Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes, 1269-1275 [2016-31365]

Download as PDF Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules distribution of power and responsibilities among the various levels of government. For the reasons discussed, 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 to the extent that it justifies making a regulatory distinction; 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 an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) AD 93–17–13, Amendment 39–8684 (58 FR 51770, October 5, 1993) and adding the following new airworthiness directive (AD): ■ mstockstill on DSK3G9T082PROD with PROPOSALS Sikorsky Aircraft Corporation (Type Certificate Previously Held By Schweizer Aircraft Corporation): Docket No. FAA–2016–6968; Directorate Identifier 2015–SW–020–AD. (a) Applicability This AD applies to Model TH55A, 269A, 269A–1, 269B, 269C and 269C–1 helicopters, with a lower coupling driveshaft (driveshaft) part number (P/N) 269–5412, 269A5504, 269A5504–003, 269A5504–005, 269A5559, or 269A5559–003 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as failure of a driveshaft. This condition could result in loss of power to the rotor system and subsequent loss of helicopter control. VerDate Sep<11>2014 20:07 Jan 04, 2017 Jkt 241001 (c) Affected ADs This AD supersedes AD 93–17–13, Amendment 39–8684 (58 FR 51770, October 5, 1993). (d) Comments Due Date We must receive comments by March 6, 2017. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) Within 25 hours time-in-service (TIS), install engine and rotor tachometer markings in accordance with Part II of Schweizer Aircraft Service Bulletin B–257.1, dated May 21, 1993. (2) Within 25 hours TIS and thereafter at intervals not to exceed 150 hours TIS: (i) Visually inspect the driveshaft for corrosion, a pit, a nick, a scratch, a dent, and a crack in accordance with the Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(6) of Sikorsky 269C Helicopter Alert Service Bulletin B–307, Basic Issue, dated December 18, 2014 (269C ASB), or Sikorsky 269C–1 Helicopter Alert Service Bulletin C1B–043, Basic Issue, dated December 18, 2014 (269C–1 ASB), whichever is applicable for your model helicopter, except we do not require that you use a Sikorsky recommended vendor list. If there is any corrosion, a pit, a nick, a scratch, a dent, or a crack, replace the driveshaft before further flight. (ii) If there is no corrosion and no pits, nicks, scratches, dents, and cracks, magnetic particle inspect the driveshaft for a crack in accordance with paragraph 3.C.(1) of the 269C ASB or 269C–1 ASB, whichever is applicable for your model helicopter. This magnetic particle inspection must be performed by a Level II or higher technician with the National Aerospace Standard 410 or equivalent certification who has performed a magnetic particle inspection within the last 12 months. If there is a crack, replace the driveshaft before further flight. (g) Credit for Actions Previously Completed Compliance with paragraph (a)(1) of AD 93–17–13, Amendment 39–8684 (58 FR 51770, October 5, 1993) before the effective date of this AD is considered acceptable for compliance with the actions specified in paragraph (f)(1) of this AD. (h) Alternative Methods of Compliance (AMOC) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Blaine Williams, Aerospace Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7161; email blaine.williams@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or PO 00000 Frm 00039 Fmt 4702 Sfmt 4702 1269 lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (i) Additional Information For service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800– Winged-S or 203–416–4299; email wcs_cust_ service_eng.gr-sik@lmco.com. You may review a copy of information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N– 321, Fort Worth, TX 76177. (j) Subject Joint Aircraft Service Component (JASC) Code: 6300, Main Rotor Drive System. Issued in Fort Worth, Texas, on December 21, 2016. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–31622 Filed 1–4–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9521; Directorate Identifier 2016–NM–061–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 CN–235, CN–235–100, CN–235–200, CN–235–300, and C–295 airplanes. This proposed AD was prompted by reports of excessive play between bushings and their respective fitting housings at certain elevator fittings. This proposed AD would require a one-time detailed inspection and repetitive eddy current inspections of the elevator hinge fitting and bracket assembly, and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 21, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: E:\FR\FM\05JAP1.SGM 05JAP1 1270 Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules • Federal eRulemaking Portal: Go to https://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, Spain; 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. mstockstill on DSK3G9T082PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9521; 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–2016–9521; Directorate Identifier 2016–NM–061–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 https:// VerDate Sep<11>2014 20:07 Jan 04, 2017 Jkt 241001 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 EADS AD 2016–0075, dated April 19, 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 CN–235, CN–235–100, CN–235– 200, CN–235–300, and C–295 airplanes. The MCAI states: Excessive play between bushings and their respective fitting housing was reported at Stabilizer Station (STA) 4850, affecting the outboard and inboard elevator hinge fittings and attachment fittings; and the horizontal stabilizer elevator linkage. Additionally, excessive misalignment was detected between the elevator hinge fittings and the elevator brackets during further analysis of the reported cases. Furthermore, an occurrence of an elevator hinge fitting crack was reported. This condition, if not detected and corrected, could lead to failure or detachment of any of the affected structural parts, possibly resulting in reduced control of the aeroplane. To address this potentially unsafe condition, Airbus Defence & Space (D&S) issued Alert Operator Transmissions (AOT) AOT–CN235–55–0001 Revision 2 and AOT– C295–55–0001 Revision 2 to provide inspection instructions to detect misalignment between the elevator hinge fittings and the elevator brackets. Additionally, Airbus D&S issued AOT– CN235–55–0003 and AOT–C295–55–0003 to provide inspection instructions to detect cracking of elevator hinge fitting and attachment fitting. For the reasons described above, this [EASA] AD requires a one-time [detailed] inspection of the elevator hinge fittings and the elevator brackets, repetitive [eddy current] inspections of elevator hinge fittings and attachment fittings, and depending on findings, accomplishment of applicable corrective action(s) [e.g. repair(s)]. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9521. Related Service Information Under 1 CFR Part 51 Airbus Defense and Space S.A. has issued the following Alert Operators Transmissions (AOT). • Airbus Defense and Space S.A. AOT AOT–CN235–55–0001, Revision 2, dated March 10, 2015. The service information describes procedures for a PO 00000 Frm 00040 Fmt 4702 Sfmt 4702 detailed visual inspection of the elevator hinge fitting and bracket assembly to detect excessive play between bushings and their respective fitting housings, and to detect cracks; and corrective actions if necessary. • Airbus Defense and Space S.A. AOT AOT–CN235–55–0003, dated December 22, 2015. The service information describes procedures for repetitive eddy current inspections to detect cracks in the elevator hinge fitting and bracket assembly, and corrective actions if necessary. • Airbus Defense and Space S.A. AOT AOT–C295–55–0001, Revision 2, dated April 09, 2015. The service information describes procedures for a detailed visual inspection of the elevator hinge fitting and bracket assembly to detect excessive play between bushings and their respective fitting housings, and to detect cracks; and corrective actions if necessary. • Airbus Defense and Space S.A. AOT AOT–C295–55–0003, dated December 22, 2015. The service information describes procedures for repetitive eddy current inspections to detect cracks in the elevator hinge fitting and bracket assembly, and corrective actions if necessary. These documents are distinct since they apply to different airplane models in different configurations. 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 these same type designs. Differences Between This Proposed AD and the MCAI or Service Information The MCAI allows credit for an inspection done in accordance with the following Airbus Defense and Space S.A. AOTs, as applicable: • AOT–CN235–55–0001, dated December 16, 2014, or • AOT–C295–55–0001, dated December 16, 2014. E:\FR\FM\05JAP1.SGM 05JAP1 1271 Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules This proposed AD does not give credit for accomplishing those initial issues of the service information because the inspection requirements are different from the initial issues of the service information in both Revision 1 and Revision 2 of Airbus Defense and Space AOT AOT–CN235–55–0001, and AOT AOT–C295–55–0001. Also, the MCAI identifies a date for Revision 1 of Airbus Defense and Space S.A. AOT AOT–C295–55–0001, which was corrected by Revision 2 of the same service information. Paragraph (m), ‘‘Credit for Previous Actions,’’ of this proposed AD shows the correct date. Costs of Compliance We estimate that this proposed AD affects 14 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Parts cost Action Labor cost Inspection ................. 2 work-hours × $85 per hour = $170 per inspection cycle. We estimate the following costs to do any necessary repairs that would be $0 Cost per product Cost on U.S. operators $170 per inspection cycle .............. required based on the results of the proposed inspection. We have no way of $2,380 per inspection cycle. determining the number of airplanes that might need this repair: ON-CONDITION COSTS Action Labor cost Repair ......................................................... 45 work-hours × $85 per hour = $3,825 ................................................. 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. mstockstill on DSK3G9T082PROD with PROPOSALS 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; VerDate Sep<11>2014 20:07 Jan 04, 2017 Jkt 241001 Cost per product $10,000 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 $13,825 (b) Affected ADs (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. 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 1. The authority citation for part 39 continues to read as follows: ■ Regulatory Findings Parts cost Authority: 49 U.S.C. 106(g), 40113, 44701. § 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–2016–9521; Directorate Identifier 2016–NM–061–AD. (a) Comments Due Date We must receive comments by February 21, 2017. PO 00000 Frm 00041 Fmt 4702 Sfmt 4702 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. (e) Reason This AD was prompted by reports of excessive play between bushings and their respective fitting housings at certain elevator fittings. We are issuing this AD to prevent excessive play between bushings and their respective fitting housings, which could lead to failure or detachment of any of the affected structural parts, with a possible result of reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) One-Time Detailed Visual Inspection Before exceeding 600 flight hours since first flight of the airplane, or within 300 flight hours after the effective date of this AD, whichever occurs later, but not before exceeding 300 flight hours since first flight of the airplane: Do a detailed visual inspection of the elevator hinge fitting and bracket assembly to detect excessive play between bushings and their respective fitting housings, and to detect cracks, in accordance with the instructions of Airbus Defense and Space S.A. Alert Operators Transmission E:\FR\FM\05JAP1.SGM 05JAP1 1272 Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules (AOT) AOT–CN235–55–0001, Revision 2, dated March 10, 2015; or AOT AOT–C295– 55–0001, Revision 2, dated April 9, 2015; as applicable. (h) Corrective Action for Discrepancies Found During Detailed Visual Inspection If, during the inspection required by paragraph (g) of this AD, any discrepancy is detected, as defined in the instructions of Airbus Defense and Space S.A. AOT AOT– CN235–55–0001, Revision 2, dated March 10, 2015; or AOT AOT–C295–55–0001 Revision 2, dated April 9, 2015; as applicable: Before further flight, accomplish applicable corrective actions, in accordance with the instructions of Airbus Defense and Space S.A. AOT AOT–CN235–55–0001, Revision 2, dated March 10, 2015; or AOT AOT–C295– 55–0001, Revision 2, dated April 9, 2015; as applicable. Where Airbus Defense and Space S.A. AOT AOT–CN235–55–0001, Revision 2, dated March 10, 2015; or AOT AOT–C295– 55–0001 Revision 2, dated April 9, 2015; specifies to contact Airbus Defense and Space S.A. for corrective actions, before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD. (i) Repetitive Eddy Current Inspections— Model CN–235, CN–235–100, CN–235–200, and CN–235–300 Airplanes For Model CN–235, CN–235–100, CN–235– 200, and CN–235–300 airplanes: Do the actions required by paragraphs (i)(1) and (i)(2) of this AD. (1) Within the applicable compliance time specified in table 1 to paragraph (i)(1) of this AD: Do an eddy current inspection to detect cracks in the elevator hinge fitting and bracket assembly, in accordance with the instructions of Airbus Defense and Space S.A. AOT AOT–CN235–55–0003, dated December 22, 2015. TABLE 1 TO PARAGRAPH (I)(1) OF THIS AD—INITIAL COMPLIANCE TIMES FOR MODEL CN–235, CN–235–100, CN–235– 200, AND CN–235–300 AIRPLANES Manufacturer’s Serial Number (MSN) Elevator hinge fitting (part No.) MSN001 through MSN154 inclusive. 35–31193–0201 35–31193–0202 MSN155 through MSN241 inclusive. 35–31193–0501 35–31193–0502 MSN242 through MSN999 inclusive. 35–31193–0503 35–31193–0504 Compliance time for initial eddy current inspection (whichever occurs later) Before exceeding 8,800 flight cycles since first flight of the airplane; or before exceeding the applicable flight hours since first flight of the airplane as calculated in table 2 to paragraph (i)(1) of this AD; whichever occurs first. Before exceeding 3,600 flight cycles since first flight of the airplane; or before exceeding the applicable flight hours since first flight of the airplane as calculated in table 2 to paragraph (i)(1) of this AD; whichever occurs first. Before exceeding 1,000 flight cycles since first flight of the airplane; or before exceeding the applicable flight hours since first flight of the airplane as calculated in table 2 to paragraph (i)(1) of this AD; whichever occurs first. Within 300 flight cycles after the effective date of this AD. Within 300 flight cycles after the effective date of this AD. Within 50 flight cycles after the effective date of this AD. TABLE 2 TO PARAGRAPH (i)(1) OF THIS AD—FLIGHT CYCLES TO FLIGHT HOURS CONVERSION SINCE FIRST FLIGHT OF THE AIRPLANE Civilian or military type certificate CN–235 (Commercial Identification S10). CN–235–100 ......................................... Civilian ........................ Civilian ........................ CN–235–200 ......................................... Civilian ........................ CN–235–300 ......................................... Civilian ........................ CN–235 (Commercial Identification S10M). CN–235–100M ...................................... Military ......................... Military ......................... CN–235–200M ...................................... Military ......................... CN–235–300M ...................................... Military ......................... CN–235–100M/IR01 .............................. Military ......................... CN–235–100M/EA02V .......................... mstockstill on DSK3G9T082PROD with PROPOSALS CN–235 model/version Military ......................... CN–235–200M/CL02 ............................. Military ......................... CN–235/EA01F (Commercial Identification S10M). CN–235–300/SM01 ............................... Military ......................... CN–235–300M/CG01, –300M/GC01, –300/MM01, –300/CL04. VerDate Sep<11>2014 20:07 Jan 04, 2017 Jkt 241001 Civilian ........................ Military ......................... PO 00000 Frm 00042 Flight cycles to flight hours conversion Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 0.861. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 0.861. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 0.806. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 0.861. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 0.861. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 2.222. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 2.222. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 2.167. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 1.389. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 1.389. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 1.389. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 0.861. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 3.125. Flight hours since first flight of the airplane = the table 1 to paragraph (i)(1) of this AD × 3.125. Fmt 4702 Sfmt 4702 E:\FR\FM\05JAP1.SGM 05JAP1 applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from applicable flight cycles from Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules (2) Repeat the eddy current inspection specified in paragraph (i)(1) of this AD thereafter within the applicable interval 1273 specified in table 3 to paragraph (i)(2) of this AD. TABLE 3 TO PARAGRAPH (i)(2) OF THIS AD—REPETITIVE INSPECTION INTERVALS Elevator attachment fitting (P/N) Manufacturer’s serial No. MSN001 through MSN154 inclusive ... 35–31193–0201 35–31193–0202 MSN155 through MSN241 inclusive ... 35–31193–0501 35–31193–0502 MSN242 through MSN999 inclusive ... 35–31193–0503 35–31193–0504 Compliance time for repetitive eddy current inspections Before exceeding 1,300 flight cycles since the most recent inspection; or before exceeding the applicable flight hours since the most recent inspection as calculated in table 4 to paragraph (i)(2) of this AD; whichever occurs first. Before exceeding 1,000 flight cycles since the most recent inspection; or before exceeding the applicable flight hours since the most recent inspection as calculated in table 4 to paragraph (i)(2) of this AD; whichever occurs first. Before exceeding 1,000 flight cycles since the most recent inspection; or before exceeding the applicable flight hours since the most recent inspection as calculated in table 4 to paragraph (i)(2) of this AD; whichever occurs first. TABLE 4 TO PARAGRAPH (i)(2) OF THIS AD—FLIGHT CYCLES TO FLIGHT HOURS CONVERSION FOR REPETITIVE INSPECTIONS CN–235 model/version Civilian or military type certificate Flight cycles to flight hours conversion CN–235 (Commercial Identification S10). CN–235–100 ....................................... Civilian ................. Civilian ................. CN–235–200 ....................................... Civilian ................. CN–235–300 ....................................... Civilian ................. CN–235 (Commercial Identification S10M). CN–235–100M .................................... Military .................. Military .................. CN–235–200M .................................... Military .................. CN–235–300M .................................... Military .................. CN–235–100M/IR01 ........................... Military .................. CN–235–100M/EA02V ....................... Military .................. CN–235–200M/CL02 .......................... Military .................. CN–235/EA01F (Commercial Identification S10M). CN–235–300/SM01 ............................ Military .................. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 0.861. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 0.861. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 0.806. Flight hours since first flight of the airplane = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 0.861. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 0.861. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 2.222. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 2.222. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 2.167. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 1.389. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 1.389. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 1.389. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 0.861. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 3.125. Flight hours since most recent inspection = the applicable flight cycles from table 3 to paragraph (i)(2) of this AD × 3.125. CN–235–300M/CG01, –300M/GC01, –300/MM01, –300/CL04. Civilian ................. Military .................. mstockstill on DSK3G9T082PROD with PROPOSALS (j) Repetitive Eddy Current Inspections— Model C–295 Airplanes For Model C–295 airplanes: Do the actions required by paragraphs (j)(1) and (j)(2) of this AD. VerDate Sep<11>2014 20:07 Jan 04, 2017 Jkt 241001 (1) At the later of the times specified in table 5 to paragraph (j)(1) of this AD: Do an eddy current inspection of the elevator hinge fitting and attachment fitting to detect cracks, in accordance with the instructions of Airbus PO 00000 Frm 00043 Fmt 4702 Sfmt 4702 Defense and Space S.A. AOT AOT–C295–55– 0003, dated December 22, 2015. E:\FR\FM\05JAP1.SGM 05JAP1 1274 Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules TABLE 5 TO PARAGRAPH (j)(1) OF THIS AD—INITIAL COMPLIANCE TIMES FOR MODEL C–295 AIRPLANES Compliance time for initial eddy current inspection (whichever occurs later) C–295 model/version Manufacturer’s Serial Number (MSN) C–295M/EA03(01–10), RJ01 (01–02), PO01(01– 08), AG01(01–06), BR01(01–03). MSN001 through MSN030 inclusive. 95–31193–0501 95–31193–0502 C–295M (from MSN 031) ... MSN031 through MSN999 inclusive. 95–31193–0503 95–31193–0504 C–295M/FI01, FI02 ............ MSN031 through MSN999 inclusive. 95–31193–0503 95–31193–0504 C–295M/PG01 .................... MSN031 through MSN999 inclusive. 95–31193–0503 95–31193–0504 C–295M/PG02, PG03 ........ MSN031 through MSN999 inclusive. 95–31193–0503 95–31193–0504 C–295M/CH01 .................... MSN031 through MSN999 inclusive. 95–31193–0503 95–31193–0504 C–295M/CH02, OM03 ........ MSN031 through MSN999 inclusive. 95–31193–0503 95–31193–0504 C–295MW ........................... MSN031 through MSN999 inclusive. 95–31193–0503 95–31193–0504 (2) Repeat the eddy current inspection specified in paragraph (j)(1) of this AD thereafter within the applicable interval Elevator hinge fitting (part no.) Since first flight of the airplane: Before exceeding 3,600 flight cycles; or before exceeding 5,040 flight hours; whichever occurs first. Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,400 flight hours; whichever occurs first. Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,000 flight hours; whichever occurs first. Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,400 flight hours; whichever occurs first. Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,900 flight hours; whichever occurs first. Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,200 flight hours; whichever occurs first. Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,500 flight hours; whichever occurs first. Since first flight of the airplane: Before exceeding 1,000 flight cycles; or before exceeding 1,400 flight hours; whichever occurs first. Within 300 flight cycles after the effective date of this AD. Within 50 flight cycles after the effective date of this AD. Within 50 flight cycles after the effective date of this AD. Within 50 flight cycles after the effective date of this AD. Within 50 flight cycles after the effective date of this AD. Within 50 flight cycles after the effective date of this AD. Within 50 flight cycles after the effective date of this AD. Within 50 flight cycles after the effective date of this AD. specified in table 6 to paragraph (j)(2) of this AD. TABLE 6 TO PARAGRAPH (j)(2) OF THIS AD—REPETITIVE INSPECTION INTERVALS FOR MODEL C–295 AIRPLANES Elevator hinge fitting (part no.) mstockstill on DSK3G9T082PROD with PROPOSALS C–295 model/version Manufacturer’s Serial Number (MSN) C–295M/EA03(01–10), RJ01 (01–02), PO01(01–08), AG01(01–06), BR01(01–03). MSN001 through MSN030 inclusive .. 95–31193–0501 95–31193–0502 C–295M (from MSN 031) ................... MSN031 through MSN999 inclusive .. 95–31193–0503 95–31193–0504 VerDate Sep<11>2014 20:07 Jan 04, 2017 Jkt 241001 PO 00000 Frm 00044 Fmt 4702 Sfmt 4702 E:\FR\FM\05JAP1.SGM Compliance time for repetitive eddy current inspections Before exceeding 1,000 flight cycles since the most recent inspection; or before exceeding 1,400 flight hours since the most recent inspection; whichever occurs first. Before exceeding 1,000 flight cycles since the most recent inspection; or before exceeding 1,400 flight hours since the most recent inspection; whichever occurs first. 05JAP1 Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules 1275 TABLE 6 TO PARAGRAPH (j)(2) OF THIS AD—REPETITIVE INSPECTION INTERVALS FOR MODEL C–295 AIRPLANES— Continued Elevator hinge fitting (part no.) C–295 model/version Manufacturer’s Serial Number (MSN) C–295M/FI01, FI02 ............................ MSN031 through MSN999 inclusive .. 95–31193–0503 95–31193–0504 C–295M/PG01 .................................... MSN031 through MSN999 inclusive .. 95–31193–0503 95–31193–0504 C–295M/PG02, PG03 ........................ MSN031 through MSN999 inclusive .. 95–31193–0503 95–31193–0504 C–295M/CH01 .................................... MSN031 through MSN999 inclusive .. 95–31193–0503 95–31193–0504 C–295M/CH02, OM03 ........................ MSN031 through MSN999 inclusive .. 95–31193–0503 95–31193–0504 C–295MW ........................................... MSN031 through MSN999 inclusive .. 95–31193–0503 95–31193–0504 mstockstill on DSK3G9T082PROD with PROPOSALS (k) Corrective Action for Discrepancies Found During Eddy Current Inspection If, during any inspection required by paragraph (i)(1), (i)(2), (j)(1), or (j)(2) of this AD, any crack is detected, as defined in Airbus Defense and Space S.A. AOT AOT– CN235–55–0003, dated December 22, 2015; or AOT AOT–C295–55–0003, dated December 22, 2015; as applicable: Before further flight, accomplish applicable corrective actions in accordance with the instructions of Airbus Defense and Space S.A. AOT AOT–CN235–55–0003, dated December 22, 2015; or AOT AOT–C295–55– 0003, dated December 22, 2015; as applicable. Where Airbus Defense and Space S.A. AOT AOT–CN235–55–0003, dated December 22, 2015; or AOT AOT–C295–55– 0003, dated December 22, 2015; specifies to contact Airbus Defense and Space S.A. for corrective actions, before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD. (l) Provision Regarding Terminating Action Accomplishing corrective actions, as required by paragraph (k) of this AD, does not constitute terminating action for the repetitive inspections required by paragraphs (i)(2) and (j)(2) of this AD, unless explicitly stated in the approved method of compliance for the corrective action. (m) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, VerDate Sep<11>2014 20:07 Jan 04, 2017 Jkt 241001 if those actions were performed before the effective date of this AD using Airbus Defense and Space S.A. AOT AOT–CN235– 55–0001, Revision 1, dated March 6, 2015; or AOT AOT–C295–55–0001, Revision 1, dated May 29, 2014. (n) 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: 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 PO 00000 Frm 00045 Fmt 4702 Sfmt 9990 Compliance time for repetitive eddy current inspections Before exceeding 1,000 flight cycles since the most recent inspection; or before exceeding 1,000 flight hours since the most recent inspection; whichever occurs first. Before exceeding 1,000 flight cycles since the most recent inspection; or before exceeding 1,400 flight hours since the most recent inspection; whichever occurs first. Before exceeding 1,000 flight cycles since the most recent inspection; or before exceeding 1,900 flight hours since the most recent inspection; whichever occurs first. Before exceeding 1,000 flight cycles since the most recent inspection; or before exceeding 1,200 flight hours since the most recent inspection; whichever occurs first. Before exceeding 1,000 flight cycles since the most recent inspection; or before exceeding 1,500 flight hours since the most recent inspection; whichever occurs first. Before exceeding 1,000 flight cycles since the most recent inspection; or before exceeding 1,400 flight hours since the most recent inspection; whichever occurs first. by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus Defense and Space S.A.’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0075, dated April 19, 2016, for related information. This MCAI may be found in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016–9521. (2) For service information identified in this AD, contact Airbus Defense and Space, Services/Engineering Support, Avenida de ´ Aragon 404, 28022 Madrid, Spain; 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 December 16, 2016. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–31365 Filed 1–4–17; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\05JAP1.SGM 05JAP1

Agencies

[Federal Register Volume 82, Number 3 (Thursday, January 5, 2017)]
[Proposed Rules]
[Pages 1269-1275]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-31365]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9521; Directorate Identifier 2016-NM-061-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 CN-235, CN-235-100, CN-235-200, CN-
235-300, and C-295 airplanes. This proposed AD was prompted by reports
of excessive play between bushings and their respective fitting
housings at certain elevator fittings. This proposed AD would require a
one-time detailed inspection and repetitive eddy current inspections of
the elevator hinge fitting and bracket assembly, and corrective actions
if necessary. We are proposing this AD to address the unsafe condition
on these products.

DATES: We must receive comments on this proposed AD by February 21,
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:

[[Page 1270]]

Federal eRulemaking Portal: Go to https://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; 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.

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9521; 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-2016-9521;
Directorate Identifier 2016-NM-061-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 https://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 EADS AD
2016-0075, dated April 19, 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
CN-235, CN-235-100, CN-235-200, CN-235-300, and C-295 airplanes. The
MCAI states:

Excessive play between bushings and their respective fitting
housing was reported at Stabilizer Station (STA) 4850, affecting the
outboard and inboard elevator hinge fittings and attachment
fittings; and the horizontal stabilizer elevator linkage.
Additionally, excessive misalignment was detected between the
elevator hinge fittings and the elevator brackets during further
analysis of the reported cases. Furthermore, an occurrence of an
elevator hinge fitting crack was reported.
This condition, if not detected and corrected, could lead to
failure or detachment of any of the affected structural parts,
possibly resulting in reduced control of the aeroplane.
To address this potentially unsafe condition, Airbus Defence &
Space (D&S) issued Alert Operator Transmissions (AOT) AOT-CN235-55-
0001 Revision 2 and AOT-C295-55-0001 Revision 2 to provide
inspection instructions to detect misalignment between the elevator
hinge fittings and the elevator brackets. Additionally, Airbus D&S
issued AOT-CN235-55-0003 and AOT-C295-55-0003 to provide inspection
instructions to detect cracking of elevator hinge fitting and
attachment fitting.
For the reasons described above, this [EASA] AD requires a one-
time [detailed] inspection of the elevator hinge fittings and the
elevator brackets, repetitive [eddy current] inspections of elevator
hinge fittings and attachment fittings, and depending on findings,
accomplishment of applicable corrective action(s) [e.g. repair(s)].

You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9521.

Related Service Information Under 1 CFR Part 51

Airbus Defense and Space S.A. has issued the following Alert
Operators Transmissions (AOT).
Airbus Defense and Space S.A. AOT AOT-CN235-55-0001,
Revision 2, dated March 10, 2015. The service information describes
procedures for a detailed visual inspection of the elevator hinge
fitting and bracket assembly to detect excessive play between bushings
and their respective fitting housings, and to detect cracks; and
corrective actions if necessary.
Airbus Defense and Space S.A. AOT AOT-CN235-55-0003, dated
December 22, 2015. The service information describes procedures for
repetitive eddy current inspections to detect cracks in the elevator
hinge fitting and bracket assembly, and corrective actions if
necessary.
Airbus Defense and Space S.A. AOT AOT-C295-55-0001,
Revision 2, dated April 09, 2015. The service information describes
procedures for a detailed visual inspection of the elevator hinge
fitting and bracket assembly to detect excessive play between bushings
and their respective fitting housings, and to detect cracks; and
corrective actions if necessary.
Airbus Defense and Space S.A. AOT AOT-C295-55-0003, dated
December 22, 2015. The service information describes procedures for
repetitive eddy current inspections to detect cracks in the elevator
hinge fitting and bracket assembly, and corrective actions if
necessary.
These documents are distinct since they apply to different airplane
models in different configurations. 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 these
same type designs.

Differences Between This Proposed AD and the MCAI or Service
Information

The MCAI allows credit for an inspection done in accordance with
the following Airbus Defense and Space S.A. AOTs, as applicable:
AOT-CN235-55-0001, dated December 16, 2014, or
AOT-C295-55-0001, dated December 16, 2014.

[[Page 1271]]

This proposed AD does not give credit for accomplishing those
initial issues of the service information because the inspection
requirements are different from the initial issues of the service
information in both Revision 1 and Revision 2 of Airbus Defense and
Space AOT AOT-CN235-55-0001, and AOT AOT-C295-55-0001.
Also, the MCAI identifies a date for Revision 1 of Airbus Defense
and Space S.A. AOT AOT-C295-55-0001, which was corrected by Revision 2
of the same service information. Paragraph (m), ``Credit for Previous
Actions,'' of this proposed AD shows the correct date.

Costs of Compliance

We estimate that this proposed AD affects 14 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection........................ 2 work-hours x $85 $0 $170 per inspection $2,380 per
per hour = $170 per cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------

We estimate the following costs to do any necessary repairs that
would be required based on the results of the proposed inspection. We
have no way of determining the number of airplanes that might need this
repair:

On-Condition Costs
------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
------------------------------------------------------------------------
Repair....................... 45 work-hours x $10,000 $13,825
$85 per hour =
$3,825.
------------------------------------------------------------------------

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-2016-9521; Directorate
Identifier 2016-NM-061-AD.

(a) Comments Due Date

We must receive comments by February 21, 2017.

(b) Affected ADs

None.

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 55, Stabilizers.

(e) Reason

This AD was prompted by reports of excessive play between
bushings and their respective fitting housings at certain elevator
fittings. We are issuing this AD to prevent excessive play between
bushings and their respective fitting housings, which could lead to
failure or detachment of any of the affected structural parts, with
a possible result of reduced control of the airplane.

(f) Compliance

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

(g) One-Time Detailed Visual Inspection

Before exceeding 600 flight hours since first flight of the
airplane, or within 300 flight hours after the effective date of
this AD, whichever occurs later, but not before exceeding 300 flight
hours since first flight of the airplane: Do a detailed visual
inspection of the elevator hinge fitting and bracket assembly to
detect excessive play between bushings and their respective fitting
housings, and to detect cracks, in accordance with the instructions
of Airbus Defense and Space S.A. Alert Operators Transmission

[[Page 1272]]

(AOT) AOT-CN235-55-0001, Revision 2, dated March 10, 2015; or AOT
AOT-C295-55-0001, Revision 2, dated April 9, 2015; as applicable.

(h) Corrective Action for Discrepancies Found During Detailed Visual
Inspection

If, during the inspection required by paragraph (g) of this AD,
any discrepancy is detected, as defined in the instructions of
Airbus Defense and Space S.A. AOT AOT-CN235-55-0001, Revision 2,
dated March 10, 2015; or AOT AOT-C295-55-0001 Revision 2, dated
April 9, 2015; as applicable: Before further flight, accomplish
applicable corrective actions, in accordance with the instructions
of Airbus Defense and Space S.A. AOT AOT-CN235-55-0001, Revision 2,
dated March 10, 2015; or AOT AOT-C295-55-0001, Revision 2, dated
April 9, 2015; as applicable. Where Airbus Defense and Space S.A.
AOT AOT-CN235-55-0001, Revision 2, dated March 10, 2015; or AOT AOT-
C295-55-0001 Revision 2, dated April 9, 2015; specifies to contact
Airbus Defense and Space S.A. for corrective actions, before further
flight, accomplish corrective actions in accordance with the
procedures specified in paragraph (n)(2) of this AD.

(i) Repetitive Eddy Current Inspections--Model CN-235, CN-235-100, CN-
235-200, and CN-235-300 Airplanes

For Model CN-235, CN-235-100, CN-235-200, and CN-235-300
airplanes: Do the actions required by paragraphs (i)(1) and (i)(2)
of this AD.
(1) Within the applicable compliance time specified in table 1
to paragraph (i)(1) of this AD: Do an eddy current inspection to
detect cracks in the elevator hinge fitting and bracket assembly, in
accordance with the instructions of Airbus Defense and Space S.A.
AOT AOT-CN235-55-0003, dated December 22, 2015.

Table 1 to Paragraph (i)(1) of This AD--Initial Compliance Times for Model CN-235, CN-235-100, CN-235-200, and
CN-235-300 Airplanes
----------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------
Manufacturer's Serial Number (MSN) Elevator hinge Compliance time for initial eddy current inspection
fitting (part (whichever occurs later)
No.)
----------------------------------------------------------------------------------------------------------------
MSN001 through MSN154 inclusive...... 35-31193-0201 Before exceeding 8,800 flight Within 300 flight
35-31193-0202 cycles since first flight of cycles after the
the airplane; or before effective date of this
exceeding the applicable AD.
flight hours since first
flight of the airplane as
calculated in table 2 to
paragraph (i)(1) of this AD;
whichever occurs first.
MSN155 through MSN241 inclusive...... 35-31193-0501 Before exceeding 3,600 flight Within 300 flight
35-31193-0502 cycles since first flight of cycles after the
the airplane; or before effective date of this
exceeding the applicable AD.
flight hours since first
flight of the airplane as
calculated in table 2 to
paragraph (i)(1) of this AD;
whichever occurs first.
MSN242 through MSN999 inclusive...... 35-31193-0503 Before exceeding 1,000 flight Within 50 flight cycles
35-31193-0504 cycles since first flight of after the effective
the airplane; or before date of this AD.
exceeding the applicable
flight hours since first
flight of the airplane as
calculated in table 2 to
paragraph (i)(1) of this AD;
whichever occurs first.
----------------------------------------------------------------------------------------------------------------

Table 2 to Paragraph (i)(1) of This AD--Flight Cycles to Flight Hours
Conversion Since First Flight of the Airplane
------------------------------------------------------------------------
Civilian or Flight cycles to
CN-235 model/version military type flight hours
certificate conversion
------------------------------------------------------------------------
CN-235 (Commercial Civilian......... Flight hours since
Identification S10). first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.861.
CN-235-100.................... Civilian......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.861.
CN-235-200.................... Civilian......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.806.
CN-235-300.................... Civilian......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.861.
CN-235 (Commercial Military......... Flight hours since
Identification S10M). first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.861.
CN-235-100M................... Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 2.222.
CN-235-200M................... Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 2.222.
CN-235-300M................... Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 2.167.
CN-235-100M/IR01.............. Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 1.389.
CN-235-100M/EA02V............. Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 1.389.
CN-235-200M/CL02.............. Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 1.389.
CN-235/EA01F (Commercial Military......... Flight hours since
Identification S10M). first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.861.
CN-235-300/SM01............... Civilian......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 3.125.
CN-235-300M/CG01, -300M/GC01, - Military......... Flight hours since
300/MM01, -300/CL04. first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 3.125.
------------------------------------------------------------------------

[[Page 1273]]

(2) Repeat the eddy current inspection specified in paragraph
(i)(1) of this AD thereafter within the applicable interval
specified in table 3 to paragraph (i)(2) of this AD.

Table 3 to Paragraph (i)(2) of This AD--Repetitive Inspection Intervals
------------------------------------------------------------------------
Elevator Compliance time for
Manufacturer's serial No. attachment repetitive eddy
fitting (P/N) current inspections
------------------------------------------------------------------------
MSN001 through MSN154 35-31193-0201 Before exceeding 1,300
inclusive. 35-31193-0202 flight cycles since
the most recent
inspection; or before
exceeding the
applicable flight
hours since the most
recent inspection as
calculated in table 4
to paragraph (i)(2)
of this AD; whichever
occurs first.
MSN155 through MSN241 35-31193-0501 Before exceeding 1,000
inclusive. 35-31193-0502 flight cycles since
the most recent
inspection; or before
exceeding the
applicable flight
hours since the most
recent inspection as
calculated in table 4
to paragraph (i)(2)
of this AD; whichever
occurs first.
MSN242 through MSN999 35-31193-0503 Before exceeding 1,000
inclusive. 35-31193-0504 flight cycles since
the most recent
inspection; or before
exceeding the
applicable flight
hours since the most
recent inspection as
calculated in table 4
to paragraph (i)(2)
of this AD; whichever
occurs first.
------------------------------------------------------------------------

Table 4 to Paragraph (i)(2) of This AD--Flight Cycles to Flight Hours
Conversion for Repetitive Inspections
------------------------------------------------------------------------
Civilian or
CN-235 model/version military type Flight cycles to flight
certificate hours conversion
------------------------------------------------------------------------
CN-235 (Commercial Civilian........ Flight hours since most
Identification S10). recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 0.861.
CN-235-100................... Civilian........ Flight hours since most
recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 0.861.
CN-235-200................... Civilian........ Flight hours since most
recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 0.806.
CN-235-300................... Civilian........ Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 0.861.
CN-235 (Commercial Military........ Flight hours since most
Identification S10M). recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 0.861.
CN-235-100M.................. Military........ Flight hours since most
recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 2.222.
CN-235-200M.................. Military........ Flight hours since most
recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 2.222.
CN-235-300M.................. Military........ Flight hours since most
recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 2.167.
CN-235-100M/IR01............. Military........ Flight hours since most
recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 1.389.
CN-235-100M/EA02V............ Military........ Flight hours since most
recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 1.389.
CN-235-200M/CL02............. Military........ Flight hours since most
recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 1.389.
CN-235/EA01F (Commercial Military........ Flight hours since most
Identification S10M). recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 0.861.
CN-235-300/SM01.............. Civilian........ Flight hours since most
recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 3.125.
CN-235-300M/CG01, -300M/GC01, Military........ Flight hours since most
-300/MM01, -300/CL04. recent inspection =
the applicable flight
cycles from table 3 to
paragraph (i)(2) of
this AD x 3.125.
------------------------------------------------------------------------

(j) Repetitive Eddy Current Inspections--Model C-295 Airplanes

For Model C-295 airplanes: Do the actions required by paragraphs
(j)(1) and (j)(2) of this AD.
(1) At the later of the times specified in table 5 to paragraph
(j)(1) of this AD: Do an eddy current inspection of the elevator
hinge fitting and attachment fitting to detect cracks, in accordance
with the instructions of Airbus Defense and Space S.A. AOT AOT-C295-
55-0003, dated December 22, 2015.

[[Page 1274]]

Table 5 to Paragraph (j)(1) of This AD--Initial Compliance Times for Model C-295 Airplanes
----------------------------------------------------------------------------------------------------------------
Compliance time
for initial eddy
Manufacturer's Elevator hinge fitting current
C-295 model/version Serial Number (part no.) inspection
(MSN) (whichever occurs
later)
----------------------------------------------------------------------------------------------------------------
C-295M/EA03(01-10), RJ01 (01- MSN001 through 95-31193-0501 Since first Within 300 flight
02), PO01(01-08), AG01(01- MSN030 inclusive. 95-31193-0502 flight of the cycles after the
06), BR01(01-03). airplane: Before effective date
exceeding 3,600 of this AD.
flight cycles;
or before
exceeding 5,040
flight hours;
whichever occurs
first.
C-295M (from MSN 031)......... MSN031 through 95-31193-0503 Since first Within 50 flight
MSN999 inclusive. 95-31193-0504 flight of the cycles after the
airplane: Before effective date
exceeding 1,000 of this AD.
flight cycles;
or before
exceeding 1,400
flight hours;
whichever occurs
first.
C-295M/FI01, FI02............. MSN031 through 95-31193-0503 Since first Within 50 flight
MSN999 inclusive. 95-31193-0504 flight of the cycles after the
airplane: Before effective date
exceeding 1,000 of this AD.
flight cycles;
or before
exceeding 1,000
flight hours;
whichever occurs
first.
C-295M/PG01................... MSN031 through 95-31193-0503 Since first Within 50 flight
MSN999 inclusive. 95-31193-0504 flight of the cycles after the
airplane: Before effective date
exceeding 1,000 of this AD.
flight cycles;
or before
exceeding 1,400
flight hours;
whichever occurs
first.
C-295M/PG02, PG03............. MSN031 through 95-31193-0503 Since first Within 50 flight
MSN999 inclusive. 95-31193-0504 flight of the cycles after the
airplane: Before effective date
exceeding 1,000 of this AD.
flight cycles;
or before
exceeding 1,900
flight hours;
whichever occurs
first.
C-295M/CH01................... MSN031 through 95-31193-0503 Since first Within 50 flight
MSN999 inclusive. 95-31193-0504 flight of the cycles after the
airplane: Before effective date
exceeding 1,000 of this AD.
flight cycles;
or before
exceeding 1,200
flight hours;
whichever occurs
first.
C-295M/CH02, OM03............. MSN031 through 95-31193-0503 Since first Within 50 flight
MSN999 inclusive. 95-31193-0504 flight of the cycles after the
airplane: Before effective date
exceeding 1,000 of this AD.
flight cycles;
or before
exceeding 1,500
flight hours;
whichever occurs
first.
C-295MW....................... MSN031 through 95-31193-0503 Since first Within 50 flight
MSN999 inclusive. 95-31193-0504 flight of the cycles after the
airplane: Before effective date
exceeding 1,000 of this AD.
flight cycles;
or before
exceeding 1,400
flight hours;
whichever occurs
first.
----------------------------------------------------------------------------------------------------------------

(2) Repeat the eddy current inspection specified in paragraph
(j)(1) of this AD thereafter within the applicable interval
specified in table 6 to paragraph (j)(2) of this AD.

Table 6 to Paragraph (j)(2) of This AD--Repetitive Inspection Intervals for Model C-295 Airplanes
----------------------------------------------------------------------------------------------------------------
Compliance time for
C-295 model/version Manufacturer's Serial Elevator hinge fitting repetitive eddy current
Number (MSN) (part no.) inspections
----------------------------------------------------------------------------------------------------------------
C-295M/EA03(01-10), RJ01 (01-02), MSN001 through MSN030 95-31193-0501 Before exceeding 1,000
PO01(01-08), AG01(01-06), BR01(01- inclusive. 95-31193-0502 flight cycles since
03). the most recent
inspection; or before
exceeding 1,400 flight
hours since the most
recent inspection;
whichever occurs
first.
C-295M (from MSN 031)................ MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since
the most recent
inspection; or before
exceeding 1,400 flight
hours since the most
recent inspection;
whichever occurs
first.

[[Page 1275]]

C-295M/FI01, FI02.................... MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since
the most recent
inspection; or before
exceeding 1,000 flight
hours since the most
recent inspection;
whichever occurs
first.
C-295M/PG01.......................... MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since
the most recent
inspection; or before
exceeding 1,400 flight
hours since the most
recent inspection;
whichever occurs
first.
C-295M/PG02, PG03.................... MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since
the most recent
inspection; or before
exceeding 1,900 flight
hours since the most
recent inspection;
whichever occurs
first.
C-295M/CH01.......................... MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since
the most recent
inspection; or before
exceeding 1,200 flight
hours since the most
recent inspection;
whichever occurs
first.
C-295M/CH02, OM03.................... MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since
the most recent
inspection; or before
exceeding 1,500 flight
hours since the most
recent inspection;
whichever occurs
first.
C-295MW.............................. MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since
the most recent
inspection; or before
exceeding 1,400 flight
hours since the most
recent inspection;
whichever occurs
first.
----------------------------------------------------------------------------------------------------------------

(k) Corrective Action for Discrepancies Found During Eddy Current
Inspection

If, during any inspection required by paragraph (i)(1), (i)(2),
(j)(1), or (j)(2) of this AD, any crack is detected, as defined in
Airbus Defense and Space S.A. AOT AOT-CN235-55-0003, dated December
22, 2015; or AOT AOT-C295-55-0003, dated December 22, 2015; as
applicable: Before further flight, accomplish applicable corrective
actions in accordance with the instructions of Airbus Defense and
Space S.A. AOT AOT-CN235-55-0003, dated December 22, 2015; or AOT
AOT-C295-55-0003, dated December 22, 2015; as applicable. Where
Airbus Defense and Space S.A. AOT AOT-CN235-55-0003, dated December
22, 2015; or AOT AOT-C295-55-0003, dated December 22, 2015;
specifies to contact Airbus Defense and Space S.A. for corrective
actions, before further flight, accomplish corrective actions in
accordance with the procedures specified in paragraph (n)(2) of this
AD.

(l) Provision Regarding Terminating Action

Accomplishing corrective actions, as required by paragraph (k)
of this AD, does not constitute terminating action for the
repetitive inspections required by paragraphs (i)(2) and (j)(2) of
this AD, unless explicitly stated in the approved method of
compliance for the corrective action.

(m) Credit for Previous Actions

This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Airbus Defense and Space S.A. AOT
AOT-CN235-55-0001, Revision 1, dated March 6, 2015; or AOT AOT-C295-
55-0001, Revision 1, dated May 29, 2014.

(n) 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 EASA; or
Airbus Defense and Space S.A.'s EASA DOA. If approved by the DOA,
the approval must include the DOA-authorized signature.

(o) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0075, dated April 19, 2016, for related
information. This MCAI may be found in the AD docket on the Internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2016-9521.
(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; 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 December 16, 2016.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-31365 Filed 1-4-17; 8:45 am]
BILLING CODE 4910-13-P

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