
[Federal Register Volume 78, Number 93 (Tuesday, May 14, 2013)]
[Proposed Rules]
[Pages 28156-28159]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-11382]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0419; Directorate Identifier 2012-NM-129-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Bombardier, Inc. Model DHC-8-400 series airplanes. This 
proposed AD was prompted by reports of excessive wear on the lower 
latch surface of the main landing gear (MLG) up-lock hook. This 
proposed AD would require revising the maintenance program. We are 
proposing 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: We must receive comments on this proposed AD by June 28, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://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.

[[Page 28157]]

     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.
    For service information identified in this proposed 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 review copies of the 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://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 proposed 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: 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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0419; 
Directorate Identifier 2012-NM-129-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    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 [Canadian] AD CF-2002-
13R2. 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 
obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

    Bombardier, Inc. has issued the following service information. The 
actions described in this service information are intended to correct 
the unsafe condition identified in the MCAI.
     Bombardier Repair Drawing 8/4-32-0190, Issue 2, dated 
January 14, 2013.
     Bombardier Q400 All Operator Message No. 515, DHC8-400-
AOM-515, Revision 2009-06-24, dated April 4, 2012.
     Bombardier Temporary Revision MRB-66, dated December 7, 
2011, to Section 1-32, ``Systems/Powerplant Maintenance Program,'' of 
Part 1 of the Bombardier Dash 8 Series 400 Maintenance Requirements 
Manual, PSM 1-84-7.

FAA's Determination and Requirements of This Proposed 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 proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 83 products of U.S. registry. We also estimate that 
it would take about 1 work-hour per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $7,055, 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

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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

[[Page 28158]]

    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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

Bombardier, Inc.: Docket No. FAA-2013-0419; Directorate Identifier 
2012-NM-129-AD.

(a) Comments Due Date

    We must receive comments by June 28, 2013.

(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 Program Revision

    Within 30 days after the effective date of this AD, revise the 
maintenance program to incorporate the information specified in Task 
Number 323100-202 as specified in Bombardier Temporary Revision MRB-
66, dated December 7, 2011, to Section 1-32, ``Systems/Powerplant 
Maintenance Program,'' of Part 1 of the Bombardier Dash 8 Series 400 
Maintenance Requirements Manual, PSM 1-84-7. Do the initial 
functional check at the applicable time specified in paragraph 
(g)(1), (g)(2), or (g)(3) of this AD.

    Note 1 to Paragraph (g) of this AD: The maintenance 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,'' into Part 1 of the Bombardier Dash 8 Series 400 
Maintenance Requirements Manual, PSM 1-84-7. When this temporary 
revision (TR) 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 effective date of this AD: Do the initial 
functional check 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 less than 15,000 total flight cycles, as of the 
effective date of this AD: Do the initial functional check 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 less than 12,000 total 
flight cycles as of the effective date of this AD: Do the initial 
functional check 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) 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 paragraph (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, in accordance with the 
Inspection Notes of Bombardier Repair Drawing 8/4-32-0190, Issue 1, 
dated April 2, 2012.
    (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) 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 (AMOC) in accordance with the procedures specified in 
paragraph (k) of this AD.

(j) Reporting

    Submit a report of the initial functional check findings at the 
applicable time specified in paragraph (j)(1) or (j)(2) of this AD 
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.
    (1) If the functional check was done on or after the effective 
date of this AD: Submit the report within 30 days after the 
functional check.
    (2) If the functional check was done before the effective date 
of this AD: Submit the report within 30 days after the effective 
date of this AD.

[[Page 28159]]

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office, 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 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.
    (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.

(l) Related Information

    (1) Refer to MCAI Canadian Airworthiness Directive CF-2012-21, 
dated June 25, 2012; and the service information specified in 
paragraphs (l)(1)(i), (l)(1)(ii), and (l)(1)(iii) of this AD for 
related information.
    (i) Bombardier Repair Drawing 8/4-32-0190, Issue 2, dated 
January 14, 2013.
    (ii) Bombardier Q400 All Operator Message No. 515, DHC8-400-AOM-
515, Revision 2009-06-24, dated April 4, 2012.
    (iii) Bombardier Temporary Revision MRB-66, dated December 7, 
2011, to Section 1-32, ``Systems/Powerplant Maintenance Program,'' 
of Part 1 of the Bombardier Dash 8 Series 400 Maintenance 
Requirements Manual, PSM 1-84-7.
    (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 review copies of the 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.

    Issued in Renton, Washington, on May 6, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-11382 Filed 5-13-13; 8:45 am]
BILLING CODE 4910-13-P


