AD 2017-01-10

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.

For service information identified in this final rule, contact Airbus Defense and Space, Services/Engineering Support, Avenida de Aragón 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9187.

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.

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.

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.

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.

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.

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.

• 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.

We estimate that this AD affects 49 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:

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.

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.

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.

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

1. The authority citation for part 39 continues to read as follows:

2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):