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[Federal Register Volume 78, Number 211 (Thursday, October 31, 2013)]
[Rules and Regulations]
[Pages 65198-65200]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25629]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0594; Directorate Identifier 2012-NM-019-AD; 
Amendment 39-17641; AD 2013-22-09]
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 adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD was 
prompted by reports of movement of the rudder pedals being impeded due 
to corrosion of the trunnion shaft of the rudder feel trim unit (RFTU). 
This AD requires an inspection to determine if certain RFTUs are 
installed, an operational check for signs of seizure of affected parts, 
repetitive lubrication of certain RFTUs, and replacement of the RFTU if 
necessary. Installing replacement RFTUs having conformal bushings 
terminates the repetitive lubrication requirements. We are issuing this 
AD to detect and correct any sign of rough movement or seizure of the 
trunnion shaft and its bushing, which could cause a rudder control jam 
or a large and rapid alternating rudder input leading to a structural 
failure of the vertical fin.

DATES: This AD becomes effective December 5, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 5, 
2013.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2012-0594 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, New 
York 11590; telephone (516) 228-7318; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 by adding an AD that would apply to the specified 
products. The SNPRM was published in the Federal Register on March 12, 
2013 (78 FR 15655). We preceded the SNPRM with a notice of proposed 
rulemaking (NPRM), which published in the Federal Register on June 12, 
2012 (77 FR 34874). The NPRM and the SNPRM both proposed to correct an 
unsafe condition for the specified products.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2012-02R1, dated October 12, 2012 (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:

    There have been several reported incidents on DHC-8 Series 400 
aeroplanes where the movement of the rudder pedals has been impeded. 
An investigation showed that the Rudder Feel Trim Unit (RFTU) 
trunnion shaft was corroded. The root cause of the corrosion was a 
quality escape where cadmium plating on the trunnion bushing within 
the RFTU assembly was not removed. Corrosion on the shaft and in the 
trunnion bushing seized the trunnion and caused difficulties in 
controlling the rudder movement.
    This condition, if not corrected, could cause a rudder control 
jam or a large and rapid alternating rudder input leading to a 
structural failure of the vertical fin.
    This [TCCA] Airworthiness Directive (AD) is issued [inspect to 
determine serial number, an operational check for seizure, 
repetitive lubrication and] to replace the affected RFTUs to limit 
the possibility of binding and replace the affected RFTUs with units 
that have been reworked with conformal bushings to terminate the 
lubrication requirements.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2012-0594-0006.

Comments

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

Request To Revise Compliance Time for Operational Check

    Horizon Air (Horizon) requested that paragraph (g)(2) of the SNPRM 
(78 FR 15655, March 12, 2013) be revised to allow operators that 
perform a review of airplane maintenance records, in lieu of visually 
inspecting the serial number of the RFTU, time to schedule the 
operational check specified by paragraph (g)(2) of the SNPRM. Horizon 
stated that the compliance time ``before further flight'' specified in 
paragraph (g)(2) of the SNPRM would immediately ground aircraft.
    We agree with Horizon's request. We have revised the compliance 
time in paragraph (g)(2) of this final rule to ``200 flight hours or 2 
months, whichever occurs first after the effective date of this AD'' 
for performing the operational check specified in that paragraph.

Explanation of Changes Made to This AD

    We have revised paragraph (h) of this final rule to specify that 
installing replacement RFTUs having conformal bushings terminates the 
repetitive lubrication requirements of paragraph

[[Page 65199]]

(g)(2)(ii) of this final rule for the affected RTFU.

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. We have determined that 
these changes:
     Are consistent with the intent that was proposed in the 
SNPRM (78 FR 15655, March 12, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (78 FR 15655, March 12, 2013).

Costs of Compliance

    We estimate that this AD affects 83 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection, Replacement,          5 work-hours x $85               $0   $425 per             $35,275 inspection,
 Lubrication.                      per hour = $425                       inspection,          replacement, and
                                   per inspection,                       replacement, and     lubrication cycle.
                                   replacement, and                      lubrication cycle.
                                   lubrication cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                      Cost per
                Action                        Labor cost            Parts cost        product
-------------------------------------------------------------------------------------------------
Replacement..........................  17 work-hours x $85 per               $0           $1,445
                                        hour = $1,445.
----------------------------------------------------------------------------------------------------------------

    Where the service information lists required parts costs that are 
covered under warranty, we have assumed that there will be no charge 
for these parts. As we do not control warranty coverage for affected 
parties, some parties may incur costs higher than estimated here.

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2012-0594; 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 
MCAI, 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:

2013-22-09 Bombardier, Inc.: Amendment 39-17641. Docket No. FAA-
2012-0594; Directorate Identifier 2012-NM-019-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective December 5, 
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 (S/N) 
4001, 4003 and subsequent, equipped with rudder feel trim unit 
(RFTU) part number (P/N) 399500-1007.

[[Page 65200]]

(d) Subject

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

(e) Reason

    This AD was prompted by reports of movement of the rudder pedals 
being impeded due to corrosion of the trunnion shaft of the RFTU. We 
are issuing this AD to detect and correct any sign of rough movement 
or seizure of the trunnion shaft and its bushing, which could cause 
a rudder control jam or a large and rapid alternating rudder input 
leading to a structural failure of the vertical fin.

(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) Inspection, Replacement, and Lubrication

    Within 200 flight hours or two months after the effective date 
of this AD, whichever occurs first: Inspect the RTFU to determine 
whether the serial number is in the range from S/N 0008 through 0509 
inclusive without a suffix `B,' in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-27-60, 
dated July 12, 2012. A review of airplane maintenance records is 
acceptable in lieu of this inspection if the serial number of the 
RFTU can be conclusively determined from that review.
    (1) If the RFTU's serial number is not in the range from S/N 
0008 through 0509 inclusive, or if the serial number has a suffix 
`B,' no further action is required for this paragraph.
    (2) If the RFTU's serial number is in the range from S/N 0008 
through 0509 inclusive, including those with a suffix `A,' but not 
including those with suffix `B': Within 200 flight hours or 2 
months, whichever occurs first after the effective date of this AD, 
perform an operational check of the RFTU for any sign of rough 
movement or seizure of the trunnion or center shaft, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
84-27-60, dated July 12, 2012.
    (i) If rough movement or seizure of the RFTU trunnion or center 
shaft is found: Before further flight, replace the RFTU with a new 
or serviceable RFTU, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 84-27-60, dated July 12, 
2012.
    (ii) If no rough movement or seizure of the RFTU trunnion or 
center shaft is found: Before further flight, lubricate the RFTU, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 84-27-60, dated July 12, 2012. Repeat the 
lubrication of the RFTU at intervals not to exceed 600 flight hours 
or 3 months, whichever occurs first, until the RFTU is replaced with 
a unit that has a serial number outside the affected range or a 
serial number with a suffix `B.'

(h) Replacement

    For airplanes having an RFTU identified in paragraph (g)(2) of 
this AD: Except as required by paragraph (g)(2)(i) of this AD, 
within 5,000 flight hours or 3 years after the effective date of 
this AD, whichever occurs first, replace all affected RFTUs with 
units that have a serial number outside the range from S/Ns 0008 
through 0509 inclusive, or that have a serial number with a suffix 
`B,' in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-27-60, dated July 12, 2012. 
Installing replacement RFTUs having conformal bushings terminates 
the repetitive lubrication requirements of paragraph (g)(2)(ii) of 
this AD for the affected RTFU.

(i) Parts Installation Limitation

    As of the effective date of this AD, no person may install an 
RFTU P/N 399500-1007 with a serial number from S/N 0008 through 0509 
inclusive, including serial numbers with suffix `A,' on any 
airplane, except that RFTUs having a serial number with suffix `B' 
may be installed.

(j) 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. If sending information 
directly to the ACO, send it to ATTN: Program Manager, Continuing 
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 
410, Westbury, New York 11590; telephone 516-228-7300; fax 516-794-
5531. Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office. The AMOC approval letter must specifically 
reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(k) Related Information

    Refer to MCAI Canadian Airworthiness Directive CF-2012-02R1, 
dated October 12, 2012, for related information, which can be found 
in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2012-0594-0006.

(l) 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 Service Bulletin 84-27-60, dated July 12, 2012.
    (ii) Reserved.
    (3) 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.
    (4) You may review copies of the 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 October 18, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-25629 Filed 10-30-13; 8:45 am]
BILLING CODE 4910-13-P
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