Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes, 70062-70064 [2016-24202]

Download as PDF 70062 Federal Register / Vol. 81, No. 196 / Tuesday, October 11, 2016 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9187; Directorate Identifier 2016–NM–032–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model C–212 airplanes. This proposed AD was prompted by multiple reports of damaged and cracked rudder torque tube shafts. This proposed AD would 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. This proposed AD also provides a modification which terminates the repetitive inspections. We are proposing 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. DATES: We must receive comments on this proposed AD by November 25, 2016. SUMMARY: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus Defense and Space, Services/Engineering Support, ´ Avenida de Aragon 404, 28022 Madrid, ehiers on DSK5VPTVN1PROD with PROPOSALS ADDRESSES: VerDate Sep<11>2014 14:38 Oct 07, 2016 Jkt 241001 Spain; telephone: +34 91 585 55 84; fax: +34 91 585 31 27; email: MTA.TechnicalService@Airbus.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–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 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: 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: 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–2016–9187; Directorate Identifier 2016–NM–032–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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA 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. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 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. This proposed AD would require 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, dated July 15, 2015. 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. Related Service Information Under 1 CFR Part 51 We reviewed the following EADS CASA 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. • Airbus Defense & Space Alert Operators Transmission AOT–C212–27– E:\FR\FM\11OCP1.SGM 11OCP1 Federal Register / Vol. 81, No. 196 / Tuesday, October 11, 2016 / Proposed Rules 0001, dated July 15, 2015. 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. 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 70063 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 We estimate that this proposed AD affects 49 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Inspections ............................. Labor cost Parts cost Up to 33 work-hours × $85 per hour = $2,805 per inspection cycle. $0 Cost per product Cost on U.S. operators Up to $2,805 per inspection cycle. Up to $137,445 per inspection cycle ESTIMATED COSTS FOR OPTIONAL ACTIONS Action Labor cost Parts cost Optional modification ............................... Up to 48 work-hours × $85 per hour = $4,080. $48,729 We have received no definitive data that would enable us to provide cost estimates for the on-condition actions and parts cost specified in this proposed AD. Authority for This Rulemaking ehiers on DSK5VPTVN1PROD with PROPOSALS 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 VerDate Sep<11>2014 14:38 Oct 07, 2016 Jkt 241001 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 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. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. Frm 00004 Fmt 4702 Sfmt 4702 Up to $52,359 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.): Docket No. FAA–2016–9187; Directorate Identifier 2016–NM–032–AD. (a) Comments Due Date We must receive comments by November 25, 2016. (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 The Proposed Amendment PO 00000 Cost per product 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. E:\FR\FM\11OCP1.SGM 11OCP1 70064 Federal Register / Vol. 81, No. 196 / Tuesday, October 11, 2016 / Proposed Rules (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, dated July 15, 2015. (2) Thereafter, before further flight after the conditions identified in paragraph 3.1.1.1 of Airbus Defense & Space Alert Operators Transmission AOT–C212–27–0001, dated July 15, 2015, do the applicable inspections identified for each condition. (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 Airbus Defense & Space Alert Operators Transmission AOT– C212–27–0001, dated July 15, 2015. Where Airbus Defense & Space Alert Operators Transmission AOT–C212–27–0001, dated July 15, 2015, specifies to contact Airbus for corrective action: Before further flight, accomplish corrective actions in accordance with 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. ehiers on DSK5VPTVN1PROD with PROPOSALS (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, VerDate Sep<11>2014 14:38 Oct 07, 2016 Jkt 241001 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: 9ANM-116-AMOC-REQUESTS@faa.gov. 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 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 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) For service information identified in this AD, contact Airbus Defense and Space, Services/Engineering Support, Avenida de ´ Aragon 404, 28022 Madrid, Spain; telephone: +34 91 585 55 84; fax: +34 91 585 31 27; email: MTA.TechnicalService@Airbus.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 September 29, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–24202 Filed 10–7–16; 8:45 am] BILLING CODE 4910–13–P ENVIRONMENTAL PROTECTION AGENCY 40 CFR Part 52 [EPA–R03–OAR–2016–0199; FRL–9953–73– Region 3] Approval and Promulgation of Air Quality Implementation Plans; District of Columbia; Revision of Regulations for Sulfur Content of Fuel Oil Environmental Protection Agency (EPA). ACTION: Proposed rule. AGENCY: The Environmental Protection Agency (EPA) proposes to approve the state implementation plan (SIP) revision submitted by the District of Columbia for the purpose of updating the District of Columbia Municipal Regulations (DCMR) to lower the sulfur content of SUMMARY: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 fuel oil. In the Final Rules section of this Federal Register, EPA is approving the District’s submittal as a direct final rule without prior proposal because the Agency views this as a noncontroversial submittal and anticipates no adverse comments. A detailed rationale for the approval is set forth in the direct final rule. If no adverse comments are received in response to this action, no further activity is contemplated. If EPA receives adverse comments, the direct final rule will be withdrawn and all public comments received will be addressed in a subsequent final rule based on this proposed rule. EPA will not institute a second comment period. Any parties interested in commenting on this action should do so at this time. DATES: Comments must be received in writing by November 10, 2016. ADDRESSES: Submit your comments, identified by Docket ID No. EPA–R03– OAR–2016–0199 at http:// www.regulations.gov, or via email to pino.maria@epa.gov. For comments submitted at Regulations.gov, follow the online instructions for submitting comments. Once submitted, comments cannot be edited or removed from Regulations.gov. For either manner of submission, the EPA may publish any comment received to its public docket. Do not submit electronically any information you consider to be confidential business information (CBI) or other information whose disclosure is restricted by statute. Multimedia submissions (audio, video, etc.) must be accompanied by a written comment. The written comment is considered the official comment and should include discussion of all points you wish to make. The EPA will generally not consider comments or comment contents located outside of the primary submission (i.e. on the web, cloud, or other file sharing system). For additional submission methods, please contact the person identified in the FOR FURTHER INFORMATION CONTACT section. For the full EPA public comment policy, information about CBI or multimedia submissions, and general guidance on making effective comments, please visit http://www2.epa.gov/dockets/ commenting-epa-dockets. FOR FURTHER INFORMATION CONTACT: Asrah Khadr, (215) 814–2071, or by email at khadr.asrah@epa.gov. SUPPLEMENTARY INFORMATION: For further information, please see the information provided in the direct final action, with the same title, that is located in the ‘‘Rules and Regulations’’ section of this Federal Register publication. Please note that if EPA receives adverse comment on an E:\FR\FM\11OCP1.SGM 11OCP1

Agencies

[Federal Register Volume 81, Number 196 (Tuesday, October 11, 2016)]
[Proposed Rules]
[Pages 70062-70064]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-24202]



[[Page 70062]]

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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]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Defense and Space S.A. Model C-212 airplanes. This proposed AD 
was prompted by multiple reports of damaged and cracked rudder torque 
tube shafts. This proposed AD would 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. This proposed AD also provides a 
modification which terminates the repetitive inspections. We are 
proposing 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.

DATES: We must receive comments on this proposed AD by November 25, 
2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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: MTA.TechnicalService@Airbus.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-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 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: 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:

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-2016-9187; 
Directorate Identifier 2016-NM-032-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
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.

    This proposed AD would require 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, dated July 15, 2015. 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.

Related Service Information Under 1 CFR Part 51

    We reviewed the following EADS CASA 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.
     Airbus Defense & Space Alert Operators Transmission AOT-
C212-27-

[[Page 70063]]

0001, dated July 15, 2015. 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.

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

    We estimate that this proposed AD affects 49 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed 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.
----------------------------------------------------------------------------------------------------------------


                                      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 $52,359
                                          per hour = $4,080.
----------------------------------------------------------------------------------------------------------------

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

    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 airworthiness 
directive (AD):

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

(a) Comments Due Date

    We must receive comments by November 25, 2016.

(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.

[[Page 70064]]

(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, dated July 15, 2015.
    (2) Thereafter, before further flight after the conditions 
identified in paragraph 3.1.1.1 of Airbus Defense & Space Alert 
Operators Transmission AOT-C212-27-0001, dated July 15, 2015, do the 
applicable inspections identified for each condition.

(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 Airbus Defense 
& Space Alert Operators Transmission AOT-C212-27-0001, dated July 
15, 2015. Where Airbus Defense & Space Alert Operators Transmission 
AOT-C212-27-0001, dated July 15, 2015, specifies to contact Airbus 
for corrective action: Before further flight, accomplish corrective 
actions in accordance with 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
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 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 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) 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: MTA.TechnicalService@Airbus.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 September 29, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-24202 Filed 10-7-16; 8:45 am]
 BILLING CODE 4910-13-P