AD 2016-04-19

We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN- 235-300, and C-295 airplanes. This AD requires a general visual inspection of the rudder control system to confirm correct alignment and installation of the adjustment device, and repair if necessary. This AD was prompted by a report of disconnection of the kinematic chain from the co-pilot rudder pedals to the rudder control bars located under the cockpit floor; subsequent investigation revealed that the failure was caused by disconnection of the pedal adjustment device from the adjustment actuator. We are issuing this AD to detect and correct incorrect alignment and incorrect installation of the adjustment device, which could lead to loss of the rudder control from the affected side and possibly result in reduced control of the airplane.

Final rule; request for comments.

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):

2016-04-19 Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.): Amendment 39-18413. Docket No. FAA-2016-3704; Directorate Identifier 2016-NM-005-AD.

(a) Effective Date

This AD becomes effective March 14, 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 CN-235, CN-235-100, CN- 235-200, CN-235-300, and C-295 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 a report of disconnection of the kinematic chain from the co-pilot rudder pedals to the rudder control bars located under the cockpit floor; subsequent investigation revealed that the failure was caused by disconnection of the pedal adjustment device from the adjustment actuator. We are issuing this AD to detect and correct incorrect alignment and incorrect installation of the adjustment device, which could lead to loss of the rudder control from the affected side and possibly result in reduced control of the airplane.

(f) Compliance

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

(g) General Visual Inspection

Within 30 days after the effective date of this AD: Do a general visual inspection of the rudder control system to confirm correct alignment and installation of the adjustment device, in accordance with the instructions of Airbus Defence and Space Alert Operators Transmission (AOT) AOT-C295-27-0001, Revision 1, dated September 29, 2015; or Airbus Defence and Space AOT AOT-CN235-27-0002, Revision 1, dated September 22, 2015; as applicable.

(h) Corrective Action

If, during the general visual inspection required by paragraph (g) of this AD, any discrepancy is found, as specified in Airbus Defence and Space AOT AOT-C295-27-0001, Revision 1, dated September 29, 2015; or Airbus Defence and Space AOT AOT-CN235-27-0002, Revision 1, dated September 22, 2015; as applicable: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus Defense and Space S.A.'s EASA Design Organization Approval (DOA).

(i) Credit for Previous Actions

This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Defence and Space AOT AOT-C295-27-0001, dated October 23, 2014; or Airbus Defence and Space AOT AOT-CN235- 27-0002, dated October 23, 2014; as applicable.

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(j) 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. The AMOC approval letter must specifically reference this AD.
(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 Airbus Defense and Space S.A.'s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.

(k) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016-0012, dated January 14, 2016, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-3704.
(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD.

(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 this AD specifies otherwise.
(i) Airbus Defence and Space Alert Operators Transmission AOT- C295-27-0001, Revision 1, dated September 29, 2015.
(ii) Airbus Defence and Space Alert Operators Transmission AOT- CN235-27-0002, Revision 1, dated September 22, 2015.
(3) For service information identified in this AD, contact Airbus Defense and Space S.A., Services/Engineering Support, Avenida de Arag[oacute]n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 3127; email MTA.TechnicalService@military.airbus.com. For U.S. operators, email alternatively TechnicalSupport@airbusmilitaryna.com.
(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.

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016-0012, dated January 14, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN-235-300, and C-295 airplanes. The MCAI states:

An occurrence was reported involving disconnection of the kinematic chain from the co-pilot rudder pedals to the rudder control bars located under the cockpit floor. Subsequent investigation revealed that the failure was caused by disconnection of the pedal adjustment device from the adjustment actuator.
This condition, if not detected and corrected, could lead to loss of the rudder control from the affected side, possibly resulting in reduced control of the aeroplane.
To address this potential unsafe condition, Airbus Defence and Space (Airbus D&S) issued Alert Operators Transmission (AOT) AOT- CN235-27-0002 and AOT-C295-27-0001, as applicable to aeroplane model, to provide inspection instructions.
For the reasons described above, this [EASA] AD requires a one- time general visual inspection (GVI) of the rudder control system and correctness of the installation connection between the adjustment actuators and the adjustment devices of the rudder pedals and, depending on findings, accomplishment of applicable corrective action(s).

You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-3704.

Related Service Information Under 1 CFR Part 51

Airbus Defence and Space has issued AOT AOT-C295-27-0001, Revision 1, dated September 29, 2015; and AOT-CN235-27-0002, Revision 1, dated September 22, 2015. The service information describes procedures for a general visual inspection of the rudder control system to confirm correct alignment and installation of the adjustment device. 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 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

FAA's Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to theflying public justifies waiving notice and comment prior to adoption of this rule because incorrect alignment and

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incorrect installation of the adjustment device could lead to loss of the rudder control from the affected side and possibly result in reduced control of the airplane. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-3704; Directorate Identifier 2016-NM-005-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD.

Costs of Compliance

We estimate that this AD affects 29 airplanes of U.S. registry.
We also estimate that it will take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $0 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $2,465, or $85 per product.
In addition, we estimate that any necessary follow-on actions will take about 8 work-hours and require parts costing $177, for a cost of $857 per product. We have no way of determining the number of aircraft that might need these actions.

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.