Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.), 2783-2785 [2016-00377]

Download as PDF Federal Register / Vol. 81, No. 11 / Tuesday, January 19, 2016 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–8465; Directorate Identifier 2014–NM–239–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2001–12– 18, for certain CASA Model CN–235 series airplanes. AD 2001–12–18 currently requires modification of the rigging of the engine control cable assembly and replacement of either the entire engine control cable assembly or a segment of the control cables. Since we issued AD 2001–12–18, we have received reports of new occurrences of cable disruption on a certain part number; the disruption is caused by microcracks along the cable surface. This proposed AD would retain the requirements of AD 2001–12–18. This proposed AD would also require repetitive replacements of each power lever and condition lever Teleflex cable with a new or serviceable part and would remove airplanes from the applicability. We are proposing this AD to prevent fatigue of the engine control cables, leading to breakage of the cables, which could result in reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by March 4, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed rule, contact EADS– CASA, Military Transport Aircraft asabaliauskas on DSK5VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 15:55 Jan 15, 2016 Jkt 238001 Division (MTAD), Integrated Customer Services (ICS), Technical Services, ´ Avenida de Aragon 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 55 05; email MTA.TechnicalService@casa.eads.net; Internet http://www.eads.net. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 8465; 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–2015–8465; Directorate Identifier 2014–NM–239–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 On June 11, 2001, we issued AD 2001–12–18, Amendment 39–12274 (66 FR 33014, June 20, 2001). AD 2001–12– 18 requires actions intended to address PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 2783 an unsafe condition on certain CASA Model CN–235 series airplanes. Since we issued AD 2001–12–18, Amendment 39–12274 (66 FR 33014, June 20, 2001), we have received reports of new occurrences of cable disruption on part number (P/N) 72830–20; the disruption is caused by microcracks along the cable surface. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0262, dated December 5, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Defense and Space S.A. Model CN–235– 100 and –200 airplanes. The MCAI states: Three occurrences of cable disruption were reported in 1999. The failed parts, having a part number (P/N) 7–44728–20, were part of the engine control system assembly P/N 7– 44728–12. Two cables were connected to the Power Lever and one cable to the Condition Lever control. Service records of the affected parts showed that each cable accumulated more than 14,000 flight cycles (FC). The subsequent investigation determined that the disruption was attributed to fatigue related crack. This condition, if not corrected, could lead to failure of the engine control system resulting in a loss of the affected engine control. Prompted by this unsafe condition, DGAC ´ ´ [Direccion General de Aviacion Civil] Spain issued AD 03/00 [which corresponds to FAA AD 2001–12–18, Amendment 39–12274 (66 FR 33014, June 20, 2001] to require rigging of the throttle stops, and one-time replacement of the affected engine control cable assembly (P/N 7–44728–12), or the affected cable (P/N 7–44728–20) before exceeding 12,000 FC. After that [DGAC Spain] AD was issued, a new occurrence of cable (P/N 72830–20) disruption was reported. In that case, the affected cable was part of the Condition Lever control and had accumulated 8,497 flight hours (FH) and 8,858 FC. Fractographic analysis of the affected cable identified that the fatigue nucleation seemed to have been induced by microcracks along the cable surface. Additionally, another case of control cable (P/N 72830–20) failure was reported, where the affected part accumulated 9,936 FH and 10,552 FC and was part of the Power Lever control. Investigation of the latter case identified again a fatigue nucleation to be the cause of the cable failure. To address this potentially unsafe condition, Airbus Military issued Alert Operators Transmission (AOT) AOT–CN235– 76–0001 to provide a repetitive replacement interval and instructions. For the reasons described above, this [EASA] AD retains the requirements of DGAC Spain AD No. 03/00, which is superseded, but requires repetitive replacement [at reduced thresholds] of the affected Teleflex cables. E:\FR\FM\19JAP1.SGM 19JAP1 2784 Federal Register / Vol. 81, No. 11 / Tuesday, January 19, 2016 / Proposed Rules Costs of Compliance 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–2015– 8465. Related Service Information Under 1 CFR Part 51 Airbus Defense and Space S.A. has issued Airbus Military Alert Operators Transmission, dated May 27, 2014. The service information describes repetitive replacements of each power lever and condition lever Teleflex cable with a new or serviceable part. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Differences Between This Proposed AD and the MCAI or Service Information EASA Airworthiness Directive 2014– 0262, dated December 5, 2014, specifies an applicability for Airbus Defense and Space S.A. Model CN–235–100 and –200 airplanes, serial numbers C–016 through C–073. This AD specifies an applicability for Model CN–235 airplanes, serial numbers C–001 through C–015 inclusive and serial number C– 074; and Model CN–235–100 and –200 airplanes, serial numbers C–016 through C–073 inclusive. The retained one-time action in paragraph (g) of this proposed AD is also applicable to Model CN–235 airplanes, serial numbers C–001 through C–015 inclusive and serial number C– 074, which are missing from EASA AD 2014–0262, dated December 5, 2014. We understand EASA considered Model CN–235 airplanes with these serial numbers that have already performed this one-time action. For this reason, Model CN–235 airplanes, serial numbers C–001 through C–015 inclusive and serial number C–074 are added to this proposed AD. This issue has been coordinated with EASA. VerDate Sep<11>2014 15:55 Jan 15, 2016 Jkt 238001 We estimate that this proposed AD affects 3 airplanes of U.S. registry. The rigging required by AD 2001–12– 18, Amendment 39–12274 (66 FR 33014, June 20, 2001), and retained in this proposed AD takes about 8 workhours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the rigging required by AD 2001–12–18 is $680 per product. The replacement required by AD 2001–12–18, Amendment 39–12274 (66 FR 33014, June 20, 2001), and retained in this proposed AD takes about 47 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $1,444 per product. Based on these figures, the estimated cost of the replacement required by AD 2001–12–18 is $5,439 per product. We also estimate that it would take about 47 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $6,480 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $31,425, or $10,475 per product. 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 PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 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 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) 2001–12–18, Amendment 39–12274 (66 FR 33014, June 20, 2001) and adding the following new AD: ■ Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.): Docket No. FAA–2015–8465; Directorate Identifier 2014–NM–239–AD. (a) Comments Due Date We must receive comments by March 4, 2016. (b) Affected ADs This AD replaces AD 2001–12–18, Amendment 39–12274 (66 FR 33014, June 20, 2001). (c) Applicability This AD applies to Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Model CN–235 airplanes, serial numbers C–001 through C–015, inclusive and serial number C–074; and Model CN–235–100 and –200 airplanes, serial numbers C–001 through C– 074, inclusive; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 76, Engine Controls. (e) Reason This AD was prompted by reports of new occurrences of cable disruption on a certain E:\FR\FM\19JAP1.SGM 19JAP1 Federal Register / Vol. 81, No. 11 / Tuesday, January 19, 2016 / Proposed Rules part number; the disruption is caused by microcracks along the cable surface. We are issuing this AD to prevent fatigue of the engine control cables, leading to breakage of the cables, which could result in reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Action for the Power Lever and Condition Lever Control Stops, With No Changes This paragraph restates the requirements of paragraph (a) of AD 2001–12–18, Amendment 39–12274 (66 FR 33014, June 20, 2001). Within 15 days after July 25, 2001 (the effective date of AD 2001–12–18): Rig the power lever and condition lever control stops, in accordance with CASA COM 235– 140, Revision 01, dated March 21, 2000. 2785 (h) New Requirement of This AD: Replacement At the applicable compliance times specified in table 1 to paragraph (h) of this AD: Replace each power lever and condition lever Teleflex cable having part number (P/ N) 72830–20 with a new or serviceable part, in accordance with Airbus Military Alert Operators Transmission AOT–CN235–76– 0001, dated May 27, 2014. Repeat the replacement thereafter at intervals not to exceed an accumulation of 5,000 total flight cycles on each Teleflex cable having P/N 72830–20. TABLE 1 TO PARAGRAPH (h) OF THIS AD—REPLACEMENT COMPLIANCE TIME Total flight cycles accumulated on the Teleflex cable having P/N 72830–20 (since first installation on an airplane) as of the effective date of this AD Fewer than 4,700 total flight cycles ......................................................... 4,700 or more, but fewer than 6,000 total flight cycles ........................... Equal to or more than 6,000 total flight cycles but fewer than 7,000 total flight cycles. Equal to or more than 7,000 total flight cycles ........................................ asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (i) Parts Installation Limitations As of the effective date of this AD, no person may install, on any airplane, a Teleflex cable having P/N 72830–20, unless the cable has accumulated fewer than 5,000 total flight cycles since its first installation on an airplane. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1112; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or EADS CASA’s EASA Design Organization Approval (DOA). If approved by VerDate Sep<11>2014 15:55 Jan 15, 2016 Jkt 238001 Compliance time Before accumulating 5,000 total flight cycles. Within 300 flight cycles or 12 months after the effective date of this AD, whichever occurs first. Within 200 flight cycles or 6 months after the effective date of this AD, whichever occurs first. Within 100 flight cycles or 3 months after the effective date of this AD, whichever occurs first. the DOA, the approval must include the DOA-authorized signature. Federal Aviation Administration (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0262, dated December 5, 2014, 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–2015–8465. (2) For service information identified in this AD, contact EADS–CASA, Military Transport Aircraft Division (MTAD), Integrated Customer Services (ICS), ´ Technical Services, Avenida de Aragon 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 55 05; email MTA.TechnicalService@casa.eads.net; Internet http://www.eads.net. 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 31, 2015. Phil Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–00377 Filed 1–15–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00024 Fmt 4702 DEPARTMENT OF TRANSPORTATION Sfmt 4702 14 CFR Part 39 [Docket No. FAA–2015–8464; Directorate Identifier 2015–NM–050–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Bombardier, Inc. Model DHC–8–400 series airplanes. This proposed AD was prompted by a revision by the manufacturer to the Certification Maintenance Requirements (CMR) of the Airworthiness Limitation Items (ALI), in the Maintenance Requirement Manual (MRM), that introduces a new CMR task that requires repetitive operational checks of the propeller overspeed governor. This proposed AD would require revising the airplane maintenance program or inspection program, as applicable, to incorporate a new CMR task. We are proposing this AD to prevent dormant failure of the propeller overspeed governor, which may lead to a loss of propeller overspeed protection and result in high propeller drag in-flight. DATES: We must receive comments on this proposed AD by March 4, 2016. SUMMARY: E:\FR\FM\19JAP1.SGM 19JAP1

Agencies

[Federal Register Volume 81, Number 11 (Tuesday, January 19, 2016)]
[Proposed Rules]
[Pages 2783-2785]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00377]



[[Page 2783]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8465; Directorate Identifier 2014-NM-239-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2001-12-
18, for certain CASA Model CN-235 series airplanes. AD 2001-12-18 
currently requires modification of the rigging of the engine control 
cable assembly and replacement of either the entire engine control 
cable assembly or a segment of the control cables. Since we issued AD 
2001-12-18, we have received reports of new occurrences of cable 
disruption on a certain part number; the disruption is caused by 
microcracks along the cable surface. This proposed AD would retain the 
requirements of AD 2001-12-18. This proposed AD would also require 
repetitive replacements of each power lever and condition lever 
Teleflex cable with a new or serviceable part and would remove 
airplanes from the applicability. We are proposing this AD to prevent 
fatigue of the engine control cables, leading to breakage of the 
cables, which could result in reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by March 4, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed rule, contact 
EADS-CASA, Military Transport Aircraft Division (MTAD), Integrated 
Customer Services (ICS), Technical Services, Avenida de Arag[oacute]n 
404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 55 
05; email MTA.TechnicalService@casa.eads.net; Internet http://www.eads.net. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8465; 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-2015-8465; 
Directorate Identifier 2014-NM-239-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

    On June 11, 2001, we issued AD 2001-12-18, Amendment 39-12274 (66 
FR 33014, June 20, 2001). AD 2001-12-18 requires actions intended to 
address an unsafe condition on certain CASA Model CN-235 series 
airplanes.
    Since we issued AD 2001-12-18, Amendment 39-12274 (66 FR 33014, 
June 20, 2001), we have received reports of new occurrences of cable 
disruption on part number (P/N) 72830-20; the disruption is caused by 
microcracks along the cable surface.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0262, dated December 5, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus 
Defense and Space S.A. Model CN-235-100 and -200 airplanes. The MCAI 
states:

    Three occurrences of cable disruption were reported in 1999. The 
failed parts, having a part number (P/N) 7-44728-20, were part of 
the engine control system assembly P/N 7-44728-12. Two cables were 
connected to the Power Lever and one cable to the Condition Lever 
control. Service records of the affected parts showed that each 
cable accumulated more than 14,000 flight cycles (FC).
    The subsequent investigation determined that the disruption was 
attributed to fatigue related crack.
    This condition, if not corrected, could lead to failure of the 
engine control system resulting in a loss of the affected engine 
control.
    Prompted by this unsafe condition, DGAC [Direcci[oacute]n 
General de Aviaci[oacute]n Civil] Spain issued AD 03/00 [which 
corresponds to FAA AD 2001-12-18, Amendment 39-12274 (66 FR 33014, 
June 20, 2001] to require rigging of the throttle stops, and one-
time replacement of the affected engine control cable assembly (P/N 
7-44728-12), or the affected cable (P/N 7-44728-20) before exceeding 
12,000 FC.
    After that [DGAC Spain] AD was issued, a new occurrence of cable 
(P/N 72830-20) disruption was reported. In that case, the affected 
cable was part of the Condition Lever control and had accumulated 
8,497 flight hours (FH) and 8,858 FC. Fractographic analysis of the 
affected cable identified that the fatigue nucleation seemed to have 
been induced by microcracks along the cable surface. Additionally, 
another case of control cable (P/N 72830-20) failure was reported, 
where the affected part accumulated 9,936 FH and 10,552 FC and was 
part of the Power Lever control. Investigation of the latter case 
identified again a fatigue nucleation to be the cause of the cable 
failure.
    To address this potentially unsafe condition, Airbus Military 
issued Alert Operators Transmission (AOT) AOT-CN235-76-0001 to 
provide a repetitive replacement interval and instructions.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC Spain AD No. 03/00, which is superseded, but 
requires repetitive replacement [at reduced thresholds] of the 
affected Teleflex cables.


[[Page 2784]]


    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-2015-
8465.

Related Service Information Under 1 CFR Part 51

    Airbus Defense and Space S.A. has issued Airbus Military Alert 
Operators Transmission, dated May 27, 2014. The service information 
describes repetitive replacements of each power lever and condition 
lever Teleflex cable with a new or serviceable part. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This Proposed AD and the MCAI or Service 
Information

    EASA Airworthiness Directive 2014-0262, dated December 5, 2014, 
specifies an applicability for Airbus Defense and Space S.A. Model CN-
235-100 and -200 airplanes, serial numbers C-016 through C-073. This AD 
specifies an applicability for Model CN-235 airplanes, serial numbers 
C-001 through C-015 inclusive and serial number C-074; and Model CN-
235-100 and -200 airplanes, serial numbers C-016 through C-073 
inclusive. The retained one-time action in paragraph (g) of this 
proposed AD is also applicable to Model CN-235 airplanes, serial 
numbers C-001 through C-015 inclusive and serial number C-074, which 
are missing from EASA AD 2014-0262, dated December 5, 2014. We 
understand EASA considered Model CN-235 airplanes with these serial 
numbers that have already performed this one-time action. For this 
reason, Model CN-235 airplanes, serial numbers C-001 through C-015 
inclusive and serial number C-074 are added to this proposed AD. This 
issue has been coordinated with EASA.

Costs of Compliance

    We estimate that this proposed AD affects 3 airplanes of U.S. 
registry.
    The rigging required by AD 2001-12-18, Amendment 39-12274 (66 FR 
33014, June 20, 2001), and retained in this proposed AD takes about 8 
work-hours per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the rigging required by 
AD 2001-12-18 is $680 per product.
    The replacement required by AD 2001-12-18, Amendment 39-12274 (66 
FR 33014, June 20, 2001), and retained in this proposed AD takes about 
47 work-hours per product, at an average labor rate of $85 per work-
hour. Required parts cost about $1,444 per product. Based on these 
figures, the estimated cost of the replacement required by AD 2001-12-
18 is $5,439 per product.
    We also estimate that it would take about 47 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $6,480 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $31,425, or $10,475 per product.

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 removing Airworthiness Directive (AD) 
2001-12-18, Amendment 39-12274 (66 FR 33014, June 20, 2001) and adding 
the following new AD:

Airbus Defense and Space S.A. (Formerly Known as Construcciones 
Aeronauticas, S.A.): Docket No. FAA-2015-8465; Directorate 
Identifier 2014-NM-239-AD.

(a) Comments Due Date

    We must receive comments by March 4, 2016.

(b) Affected ADs

    This AD replaces AD 2001-12-18, Amendment 39-12274 (66 FR 33014, 
June 20, 2001).

(c) Applicability

    This AD applies to Airbus Defense and Space S.A. (Formerly Known 
as Construcciones Aeronauticas, S.A.) Model CN-235 airplanes, serial 
numbers C-001 through C-015, inclusive and serial number C-074; and 
Model CN-235-100 and -200 airplanes, serial numbers C-001 through C-
074, inclusive; certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 76, Engine 
Controls.

(e) Reason

    This AD was prompted by reports of new occurrences of cable 
disruption on a certain

[[Page 2785]]

part number; the disruption is caused by microcracks along the cable 
surface. We are issuing this AD to prevent fatigue of the engine 
control cables, leading to breakage of the cables, which could 
result in reduced controllability of the airplane.

(f) Compliance

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

(g) Retained Action for the Power Lever and Condition Lever Control 
Stops, With No Changes

    This paragraph restates the requirements of paragraph (a) of AD 
2001-12-18, Amendment 39-12274 (66 FR 33014, June 20, 2001). Within 
15 days after July 25, 2001 (the effective date of AD 2001-12-18): 
Rig the power lever and condition lever control stops, in accordance 
with CASA COM 235-140, Revision 01, dated March 21, 2000.

(h) New Requirement of This AD: Replacement

    At the applicable compliance times specified in table 1 to 
paragraph (h) of this AD: Replace each power lever and condition 
lever Teleflex cable having part number (P/N) 72830-20 with a new or 
serviceable part, in accordance with Airbus Military Alert Operators 
Transmission AOT-CN235-76-0001, dated May 27, 2014. Repeat the 
replacement thereafter at intervals not to exceed an accumulation of 
5,000 total flight cycles on each Teleflex cable having P/N 72830-
20.

    Table 1 to Paragraph (h) of This AD--Replacement Compliance Time
------------------------------------------------------------------------
 Total flight cycles accumulated on the
   Teleflex cable having P/N 72830-20
    (since first installation on an              Compliance time
 airplane) as of the effective date of
                this AD
------------------------------------------------------------------------
Fewer than 4,700 total flight cycles...  Before accumulating 5,000 total
                                          flight cycles.
4,700 or more, but fewer than 6,000      Within 300 flight cycles or 12
 total flight cycles.                     months after the effective
                                          date of this AD, whichever
                                          occurs first.
Equal to or more than 6,000 total        Within 200 flight cycles or 6
 flight cycles but fewer than 7,000       months after the effective
 total flight cycles.                     date of this AD, whichever
                                          occurs first.
Equal to or more than 7,000 total        Within 100 flight cycles or 3
 flight cycles.                           months after the effective
                                          date of this AD, whichever
                                          occurs first.
------------------------------------------------------------------------

(i) Parts Installation Limitations

    As of the effective date of this AD, no person may install, on 
any airplane, a Teleflex cable having P/N 72830-20, unless the cable 
has accumulated fewer than 5,000 total flight cycles since its first 
installation on an airplane.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Shahram 
Daneshmandi, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1112; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or EADS CASA's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0262, dated December 5, 
2014, 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-2015-8465.
    (2) For service information identified in this AD, contact EADS-
CASA, Military Transport Aircraft Division (MTAD), Integrated 
Customer Services (ICS), Technical Services, Avenida de 
Arag[oacute]n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; 
fax +34 91 585 55 05; email MTA.TechnicalService@casa.eads.net; 
Internet http://www.eads.net. 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 31, 2015.
Phil Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-00377 Filed 1-15-16; 8:45 am]
BILLING CODE 4910-13-P