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[Federal Register Volume 79, Number 57 (Tuesday, March 25, 2014)]
[Proposed Rules]
[Pages 16245-16247]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-06493]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0144; Directorate Identifier 2013-NM-232-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 Model DHC-8-400, -401, and -402 airplanes. This 
proposed AD was prompted by reports of rudder bearings falling out of 
the fore rudder hinge bracket during assembly. This proposed AD would 
require a proof load test and detailed inspections; and installation of 
a new bearing, reaming, or repair of the bearing if necessary. We are 
proposing this AD to detect and correct improper bearing installation, 
which could result in abnormal wear and potential increased freeplay in 
the rudder system, and resultant airframe vibration, leading to 
compromise of the flutter margins of the airplane.

DATES: We must receive comments on this proposed AD by May 9, 2014.

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.
     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 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0144; 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 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: Ricardo Garcia, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone 516-228-7331; fax 516-794-5531.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about

[[Page 16246]]

this proposed AD. Send your comments to an address listed under the 
ADDRESSES section. Include ``Docket No. FAA-2014-0144; Directorate 
Identifier 2013-NM-232-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-
2013-34, dated November 1, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for the specified products. The MCAI 
states:

    It was reported that rudder bearings were falling out of the 
fore rudder hinge bracket during assembly. Investigation revealed 
the root cause as improper application of the adhesive compound and 
the lack of application of sealant during the installation of the 
rudder bearings into the fore rudder hinge bracket. The improper 
bearing installation, if not corrected, could result in abnormal 
wear and could potentially increase the freeplay in the rudder 
system. This may result in airframe vibration, eventually 
compromising the flutter-margins of the aeroplane.
    This [Canadian] AD mandates the inspection, and rectification as 
required, of the fore rudder bearings in the hinge bracket assembly.

Required actions include a proof load test for slippage and freeplay. 
Related investigative actions include a detailed inspection of a 
certain bearing for damage, corrosion, and dimension conformity; and a 
detailed inspection of the fitting bore of the fore rudder hinge 
bracket for wear, damage, corrosion, and dimension conformity. 
Corrective actions include installation of a new bearing, reaming, or 
repair of the bearing. 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-2014-0144.

Relevant Service Information

    Bombardier has issued Service Bulletin 84-27-44, Revision `A,' 
dated June 10, 2009. 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 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.
    In many FAA transport ADs, when the service information specifies 
to contact the manufacturer for further instructions if certain 
discrepancies are found, we typically include in the AD a requirement 
to accomplish the action using a method approved by either the FAA or 
the State of Design Authority (or its delegated agent).
    We have recently been notified that certain laws in other countries 
do not allow such delegation of authority, but some countries do 
recognize design approval organizations. In addition, we have become 
aware that some U.S. operators have used repair instructions that were 
previously approved by a State of Design Authority or a Design Approval 
Holder (DAH) as a method of compliance with this provision in FAA ADs. 
Frequently, in these cases, the previously approved repair instructions 
come from the airplane structural repair manual or the DAH repair 
approval statements that were not specifically developed to address the 
unsafe condition corrected by the AD. Using repair instructions that 
were not specifically approved for a particular AD creates the 
potential for doing repairs that were not developed to address the 
unsafe condition identified by the MCAI AD, the FAA AD, or the 
applicable service information, which could result in the unsafe 
condition not being fully corrected.
    To prevent the use of repairs that were not specifically developed 
to correct the unsafe condition, this proposed AD would require that 
the repair approval specifically refer to the FAA AD. This change is 
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 use the 
phrase ``its delegated agent, or the DAH with State of Design Authority 
design organization approval, as applicable'' in this proposed AD to 
refer to a DAH authorized to approve required repairs for this proposed 
AD.

Costs of Compliance

    We estimate that this proposed AD affects 78 airplanes of U.S. 
registry.
    We also estimate that it would take about 7 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost $0 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be $46,410, or $595 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 8 work-hours and require parts costing $155, for a cost of 
$835 per product. We have no way of determining the number of aircraft 
that might need this action.

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);

[[Page 16247]]

    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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

0
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. Amend Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Bombardier, Inc.: Docket No. FAA-2014-0144; Directorate Identifier 
2013-NM-232-AD.

(a) Comments Due Date

    We must receive comments by May 9, 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 4166 
through 4175, inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Reason

    This AD was prompted by reports of rudder bearings falling out 
of the fore rudder hinge bracket during assembly. We are issuing 
this AD to detect and correct improper bearing installation, which 
could result in abnormal wear and potential increased freeplay in 
the rudder system, and resultant airframe vibration, leading to 
compromise of the flutter margins of the airplane.

 (f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Proof Load Test

    Within 2,000 flight hours or 12 months after the effective date 
of this AD, whichever occurs first, do a proof load test for 
slippage and freeplay (relative movement between the bearing and 
fitting), in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-27-44, Revision `A,' dated June 10, 
2009. If no slippage or freeplay is detected during the proof load 
test required by this paragraph, before further flight, identify the 
area with a marker and apply sealant if missing, in accordance with 
the Accomplishment Instructions of Bombardier Service Bulletin 84-
27-44, Revision `A,' dated June 10, 2009; and after identifying the 
area with a marker and applying sealant, no further action is 
required by this AD.

(h) Rectification

    If any slippage or freeplay (relative movement between the 
bearing and fitting) is detected during the test required by 
paragraph (g) of this AD, before further flight, do the actions 
specified in paragraphs (h)(1) and (h)(2) of this AD.
    (1) Do a detailed inspection of bearing DSC8-6 for damage, 
corrosion, and dimension conformity, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-27-44, 
Revision `A,' dated June 10, 2009. If damage, corrosion, or 
dimension non-conformity is found, before further flight, install 
new bearing DSC8-6, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 84-27-44, Revision `A,' 
dated June 10, 2009.
    (2) Do a detailed inspection of the fitting bore of the fore 
rudder hinge bracket assembly for wear, damage, corrosion, and 
dimension conformity, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 84-27-44, Revision `A,' 
dated June 10, 2009.
    (i) If damage, corrosion, or dimension non-conformity is found 
during the inspection required by paragraph (h)(2) of this AD, 
before further flight, ream the inside diameter, in accordance with 
the Accomplishment Instructions of Bombardier Service Bulletin 84-
27-44, Revision `A,' dated June 10, 2009.
    (ii) If bore wear or damage beyond 0.8140-inch diameter is found 
during the inspection required by paragraph (h)(2) of this AD, 
before further flight, repair using a method approved by the 
Manager, New York Aircraft Certification Office (ACO), FAA; or 
Transport Canada Civil Aviation (TCCA) (or its delegated agent, or 
the Design Approval Holder (DAH) with TCCA design organization 
approval). For a repair method to be approved, the repair approval 
must specifically refer to this AD.

(i) Credit for Previous Actions

    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 Service 
Bulletin 84-27-44, dated April 13, 2009, which is not incorporated 
by reference in this AD.

(j) Other FAA AD Provisions

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

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2013-34, dated November 
1, 2013, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2014-0144.
    (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 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 March 14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-06493 Filed 3-24-14; 8:45 am]
BILLING CODE 4910-13-P
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