
[Federal Register Volume 79, Number 64 (Thursday, April 3, 2014)]
[Rules and Regulations]
[Pages 18611-18615]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-05425]



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 Rules and Regulations
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  Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules 
and Regulations  

[[Page 18611]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0419; Directorate Identifier 2012-NM-129-AD; 
Amendment 39-17800; AD 2014-05-28]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted 
by reports of excessive wear on the lower latch surface of the main 
landing gear (MLG) up-lock hook. This AD requires revising the 
maintenance program. We are issuing this AD to detect and correct up-
lock hooks worn beyond the wear limit, which could prevent the 
successful extension of the MLG using the primary landing gear 
extension system, which in combination with an alternate extension 
system failure could result in the inability to extend the MLG.

DATES: This AD becomes effective May 8, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 8, 2014.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0419-0002 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 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 thd.qseries@aero.bombardier.com; 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 include an AD that would apply to certain Bombardier, Inc. 
Model DHC-8-400 series airplanes. The NPRM published in the Federal 
Register on May 14, 2013 (78 FR 28156). The NPRM was prompted by 
reports of excessive wear on the lower latch surface of the main 
landing gear (MLG) up-lock hook. The NPRM proposed to require revising 
the maintenance program. We are issuing this AD to detect and correct 
up-lock hooks worn beyond the wear limit, which could prevent the 
successful extension of the MLG using the primary landing gear 
extension system, which in combination with an alternate extension 
system failure could result in the inability to extend the MLG.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2012-21, dated June 25, 2012 (referred to after this as ``the MCAI''), 
to correct an unsafe condition for the specified products. The MCAI 
states:

    The main landing gear up-lock assembly part number (P/N) 46500-7 
was introduced as the terminating action to AD CF-2002-13R2 [http://www.regulations.gov/#!documentDetail;D=FAA-2013-0419-0002]. The main 
landing gear up-lock assembly P/N 46500-9 was later introduced as a 
product improvement and has the same up-lock hook as P/N 46500-7.
    Due to a delay in the release of the new Maintenance Review 
Board (MRB) task associated with P/Ns 46500-7 and 46500-9, it is 
anticipated that in-service aeroplanes may be operating with up-lock 
hooks worn beyond the wear limit. An up-lock hook worn beyond the 
wear limit could prevent the successful extension of the main 
landing gear using the primary landing gear extension system. In 
combination with an alternate extension system failure, this could 
result in the inability to extend the main landing gear.
    This [Canadian] AD mandates the incorporation of the MRB task 
number 323100-202.

MRB Task Number 323100-202 adds a functional check of the main landing 
gear up-lock assembly latch to the maintenance program. You may examine 
the MCAI in the AD docket on the Internet at http://www.regulations.gov 
by searching for and locating it in Docket No. FAA-2013-0419.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request for Clarification of Maintenance Program Requirement

    Horizon Air requested that we revise paragraph (g) of the NPRM (78 
FR 28156, May 14, 2013) to clarify which maintenance program (the 
operator or maintenance program in PSM 1-84-7) would require revision. 
Horizon Air also asked whether the operators are required to put the 
MRB task into their program and revise PSM 1-84-7, or just revise PSM 
1-84-7.
    We agree to clarify. We have revised the language in paragraph (g) 
by replacing the phrase ``revise the maintenance program'' with the 
phrase ``revise the maintenance or inspection program as applicable.'' 
The AD requires revising the maintenance or inspection program, as 
applicable, to incorporate the information in Bombardier Temporary 
Revision MRB-66, dated December 7, 2011, to Section 1-32, Systems/
Powerplant Maintenance Program of MRB Report Part 1, Bombardier Q400 
Dash 8 Maintenance Requirements Manual, PSM 1-84-7. We have revised the 
introductory text of paragraph (g) of this final rule to include this 
terminology.

[[Page 18612]]

Request for Clarification of Procedures

    Horizon Air requested clarification of the procedures to be used to 
accomplish the actions specified in paragraph (g) of the NPRM (78 FR 
28156, May 14, 2013). Horizon Air stated that paragraph (g) would 
mandate implementation of Task Number 323100-202 into the maintenance 
program, but is silent on which procedures are used to accomplish the 
task.
    We agree to clarify. This final rule requires incorporating Task 
Number 323100-202, as introduced by Temporary Revision (TR) MRB-66 into 
the maintenance or inspection program. Bombardier Temporary Revision 
MRB-66, dated December 7, 2011, to Section 1-32, Systems/Powerplant 
Maintenance Program of MRB Report Part 1, Bombardier Q400 Dash 8 
Maintenance Requirements Manual, PSM 1-84-7 provides information on how 
to accomplish the task. No change has been made to this final rule in 
this regard.

Request for Credit for Actions Done Previously

    Horizon Air requested that we allow credit for actions done prior 
to the effective date of the AD using airplane maintenance manual (AMM) 
Task Number 32-31-21-220-801 for the corresponding actions specified in 
paragraphs (g)(1), (g)(2), and (g)(3) of the NPRM (78 FR 28156, May 14, 
2013).
    We agree to allow credit as requested. The final rule provides an 
initial compliance time for the performance of MRB Task Number 323100-
202. If the operator has already performed the initial task using AMM 
Task 32-31-21-220-801, then the intent of the final rule is met for the 
initial task. No change has been made to this final rule in this 
regard.

Request To Allow Replacement of Up-Lock With Serviceable Up-Lock

    Horizon Air (the commenter) requested that we revise paragraph (h) 
of the NPRM (78 FR 28156, May 14, 2013) to require that replacement up-
locks be ``serviceable'' rather than ``new.'' The commenter stated that 
operators are required to purchase zero time ``new'' up-locks to meet 
the intent of the final rule, which places an unnecessary financial 
burden on operators.
    We agree with the commenter that operators should be allowed to use 
a serviceable (i.e., reworked) up-lock. Paragraphs (h)(2)(i), 
(h)(2)(ii), (h)(2)(iii), and (h)(4)(ii), as stated in the NPRM (78 FR 
28156, May 14, 2013), give the option to replace the affected parts 
with new or reworked (serviceable) parts, or a new up-lock assembly. No 
change has been made to this final rule in this regard.

Request To Change Heading of Paragraph (h) of the NPRM (78 FR 28156, 
May 14, 2013)

    Horizon Air (the commenter) requested that we change the heading 
for paragraph (h) of the NPRM (78 FR 28156, May 14, 2013) to ``Optional 
Method of Compliance.'' The commenter stated that the paragraph 
provides instructions that may be used in lieu of the initial 
functional check required by paragraph (g).
    We agree with the commenter. We have changed the heading of 
paragraph (h) of this final rule to ``Optional Method of Compliance.''

Request To Allow Operators To Reduce the Repetitive Intervals

    Horizon Air (the commenter) requested that the requirements of 
paragraph (i) of the NPRM (78 FR 28156, May 14, 2013) be changed to 
allow operators to set repetitive intervals at times less than those 
required by Bombardier Temporary Revision MRB-66, dated December 7, 
2011. The commenter stated the language in paragraph (i) of the NPRM is 
too restrictive in regard to the repetitive intervals.
    We agree to clarify the repetitive interval that is specified in 
Bombardier Temporary Revision MRB-66, dated December 7, 2011. In 
paragraph (g) of this final rule, we have added a sentence to specify 
that the repetitive interval is not to exceed 6,000 flight hours or 60 
months, whichever occurs first. Because the compliance time is 
specified as ``not to exceed'' the interval, operators are allowed to 
do the actions earlier than the specified interval. We have not changed 
paragraph (j) of this final rule (referred to as paragraph (i) of the 
NPRM (78 FR 28156, May 14, 2013)), which specifies that no alternative 
intervals may be used unless the intervals are approved as an 
alternative method of compliance in accordance with the procedures 
specified in paragraph (l) of this final rule.

Request To Remove Reporting Requirements

    Horizon Air (the commenter) requested that we remove the reporting 
requirements from the NPRM (78 FR 28156, May 14, 2013). The commenter 
stated that the AMM task and TR MRB-66, dated December 7, 2011, of PSM 
1-84-7, do not include a reporting requirement. The commenter stated 
that an operator that performed the AMM task or the MRB task prior to 
the release of the final rule would not have recorded the wear 
dimensions because there was no requirement to record it in either 
task. The commenter stated that to force operators who have proactively 
accomplished the inspection to go back and perform the task again just 
to get a wear measurement to fulfill the requirements of paragraph (j) 
of the NPRM places an unnecessary financial burden on the operator, and 
provides data that do nothing to enlighten the manufacturer to the 
amount of hook wear occurring on high-time up-locks.
    We agree that any operator that has performed the AMM task prior to 
publication of the NPRM (78 FR 28156, May 14, 2013) would not have 
recorded any dimension. However, we disagree with the request to remove 
the requirement entirely, because it is beneficial for any operator 
that has not performed the required task to submit the report. We have 
revised paragraph (j) of this final rule to state: ``For airplanes on 
which the requirements of paragraph (g) or (h) of this AD have been 
accomplished after the effective date of this AD: Within 30 days after 
the functional check, submit a report of the initial functional check 
findings using Form No ISETS-03-AOM Q400 in Bombardier Q400 All 
Operator Message DHC8-400-AOM-515, Revision 2009-06-24, dated April 4, 
2012. Send the report to Bombardier, Inc., Technical Help Desk, phone: 
416-375-4000; fax: 416-375-4539; email: 
thd.qseries@aero.bombardier.com.''

Other Changes to This Final Rule

    We have revised the introductory text to paragraph (g) and 
paragraphs (g)(1), (g)(2), and (g)(3) of this final rule to clarify the 
requirements regarding the compliance time for doing the initial 
functional check. The compliance time has not changed.
    We have removed the reference to Bombardier Repair Drawing 8/4-32-
0190, Issue 1, dated April 2, 2012, in paragraph (h)(3) of this final 
rule because the introductory text of paragraph (h) already refers to 
the service information.
    We have also added new paragraph (i) to this final rule to allow 
credit for using Bombardier Repair Drawing 8/4-32-0190, Issue 1, dated 
April 2, 2012. We have re-designated subsequent paragraphs accordingly.

Conclusion

    We reviewed the relevant data, including the comments received, and 
determined that air safety and the public interest require adopting 
this AD

[[Page 18613]]

with the changes described previously and minor editorial changes. We 
have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 28156, May 14, 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 28156, May 14, 2013).

Costs of Compliance

    Based on the service information, we estimate that this AD affects 
about 83 products of U.S. registry. We also estimate that it takes 
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 the AD on U.S. operators to be $7,055, 
or $85 per product.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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 http://www.regulations.gov/#!documentDetail;D=FAA-2013-0419-0002; 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2014-05-28 Bombardier, Inc.: Amendment 39-17800. Docket No. FAA-
2013-0419; Directorate Identifier 2012-NM-129-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective May 8, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -
402 airplanes, certificated in any category, serial numbers 4001 and 
subsequent, equipped with a main landing gear (MLG) up-lock having 
part number 46500-7 or 46500-9.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
gear.

(e) Reason

    This AD was prompted by reports of excessive wear on the lower 
latch surface of the MLG up-lock hook. We are issuing this AD to 
detect and correct up-lock hooks worn beyond the wear limit, which 
could prevent the successful extension of the MLG using the primary 
landing gear extension system, which in combination with an 
alternate extension system failure could result in the inability to 
extend the MLG.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Maintenance/Inspection Program Revision

    Within 30 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate the 
information specified in Task Number 323100-202 of Bombardier 
Temporary Revision MRB-66, dated December 7, 2011, to Section 1-32, 
Systems/Powerplant Maintenance Program of MRB Report Part 1, 
Bombardier Q400 Dash 8 Maintenance Requirements Manual, PSM 1-84-7. 
The compliance time for the initial functional check is at the 
applicable time specified in paragraph (g)(1), (g)(2), or (g)(3) of 
this AD. The compliance time for the repetitive interval is at 
intervals not to exceed 6,000 flight hours or 60 months, whichever 
occurs first.

    Note 1 to Paragraph (g) of this AD:  The maintenance or 
inspection program revision required by paragraph (g) of this AD may 
be done by inserting a copy of Bombardier Temporary Revision MRB-66, 
dated December 7, 2011, to Section 1-32, Systems/Powerplant 
Maintenance Program of MRB Report Part 1, Bombardier Q400 Dash 8 
Maintenance Requirements Manual, PSM 1-84-7. When this temporary 
revision has been included in general revisions of the PSM, the 
general revisions may be inserted in the PSM, provided the relevant 
information in the general revision is identical to that in TR MRB-
66.

    (1) For up-lock hook assemblies that have 15,000 total flight 
cycles or more as of the

[[Page 18614]]

effective date of this AD: The compliance time for doing the initial 
functional check is within 600 flight cycles after the effective 
date of this AD.
    (2) For up-lock hook assemblies that have 12,000 total flight 
cycles or more, but fewer than 15,000 total flight cycles, as of the 
effective date of this AD: The compliance time for doing the initial 
functional check is within 1,200 flight cycles after the effective 
date of this AD, but before the accumulation of 15,600 total flight 
cycles on the assembly.
    (3) For up-lock hook assemblies with fewer than 12,000 total 
flight cycles as of the effective date of this AD: The compliance 
time for doing the initial functional check is within 6,000 flight 
cycles after the effective date of this AD, but before the 
accumulation of 13,200 total flight cycles on the assembly.

(h) Optional Method of Compliance

    For any up-lock assembly outside the wear limit specified in the 
Inspection Notes of Bombardier Repair Drawing 8/4-32-0190, Issue 2, 
dated January 14, 2013; and on which the up-lock roller on the MLG 
shock strut is free to rotate and free of any damage or flat spots 
on the riding surface: In lieu of doing the initial functional 
check, as required by paragraph (g) of this AD, accomplishing the 
actions specified in paragraphs (h)(1) through (h)(4) of this AD in 
accordance with Bombardier Repair Drawing 8/4-32-0190, Issue 2, 
dated January 14, 2013, may be done. However, as of 36 months after 
the effective date of this AD, the initial functional check must be 
done in accordance with the requirements of paragraph (g) of this 
AD.
    (1) Do a detailed inspection for deformation, corrosion, or 
broken springs of the up-lock assembly of the MLG. If deformation, 
corrosion, or broken springs are found, before further flight, 
replace the spring.
    (2) Measure the groove depth of the lower latch working surface.
    (i) If the groove depth is greater than or equal to 0.022 inch, 
before further flight, replace the up-lock assembly part number (P/
N) 46500-7 or 46500-9 with a new assembly, or an assembly with a new 
or reworked hook installed.
    (ii) If the groove depth is greater than 0.017 inch and less 
than or equal to 0.0215 inch: Within 600 flight cycles after 
accomplishing the measurement, do the up-lock inspection as 
specified in paragraphs (h)(1) and (h)(2) of this AD, and repeat the 
inspections thereafter at intervals not to exceed 600 flight cycles. 
Replacing the up-lock hook with a new or reworked hook, or 
installing a new up-lock assembly, terminates the repetitive 
inspections.
    (iii) If the groove depth is between 0.0215 and 0.0220 inch: 
Within 300 flight cycles after the measurement, replace the up-lock 
hook with a new or reworked hook, or with a new up-lock assembly.
    (3) Unless already accomplished, within 6,000 flight hours or 36 
months after doing the initial inspection specified in paragraph 
(h)(1) of this AD: Replace the up-lock assembly with a new assembly, 
or a new or reworked hook installed.
    (4) Inspect the up-lock roller on both main gear shock struts 
for freedom of movement.
    (i) If the up-lock roller cannot be freely rotated by finger 
force, or any flat spots exceeding 0.060 inch (across the flats) are 
found, before further flight, replace the up-lock roller.
    (ii) Repeat the inspections thereafter at intervals not to 
exceed 50 flight hours until the up-lock has been replaced with a 
new assembly, or a new or reworked up-lock hook has been installed. 
Replacing the up-lock with a new assembly, or installing a new or 
reworked up-lock hook, terminates the repetitive inspection 
requirements.

(i) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Bombardier Repair Drawing 8/4-32-
0190, Issue 1, dated April 2, 2012, which is not incorporated by 
reference in this AD.

(j) No Alternative Actions or Intervals

    After accomplishing the revision required by paragraph (g) of 
this AD, no alternative actions (e.g., inspections) or intervals may 
be used, except as provided by paragraph (h) of this AD unless the 
actions or intervals are approved as an alternative method of 
compliance in accordance with the procedures specified in paragraph 
(l) of this AD.

(k) Reporting

    For airplanes on which the requirements of paragraph (g) or (h) 
of this AD have been accomplished after the effective date of this 
AD: Within 30 days after the functional check, submit a report of 
the initial functional check findings using Form No ISETS-03-AOM 
Q400 in Bombardier Q400 All Operator Message DHC8-400-AOM-515, 
Revision 2009-06-24, dated April 4, 2012. Send the report to 
Bombardier, Inc., Technical Help Desk, phone: 416-375-4000; fax: 
416-375-4539; email: thd.qseries@aero.bombardier.com.

(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, ANE-170, FAA, has the authority 
to approve AMOCs for this AD, if requested using the procedures 
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your 
request to your principal inspector or local Flight Standards 
District Office, as appropriate. If sending information directly to 
the ACO, send it to ATTN: Program Manager, Continuing Operational 
Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone 516-228-7300; fax 516-794-5531. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or by the Design Approval Holder with a State of 
Design Authority's design organization approval). For a repair 
method to be approved, the repair approval must specifically refer 
to this AD. You are required to ensure the product is airworthy 
before it is returned to service.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2012-21, dated June 25, 
2012, for related information. This MCAI can be found in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0419-0002.
    (2) 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 thd.qseries@aero.bombardier.com; 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.

(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 the AD specifies otherwise.
    (i) Bombardier Q400 All Operator Message DHC8-400-AOM-515, 
Revision 2009-06-24, dated April 4, 2012.
    (ii) Bombardier Repair Drawing 8/4-32-0190, Issue 2, including 
handwritten annotations, dated January 14, 2013.
    (iii) Bombardier Temporary Revision MRB-66, dated December 7, 
2011, to Section 1-32, Systems/Powerplant Maintenance Program of MRB 
Report Part 1, Bombardier Q400 Dash 8 Maintenance Requirements 
Manual, PSM 1-84-7.
    (3) For service information identified in this AD, contact 
Bombardier, Inc., Q-Series

[[Page 18615]]

Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 
1Y5, Canada; telephone 416-375-4000; fax 416-375-4539; email 
thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-05425 Filed 4-2-14; 8:45 am]
BILLING CODE 4910-13-P


