unless already
done.
Inspections
(g) Within 4,500 flight cycles after the
effective date of this AD, do a detailed
inspection for distress in and existing repairs
to the leading edge structure of the vertical
stabilizer at the splice at Station Zfs=52.267,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
MD80–55A067, dated June 24, 2010.
Repetitive Inspections for Cracks, and
Related Investigative and Corrective Actions
(h) Before further flight after doing the
inspection required by paragraph (g) of this
AD, inspect for cracks of the left and right
vertical stabilizer front spar cap, in
accordance with either Option 1 or Option 2
as specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
MD80–55A067, dated June 24, 2010. If any
crack is found, before further flight, evaluate
and verify to confirm all crack indications, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
MD80–55A067, dated June 24, 2010.
(1) If any cracking is confirmed, before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (l) of this AD.
(2) If no cracking is confirmed, repeat the
inspection thereafter at intervals not to
exceed the applicable interval specified in
paragraph (h)(2)(i) or (h)(2)(ii) of this AD.
(i) If the most recent inspection was done
using Option 1, the next inspection must be
done within 4,400 flight cycles.
(ii) If the most recent inspection was done
using Option 2, the next inspection must be
done within 3,000 flight cycles.
mstockstill on DSK4VPTVN1PROD with RULES
Leading Edge Repair
(i) If leading edge distress is found during
the detailed inspection required by paragraph
(g) of this AD, before further flight and after
accomplishing the inspection required by
paragraph (h) of this AD, repair the leading
edge, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin MD80–55A067, dated June
24, 2010.
Inspection for Loose/Missing Fasteners
(j) For airplanes on which no cracking is
confirmed during the initial inspection
required by paragraph (h) of this AD: At the
applicable time specified in paragraph (j)(1)
or (j)(2) of this AD, do a detailed inspection
for indications of loose and missing fasteners,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
MD80–55A067, dated June 24, 2010. If any
loose or missing fastener is found, before
further flight, repair the leading edge, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
MD80–55A067, dated June 24, 2010.
(1) If the inspection required by paragraph
(h) was done using Option 1, do the
inspection required by paragraph (j) of this
VerDate Mar<15>2010
15:47 Jul 14, 2011
Jkt 223001
AD within 4,400 flight cycles after
accomplishing the inspection required by
paragraph (h) of this AD.
(2) If inspection required by paragraph (h)
was done using Option 2, do the inspection
required by paragraph (j) of this AD within
3,000 flight cycles after accomplishing the
inspection required by paragraph (h) of this
AD.
(k) For airplanes on which no cracking is
confirmed during the most recent inspection
required by paragraph (h) of this AD: Repeat
the inspection for loose and missing fasteners
required by paragraph (j) of this AD thereafter
at intervals not to exceed the applicable time
specified in paragraph (k)(1) or (k)(2) of this
AD.
(1) If the most recent inspection required
by paragraph (h) was done using Option 1,
the next inspection required by paragraph (j)
of this AD must be done within 4,400 flight
cycles after accomplishing the most recent
inspection required by paragraph (j) of this
AD.
(2) If the most recent inspection required
by paragraph (h) was done using Option 2,
the next inspection required by paragraph (j)
of this AD must be done within 3,000 flight
cycles after the most recent inspection
required by paragraph (j) of this AD.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane and 14
CFR 25.571, Amendment 45, and the
approval must specifically refer to this AD.
Related Information
(m) For more information about this AD,
contact Roger Durbin, Aerospace Engineer,
Airframe Branch, ANM–120L, Los Angeles
Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712–
4137; phone: 562–627–5233; fax: 562–627–
5210; e-mail: Roger.Durbin@faa.gov.
Material Incorporated by Reference
(n) You must use Boeing Alert Service
Bulletin MD80–55A067, dated June 24, 2010,
to do the actions required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
PO 00000
Frm 00065
Fmt 4700
Sfmt 4700
41653
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, 3855 Lakewood Boulevard, MC
D800–0019, Long Beach, California 90846–
0001; telephone 206–544–5000, extension 2;
fax 206–766–5683; e-mail
dse.boecom@boeing.com; Internet https://
www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at an NARA facility, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on July 1,
2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–17400 Filed 7–14–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1307; Directorate
Identifier 2010–NM–049–AD; Amendment
39–16671; AD 2011–09–09]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Model CL–600–2A12 (CL–601) and
CL–600–2B16 (CL–601–3A, CL–601–
3R, and CL–604 Variants) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
SUMMARY:
During flight-testing of a wing anti-ice
piccolo tube containing a deliberate small
breach, it was determined that the wing
leading edge thermal switches were not
detecting the consequent bleed leak at the
design threshold. As a result, new
E:\FR\FM\15JYR1.SGM
15JYR1
41654
Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations
Airworthiness Limitation tasks, consisting of
a functional test of the wing leading edge
thermal switches and an inspection of the
wing anti-ice duct piccolo tubes, have been
introduced in order to limit exposure to
dormant failure of the switches in the event
of piccolo tube failure, which could
potentially compromise the structural
integrity of the wing leading edge and the
effectiveness of the wing anti-ice system.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
August 19, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 19, 2011.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7318; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
mstockstill on DSK4VPTVN1PROD with RULES
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on January 5, 2011 (76 FR 477).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
During flight-testing of a wing anti-ice
piccolo tube containing a deliberate small
breach, it was determined that the wing
leading edge thermal switches were not
detecting the consequent bleed leak at the
design threshold. As a result, new
Airworthiness Limitation tasks, consisting of
a functional test of the wing leading edge
thermal switches and an inspection of the
wing anti-ice duct piccolo tubes, have been
introduced in order to limit exposure to
dormant failure of the switches in the event
of piccolo tube failure, which could
potentially compromise the structural
integrity of the wing leading edge and the
effectiveness of the wing anti-ice system.
This directive mandates the revision of the
approved maintenance schedule to include
these new tasks, including phase-in
schedules.
This revision clarifies the applicability of
the directive for CL–600–2A12 aircraft, serial
numbers 3001 through 3066, and for CL–
VerDate Mar<15>2010
15:47 Jul 14, 2011
Jkt 223001
600–2B16 aircraft, serial numbers 5001
through 5194. The directive is only
applicable to these aircraft if Bombardier
Service Bulletin (SB) 601–0590 [Scheduled
Maintenance Instructions (MSG–3) Derived—
Qualification] has been incorporated. There
is no change required to the approved
maintenance schedule if SB 601–0590 has
not been incorporated.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
103 products of U.S. registry. We also
estimate that it will take about 1 workhour per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $8,755, or $85 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
PO 00000
Frm 00066
Fmt 4700
Sfmt 4700
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
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); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; 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 the NPRM, 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. Comments will be available in
the AD docket shortly after receipt.
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.
E:\FR\FM\15JYR1.SGM
15JYR1
Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2011–09–09 Bombardier, Inc.: Amendment
39–16671. Docket No. FAA–2010–1307;
Directorate Identifier 2010–NM–049–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective August 19, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes
identified in paragraphs (c)(1), (c)(2), (c)(3),
and (c)(4) of this AD; certificated in any
category.
(1) Bombardier, Inc. Model CL–600–2A12
(CL–601) airplanes, serial numbers 3001
through 3066 inclusive on which Bombardier
Service Bulletin 601–0590 has been
accomplished.
(2) Bombardier, Inc. CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes,
serial numbers 5001 through 5194 inclusive
on which Bombardier Service Bulletin 601–
0590 has been accomplished.
(3) Bombardier, Inc. CL–600–2B16 (CL–604
Variants) airplanes, serial numbers 5301
through 5665 inclusive.
(4) Bombardier, Inc. CL–600–2B16 (CL–604
Variants) airplanes, serial numbers 5701 and
subsequent.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections 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 (j) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued operational safety of the airplane.
Subject
(d) Air Transport Association (ATA) of
America Codes 30 and 36: Ice and Rain
Protection and Pneumatic, respectively.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
41655
During flight-testing of a wing anti-ice
piccolo tube containing a deliberate small
breach, it was determined that the wing
leading edge thermal switches were not
detecting the consequent bleed leak at the
design threshold. As a result, new
Airworthiness Limitation tasks, consisting of
a functional test of the wing leading edge
thermal switches and an inspection of the
wing anti-ice duct piccolo tubes, have been
introduced in order to limit exposure to
dormant failure of the switches in the event
of piccolo tube failure, which could
potentially compromise the structural
integrity of the wing leading edge and the
effectiveness of the wing anti-ice system.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Actions
(g) Within 30 days after the effective date
of this AD: Revise the Airworthiness
Limitations Section of the Instructions for
Continued Airworthiness by incorporating
the applicable tasks identified in table 1 of
this AD.
TABLE 1—AIRWORTHINESS LIMITATIONS TASKS
For Bombardier, Inc. model—
Incorporate task(s)—
Identified in—
CL-600-2A12 (CL-601) airplanes, serial numbers 3001 through 3066 inclusive on which
Bombardier Service Bulletin 601-0590 has
been accomplished.
CL-600-2B16 (CL-601-3A and CL-601-3R
Variants) airplanes, serial numbers 5001
through 5194 inclusive on which Bombardier
Service Bulletin 601–0590 has been accomplished.
CL–600–2B16 (CL–604 Variants) airplanes, serial numbers 5301 through 5665 inclusive.
30–11–00–101, Wing Anti-icing, and 30–11–
00–102, Wing Anti-icing.
Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601–5, Revision 38,
dated June 19, 2009.
30–11–00–101, Wing Anti-icing, and 30–11–
00–102, Wing Anti-icing.
Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601A–5, Revision 34,
dated June 19, 2009.
30–11–00–101, Detailed Inspection of the
Wing Anti-Ice Duct Piccolo-Tube, and
36-21-00-101, Functional Test of the Leading Edge Thermal Switches.
30–11–00–101, Detailed Inspection of the
Wing Anti-Ice Duct Piccolo-Tube, and
36-21-00-101, Functional Test of the Leading Edge Thermal Switches.
Bombardier Challenger 604 Time Limits/Maintenance Checks, CH 604 TLMC, Revision
13, dated August 12, 2009.
CL–600–2B16 (CL–604 Variants) airplanes, serial numbers 5701 and subsequent.
(h) For all tasks identified in paragraph (g)
of this AD, the initial compliance times for
Bombardier Challenger 605 Time Limits/Maintenance Checks, CH 605 TLMC, Revision
1, dated August 12, 2009.
those tasks are within the applicable times
specified in table 2 of this AD.
TABLE 2—INITIAL COMPLIANCE TIMES FOR AIRWORTHINESS LIMITATIONS TASKS
mstockstill on DSK4VPTVN1PROD with RULES
Bombardier, Inc. model—
Task(s)—
Initial compliance time (whichever
occurs later)—
CL-600-2A12 (CL-601) airplanes,
serial numbers 3001 through
3066
inclusive;
and
CL-600-2B16 (CL-601-3A and
CL-601-3R Variants) airplanes,
serial numbers 5001 through
5194 inclusive; on which Bombardier Service Bulletin 601–
0590 has been accomplished.
30–11–00–101, Wing Anti-icing ...
Prior to the accumulation of 4,800
total flight hours; or within 4,800
flight hours after accomplishing
Task 30-11-06-204 in Section
5-20–15 of the applicable Time
Limits/Maintenance
Checks
manual specified in table 1 of
this AD; whichever occurs later.
VerDate Mar<15>2010
15:47 Jul 14, 2011
Jkt 223001
PO 00000
Frm 00067
Fmt 4700
Sfmt 4700
E:\FR\FM\15JYR1.SGM
Within 240 flight hours after the
effective date of this AD.
15JYR1
41656
Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations
TABLE 2—INITIAL COMPLIANCE TIMES FOR AIRWORTHINESS LIMITATIONS TASKS—Continued
Bombardier, Inc. model—
Task(s)—
Initial compliance time (whichever
occurs later)—
CL-600-2A12 (CL-601) airplanes,
serial numbers 3001 through
3066
inclusive;
and
CL-600-2B16 (CL-601-3A and
CL-601-3R Variants) airplanes,
serial numbers 5001 through
5194 inclusive; on which Bombardier Service Bulletin 601–
0590 has been accomplished.
CL–600–2B16 (CL–604 Variants)
airplanes, serial numbers 5301
through 5665 inclusive.
30–11–00–102, Wing Anti-icing ...
Prior to the accumulation of 4,800
total flight hours; or within 4,800
flight hours after accomplishing
Task 30-13-00-205 in Section
5-20–15 of the applicable Time
Limits/Maintenance
Checks
manual specified in table 1 of
this AD; whichever occurs later.
Within 240 flight hours after the
effective date of this AD.
30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct
Piccolo-Tube,
and
36-21-00-101, Functional Test
of the Leading Edge Thermal
Switches.
Within 320 flight hours after the
effective date of this AD.
CL–600–2B16 (CL–604 Variants)
airplanes, serial numbers 5701
and subsequent.
30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct
Piccolo-Tube,
and
36-21-00-101, Functional Test
of the Leading Edge Thermal
Switches.
Prior to the accumulation of 6,400
total flight hours; except for airplanes having 6,400 total flight
hours or more as of the effective date of this AD on which
the task has not been accomplished: prior to the next scheduled 6,400 flight hour task inspection or prior to the next
scheduled accomplishment of
Task 57-10-00–208 in the applicable Time Limits/Maintenance
Checks manual specified in
table 1 of this AD, whichever
occurs first.
Prior to the accumulation of 6,400
total flight hours.
(i) After accomplishing the actions
required by paragraph (g) of this AD, no
alternative tasks or task intervals may be
used unless the tasks or task intervals are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (j)(1) of
this AD.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(j) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the ACO, send it to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone 516–228–7300; fax 516–
794–5531. Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
Within 320 flight hours after the
effective date of this AD.
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
Related Information
(k) Refer to MCAI Canadian Airworthiness
Directive CF–2009–49R1, dated January 21,
2010, and the service information specified
in Table 1 of this AD, for related information.
Material Incorporated by Reference
(l) You must use the applicable service
information contained in table 3 of this AD
to do the actions required by this AD, unless
the AD specifies otherwise.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE
mstockstill on DSK4VPTVN1PROD with RULES
Document
Revision
Tasks 30–11–00–101, Wing Anti-icing, and 30–11–00–102, Wing Anti-icing, of the Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601–5.
Tasks 30–11–00–101, Wing Anti-icing, and 30–11–00–102, Wing Anti-icing, of the Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601A–5.
Tasks 30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct Piccolo-Tube, and 36–21–00–101,
Functional Test of the Leading Edge Thermal Switches, of the Bombardier Challenger 604 Time Limits/
Maintenance Checks, CH 604 TLMC.
Tasks 30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct Piccolo-Tube, and 36–21–00–101,
Functional Test of the Leading Edge Thermal Switches, of the Bombardier Challenger 605 Time Limits/
Maintenance Checks, CH 605 TLMC.
VerDate Mar<15>2010
15:47 Jul 14, 2011
Jkt 223001
PO 00000
Frm 00068
Fmt 4700
Sfmt 4700
E:\FR\FM\15JYR1.SGM
15JYR1
Date
38
June 19, 2009.
34
June 19, 2009.
13
August 12, 2009.
1
August 12, 2009.
Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations
The title pages of these documents do not
indicate the revision level or issue date of the
documents. Only the Record of Revisions of
these documents contains the revision level
of these documents.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) 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; e-mail
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(4) You may also review copies of the
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/
code_of_federal_regulations/ibr_
locations.html.
Issued in Renton, Washington, on April 13,
2011.
Ali Bahrami,
Manager,Transport Airplane
Directorate,Aircraft Certification Service.
[manufacturer serial number], for which
Airbus modification 40391 was indicated as
fully embodied inside the Aircraft Inspection
Report (AIR), did not have Modification
Proposal (MP–S10437) which is part of this
modification embodied in production.
As a result, ALI [Airworthiness Limitation
Item] task 533105–01–02 has not been
performed on the MSN listed in the
applicability section of this AD, which
constitutes an unsafe condition.
*
*
*
*
*
[Docket No. FAA–2011–0653; Directorate
Identifier 2010–NM–249–AD; Amendment
39–16745; AD 2011–14–10]
The unsafe condition is fatigue cracking
of the internal structure of the fuselage,
which could adversely affect the
structural integrity of the airplane. This
AD requires actions that are intended to
address the unsafe condition described
in the MCAI.
DATES: This AD becomes effective
August 1, 2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of August 1, 2011.
We must receive comments on this
AD by August 29, 2011.
ADDRESSES: You may send comments 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.
• Mail: 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: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC, between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
RIN 2120–AA64
Examining the AD Docket
Airworthiness Directives; Airbus Model
A330–342 Airplanes
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
[FR Doc. 2011–17402 Filed 7–14–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
*
*
*
*
*
mstockstill on DSK4VPTVN1PROD with RULES
SUMMARY:
Following a query from an operator,
investigations revealed that some MSN
VerDate Mar<15>2010
15:47 Jul 14, 2011
Jkt 223001
PO 00000
Frm 00069
Fmt 4700
Sfmt 4700
41657
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2010–0173,
dated August 17, 2010 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Airworthiness Limitation Item (ALI) task
533105–01–02 is applicable to aeroplanes on
which Airbus modification 40391 has not
been embodied in production. The
requirements associated to this task are
applicable to aeroplanes on which
Modification Proposal (MP–S10437) has not
been embodied.
Following a query from an operator,
investigations revealed that some MSN
[manufacturer serial numbers], for which
Airbus modification 40391 was indicated as
fully embodied inside the Aircraft Inspection
Report (AIR), did not have Modification
Proposal (MP–S10437) which is part of this
modification embodied in production.
As a result, ALI task 533105–01–02 has not
been performed on the MSN listed in the
applicability section of this AD, which
constitutes an unsafe condition.
For the reasons described above, this AD
requires repetitive special detailed
inspections [for fatigue cracking of the
internal structure of the fuselage]
corresponding to ALI task 533105–01–02 and
the accomplishment of the associated
corrective actions.
The unsafe condition is fatigue cracking
of the internal structure of the fuselage,
which could adversely affect the
structural integrity of the airplane. The
special detailed inspection is defined as
an ultrasonic inspection in this AD. The
corrective action is repairing any cracks
in accordance with a method approved
by the FAA or EASA (or its delegated
agent). You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A330–53–3185, including
Appendices 01 and 02, dated May 20,
2010. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
E:\FR\FM\15JYR1.SGM
15JYR1
]]>Agencies
[Federal Register Volume 76, Number 136 (Friday, July 15, 2011)]
[Rules and Regulations]
[Pages 41653-41657]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-17402]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1307; Directorate Identifier 2010-NM-049-AD;
Amendment 39-16671; AD 2011-09-09]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model CL-600-2A12 (CL-
601) and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants)
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
During flight-testing of a wing anti-ice piccolo tube containing
a deliberate small breach, it was determined that the wing leading
edge thermal switches were not detecting the consequent bleed leak
at the design threshold. As a result, new
[[Page 41654]]
Airworthiness Limitation tasks, consisting of a functional test of
the wing leading edge thermal switches and an inspection of the wing
anti-ice duct piccolo tubes, have been introduced in order to limit
exposure to dormant failure of the switches in the event of piccolo
tube failure, which could potentially compromise the structural
integrity of the wing leading edge and the effectiveness of the wing
anti-ice system.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective August 19, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 19,
2011.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7318; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on January 5, 2011 (76
FR 477). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During flight-testing of a wing anti-ice piccolo tube containing
a deliberate small breach, it was determined that the wing leading
edge thermal switches were not detecting the consequent bleed leak
at the design threshold. As a result, new Airworthiness Limitation
tasks, consisting of a functional test of the wing leading edge
thermal switches and an inspection of the wing anti-ice duct piccolo
tubes, have been introduced in order to limit exposure to dormant
failure of the switches in the event of piccolo tube failure, which
could potentially compromise the structural integrity of the wing
leading edge and the effectiveness of the wing anti-ice system. This
directive mandates the revision of the approved maintenance schedule
to include these new tasks, including phase-in schedules.
This revision clarifies the applicability of the directive for
CL-600-2A12 aircraft, serial numbers 3001 through 3066, and for CL-
600-2B16 aircraft, serial numbers 5001 through 5194. The directive
is only applicable to these aircraft if Bombardier Service Bulletin
(SB) 601-0590 [Scheduled Maintenance Instructions (MSG-3) Derived--
Qualification] has been incorporated. There is no change required to
the approved maintenance schedule if SB 601-0590 has not been
incorporated.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 103 products of U.S. registry.
We also estimate that it will take about 1 work-hour per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $8,755, or $85 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
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); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; 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 the NPRM, 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. Comments will be available in the AD docket shortly
after receipt.
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.
[[Page 41655]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2011-09-09 Bombardier, Inc.: Amendment 39-16671. Docket No. FAA-
2010-1307; Directorate Identifier 2010-NM-049-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
19, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any
category.
(1) Bombardier, Inc. Model CL-600-2A12 (CL-601) airplanes,
serial numbers 3001 through 3066 inclusive on which Bombardier
Service Bulletin 601-0590 has been accomplished.
(2) Bombardier, Inc. CL-600-2B16 (CL-601-3A and CL-601-3R
Variants) airplanes, serial numbers 5001 through 5194 inclusive on
which Bombardier Service Bulletin 601-0590 has been accomplished.
(3) Bombardier, Inc. CL-600-2B16 (CL-604 Variants) airplanes,
serial numbers 5301 through 5665 inclusive.
(4) Bombardier, Inc. CL-600-2B16 (CL-604 Variants) airplanes,
serial numbers 5701 and subsequent.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections 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 (j) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued operational safety of the airplane.
Subject
(d) Air Transport Association (ATA) of America Codes 30 and 36:
Ice and Rain Protection and Pneumatic, respectively.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During flight-testing of a wing anti-ice piccolo tube containing
a deliberate small breach, it was determined that the wing leading
edge thermal switches were not detecting the consequent bleed leak
at the design threshold. As a result, new Airworthiness Limitation
tasks, consisting of a functional test of the wing leading edge
thermal switches and an inspection of the wing anti-ice duct piccolo
tubes, have been introduced in order to limit exposure to dormant
failure of the switches in the event of piccolo tube failure, which
could potentially compromise the structural integrity of the wing
leading edge and the effectiveness of the wing anti-ice system.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Actions
(g) Within 30 days after the effective date of this AD: Revise
the Airworthiness Limitations Section of the Instructions for
Continued Airworthiness by incorporating the applicable tasks
identified in table 1 of this AD.
Table 1--Airworthiness Limitations Tasks
------------------------------------------------------------------------
Incorporate
For Bombardier, Inc. model-- task(s)-- Identified in--
------------------------------------------------------------------------
CL[dash]600[dash]2A12 30-11-00-101, Wing Bombardier
(CL[dash]601) airplanes, serial Anti-icing, and Challenger 601
numbers 3001 through 3066 30-11-00-102, Time Limits/
inclusive on which Bombardier Wing Anti-icing. Maintenance
Service Bulletin 601[dash]0590 Checks, PSP 601-
has been accomplished. 5, Revision 38,
dated June 19,
2009.
CL[dash]600[dash]2B16 30-11-00-101, Wing Bombardier
(CL[dash]601[dash]3A and Anti-icing, and Challenger 601
CL[dash]601[dash]3R Variants) 30-11-00-102, Time Limits/
airplanes, serial numbers 5001 Wing Anti-icing. Maintenance
through 5194 inclusive on which Checks, PSP 601A-
Bombardier Service Bulletin 601- 5, Revision 34,
0590 has been accomplished. dated June 19,
2009.
CL-600-2B16 (CL-604 Variants) 30-11-00-101, Bombardier
airplanes, serial numbers 5301 Detailed Challenger 604
through 5665 inclusive. Inspection of the Time Limits/
Wing Anti-Ice Maintenance
Duct Piccolo- Checks, CH 604
Tube, and TLMC, Revision
36[dash]21[dash]0 13, dated August
0[dash]101, 12, 2009.
Functional Test
of the Leading
Edge Thermal
Switches.
CL-600-2B16 (CL-604 Variants) 30-11-00-101, Bombardier
airplanes, serial numbers 5701 Detailed Challenger 605
and subsequent. Inspection of the Time Limits/
Wing Anti-Ice Maintenance
Duct Piccolo- Checks, CH 605
Tube, and TLMC, Revision 1,
36[dash]21[dash]0 dated August 12,
0[dash]101, 2009.
Functional Test
of the Leading
Edge Thermal
Switches.
------------------------------------------------------------------------
(h) For all tasks identified in paragraph (g) of this AD, the
initial compliance times for those tasks are within the applicable
times specified in table 2 of this AD.
Table 2--Initial Compliance Times for Airworthiness Limitations Tasks
----------------------------------------------------------------------------------------------------------------
Initial compliance time
Bombardier, Inc. model-- Task(s)-- (whichever occurs
later)--
----------------------------------------------------------------------------------------------------------------
CL[dash]600[dash]2A12 (CL[dash]601) 30-11-00-101, Wing Anti- Prior to the Within 240 flight hours
airplanes, serial numbers 3001 icing. accumulation of 4,800 after the effective
through 3066 inclusive; and total flight hours; or date of this AD.
CL[dash]600[dash]2B16 within 4,800 flight
(CL[dash]601[dash]3A and hours after
CL[dash]601[dash]3R Variants) accomplishing Task
airplanes, serial numbers 5001 30[dash]11[dash]06[das
through 5194 inclusive; on which h]204 in Section
Bombardier Service Bulletin 601-0590 5[dash]20-15 of the
has been accomplished. applicable Time Limits/
Maintenance Checks
manual specified in
table 1 of this AD;
whichever occurs later.
[[Page 41656]]
CL[dash]600[dash]2A12 (CL[dash]601) 30-11-00-102, Wing Anti- Prior to the Within 240 flight hours
airplanes, serial numbers 3001 icing. accumulation of 4,800 after the effective
through 3066 inclusive; and total flight hours; or date of this AD.
CL[dash]600[dash]2B16 within 4,800 flight
(CL[dash]601[dash]3A and hours after
CL[dash]601[dash]3R Variants) accomplishing Task
airplanes, serial numbers 5001 30[dash]13[dash]00[das
through 5194 inclusive; on which h]205 in Section
Bombardier Service Bulletin 601-0590 5[dash]20-15 of the
has been accomplished. applicable Time Limits/
Maintenance Checks
manual specified in
table 1 of this AD;
whichever occurs later.
CL-600-2B16 (CL-604 Variants) 30-11-00-101, Detailed Prior to the Within 320 flight hours
airplanes, serial numbers 5301 Inspection of the Wing accumulation of 6,400 after the effective
through 5665 inclusive. Anti-Ice Duct Piccolo- total flight hours; date of this AD.
Tube, and except for airplanes
36[dash]21[dash]00[das having 6,400 total
h]101, Functional Test flight hours or more
of the Leading Edge as of the effective
Thermal Switches. date of this AD on
which the task has not
been accomplished:
prior to the next
scheduled 6,400 flight
hour task inspection
or prior to the next
scheduled
accomplishment of Task
57[dash]10[dash]00-208
in the applicable Time
Limits/Maintenance
Checks manual
specified in table 1
of this AD, whichever
occurs first.
CL-600-2B16 (CL-604 Variants) 30-11-00-101, Detailed Prior to the Within 320 flight hours
airplanes, serial numbers 5701 and Inspection of the Wing accumulation of 6,400 after the effective
subsequent. Anti-Ice Duct Piccolo- total flight hours. date of this AD.
Tube, and
36[dash]21[dash]00[das
h]101, Functional Test
of the Leading Edge
Thermal Switches.
----------------------------------------------------------------------------------------------------------------
(i) After accomplishing the actions required by paragraph (g) of
this AD, no alternative tasks or task intervals may be used unless
the tasks or task intervals are approved as an alternative method of
compliance (AMOC) in accordance with the procedures specified in
paragraph (j)(1) of this AD.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(j) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), ANE-170, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the ACO, send it to ATTN: Program Manager, Continuing
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite
410, Westbury, New York 11590; telephone 516-228-7300; fax 516-794-
5531. Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office. The AMOC approval letter must specifically
reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
Related Information
(k) Refer to MCAI Canadian Airworthiness Directive CF-2009-49R1,
dated January 21, 2010, and the service information specified in
Table 1 of this AD, for related information.
Material Incorporated by Reference
(l) You must use the applicable service information contained in
table 3 of this AD to do the actions required by this AD, unless the
AD specifies otherwise.
Table 3--Material Incorporated by Reference
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Tasks 30-11-00-101, Wing Anti- 38 June 19, 2009.
icing, and 30-11-00-102,
Wing Anti-icing, of the
Bombardier Challenger 601
Time Limits/Maintenance
Checks, PSP 601-5.
Tasks 30-11-00-101, Wing Anti- 34 June 19, 2009.
icing, and 30-11-00-102,
Wing Anti-icing, of the
Bombardier Challenger 601
Time Limits/Maintenance
Checks, PSP 601A-5.
Tasks 30-11-00-101, Detailed 13 August 12, 2009.
Inspection of the Wing Anti-
Ice Duct Piccolo-Tube, and
36-21-00-101, Functional
Test of the Leading Edge
Thermal Switches, of the
Bombardier Challenger 604
Time Limits/Maintenance
Checks, CH 604 TLMC.
Tasks 30-11-00-101, Detailed 1 August 12, 2009.
Inspection of the Wing Anti-
Ice Duct Piccolo-Tube, and
36-21-00-101, Functional
Test of the Leading Edge
Thermal Switches, of the
Bombardier Challenger 605
Time Limits/Maintenance
Checks, CH 605 TLMC.
------------------------------------------------------------------------
[[Page 41657]]
The title pages of these documents do not indicate the revision
level or issue date of the documents. Only the Record of Revisions
of these documents contains the revision level of these documents.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) 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; e-mail thd.crj@aero.bombardier.com; Internet https://www.bombardier.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the 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/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on April 13, 2011.
Ali Bahrami,
Manager,Transport Airplane Directorate,Aircraft Certification Service.
[FR Doc. 2011-17402 Filed 7-14-11; 8:45 am]
BILLING CODE 4910-13-P
