81 FR 2783 - Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.)
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 11 (January 19, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 11 (January 19, 2016)
| Page Range | 2783-2785 | |
| FR Document | 2016-00377 |
[Federal Register Volume 81, Number 11 (Tuesday, January 19, 2016)] [Proposed Rules] [Pages 2783-2785] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-00377] [[Page 2783]] ======================================================================= ----------------------------------------------------------------------- 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). ----------------------------------------------------------------------- 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 [email protected]; 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: [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. 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 [email protected]; 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
![Federal Register / Vol. 81, No. 11 / Tuesday, January 19, 2016 / Proposed Rules 2783
DEPARTMENT OF TRANSPORTATION Division (MTAD), Integrated Customer an unsafe condition on certain CASA
Services (ICS), Technical Services, Model CN–235 series airplanes.
Federal Aviation Administration Avenida de Aragón 404, 28022 Madrid, Since we issued AD 2001–12–18,
Spain; telephone +34 91 585 55 84; fax Amendment 39–12274 (66 FR 33014,
14 CFR Part 39 +34 91 585 55 05; email June 20, 2001), we have received reports
[Docket No. FAA–2015–8465; Directorate MTA.TechnicalService@casa.eads.net; of new occurrences of cable disruption
Identifier 2014–NM–239–AD] Internet http://www.eads.net. You may on part number (P/N) 72830–20; the
view this referenced service information disruption is caused by microcracks
RIN 2120–AA64 at the FAA, Transport Airplane along the cable surface.
Directorate, 1601 Lind Avenue SW., The European Aviation Safety Agency
Airworthiness Directives; Airbus (EASA), which is the Technical Agent
Renton, WA. For information on the
Defense and Space S.A. (Formerly for the Member States of the European
availability of this material at the FAA,
Known as Construcciones Union, has issued EASA Airworthiness
call 425–227–1221.
Aeronauticas, S.A.) Directive 2014–0262, dated December 5,
Examining the AD Docket 2014 (referred to after this as the
AGENCY: Federal Aviation
Administration (FAA), DOT. You may examine the AD docket on Mandatory Continuing Airworthiness
ACTION: Notice of proposed rulemaking the Internet at http:// Information, or ‘‘the MCAI’’), to correct
(NPRM). www.regulations.gov by searching for an unsafe condition for certain Airbus
and locating Docket No. FAA–2015– Defense and Space S.A. Model CN–235–
SUMMARY: We propose to supersede 8465; or in person at the Docket 100 and –200 airplanes. The MCAI
Airworthiness Directive (AD) 2001–12– Management Facility between 9 a.m. states:
18, for certain CASA Model CN–235 and 5 p.m., Monday through Friday, Three occurrences of cable disruption were
series airplanes. AD 2001–12–18 except Federal holidays. The AD docket reported in 1999. The failed parts, having a
currently requires modification of the contains this proposed AD, the part number (P/N) 7–44728–20, were part of
rigging of the engine control cable regulatory evaluation, any comments the engine control system assembly P/N 7–
assembly and replacement of either the received, and other information. The 44728–12. Two cables were connected to the
street address for the Docket Operations Power Lever and one cable to the Condition
entire engine control cable assembly or
Lever control. Service records of the affected
a segment of the control cables. Since office (telephone 800–647–5527) is in parts showed that each cable accumulated
we issued AD 2001–12–18, we have the ADDRESSES section. Comments will more than 14,000 flight cycles (FC).
received reports of new occurrences of be available in the AD docket shortly The subsequent investigation determined
cable disruption on a certain part after receipt. that the disruption was attributed to fatigue
number; the disruption is caused by FOR FURTHER INFORMATION CONTACT: related crack.
microcracks along the cable surface. This condition, if not corrected, could lead
Shahram Daneshmandi, Aerospace to failure of the engine control system
This proposed AD would retain the Engineer, International Branch, ANM– resulting in a loss of the affected engine
requirements of AD 2001–12–18. This 116, Transport Airplane Directorate, control.
proposed AD would also require FAA, 1601 Lind Avenue SW., Renton, Prompted by this unsafe condition, DGAC
repetitive replacements of each power WA 98057–3356; telephone 425–227– [Dirección General de Aviación Civil] Spain
lever and condition lever Teleflex cable 1112; fax 425–227–1149. issued AD 03/00 [which corresponds to FAA
with a new or serviceable part and AD 2001–12–18, Amendment 39–12274 (66
SUPPLEMENTARY INFORMATION: FR 33014, June 20, 2001] to require rigging
would remove airplanes from the
applicability. We are proposing this AD Comments Invited of the throttle stops, and one-time
replacement of the affected engine control
to prevent fatigue of the engine control We invite you to send any written cable assembly (P/N 7–44728–12), or the
cables, leading to breakage of the cables, relevant data, views, or arguments about affected cable (P/N 7–44728–20) before
which could result in reduced this proposed AD. Send your comments exceeding 12,000 FC.
controllability of the airplane. to an address listed under the After that [DGAC Spain] AD was issued, a
DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No. new occurrence of cable (P/N 72830–20)
this proposed AD by March 4, 2016. disruption was reported. In that case, the
FAA–2015–8465; Directorate Identifier affected cable was part of the Condition
ADDRESSES: You may send comments by 2014–NM–239–AD’’ at the beginning of Lever control and had accumulated 8,497
any of the following methods: your comments. We specifically invite flight hours (FH) and 8,858 FC. Fractographic
• Federal eRulemaking Portal: Go to comments on the overall regulatory, analysis of the affected cable identified that
http://www.regulations.gov. Follow the economic, environmental, and energy the fatigue nucleation seemed to have been
instructions for submitting comments. aspects of this proposed AD. We will induced by microcracks along the cable
• Fax: 202–493–2251. consider all comments received by the surface. Additionally, another case of control
• Mail: U.S. Department of closing date and may amend this cable (P/N 72830–20) failure was reported,
Transportation, Docket Operations, M– where the affected part accumulated 9,936
proposed AD based on those comments.
FH and 10,552 FC and was part of the Power
30, West Building Ground Floor, Room We will post all comments we Lever control. Investigation of the latter case
W12–140, 1200 New Jersey Avenue SE., receive, without change, to http:// identified again a fatigue nucleation to be the
Washington, DC 20590. www.regulations.gov, including any cause of the cable failure.
• Hand Delivery: U.S. Department of personal information you provide. We To address this potentially unsafe
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Transportation, Docket Operations, M– will also post a report summarizing each condition, Airbus Military issued Alert
30, West Building Ground Floor, Room substantive verbal contact we receive Operators Transmission (AOT) AOT–CN235–
W12–140, 1200 New Jersey Avenue SE., about this proposed AD. 76–0001 to provide a repetitive replacement
Washington, DC, between 9 a.m. and 5 interval and instructions.
p.m., Monday through Friday, except Discussion For the reasons described above, this
[EASA] AD retains the requirements of DGAC
Federal holidays. On June 11, 2001, we issued AD Spain AD No. 03/00, which is superseded,
For service information identified in 2001–12–18, Amendment 39–12274 (66 but requires repetitive replacement [at
this proposed rule, contact EADS– FR 33014, June 20, 2001). AD 2001–12– reduced thresholds] of the affected Teleflex
CASA, Military Transport Aircraft 18 requires actions intended to address cables.
VerDate Sep<11>2014 15:55 Jan 15, 2016 Jkt 238001 PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 E:\FR\FM\19JAP1.SGM 19JAP1](https://thefederalregister.org/doc/81_FR_2794/page/1.svg)
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You may examine the MCAI in the Costs of Compliance responsibilities among the various
AD docket on the Internet at http:// We estimate that this proposed AD levels of government.
www.regulations.gov by searching for affects 3 airplanes of U.S. registry. For the reasons discussed above, I
and locating Docket No. FAA–2015– The rigging required by AD 2001–12– certify this proposed regulation:
8465. 18, Amendment 39–12274 (66 FR 1. Is not a ‘‘significant regulatory
33014, June 20, 2001), and retained in action’’ under Executive Order 12866;
Related Service Information Under 1 2. Is not a ‘‘significant rule’’ under the
CFR Part 51 this proposed AD takes about 8 work-
hours per product, at an average labor DOT Regulatory Policies and Procedures
Airbus Defense and Space S.A. has rate of $85 per work-hour. Based on (44 FR 11034, February 26, 1979);
issued Airbus Military Alert Operators 3. Will not affect intrastate aviation in
these figures, the estimated cost of the
Transmission, dated May 27, 2014. The Alaska; and
rigging required by AD 2001–12–18 is
service information describes repetitive 4. Will not have a significant
$680 per product.
economic impact, positive or negative,
replacements of each power lever and The replacement required by AD
on a substantial number of small entities
condition lever Teleflex cable with a 2001–12–18, Amendment 39–12274 (66
under the criteria of the Regulatory
new or serviceable part. This service FR 33014, June 20, 2001), and retained
Flexibility Act.
information is reasonably available in this proposed AD takes about 47
because the interested parties have work-hours per product, at an average List of Subjects in 14 CFR Part 39
access to it through their normal course labor rate of $85 per work-hour. Air transportation, Aircraft, Aviation
of business or by the means identified Required parts cost about $1,444 per safety, Incorporation by reference,
in the ADDRESSES section. product. Based on these figures, the Safety.
estimated cost of the replacement
FAA’s Determination and Requirements required by AD 2001–12–18 is $5,439 The Proposed Amendment
of This Proposed AD per product. Accordingly, under the authority
This product has been approved by We also estimate that it would take delegated to me by the Administrator,
the aviation authority of another about 47 work-hours per product to the FAA proposes to amend 14 CFR part
country, and is approved for operation comply with the basic requirements of 39 as follows:
in the United States. Pursuant to our this proposed AD. The average labor
bilateral agreement with the State of rate is $85 per work-hour. Required PART 39—AIRWORTHINESS
Design Authority, we have been notified parts would cost about $6,480 per DIRECTIVES
of the unsafe condition described in the product. Based on these figures, we
estimate the cost of this proposed AD on ■ 1. The authority citation for part 39
MCAI and service information
U.S. operators to be $31,425, or $10,475 continues to read as follows:
referenced above. We are proposing this
per product. Authority: 49 U.S.C. 106(g), 40113, 44701.
AD because we evaluated all pertinent
information and determined an unsafe Authority for This Rulemaking § 39.13 [Amended]
condition exists and is likely to exist or Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by
develop on other products of the same specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
type design. rules on aviation safety. Subtitle I, 2001–12–18, Amendment 39–12274 (66
Differences Between This Proposed AD section 106, describes the authority of FR 33014, June 20, 2001) and adding the
and the MCAI or Service Information the FAA Administrator. ‘‘Subtitle VII: following new AD:
Aviation Programs,’’ describes in more Airbus Defense and Space S.A. (Formerly
EASA Airworthiness Directive 2014– detail the scope of the Agency’s Known as Construcciones Aeronauticas,
0262, dated December 5, 2014, specifies authority. S.A.): Docket No. FAA–2015–8465;
an applicability for Airbus Defense and We are issuing this rulemaking under Directorate Identifier 2014–NM–239–AD.
Space S.A. Model CN–235–100 and the authority described in ‘‘Subtitle VII,
–200 airplanes, serial numbers C–016 (a) Comments Due Date
Part A, Subpart III, Section 44701:
through C–073. This AD specifies an General requirements.’’ Under that We must receive comments by March 4,
applicability for Model CN–235 section, Congress charges the FAA with 2016.
airplanes, serial numbers C–001 through promoting safe flight of civil aircraft in (b) Affected ADs
C–015 inclusive and serial number C– air commerce by prescribing regulations This AD replaces AD 2001–12–18,
074; and Model CN–235–100 and –200 for practices, methods, and procedures Amendment 39–12274 (66 FR 33014, June
airplanes, serial numbers C–016 through the Administrator finds necessary for 20, 2001).
C–073 inclusive. The retained one-time safety in air commerce. This regulation (c) Applicability
action in paragraph (g) of this proposed is within the scope of that authority
AD is also applicable to Model CN–235 because it addresses an unsafe condition This AD applies to Airbus Defense and
airplanes, serial numbers C–001 through Space S.A. (Formerly Known as
that is likely to exist or develop on Construcciones Aeronauticas, S.A.) Model
C–015 inclusive and serial number C– products identified in this rulemaking CN–235 airplanes, serial numbers C–001
074, which are missing from EASA AD action. through C–015, inclusive and serial number
2014–0262, dated December 5, 2014. We
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Regulatory Findings C–074; and Model CN–235–100 and –200
understand EASA considered Model airplanes, serial numbers C–001 through C–
CN–235 airplanes with these serial We determined that this proposed AD 074, inclusive; certificated in any category.
numbers that have already performed would not have federalism implications (d) Subject
this one-time action. For this reason, under Executive Order 13132. This
Model CN–235 airplanes, serial proposed AD would not have a Air Transport Association (ATA) of
America Code 76, Engine Controls.
numbers C–001 through C–015 substantial direct effect on the States, on
inclusive and serial number C–074 are the relationship between the national (e) Reason
added to this proposed AD. This issue Government and the States, or on the This AD was prompted by reports of new
has been coordinated with EASA. distribution of power and occurrences of cable disruption on a certain
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![Federal Register / Vol. 81, No. 11 / Tuesday, January 19, 2016 / Proposed Rules 2785
part number; the disruption is caused by (g) Retained Action for the Power Lever and (h) New Requirement of This AD:
microcracks along the cable surface. We are Condition Lever Control Stops, With No Replacement
issuing this AD to prevent fatigue of the Changes At the applicable compliance times
engine control cables, leading to breakage of This paragraph restates the requirements of specified in table 1 to paragraph (h) of this
the cables, which could result in reduced paragraph (a) of AD 2001–12–18, AD: Replace each power lever and condition
controllability of the airplane. Amendment 39–12274 (66 FR 33014, June lever Teleflex cable having part number (P/
N) 72830–20 with a new or serviceable part,
(f) Compliance 20, 2001). Within 15 days after July 25, 2001
in accordance with Airbus Military Alert
(the effective date of AD 2001–12–18): Rig
Comply with this AD within the Operators Transmission AOT–CN235–76–
the power lever and condition lever control 0001, dated May 27, 2014. Repeat the
compliance times specified, unless already stops, in accordance with CASA COM 235– replacement thereafter at intervals not to
done. 140, Revision 01, dated March 21, 2000. 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 Compliance time
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 total flight cycles ........................... Within 300 flight cycles or 12 months after the effective date of this AD,
whichever occurs first.
Equal to or more than 6,000 total flight cycles but fewer than 7,000 Within 200 flight cycles or 6 months after the effective date of this AD,
total flight cycles. whichever occurs first.
Equal to or more than 7,000 total flight cycles ........................................ Within 100 flight cycles or 3 months after the effective date of this AD,
whichever occurs first.
(i) Parts Installation Limitations the DOA, the approval must include the DEPARTMENT OF TRANSPORTATION
As of the effective date of this AD, no DOA-authorized signature.
person may install, on any airplane, a Federal Aviation Administration
(k) Related Information
Teleflex cable having P/N 72830–20, unless
the cable has accumulated fewer than 5,000 (1) Refer to Mandatory Continuing 14 CFR Part 39
total flight cycles since its first installation on Airworthiness Information (MCAI) EASA
an airplane. Airworthiness Directive 2014–0262, dated [Docket No. FAA–2015–8464; Directorate
December 5, 2014, for related information. Identifier 2015–NM–050–AD]
(j) Other FAA AD Provisions
This MCAI may be found in the AD docket RIN 2120–AA64
The following provisions also apply to this
on the Internet at http://www.regulations.gov
AD: Airworthiness Directives; Bombardier,
(1) Alternative Methods of Compliance by searching for and locating Docket No.
(AMOCs): The Manager, International FAA–2015–8465. Inc. Airplanes
Branch, ANM–116, Transport Airplane (2) For service information identified in
AGENCY: Federal Aviation
Directorate, FAA, has the authority to this AD, contact EADS–CASA, Military
Administration (FAA), DOT.
approve AMOCs for this AD, if requested Transport Aircraft Division (MTAD),
using the procedures found in 14 CFR 39.19. ACTION: Notice of proposed rulemaking
Integrated Customer Services (ICS),
In accordance with 14 CFR 39.19, send your Technical Services, Avenida de Aragón 404, (NPRM).
request to your principal inspector or local 28022 Madrid, Spain; telephone +34 91 585
Flight Standards District Office, as
SUMMARY: We propose to adopt a new
55 84; fax +34 91 585 55 05; email airworthiness directive (AD) for all
appropriate. If sending information directly MTA.TechnicalService@casa.eads.net;
to the International Branch, send it to ATTN: Bombardier, Inc. Model DHC–8–400
Internet http://www.eads.net. You may view series airplanes. This proposed AD was
Shahram Daneshmandi, Aerospace Engineer,
International Branch, ANM–116, Transport this service information at the FAA, prompted by a revision by the
Airplane Directorate, FAA, 1601 Lind Transport Airplane Directorate, 1601 Lind manufacturer to the Certification
Avenue SW., Renton, WA 98057–3356; Avenue SW., Renton, WA. For information Maintenance Requirements (CMR) of the
telephone 425–227–1112; fax 425–227–1149. on the availability of this material at the Airworthiness Limitation Items (ALI), in
Information may be emailed to: 9-ANM-116- FAA, call 425–227–1221. the Maintenance Requirement Manual
AMOC-REQUESTS@faa.gov. Before using (MRM), that introduces a new CMR task
Issued in Renton, Washington, on
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal December 31, 2015. that requires repetitive operational
inspector, the manager of the local flight Phil Forde, checks of the propeller overspeed
standards district office/certificate holding Acting Manager, Transport Airplane
governor. This proposed AD would
district office. The AMOC approval letter Directorate, Aircraft Certification Service. require revising the airplane
must specifically reference this AD. maintenance program or inspection
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
[FR Doc. 2016–00377 Filed 1–15–16; 8:45 am]
(2) Contacting the Manufacturer: As of the program, as applicable, to incorporate a
effective date of this AD, for any requirement BILLING CODE 4910–13–P
new CMR task. We are proposing this
in this AD to obtain corrective actions from AD to prevent dormant failure of the
a manufacturer, the action must be propeller overspeed governor, which
accomplished using a method approved by may lead to a loss of propeller
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
overspeed protection and result in high
the European Aviation Safety Agency propeller drag in-flight.
(EASA); or EADS CASA’s EASA Design DATES: We must receive comments on
Organization Approval (DOA). If approved by this proposed AD by March 4, 2016.
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Document Created: 2016-01-16 01:11:26
Document Modified: 2016-01-16 01:11:26
| 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 March 4, 2016. | |
| 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 | 81 FR 2783 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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