[Federal Register Volume 79, Number 160 (Tuesday, August 19, 2014)]
[Rules and Regulations]
[Pages 48968-48972]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-19150]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0129; Directorate Identifier 2013-NM-105-AD;
Amendment 39-17931; AD 2014-16-07]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2011-15-09 for
certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. AD
2011-15-09 required repetitive inspections for proper operation of the
main landing gear (MLG) alternate extension system (AES), and
corrective actions if necessary. This new AD requires, for certain
airplanes, new repetitive inspections for proper operation of the MLG
AES, and corrective actions if necessary. This new AD also requires
eventually replacing the MLG AES cam mechanism assembly with a new
assembly, which terminates the repetitive inspections for those
airplanes. This AD was prompted by a determination that, for certain
airplanes not affected by AD 2011-15-09, a different MLG AES cam
mechanism assembly was installed, resulting in input lever fractures
and inability to open the MLG door; those assemblies could be subject
to the same unsafe condition in AD 2011-15-09. We are issuing this AD
to prevent improper operation of the cam mechanism or rupture of the
door release cable, which
[[Page 48969]]
could result in loss of control of the airplane during landing.
DATES: This AD becomes effective September 23, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 23,
2014.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of August
2, 2011 (76 FR 42033, July 18, 2011).
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0129; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
For service information identified in this AD, contact Bombardier,
Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto,
Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-4539;
email [email protected]; Internet http://www.bombardier.com. You may view this referenced service information at
the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of this material at the FAA,
call 425-227-1221.
FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone (516) 228-7318; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2011-15-09, Amendment 39-16756 (76 FR 42033,
July 18, 2011). AD 2011-15-09 applied to certain Bombardier, Inc. Model
DHC-8-400, -401, and -402 airplanes. The NPRM published in the Federal
Register on March 5, 2014 (79 FR 12428).
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2011-01R2, dated May 21, 2013 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for certain Bombardier, Inc. Model DHC-8-400, -401,
and -402 airplanes. The MCAI states:
Two cases of the main landing gear (MLG) alternate extension
system (AES) cam mechanism failure were found during line checks.
The cam mechanism operates the cable to open the MLG door and
releases the MLG uplock in sequence. In the case where it is
necessary to deploy the MLG using the AES, the failure of the MLG
AES cam mechanism on one side will lead to an unsafe asymmetrical
landing configuration.
Preliminary investigation indicates that the cam mechanism
failure may have occurred and remained dormant after a previous AES
operation. The cam mechanism may not have fully returned to the
normal rested position. With the cam mechanism out of normal rested
position, normal powered landing gear door operation could introduce
sufficient loads to fracture the cam mechanism or rupture the door
release cable.
This [Canadian] AD mandates the initial and subsequent
[detailed] inspections for proper operation of the MLG AES cam
mechanism, and rectify [repair or replace cam assembly with new or
serviceable cam assembly] as necessary.
Since the original issue of this [Canadian] AD, Bombardier Inc.
has determined that the existing inspection procedure is
insufficient for verification of proper MLG AES cam mechanism
operation, and has superseded this inspection procedure. Revision 1
of this [Canadian] AD mandates the use of the revised inspection
[and rectification] procedure.
Prior to the introduction of MLG AES cam mechanism assembly part
number (P/N) 48510-5 as terminating action, an interim MLG AES cam
mechanism assembly P/N 48510-3 was introduced.
Revision 2 of this [Canadian] AD updates the applicability
paragraph, updates the MLG AES cam mechanism inspection criteria and
mandates the terminating action.
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0129.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received. The commenter supported
the NPRM (79 FR 12428, March 5, 2014).
``Contacting the Manufacturer'' Paragraph in This AD
Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
The MCAI or referenced service information in an FAA AD often
directs the owner/operator to contact the manufacturer for corrective
actions, such as a repair. Briefly, the Airworthy Product paragraph
allowed owners/operators to use corrective actions provided by the
manufacturer if those actions were FAA-approved. In addition, the
paragraph stated that any actions approved by the State of Design
Authority (or its delegated agent) are considered to be FAA-approved.
In the NPRM (79 FR 12428, March 5, 2014), we proposed to prevent
the use of repairs that were not specifically developed to correct the
unsafe condition, by requiring that the repair approval provided by the
State of Design Authority or its delegated agent specifically refer to
this FAA AD. This change was intended to clarify the method of
compliance and to provide operators with better visibility of repairs
that are specifically developed and approved to correct the unsafe
condition. In addition, we proposed to change the phrase ``its
delegated agent'' to include a design approval holder (DAH) with State
of Design Authority design organization approval (DOA), as applicable,
to refer to a DAH authorized to approve required repairs for the
proposed AD.
No comments were provided to the NPRM (79 FR 12428, March 5, 2014)
about these proposed changes. However, a comment was provided for an
NPRM having Directorate Identifier 2012-NM-101-AD (78 FR 78285,
December 26, 2013). The commenter stated the following: ``The proposed
wording, being specific to repairs, eliminates the interpretation that
Airbus messages are acceptable for approving minor deviations
(corrective actions) needed during accomplishment of an AD mandated
Airbus service bulletin.''
This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the
[[Page 48970]]
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, TCCA, or Bombardier,
Inc.'s TCCA Design Approval Organization (DAO).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DAO, the approval must include the DAO-authorized
signature. The DAO signature indicates that the data and information
contained in the document are TCCA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DAO-authorized signature approval are not TCCA-
approved, unless TCCA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that in many cases
the foreign manufacturer's service bulletin and the foreign authority's
MCAI might have been issued some time before the FAA AD. Therefore, the
DOA might have provided U.S. operators with an approved repair,
developed with full awareness of the unsafe condition, before the FAA
AD is issued. Under these circumstances, to comply with the FAA AD, the
operator would be required to go back to the manufacturer's DOA and
obtain a new approval document, adding time and expense to the
compliance process with no safety benefit.
Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this AD. Before adopting such a
requirement, the FAA will coordinate with affected DAHs and verify they
are prepared to implement means to ensure that their repair approvals
consider the unsafe condition addressed in this AD. Any such
requirements will be adopted through the normal AD rulemaking process,
including notice-and-comment procedures, when appropriate.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``DAH with State of Design Authority design
organization approval,'' but instead we have provided the specific
delegation approval granted by the State of Design Authority for the
DAH throughout this AD.
Change to Paragraph (g)(3) of This AD
For clarity purposes, we have revised paragraph (g)(3) of this AD
by adding new paragraphs (g)(3)(i) and (g)(3)(ii) to this AD.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 12428, March 5, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 12428, March 5, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 75 airplanes of U.S. registry.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection in AD 2011-15-09, Up to 24 $2,609............ Up to $4,649 per Up to $348,675 per
Amendment 39-16756 (76 FR work[dash]hours x inspection cycle. inspection cycle.
42033, July 18, 2011). $85 per hour = up
to $2,040 per
inspection cycle.
Inspection [new action]......... 1 work-hour x $85 $0................ $85 per inspection $6,375 per
per hour = $85 cycle. inspection cycle.
per inspection
cycle.
Replacement of both cam 4 work-hours x $85 $7,676 (2 cam $80,167........... $601,200.
assemblies [new terminating per hour = $680 assemblies).
action]. [$340 per cam
assembly].
----------------------------------------------------------------------------------------------------------------
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
[[Page 48971]]
under the criteria of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0129; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2011-15-09, Amendment 39-16756 (76 FR 42033, July 18, 2011), and adding
the following new AD:
2014-16-07 Bombardier, Inc.: Amendment 39-17931. Docket No. FAA-
2014-0129; Directorate Identifier 2013-NM-105-AD.
(a) Effective Date
This AD becomes effective September 23, 2014.
(b) Affected ADs
This AD replaces AD 2011-15-09, Amendment 39-16756 (76 FR 42033,
July 18, 2011).
(c) Applicability
This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -
402 airplanes, certificated in any category, serial numbers 4001,
4003 through 4418 inclusive, 4422 and 4423.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by a determination that a different main
landing gear (MLG) alternate extension system (AES) cam mechanism
assembly was installed resulting in input lever fractures and
inability to open the MLG door; those assemblies could be subject to
the same unsafe condition in the existing AD. We are issuing this AD
to prevent improper operation of the cam mechanism or rupture of the
door release cable, which could result in loss of control of the
airplane during landing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Detailed Inspection for Proper Operation of the MLG
This paragraph restates the requirement in paragraph (i) of AD
2011-15-09, Amendment 39-16756 (76 FR 42033, July 18, 2011), with
revised service information. For airplanes with a MLG AES cam
mechanism assembly having part number (P/N) 48510-1: Within 50
flight hours or 10 days after August 2, 2011 (the effective date of
AD 2011-15-09, Amendment 39-16756 (76 FR 42033, July 18, 2011)),
whichever occurs first, do a detailed inspection for proper
operation of the MLG AES cam mechanism, in accordance with paragraph
A) of Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated February
15, 2011; or Bombardier Repair Drawing 8/4-32-0160, Issue 6, dated
June 27, 2012. As of the effective date of this AD, use only
Bombardier Repair Drawing 8/4-32-0160, Issue 6, dated June 27, 2012.
Repeat the inspection thereafter at intervals not to exceed 50
flight hours or 10 days, whichever occurs first.
(1) If the cam mechanism is found to reset to the normal rested
position without any sticking or binding, it is operating properly.
(2) If the cam mechanism has not reset to its normal rested
position, or if any sticking or binding is observed, before further
flight, remove the cam assembly, in accordance with paragraph A) of
Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated February 15,
2011; or Bombardier Repair Drawing 8/4-32-0160, Issue 6, dated June
27, 2012, and do the actions in paragraph (g)(2)(i) or (g)(2)(ii) of
this AD. As of the effective date of this AD, use only Bombardier
Repair Drawing 8/4-32-0160, Issue 6, dated June 27, 2012.
(i) Repair the cam mechanism assembly, including doing detailed
inspections for discrepancies (an inspection to determine proper
operation, an inspection for damage, an inspection for corrosion and
cadmium coating degradation, and inspections to determine dimensions
are within the limits specified in paragraph B) of Bombardier Repair
Drawing 8/4-32-0160, Issue 3, dated February 15, 2011; or Bombardier
Repair Drawing 8/4-32-0160 Issue 6, dated June 27, 2012, in
accordance with paragraph B) of Bombardier Repair Drawing 8/4-32-
0160, Issue 3, dated February 15, 2011; and install the repaired cam
assembly in accordance with paragraph C) of Bombardier Repair
Drawing 8/4-32-0160, Issue 3, dated February 15, 2011; or Bombardier
Repair Drawing 8/4-32-0160, Issue 6, dated June 27, 2012. As of the
effective date of this AD, use only Bombardier Repair Drawing 8/4-
32-0160, Issue 6, dated June 27, 2012.
(ii) Install a new or serviceable cam assembly, in accordance
with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 3,
dated February 15, 2011; or Bombardier Repair Drawing 8/4-32-0160,
Issue 6, dated June 27, 2012. As of the effective date of this AD,
use only Bombardier Repair Drawing 8/4-32-0160, Issue 6, dated June
27, 2012.
(3) If the cam mechanism is found damaged or inoperative during
the repair specified in paragraph (g)(2)(i) of this AD; or if any
discrepancies are found and Bombardier Repair Drawing 8/4-32-0160,
Issue 3, dated February 15, 2011, or Bombardier Repair Drawing 8/4-
32-0160, Issue 6, dated June 27, 2012, does not specify repairs for
those discrepancies; or repairs specified in paragraph (g)(2)(i) of
this AD cannot be accomplished: Before further flight, accomplish
paragraph (g)(3)(i) or (g)(3)(ii) of this AD.
(i) Repair and reinstall 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.
(ii) Install a new or serviceable cam assembly, in accordance
with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 3,
dated February 15, 2011; or Bombardier Repair Drawing 8/4-32-0160,
Issue 6, dated June 27, 2012. As of the effective date of this AD,
use only Bombardier Repair Drawing 8/4-32-0160, Issue 6, dated June
27, 2012, to install the cam assembly.
(h) New Inspection for Proper Operation of the MLG Replacement Part
For airplanes with a MLG AES cam mechanism assembly having P/N
48510-3: Within 1,800 flight hours or 9 months after installation of
the assembly, whichever occurs first after the effective date of
this AD, do a detailed inspection for proper operation of the MLG
AES cam mechanism, in accordance with paragraph A) of Bombardier
Repair Drawing 8/4-32-0160, Issue 6, dated June 27, 2012. Repeat the
inspection thereafter at intervals not to exceed 600 flight hours or
3 months, whichever occurs first.
(1) If the cam mechanism is found to reset to the normal rested
position without any sticking or binding, it is operating properly.
(2) If the cam mechanism has not reset to its normal rested
position, or if any sticking or binding is observed, before further
flight, remove the cam assembly, in accordance with paragraph A) of
Bombardier Repair Drawing 8/4-32-0160, Issue 6, dated June 27, 2012,
and do the actions required by paragraphs (h)(2)(i) or (h)(2)(ii) of
this AD.
(i) Repair the cam mechanism assembly, including doing detailed
inspections for discrepancies (an inspection to determine proper
operation, an inspection for damage, an inspection for corrosion and
cadmium coating degradation, and inspections to determine dimensions
are within the limits specified in paragraph B) of Bombardier Repair
Drawing 8/4-32-0160, Issue 6, dated June 27, 2012), in accordance
with paragraph
[[Page 48972]]
B) of Bombardier Repair Drawing 8/4-32-0160, Issue 6, dated June 27,
2012; and install the repaired cam assembly in accordance with
paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 6,
dated June 27, 2012.
(ii) Install a new or serviceable cam assembly, in accordance
with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 6,
dated June 27, 2012.
(3) If the cam mechanism is found damaged or inoperative during
the repair specified in paragraph (h)(2)(i) of this AD; or if any
discrepancies are found and Bombardier Repair Drawing 8/4-32-0160,
Issue 6, dated June 27, 2012, does not specify repairs for those
discrepancies; or repairs specified in paragraph (h)(2)(i) of this
AD cannot be accomplished: Before further flight, do the applicable
actions required by paragraph (h)(3)(i) or (h)(3)(ii) of this AD.
(i) Repair and reinstall using a method approved by the Manager,
ANE-170, New York ACO, FAA, or TCCA; or Bombardier, Inc.'s TCCA
Design Approval Organization (DAO). If approved by the DAO, the
approval must include the DAO-authorized signature.
(ii) Install a new or serviceable cam assembly, in accordance
with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 6,
dated June 27, 2012.
(i) New Credit for Previous Actions for Paragraphs (g) and (h) of This
AD
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Bombardier Repair Drawing
8/4-32-0160, Issue 5, dated June 6, 2012, which is not incorporated
by reference in this AD.
(j) New Terminating Action
Within 6,000 flight hours or 36 months after the effective date
of this AD, whichever occurs first, replace any MLG AES cam
mechanism assembly having P/N 48510-1 or P/N 48510-3 with a new MLG
AES cam mechanism assembly having P/N 48510-5, in accordance with
the Accomplishment Instructions of Bombardier Service Bulletin 84-
32-100, Revision A, dated August 30, 2012. Accomplishing this
replacement terminates the repetitive inspections required by this
AD.
(k) New Credit for Previous Actions for Paragraph (j) of This AD
This paragraph provides credit for actions required by paragraph
(j) of this AD, if those actions were performed before the effective
date of this AD using Bombardier Service Bulletin 84-32-100, dated
August 15, 2012, which is not incorporated by reference in this AD.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), ANE-170, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. ATTN: Program Manager,
Continuing Operational Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax
516-794-5531. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must
specifically reference this AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, New York ACO,
ANE-170, Engine and Propeller Directorate, FAA; or TCCA; or
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If
approved by the DAO, the approval must include the DAO-authorized
signature.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2011-01R2, dated May 21,
2013, for related information. You may examine the MCAI in the AD
docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0129.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(5) and (n)(6) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
September 23, 2014.
(i) Bombardier Repair Drawing 8/4-32-0160, Issue 6, dated June
27, 2012. The issue dates for this document are identified only on
sheets 1 and 1A of this document.
(ii) Bombardier Service Bulletin 84-32-100, Revision A, dated
August 30, 2012.
(4) The following service information was approved for IBR on
August 2, 2011 (76 FR 42033, July 18, 2011).
(i) Bombardier Repair Drawing 8/4-32-0160, Issue 3, dated
February 15, 2011. The issue dates for this document are identified
only on the first page of this document.
(ii) Reserved.
(5) For service information identified in this AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000;
fax 416-375-4539; email [email protected]; Internet
http://www.bombardier.com.
(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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on July 30, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-19150 Filed 8-18-14; 8:45 am]
BILLING CODE 4910-13-P