[Federal Register Volume 82, Number 11 (Wednesday, January 18, 2017)]
[Rules and Regulations]
[Pages 5356-5359]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-00407]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9187; Directorate Identifier 2016-NM-032-AD; 
Amendment 39-18777; AD 2017-01-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Defense and Space S.A. (Formerly 
Known as Construcciones Aeronauticas, S.A.) Airplanes

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

ACTION: Final rule.

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[[Page 5357]]

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Defense and Space S.A. Model C-212 airplanes. This AD was 
prompted by multiple reports of damaged and cracked rudder torque tube 
shafts. This AD requires various repetitive inspections, and corrective 
actions if necessary. This AD also provides a modification which 
terminates the repetitive inspections. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective February 22, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 22, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Defense and Space, Services/Engineering Support, Avenida 
de Arag[oacute]n 404, 28022 Madrid, Spain; telephone: +34 91 585 55 84; 
fax: +34 91 585 31 27; email: [email protected]. 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. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-9187.

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-2016-
9187; 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 Office (telephone: 
800-647-5527) is 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 20590.

FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace 
Engineer, International Branch, ANM-116, Transport Airplane 
Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
telephone: 425-227-1112; fax: 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Defense and 
Space S.A. Model C-212 airplanes. The NPRM published in the Federal 
Register on October 11, 2016 (81 FR 70062). The NPRM was prompted by 
multiple reports of damaged and cracked rudder torque tube shafts. The 
NPRM proposed to require repetitive general visual and high frequency 
eddy current (HFEC) inspections of the inner rudder torque tube shaft 
for cracks, deformation, and damage; repetitive detailed inspections, 
and HFEC inspections, if necessary, of the inner and outer rudder 
torque tube shaft for cracks, deformation, and damage; and corrective 
actions if necessary. We are issuing this AD to detect and correct 
damaged and cracked rudder torque tube shafts, which could lead to 
structural failure of the affected rudder torque tube shaft and 
possible reduced control of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0052, dated March 14, 2016 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus Defense and Space S.A. Model 
C-212 airplanes. The MCAI states:

    Occurrences were reported of finding a damaged and cracked 
rudder torque tube shaft, Part Number (P/N) 212-46237-01. Subsequent 
investigation determined that this damage occurred after parking of 
the aeroplane during a heavy wind gust, without having set the 
flight control surfaces in locked position.
    This condition, if not detected and corrected, could lead to 
structural failure of the affected rudder torque tube shaft, 
possibly resulting in reduced control of the aeroplane.
    To address this potential unsafe condition, EADS-CASA issued 
Alert Operators Transmission (AOT) AOT-C212-27-0001 to provide 
inspection instructions, and Service Bulletin (SB) SB-212-27-0058 
providing modification instructions.
    For the reasons described above, this [EASA] AD requires 
repetitive inspections of the affected rudder torque tube shaft, and 
introduces an optional modification [replacement], which constitutes 
terminating action for those repetitive inspections.

    Required actions include repetitive general visual and HFEC 
inspections of the inner rudder torque tube shaft for cracks, 
deformation, and damage; repetitive detailed inspections, and HFEC 
inspections, if necessary, of the inner and outer rudder torque tube 
shaft for cracks, deformation, and damage; a general visual inspection 
to verify rudder alignment if necessary; and corrective actions if 
necessary. Repetitive inspections are done depending on conditions 
(wind conditions, gust lock engagement, and rudder deviation) 
identified in Airbus Defense & Space Alert Operators Transmission AOT-
C212-27-0001, Revision 0, dated July 15, 2015 (``AOT-C212-27-0001, Rev. 
0''). Damage may include bulging, dents, peeled paint, or visible 
corrosion. Corrective actions include replacement of the rudder torque 
tube shaft with a new rudder torque tube shaft, and repair. The 
optional terminating action includes replacement of the rudder torque 
tube shaft with an improved rudder torque tube shaft. You may examine 
the MCAI in the AD docket on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2016-9187.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Clarification of the Actions in Paragraph (g)(2) of the Proposed AD

    Paragraph (g)(2) of the proposed AD specifies to do inspections 
``after the conditions'' identified in paragraph 3.1.1.1 of AOT-C212-
27-0001, Rev. 0. We have revised paragraph (g)(2) of the AD to clarify 
the inspections are done after any weather event that includes the 
conditions identified in paragraph 3.1.1.1 of AOT-C212-27-0001, Rev. 0.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD with the change described 
previously and minor editorial changes. We have determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Airbus Defense and Space service 
information.
     EADS CASA Service Bulletin SB-212-27-0058, dated April 25, 
2014. This service information describes procedures for replacement of 
the rudder torque tube shaft with an improved rudder torque tube shaft.

[[Page 5358]]

     AOT-C212-27-0001, Rev. 0. This service information 
describes procedures for general visual and HFEC inspections of the 
inner rudder torque tube shaft for cracks, deformation, and damage; 
detailed inspections, and HFEC inspections, if necessary, of the inner 
and outer rudder torque tube shaft for cracks, deformation, and damage; 
a general visual inspection to verify rudder alignment; and corrective 
actions, if necessary.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 49 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
----------------------------------------------------------------------------------------------------------------
Inspections.....................  Up to 33 work-hours              $0   Up to $2,805 per     Up to $137,445 per
                                   x $85 per hour =                      inspection cycle.    inspection cycle.
                                   $2,805 per
                                   inspection cycle.
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                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                 Action                          Labor cost             Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Optional modification..................  Up to 48 work-hours x $85          $48,729   Up to $52,809.
                                          per hour = $4,080.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions and parts cost specified in 
this AD.

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.

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 airworthiness 
directive (AD):

2017-01-10 Airbus Defense and Space S.A. (Formerly Known as 
Construcciones Aeronauticas, S.A.): Amendment 39-18777; Docket No. 
FAA-2016-9187; Directorate Identifier 2016-NM-032-AD.

(a) Effective Date

    This AD is effective February 22, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Defense and Space S.A. (formerly known 
as Construcciones Aeronauticas, S.A.) Model C-212-CB, C-212-CC, C-
212-CD, C-212-CE, C-212-CF, C-212-DF, and C-212-DE airplanes, 
certificated in any category, all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by multiple reports of damaged and cracked 
rudder torque tube shafts. We are issuing this AD to detect and 
correct damaged and cracked rudder torque tube shafts, which could 
lead to structural failure of the affected rudder torque tube shaft 
and possible reduced control of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    For airplanes equipped with a rudder torque tube shaft having 
part number (P/N) 212-46237-01: Do the actions specified in 
paragraphs (g)(1) and (g)(2) of this AD.
    (1) Within 30 days after the effective date of this AD: Do 
general visual, detailed, and high frequency eddy current (HFEC) 
inspections of the inner and outer surfaces of the rudder torque 
tube shaft, as applicable, for cracks, deformation, and damage, in 
accordance with the instructions of Airbus Defense & Space Alert 
Operators Transmission AOT-C212-27-0001, Revision 0, dated July 15, 
2015 (``AOT-C212-27-0001, Rev. 0'').
    (2) Thereafter, before further flight after any weather event 
that includes the conditions identified in paragraph 3.1.1.1 of AOT-
C212-27-0001, Rev. 0, do the applicable inspections identified for 
each condition.

[[Page 5359]]

(h) Corrective Actions

    If, during any inspection required by paragraph (g) of this AD, 
any crack, deformation, or damage is found, before further flight do 
all applicable corrective actions, in accordance with AOT-C212-27-
0001, Rev. 0. Where AOT-C212-27-0001, Rev. 0, specifies to contact 
Airbus for corrective action: Before further flight, accomplish 
corrective actions in accordance with the procedures specified in 
paragraph (k)(2) of this AD.

(i) Optional Modification

    Modification of an airplane by replacing the rudder torque tube 
shaft P/N 212-46237-01 with an improved part, in accordance with the 
Accomplishment Instructions of EADS CASA Service Bulletin SB-212-27-
0058, dated April 25, 2014, constitutes terminating action for the 
inspections required by paragraphs (g)(1) and (g)(2) of this AD for 
the modified airplane.

(j) 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 Airbus Military All 
Operator Letter (AOL) AOL-212-037, Revision 01, dated April 11, 
2014.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Shahram 
Daneshmandi, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone: 425-227-1112; fax: 425-227-1149. 
Information may be emailed to: [email protected]. 
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.
    (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, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or EADS CASA's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0052, dated March 14, 2016, 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-2016-9187.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) 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.
    (i) EADS CASA Service Bulletin SB-212-27-0058, dated April 25, 
2014.
    (ii) Airbus Defense & Space Alert Operators Transmission AOT-
C212-27-0001, Revision 0, dated July 15, 2015.
    (3) For service information identified in this AD, contact 
Airbus Defense and Space, Services/Engineering Support, Avenida de 
Arag[oacute]n 404, 28022 Madrid, Spain; telephone: +34 91 585 55 84; 
fax: +34 91 585 31 27; email: [email protected].
    (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 January 4, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-00407 Filed 1-17-17; 8:45 am]
 BILLING CODE 4910-13-P