82 FR 1269 - Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 3 (January 5, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 3 (January 5, 2017)
| Page Range | 1269-1275 | |
| FR Document | 2016-31365 |
[Federal Register Volume 82, Number 3 (Thursday, January 5, 2017)] [Proposed Rules] [Pages 1269-1275] From the Federal Register Online [www.thefederalregister.org] [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 http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus Defense and Space, Services/Engineering Support, Avenida de Arag[oacute]n 404, 28022 Madrid, Spain; fax +34 91 585 31 27; email [email protected]. 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 http://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 http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued 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 http://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. (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 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: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or 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 http://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 [email protected]. 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
![Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules 1269
distribution of power and (c) Affected ADs lacking a principal inspector, the manager of
responsibilities among the various This AD supersedes AD 93–17–13, the local flight standards district office or
levels of government. Amendment 39–8684 (58 FR 51770, October certificate holding district office before
5, 1993). operating any aircraft complying with this
For the reasons discussed, I certify AD through an AMOC.
this proposed regulation: (d) Comments Due Date
(i) Additional Information
1. Is not a ‘‘significant regulatory We must receive comments by March 6,
For service information identified in this
action’’ under Executive Order 12866; 2017.
AD, contact Sikorsky Aircraft Corporation,
2. Is not a ‘‘significant rule’’ under the (e) Compliance Customer Service Engineering, 124 Quarry
DOT Regulatory Policies and Procedures You are responsible for performing each Road, Trumbull, CT 06611; telephone 1–800–
(44 FR 11034, February 26, 1979); action required by this AD within the Winged-S or 203–416–4299; email wcs_cust_
service_eng.gr-sik@lmco.com. You may
3. Will not affect intrastate aviation in specified compliance time unless it has
review a copy of information at the FAA,
Alaska to the extent that it justifies already been accomplished prior to that time.
Office of the Regional Counsel, Southwest
making a regulatory distinction; and (f) Required Actions Region, 10101 Hillwood Pkwy, Room 6N–
4. Will not have a significant (1) Within 25 hours time-in-service (TIS), 321, Fort Worth, TX 76177.
economic impact, positive or negative, install engine and rotor tachometer markings (j) Subject
on a substantial number of small entities in accordance with Part II of Schweizer Joint Aircraft Service Component (JASC)
under the criteria of the Regulatory Aircraft Service Bulletin B–257.1, dated May Code: 6300, Main Rotor Drive System.
Flexibility Act. 21, 1993.
(2) Within 25 hours TIS and thereafter at Issued in Fort Worth, Texas, on December
We prepared an economic evaluation intervals not to exceed 150 hours TIS: 21, 2016.
of the estimated costs to comply with (i) Visually inspect the driveshaft for Lance T. Gant,
this proposed AD and placed it in the corrosion, a pit, a nick, a scratch, a dent, and Manager, Rotorcraft Directorate, Aircraft
AD docket. a crack in accordance with the Certification Service.
Accomplishment Instructions, paragraph [FR Doc. 2016–31622 Filed 1–4–17; 8:45 am]
List of Subjects in 14 CFR Part 39 3.B.(1) through 3.B.(6) of Sikorsky 269C
BILLING CODE 4910–13–P
Helicopter Alert Service Bulletin B–307,
Air transportation, Aircraft, Aviation Basic Issue, dated December 18, 2014 (269C
safety, Incorporation by Reference, ASB), or Sikorsky 269C–1 Helicopter Alert
Safety. Service Bulletin C1B–043, Basic Issue, dated DEPARTMENT OF TRANSPORTATION
December 18, 2014 (269C–1 ASB), whichever
The Proposed Amendment Federal Aviation Administration
is applicable for your model helicopter,
Accordingly, under the authority except we do not require that you use a
Sikorsky recommended vendor list. If there is 14 CFR Part 39
delegated to me by the Administrator,
any corrosion, a pit, a nick, a scratch, a dent,
the FAA proposes to amend 14 CFR part or a crack, replace the driveshaft before
[Docket No. FAA–2016–9521; Directorate
39 as follows: Identifier 2016–NM–061–AD]
further flight.
(ii) If there is no corrosion and no pits, RIN 2120–AA64
PART 39—AIRWORTHINESS nicks, scratches, dents, and cracks, magnetic
DIRECTIVES particle inspect the driveshaft for a crack in Airworthiness Directives; Airbus
accordance with paragraph 3.C.(1) of the Defense and Space S.A. (Formerly
■ 1. The authority citation for part 39 269C ASB or 269C–1 ASB, whichever is Known as Construcciones
continues to read as follows: applicable for your model helicopter. This Aeronauticas, S.A.) Airplanes
magnetic particle inspection must be
Authority: 49 U.S.C. 106(g), 40113, 44701. performed by a Level II or higher technician AGENCY: Federal Aviation
§ 39.13 [Amended] with the National Aerospace Standard 410 or Administration (FAA), DOT.
equivalent certification who has performed a ACTION: Notice of proposed rulemaking
■ 2. The FAA amends § 39.13 by magnetic particle inspection within the last
(NPRM).
removing Airworthiness Directive (AD) 12 months. If there is a crack, replace the
AD 93–17–13, Amendment 39–8684 (58 driveshaft before further flight. SUMMARY: We propose to adopt a new
FR 51770, October 5, 1993) and adding (g) Credit for Actions Previously Completed airworthiness directive (AD) for all
the following new airworthiness Compliance with paragraph (a)(1) of AD Airbus Defense and Space S.A. Model
directive (AD): 93–17–13, Amendment 39–8684 (58 FR CN–235, CN–235–100, CN–235–200,
Sikorsky Aircraft Corporation (Type 51770, October 5, 1993) before the effective CN–235–300, and C–295 airplanes. This
Certificate Previously Held By date of this AD is considered acceptable for proposed AD was prompted by reports
Schweizer Aircraft Corporation): Docket compliance with the actions specified in of excessive play between bushings and
No. FAA–2016–6968; Directorate paragraph (f)(1) of this AD. their respective fitting housings at
Identifier 2015–SW–020–AD. certain elevator fittings. This proposed
(h) Alternative Methods of Compliance
(a) Applicability (AMOC) AD would require a one-time detailed
(1) The Manager, Boston Aircraft
inspection and repetitive eddy current
This AD applies to Model TH55A, 269A,
269A–1, 269B, 269C and 269C–1 helicopters, Certification Office, FAA, may approve inspections of the elevator hinge fitting
with a lower coupling driveshaft (driveshaft) AMOCs for this AD. Send your proposal to: and bracket assembly, and corrective
part number (P/N) 269–5412, 269A5504, Blaine Williams, Aerospace Engineer, Boston actions if necessary. We are proposing
mstockstill on DSK3G9T082PROD with PROPOSALS
269A5504–003, 269A5504–005, 269A5559, Aircraft Certification Office, Engine & this AD to address the unsafe condition
or 269A5559–003 installed, certificated in Propeller Directorate, 12 New England on these products.
any category. Executive Park, Burlington, Massachusetts DATES: We must receive comments on
01803; telephone (781) 238–7161; email this proposed AD by February 21, 2017.
(b) Unsafe Condition blaine.williams@faa.gov.
This AD defines the unsafe condition as (2) For operations conducted under a 14 ADDRESSES: You may send comments,
failure of a driveshaft. This condition could CFR part 119 operating certificate or under using the procedures found in 14 CFR
result in loss of power to the rotor system 14 CFR part 91, subpart K, we suggest that 11.43 and 11.45, by any of the following
and subsequent loss of helicopter control. you notify your principal inspector, or methods:
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![1270 Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules
• Federal eRulemaking Portal: Go to www.regulations.gov, including any detailed visual inspection of the
http://www.regulations.gov. Follow the personal information you provide. We elevator hinge fitting and bracket
instructions for submitting comments. will also post a report summarizing each assembly to detect excessive play
• Fax: 202–493–2251. substantive verbal contact we receive between bushings and their respective
• Mail: U.S. Department of about this proposed AD. fitting housings, and to detect cracks;
Transportation, Docket Operations, M– and corrective actions if necessary.
30, West Building Ground Floor, Room Discussion
• Airbus Defense and Space S.A.
W12–140, 1200 New Jersey Avenue SE., The European Aviation Safety Agency AOT AOT–CN235–55–0003, dated
Washington, DC 20590. (EASA), which is the Technical Agent December 22, 2015. The service
• Hand Delivery: Deliver to Mail for the Member States of the European information describes procedures for
address above between 9 a.m. and 5 Union, has issued EADS AD 2016–0075, repetitive eddy current inspections to
p.m., Monday through Friday, except dated April 19, 2016 (referred to after detect cracks in the elevator hinge
Federal holidays. this as the Mandatory Continuing fitting and bracket assembly, and
For service information identified in Airworthiness Information, or ‘‘the corrective actions if necessary.
this NPRM, contact Airbus Defense and MCAI’’), to correct an unsafe condition • Airbus Defense and Space S.A.
Space, Services/Engineering Support, for all Airbus Defense and Space S.A. AOT AOT–C295–55–0001, Revision 2,
Avenida de Aragón 404, 28022 Madrid, Model CN–235, CN–235–100, CN–235– dated April 09, 2015. The service
Spain; fax +34 91 585 31 27; email 200, CN–235–300, and C–295 airplanes.
MTA.TechnicalService@airbus.com. information describes procedures for a
The MCAI states: detailed visual inspection of the
You may view this service information
at the FAA, Transport Airplane Excessive play between bushings and their elevator hinge fitting and bracket
respective fitting housing was reported at assembly to detect excessive play
Directorate, 1601 Lind Avenue SW., Stabilizer Station (STA) 4850, affecting the
Renton, WA. For information on the between bushings and their respective
outboard and inboard elevator hinge fittings fitting housings, and to detect cracks;
availability of this material at the FAA, and attachment fittings; and the horizontal
call 425–227–1221. and corrective actions if necessary.
stabilizer elevator linkage. Additionally,
excessive misalignment was detected • Airbus Defense and Space S.A.
Examining the AD Docket between the elevator hinge fittings and the AOT AOT–C295–55–0003, dated
You may examine the AD docket on elevator brackets during further analysis of December 22, 2015. The service
the Internet at http:// the reported cases. Furthermore, an information describes procedures for
www.regulations.gov by searching for occurrence of an elevator hinge fitting crack repetitive eddy current inspections to
and locating Docket No. FAA–2016– was reported. detect cracks in the elevator hinge
This condition, if not detected and fitting and bracket assembly, and
9521; or in person at the Docket corrected, could lead to failure or detachment
Management Facility between 9 a.m. of any of the affected structural parts,
corrective actions if necessary.
and 5 p.m., Monday through Friday, possibly resulting in reduced control of the These documents are distinct since
except Federal holidays. The AD docket aeroplane. they apply to different airplane models
contains this proposed AD, the To address this potentially unsafe in different configurations. This service
regulatory evaluation, any comments condition, Airbus Defence & Space (D&S) information is reasonably available
received, and other information. The issued Alert Operator Transmissions (AOT) because the interested parties have
street address for the Docket Operations AOT–CN235–55–0001 Revision 2 and AOT– access to it through their normal course
C295–55–0001 Revision 2 to provide
office (telephone: 800–647–5527) is in of business or by the means identified
inspection instructions to detect
the ADDRESSES section. Comments will misalignment between the elevator hinge in the ADDRESSES section.
be available in the AD docket shortly fittings and the elevator brackets. FAA’s Determination and Requirements
after receipt. Additionally, Airbus D&S issued AOT– of This Proposed AD
FOR FURTHER INFORMATION CONTACT: CN235–55–0003 and AOT–C295–55–0003 to
Shahram Daneshmandi, Aerospace provide inspection instructions to detect This product has been approved by
Engineer, International Branch, ANM– cracking of elevator hinge fitting and the aviation authority of another
attachment fitting. country, and is approved for operation
116, Transport Airplane Directorate,
For the reasons described above, this in the United States. Pursuant to our
FAA, 1601 Lind Avenue SW., Renton, [EASA] AD requires a one-time [detailed]
WA 98057–3356; telephone: 425–227– bilateral agreement with the State of
inspection of the elevator hinge fittings and
1112; fax: 425–227–1149. the elevator brackets, repetitive [eddy Design Authority, we have been notified
SUPPLEMENTARY INFORMATION: current] inspections of elevator hinge fittings of the unsafe condition described in the
and attachment fittings, and depending on MCAI and service information
Comments Invited findings, accomplishment of applicable referenced above. We are proposing this
We invite you to send any written corrective action(s) [e.g. repair(s)]. AD because we evaluated all pertinent
relevant data, views, or arguments about You may examine the MCAI in the information and determined an unsafe
this proposed AD. Send your comments AD docket on the Internet at http:// condition exists and is likely to exist or
to an address listed under the www.regulations.gov by searching for develop on other products of these same
ADDRESSES section. Include ‘‘Docket No. and locating Docket No. FAA–2016– type designs.
FAA–2016–9521; Directorate Identifier 9521. Differences Between This Proposed AD
2016–NM–061–AD’’ at the beginning of and the MCAI or Service Information
your comments. We specifically invite Related Service Information Under 1
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comments on the overall regulatory, CFR Part 51 The MCAI allows credit for an
economic, environmental, and energy Airbus Defense and Space S.A. has inspection done in accordance with the
aspects of this proposed AD. We will issued the following Alert Operators following Airbus Defense and Space
consider all comments received by the Transmissions (AOT). S.A. AOTs, as applicable:
closing date and may amend this • Airbus Defense and Space S.A. • AOT–CN235–55–0001, dated
proposed AD based on those comments. AOT AOT–CN235–55–0001, Revision 2, December 16, 2014, or
We will post all comments we dated March 10, 2015. The service • AOT–C295–55–0001, dated
receive, without change, to http:// information describes procedures for a December 16, 2014.
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![Federal Register / Vol. 82, No. 3 / Thursday, January 5, 2017 / Proposed Rules 1271
This proposed AD does not give credit AOT AOT–CN235–55–0001, and AOT ‘‘Credit for Previous Actions,’’ of this
for accomplishing those initial issues of AOT–C295–55–0001. proposed AD shows the correct date.
the service information because the Also, the MCAI identifies a date for Costs of Compliance
inspection requirements are different Revision 1 of Airbus Defense and Space
from the initial issues of the service We estimate that this proposed AD
S.A. AOT AOT–C295–55–0001, which
information in both Revision 1 and affects 14 airplanes of U.S. registry.
was corrected by Revision 2 of the same We estimate the following costs to
Revision 2 of Airbus Defense and Space service information. Paragraph (m), comply with this proposed AD:
ESTIMATED COSTS
Parts
Action Labor cost Cost per product Cost on U.S. operators
cost
Inspection ................. 2 work-hours × $85 per hour = $0 $170 per inspection cycle .............. $2,380 per inspection cycle.
$170 per inspection cycle.
We estimate the following costs to do required based on the results of the determining the number of airplanes
any necessary repairs that would be proposed inspection. We have no way of that might need this repair:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair ......................................................... 45 work-hours × $85 per hour = $3,825 ................................................. $10,000 $13,825
Authority for This Rulemaking 2. Is not a ‘‘significant rule’’ under the (b) Affected ADs
Title 49 of the United States Code DOT Regulatory Policies and Procedures None.
specifies the FAA’s authority to issue (44 FR 11034, February 26, 1979);
(c) Applicability
rules on aviation safety. Subtitle I, 3. Will not affect intrastate aviation in
Alaska; and This AD applies to Airbus Defense and
section 106, describes the authority of Space S.A. (formerly known as
the FAA Administrator. ‘‘Subtitle VII: 4. Will not have a significant Construcciones Aeronauticas, S.A.) Model
Aviation Programs,’’ describes in more economic impact, positive or negative, CN–235, CN–235–100, CN–235–200, CN–
detail the scope of the Agency’s on a substantial number of small entities 235–300, and C–295 airplanes, certificated in
authority. under the criteria of the Regulatory any category, all manufacturer serial
We are issuing this rulemaking under Flexibility Act. numbers.
the authority described in ‘‘Subtitle VII, List of Subjects in 14 CFR Part 39 (d) Subject
Part A, Subpart III, Section 44701: Air Transport Association (ATA) of
General requirements.’’ Under that Air transportation, Aircraft, Aviation
America Code 55, Stabilizers.
section, Congress charges the FAA with safety, Incorporation by reference,
promoting safe flight of civil aircraft in Safety. (e) Reason
air commerce by prescribing regulations The Proposed Amendment This AD was prompted by reports of
for practices, methods, and procedures excessive play between bushings and their
the Administrator finds necessary for Accordingly, under the authority respective fitting housings at certain elevator
delegated to me by the Administrator, fittings. We are issuing this AD to prevent
safety in air commerce. This regulation excessive play between bushings and their
is within the scope of that authority the FAA proposes to amend 14 CFR part
39 as follows: respective fitting housings, which could lead
because it addresses an unsafe condition to failure or detachment of any of the affected
that is likely to exist or develop on PART 39—AIRWORTHINESS structural parts, with a possible result of
products identified in this rulemaking DIRECTIVES reduced control of the airplane.
action. (f) Compliance
Regulatory Findings ■ 1. The authority citation for part 39 Comply with this AD within the
continues to read as follows: compliance times specified, unless already
We determined that this proposed AD
Authority: 49 U.S.C. 106(g), 40113, 44701. done.
would not have federalism implications
under Executive Order 13132. This § 39.13 [Amended] (g) One-Time Detailed Visual Inspection
proposed AD would not have a Before exceeding 600 flight hours since
■ 2. The FAA amends § 39.13 by adding
substantial direct effect on the States, on first flight of the airplane, or within 300 flight
the following new airworthiness hours after the effective date of this AD,
the relationship between the national
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directive (AD): whichever occurs later, but not before
Government and the States, or on the
distribution of power and Airbus Defense and Space S.A. (Formerly exceeding 300 flight hours since first flight of
responsibilities among the various Known as Construcciones Aeronauticas, the airplane: Do a detailed visual inspection
S.A.): Docket No. FAA–2016–9521; of the elevator hinge fitting and bracket
levels of government. assembly to detect excessive play between
Directorate Identifier 2016–NM–061–AD.
For the reasons discussed above, I bushings and their respective fitting
certify this proposed regulation: (a) Comments Due Date housings, and to detect cracks, in accordance
1. Is not a ‘‘significant regulatory We must receive comments by February with the instructions of Airbus Defense and
action’’ under Executive Order 12866; 21, 2017. Space S.A. Alert Operators Transmission
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![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 Compliance time for repetitive eddy
C–295 model/version Manufacturer’s Serial Number (MSN) (part no.) current inspections
C–295M/FI01, FI02 ............................ MSN031 through MSN999 inclusive .. 95–31193–0503 Before exceeding 1,000 flight cycles
95–31193–0504 since the most recent inspection;
or before exceeding 1,000 flight
hours since the most recent in-
spection; whichever occurs first.
C–295M/PG01 .................................... MSN031 through MSN999 inclusive .. 95–31193–0503 Before exceeding 1,000 flight cycles
95–31193–0504 since the most recent inspection;
or before exceeding 1,400 flight
hours since the most recent in-
spection; whichever occurs first.
C–295M/PG02, PG03 ........................ MSN031 through MSN999 inclusive .. 95–31193–0503 Before exceeding 1,000 flight cycles
95–31193–0504 since the most recent inspection;
or before exceeding 1,900 flight
hours since the most recent in-
spection; whichever occurs first.
C–295M/CH01 .................................... MSN031 through MSN999 inclusive .. 95–31193–0503 Before exceeding 1,000 flight cycles
95–31193–0504 since the most recent inspection;
or before exceeding 1,200 flight
hours since the most recent in-
spection; whichever occurs first.
C–295M/CH02, OM03 ........................ MSN031 through MSN999 inclusive .. 95–31193–0503 Before exceeding 1,000 flight cycles
95–31193–0504 since the most recent inspection;
or before exceeding 1,500 flight
hours since the most recent in-
spection; whichever occurs first.
C–295MW ........................................... MSN031 through MSN999 inclusive .. 95–31193–0503 Before exceeding 1,000 flight cycles
95–31193–0504 since the most recent inspection;
or before exceeding 1,400 flight
hours since the most recent in-
spection; whichever occurs first.
(k) Corrective Action for Discrepancies if those actions were performed before the by the Manager, International Branch, ANM–
Found During Eddy Current Inspection effective date of this AD using Airbus 116, Transport Airplane Directorate, FAA; or
If, during any inspection required by Defense and Space S.A. AOT AOT–CN235– EASA; or Airbus Defense and Space S.A.’s
paragraph (i)(1), (i)(2), (j)(1), or (j)(2) of this 55–0001, Revision 1, dated March 6, 2015; or EASA DOA. If approved by the DOA, the
AD, any crack is detected, as defined in AOT AOT–C295–55–0001, Revision 1, dated approval must include the DOA-authorized
Airbus Defense and Space S.A. AOT AOT– May 29, 2014.
signature.
CN235–55–0003, dated December 22, 2015; (n) Other FAA AD Provisions
or AOT AOT–C295–55–0003, dated (o) Related Information
December 22, 2015; as applicable: Before The following provisions also apply to this
AD: (1) Refer to Mandatory Continuing
further flight, accomplish applicable Airworthiness Information (MCAI) EASA AD
corrective actions in accordance with the (1) Alternative Methods of Compliance
(AMOCs): The Manager, International 2016–0075, dated April 19, 2016, for related
instructions of Airbus Defense and Space
S.A. AOT AOT–CN235–55–0003, dated Branch, ANM–116, Transport Airplane information. This MCAI may be found in the
December 22, 2015; or AOT AOT–C295–55– Directorate, FAA, has the authority to AD docket on the Internet at http://
0003, dated December 22, 2015; as approve AMOCs for this AD, if requested www.regulations.gov by searching for and
applicable. Where Airbus Defense and Space using the procedures found in 14 CFR 39.19. locating Docket No. FAA–2016–9521.
S.A. AOT AOT–CN235–55–0003, dated In accordance with 14 CFR 39.19, send your (2) For service information identified in
December 22, 2015; or AOT AOT–C295–55– request to your principal inspector or local this AD, contact Airbus Defense and Space,
0003, dated December 22, 2015; specifies to Flight Standards District Office, as
Services/Engineering Support, Avenida de
contact Airbus Defense and Space S.A. for appropriate. If sending information directly
Aragón 404, 28022 Madrid, Spain; fax +34 91
corrective actions, before further flight, to the International Branch, send it to ATTN:
Shahram Daneshmandi, Aerospace Engineer, 585 31 27; email MTA.TechnicalService@
accomplish corrective actions in accordance
International Branch, ANM–116, Transport airbus.com. You may view this service
with the procedures specified in paragraph
(n)(2) of this AD. Airplane Directorate, FAA, 1601 Lind information at the FAA, Transport Airplane
Avenue SW., Renton, WA 98057–3356; Directorate, 1601 Lind Avenue SW., Renton,
(l) Provision Regarding Terminating Action telephone: 425–227–1112; fax: 425–227– WA. For information on the availability of
Accomplishing corrective actions, as 1149. Information may be emailed to: 9- this material at the FAA, call 425–227–1221.
required by paragraph (k) of this AD, does ANM-116-AMOC-REQUESTS@faa.gov.
mstockstill on DSK3G9T082PROD with PROPOSALS
Before using any approved AMOC, notify Issued in Renton, Washington, on
not constitute terminating action for the
repetitive inspections required by paragraphs your appropriate principal inspector, or December 16, 2016.
(i)(2) and (j)(2) of this AD, unless explicitly lacking a principal inspector, the manager of Ross Landes,
stated in the approved method of compliance the local flight standards district office/ Acting Manager, Transport Airplane
for the corrective action. certificate holding district office. Directorate, Aircraft Certification Service.
(2) Contacting the Manufacturer: For any
(m) Credit for Previous Actions requirement in this AD to obtain corrective [FR Doc. 2016–31365 Filed 1–4–17; 8:45 am]
This paragraph provides credit for the actions from a manufacturer, the action must BILLING CODE 4910–13–P
actions required by paragraph (g) of this AD, be accomplished using a method approved
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Document Created: 2018-02-01 14:51:23
Document Modified: 2018-02-01 14:51:23
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by February 21, 2017. | |
| 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. | |
| FR Citation | 82 FR 1269 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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