Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes, 25587-25590 [2018-11699]

Download as PDF sradovich on DSK3GMQ082PROD with PROPOSALS Federal Register / Vol. 83, No. 107 / Monday, June 4, 2018 / Proposed Rules benefit include adding a savings component, financial education, reporting of members’ payment of PALs I loans to credit bureaus, or electronic loan transactions as part of a PALs I program. In addition, although a Federal credit union cannot require members to authorize a payroll deduction, a Federal credit union should encourage or incentivize members to utilize payroll deduction. (2) Underwriting. Federal credit unions need to develop minimum underwriting standards that account for a member’s need for quickly available funds, while adhering to principles of responsible lending. Underwriting standards should address required documentation for proof of employment or income, including at least two recent paycheck stubs. Federal credit unions should be able to use a borrower’s proof of recurring income as the key criterion in developing standards for maturity lengths and loan amounts so a borrower can manage repayment of the loan. For members with established accounts, Federal credit unions should only need to review a member’s account records and proof of recurring income or employment. (3) Risk avoidance. Federal credit unions need to consider risk avoidance strategies, including: Requiring members to participate in direct deposit and conducting a thorough evaluation of the Federal credit union’s resources and ability to engage in a PALs I loan program. (iv)(A) Payday alternative loans II (PALs II). Notwithstanding the provisions in paragraph (c)(7)(ii) of this section, a Federal credit union may charge an interest rate of 1000 basis points above the maximum interest rate as established by the Board, provided the Federal credit union is making a closed-end loan in accordance with the following conditions: (1) The principal of the loan is not more than $2,000; (2) The loan has a minimum maturity term of one month and a maximum maturity term of twelve months; (3) The Federal credit union does not make more than one PALs loan at a time to a borrower; (4) The Federal credit union must not roll-over any PALs II loan; (i) The prohibition against roll-overs does not apply to an extension of the loan term within the maximum loan terms in paragraph (c)(7)(iv)(2)(j)(1)(ii) provided the Federal credit union does not charge any additional fees or extend any new credit. (ii) [Reserved] (5) The Federal credit union fully amortizes the loan; VerDate Sep<11>2014 16:57 Jun 01, 2018 Jkt 244001 (6) The Federal credit union charges an application fee to all members applying for a new loan that reflects the actual costs associated with processing the application, but in no case may the application fee exceed $20; and (7) The Federal credit union includes, in its written lending policies, a limit on the aggregate dollar amount of PALs I and PALs II loans made under this section of a maximum of 20% of net worth and implements appropriate underwriting guidelines to minimize risk; for example, requiring a borrower to verify employment by producing at least two recent pay stubs. (B) PALs II Loan Program guidance and best practices. The PALs II loan program guidance and best practices are the same as those outlined for PALs I in paragraph (c)(7)(iii)(B) of this section. [FR Doc. 2018–11591 Filed 6–1–18; 8:45 am] BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration [Docket No. FAA–2018–0493; Product Identifier 2017–NM–141–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN–235, CN–235–100, CN–235–200, CN–235–300, and C–295 airplanes. This proposed AD was prompted by reports that cracks were found on the door mechanism actuator shaft assemblies of the nose landing gear (NLG). This proposed AD would require repetitive inspections of the NLG door mechanism actuator shaft assemblies having certain part numbers, and corrective actions if necessary. This proposed AD would also provide an optional terminating action for the repetitive inspections for Model CN–235, CN–235–100, CN–235– 200, and CN–235–300 airplanes. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 19, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR SUMMARY: Frm 00005 Fmt 4702 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus Defense and Space Services/Engineering Support, ´ Avenida de Aragon 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 31 27; email MTA.TechnicalService@airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Examining the AD Docket 14 CFR Part 39 PO 00000 25587 Sfmt 4702 You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0493; 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 NPRM, 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 Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3220. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2018–0493; Product Identifier 2017– NM–141–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM based on those comments. E:\FR\FM\04JNP1.SGM 04JNP1 25588 Federal Register / Vol. 83, No. 107 / Monday, June 4, 2018 / Proposed Rules 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 NPRM. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0181, dated September 18, 2017 (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: Cracks were reportedly found on nose landing gear (NLG) door actuator shaft assemblies on CN–235 aeroplanes. The subsequent design review determined that combined or multiple rupture of the affected shaft assembly could occur, without this being signalised to the flight crew. This condition, if not detected and corrected, could lead to an in-flight NLG door opening, possibly resulting in detachment of the affected door, with consequent damage to, or reduced control of, the aeroplane and injury to persons on the ground. To address this unsafe condition, Airbus Defence & Space (D&S) issued Alert Operators Transmissions AOT–CN235–32– 0001 Revision (Rev.) 2 and AOT–C295–32– 0001 Rev. 2 to provide inspection instructions. For the reasons described above, this [EASA] AD requires repetitive detailed (DET) or special detailed [rototest] inspections of the NLG door actuator shaft assembly, as applicable, and, depending on findings, corrective actions [including replacement of any cracked component, or cracked NLG door mechanism actuator shaft assembly with a serviceable part]. This [EASA] AD also introduces a modification for CN–235 aeroplanes as (optional) terminating action for the repetitive inspections as required by this [EASA] AD. 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–2018– 0493. Related Service Information Under 1 CFR Part 51 Airbus Defence and Space has issued Alert Operators Transmission (AOT) AOT–CN235–32–0001, Revision 2, dated October 26, 2016; and AOT AOT– C295–32–0001, Revision 2, dated October 26, 2016. This service information describes procedures for inspections for cracking of the door mechanism actuator shaft assemblies of the NLG, and corrective actions. These documents are distinct since they apply to different airplane models. Airbus Defence and Space has also issued Service Bulletin 235–32–0031C, dated September 22, 2016. This service information describes procedures for modification of the NLG door latching mechanism. 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. 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 Action Labor cost Parts cost Inspections .................... 21 work-hours × $85 per hour = $1,785 per inspection cycle. $0 ................. Cost per product Cost on U.S. operators $1,785 per inspection cycle. $24,990 per inspection cycle. OPTIONAL TERMINATING ACTION Action Labor cost Modification for Model CN–235 airplanes. 10 work-hours × $85 per hour = $850 ...................................................... We estimate the following costs to do any necessary replacements that would Parts cost be required based on the results of the proposed inspections. We have no way $33,626 Cost per product $34,476 of determining the number of aircraft that might need these replacements: ON-CONDITION COSTS sradovich on DSK3GMQ082PROD with PROPOSALS Action Labor cost Replacement .................................... 14 work-hours × $85 per hour = $1,190 ................................................... 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 VerDate Sep<11>2014 16:57 Jun 01, 2018 Jkt 244001 Parts cost the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 $18,720 Cost per product $19,910 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 E:\FR\FM\04JNP1.SGM 04JNP1 25589 Federal Register / Vol. 83, No. 107 / Monday, June 4, 2018 / Proposed Rules 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. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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. sradovich on DSK3GMQ082PROD with PROPOSALS 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. VerDate Sep<11>2014 16:57 Jun 01, 2018 Jkt 244001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.): Docket No. FAA–2018–0493; Product Identifier 2017–NM–141–AD. (a) Comments Due Date We must receive comments by July 19, 2018. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus Defense and Space S.A. airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model CN–235, CN–235–100, CN–235– 200, and CN–235–300 airplanes. (2) Model C–295 airplanes. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by reports that cracks were found on the door mechanism actuator shaft assemblies of the nose landing gear (NLG). We are issuing this AD to address such cracking, which could lead to an inflight NLG door opening and possibly result in detachment of the affected door, and consequent damage to, or reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Affected NLG Door Mechanism Actuator Shaft Assembly For the purpose of this AD, an affected NLG door mechanism actuator shaft assembly has part number (P/N) 35–42311– 00 or P/N 95–42315–00, depending on airplane model. (h) Detailed and Rototest Inspections (1) For any affected NLG door mechanism actuator shaft assembly: Before exceeding 600 flight hours accumulated by any NLG door mechanism lever or cam since new, or within 60 flight hours after the effective date of this AD, whichever occurs later, on the NLG door mechanism actuator shaft assembly with the NLG actuator shaft installed, do a detailed inspection for cracking of all installed NLG door mechanism levers and cams, in accordance with the instructions in Airbus Defence and Space Alert Operators Transmission (AOT) AOT–CN235–32–0001, Revision 2, dated October 26, 2016; or AOT AOT–C295–32– 0001, Revision 2, dated October 26, 2016; as applicable. Repeat the inspection thereafter at intervals not to exceed those specified in figure 1 to paragraph (h)(1) of this AD, depending on the findings or corrective actions completed, as specified in paragraphs (i)(1) and (i)(2) of this AD, after the previous inspection. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 FIGURE 1 TO PARAGRAPH (H)(1) OF THIS AD—REPETITIVE INSPECTION INTERVALS Findings/corrective action completed (after the previous inspection) NLG door vibration observed (during previous flights) ......... No findings ............................ Damaged components replaced. NLG door actuator shaft assembly replaced by new assembly. Interval 150 flight hours. 300 flight hours. 300 flight hours. 600 flight hours. (2) For any affected NLG door mechanism actuator shaft assembly: Before exceeding 1,800 flight hours accumulated by the NLG door shaft of the NLG door mechanism actuator shaft assembly since new, or within 60 flight hours after the effective date of this AD, whichever occurs later, do a rototest or detailed inspection of the NLG door actuator shaft, in accordance with the instructions in Airbus Defence and Space AOT AOT– CN235–32–0001, Revision 2, dated October 26, 2016; or AOT AOT–C295–32–0001, Revision 2, dated October 26, 2016; as applicable. Repeat the rototest or detailed inspection thereafter at intervals not to exceed those specified in figure 2 to paragraph (h)(2) of this AD, depending on the inspection method used during the most recent inspection. FIGURE 2 TO PARAGRAPH (H)(2) OF THIS AD—REPETITIVE INSPECTION INTERVALS Inspection method Rototest ..................... Detailed ..................... Interval 900 flight hours. 600 flight hours. (i) Corrective Actions (1) During any detailed inspection required by paragraph (h)(1) of this AD, if any crack with a length of 18 millimeters (mm) (0.709 inches) or more is found, or if there is more than one crack with a length of less than 18 mm (0.709 inch) found, before further flight, replace the cracked component, or replace the NLG door mechanism actuator shaft assembly with a serviceable part, in accordance with the instructions of Airbus Defence and Space AOT AOT–CN235–32– 0001, Revision 2, dated October 26, 2016; or AOT AOT–C295–32–0001, Revision 2, dated October 26, 2016; as applicable. (2) During any detailed inspection required by paragraph (h)(1) of this AD, if a single crack with a length of less than 18 mm (0.709 inch) is found, within 5 flight cycles after the detailed inspection when the crack was found, replace any cracked component, or replace the NLG door mechanism actuator shaft assembly with a serviceable part, in accordance with the instructions of Airbus Defence and Space AOT AOT–CN235–32– 0001, Revision 2, dated October 26, 2016; or AOT AOT–C295–32–0001, Revision 2, dated October 26, 2016; as applicable. E:\FR\FM\04JNP1.SGM 04JNP1 25590 Federal Register / Vol. 83, No. 107 / Monday, June 4, 2018 / Proposed Rules (3) During any detailed or rototest inspection required by paragraph (h)(2) of this AD, if any crack is found, before further flight, replace the NLG door mechanism actuator shaft with a serviceable part, in accordance with the instructions of Airbus Defence and Space AOT AOT–CN235–32– 0001, Revision 2, dated October 26, 2016; or AOT AOT–C295–32–0001, Revision 2, dated October 26, 2016; as applicable. (j) Replacement not Terminating Action Accomplishment of any corrective action on an airplane, as required by paragraph (i)(1), (i)(2), or (i)(3) of this AD, as applicable, is not terminating action for the repetitive detailed or rototest inspections required by paragraphs (h)(1) and (h)(2) of this AD, for that airplane. (k) Optional Terminating Action For Model CN–235, CN–235–100, CN–235– 200, and CN–235–300 airplanes: Modification of the NLG door latching mechanism, in accordance with the Accomplishment Instructions of Airbus Defence and Space Service Bulletin SB–235– 32–0031C, dated September 22, 2016, is terminating action for the repetitive inspections required by paragraphs (h)(1) and (h)(2) of this AD, for that airplane. (l) Parts Installation Limitation As of the effective date of this AD, installation of an NLG door mechanism actuator shaft assembly having P/N 35– 42311–00 or P/N 95–42315–00, or any of its components, is allowed, provided that the part is new; or provided that the assembly or the components, as applicable, has passed an inspection; in accordance with the instructions of Airbus Space and Defence AOT AOT–CN235–32–0001, Revision 2, dated October 26, 2016; or AOT AOT–C295– 32–0001, Revision 2, dated October 26, 2016; as applicable. sradovich on DSK3GMQ082PROD with PROPOSALS (m) Reporting Not Required Although Airbus Space and Defence AOT AOT–CN235–32–0001, Revision 2, dated October 26, 2016; and AOT AOT–C295–32– 0001, Revision 2, dated October 26, 2016; both specify to submit certain information to the manufacturer, this AD does not include that requirement. (n) Credit for Previous Actions This paragraph provides credit for the initial inspection required by paragraph (h)(1) and (h)(2) of this AD, and the corrective actions required by paragraphs (i)(1), (i)(2), and (i)(3) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraphs (n)(1) through (n)(4) of this AD. (1) Airbus Space and Defence AOT AOT– CN235–32–0001, dated September 29, 2015. (2) Airbus Space and Defence AOT AOT– CN235–32–0001, Revision 1, dated February 19, 2016. (3) Airbus Space and Defence AOT AOT– C295–32–0001, dated September 29, 2015. (4) Airbus Space and Defence AOT AOT– C295–32–0001, Revision 1, dated February 19, 2016. VerDate Sep<11>2014 16:57 Jun 01, 2018 Jkt 244001 (o) Other FAA AD Provisions DEPARTMENT OF TRANSPORTATION The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, 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 Section, send it to the attention of the person identified in paragraph (p)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus Space and Defense’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0181, dated September 18, 2017, 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–2018–0493. (2) For more information about this AD, contact Shahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3220. (3) For service information identified in this AD, contact Airbus Defense and Space Services/Engineering Support, Avenida de ´ Aragon 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 31 27; email MTA.TechnicalService@airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on May 23, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–11699 Filed 6–1–18; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0497; Product Identifier 2017–NM–140–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A300 B4–603, B4–620, and B4–622 airplanes; Model A300 F4– 605R airplanes; Model A300 C4–605R Variant F airplanes; and Model A300 B4–600R series airplanes. This proposed AD was prompted by reports of cracking on the frame (FR) 47 angle fitting. This proposed AD would require, depending on airplane configuration, a modification of certain angle fitting attachment holes, repetitive inspections for cracking of certain holes of the internal lower angle fitting web, certain holes of the internal lower angle fitting horizontal splicing, the aft bottom panel, and the FR47/Rib 1 junction area, and related investigative 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 July 19, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: 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 SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 SUMMARY: E:\FR\FM\04JNP1.SGM 04JNP1

Agencies

[Federal Register Volume 83, Number 107 (Monday, June 4, 2018)]
[Proposed Rules]
[Pages 25587-25590]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11699]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0493; Product Identifier 2017-NM-141-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 
that cracks were found on the door mechanism actuator shaft assemblies 
of the nose landing gear (NLG). This proposed AD would require 
repetitive inspections of the NLG door mechanism actuator shaft 
assemblies having certain part numbers, and corrective actions if 
necessary. This proposed AD would also provide an optional terminating 
action for the repetitive inspections for Model CN-235, CN-235-100, CN-
235-200, and CN-235-300 airplanes. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 19, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: 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; telephone +34 91 585 55 84; fax 
+34 91 585 31 27; email [email protected]. You may view 
this referenced service information at the FAA, Transport Standards 
Branch, 2200 South 216th St., Des Moines, WA. For information on the 
availability of this material at the FAA, call 206-231-3195.

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-2018-
0493; 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 NPRM, 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 Section, Transport Standards Branch, FAA, 2200 
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3220.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0493; 
Product Identifier 2017-NM-141-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM based on 
those comments.

[[Page 25588]]

    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 NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0181, dated September 18, 2017 (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:

    Cracks were reportedly found on nose landing gear (NLG) door 
actuator shaft assemblies on CN-235 aeroplanes. The subsequent 
design review determined that combined or multiple rupture of the 
affected shaft assembly could occur, without this being signalised 
to the flight crew.
    This condition, if not detected and corrected, could lead to an 
in-flight NLG door opening, possibly resulting in detachment of the 
affected door, with consequent damage to, or reduced control of, the 
aeroplane and injury to persons on the ground.
    To address this unsafe condition, Airbus Defence & Space (D&S) 
issued Alert Operators Transmissions AOT-CN235-32-0001 Revision 
(Rev.) 2 and AOT-C295-32-0001 Rev. 2 to provide inspection 
instructions.
    For the reasons described above, this [EASA] AD requires 
repetitive detailed (DET) or special detailed [rototest] inspections 
of the NLG door actuator shaft assembly, as applicable, and, 
depending on findings, corrective actions [including replacement of 
any cracked component, or cracked NLG door mechanism actuator shaft 
assembly with a serviceable part]. This [EASA] AD also introduces a 
modification for CN-235 aeroplanes as (optional) terminating action 
for the repetitive inspections as required by this [EASA] AD.

    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-2018-
0493.

Related Service Information Under 1 CFR Part 51

    Airbus Defence and Space has issued Alert Operators Transmission 
(AOT) AOT-CN235-32-0001, Revision 2, dated October 26, 2016; and AOT 
AOT-C295-32-0001, Revision 2, dated October 26, 2016. This service 
information describes procedures for inspections for cracking of the 
door mechanism actuator shaft assemblies of the NLG, and corrective 
actions. These documents are distinct since they apply to different 
airplane models.
    Airbus Defence and Space has also issued Service Bulletin 235-32-
0031C, dated September 22, 2016. This service information describes 
procedures for modification of the NLG door latching mechanism.
    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.

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
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
            Action                    Labor cost            Parts cost       Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Inspections...................  21 work-hours x $85     $0................  $1,785 per         $24,990 per
                                 per hour = $1,785 per                       inspection cycle.  inspection
                                 inspection cycle.                                              cycle.
----------------------------------------------------------------------------------------------------------------


                                           Optional Terminating Action
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Modification for Model CN-235 airplanes....  10 work-hours x $85 per hour = $850         $33,626         $34,476
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed 
inspections. We have no way of determining the number of aircraft that 
might need these replacements:

                                               On-condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement................................  14 work-hours x $85 per hour =              $18,720         $19,910
                                              $1,190.
----------------------------------------------------------------------------------------------------------------

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

[[Page 25589]]

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.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

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-2018-0493; Product Identifier 
2017-NM-141-AD.

(a) Comments Due Date

    We must receive comments by July 19, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus Defense and Space S.A. airplanes 
identified in paragraphs (c)(1) and (c)(2) of this AD, certificated 
in any category, all manufacturer serial numbers.
    (1) Model CN-235, CN-235-100, CN-235-200, and CN-235-300 
airplanes.
    (2) Model C-295 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by reports that cracks were found on the 
door mechanism actuator shaft assemblies of the nose landing gear 
(NLG). We are issuing this AD to address such cracking, which could 
lead to an in-flight NLG door opening and possibly result in 
detachment of the affected door, and consequent damage to, or 
reduced control of the airplane.

(f) Compliance

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

(g) Definition of Affected NLG Door Mechanism Actuator Shaft Assembly

    For the purpose of this AD, an affected NLG door mechanism 
actuator shaft assembly has part number (P/N) 35-42311-00 or P/N 95-
42315-00, depending on airplane model.

(h) Detailed and Rototest Inspections

    (1) For any affected NLG door mechanism actuator shaft assembly: 
Before exceeding 600 flight hours accumulated by any NLG door 
mechanism lever or cam since new, or within 60 flight hours after 
the effective date of this AD, whichever occurs later, on the NLG 
door mechanism actuator shaft assembly with the NLG actuator shaft 
installed, do a detailed inspection for cracking of all installed 
NLG door mechanism levers and cams, in accordance with the 
instructions in Airbus Defence and Space Alert Operators 
Transmission (AOT) AOT-CN235-32-0001, Revision 2, dated October 26, 
2016; or AOT AOT-C295-32-0001, Revision 2, dated October 26, 2016; 
as applicable. Repeat the inspection thereafter at intervals not to 
exceed those specified in figure 1 to paragraph (h)(1) of this AD, 
depending on the findings or corrective actions completed, as 
specified in paragraphs (i)(1) and (i)(2) of this AD, after the 
previous inspection.

Figure 1 to Paragraph (h)(1) of This AD--Repetitive Inspection Intervals
------------------------------------------------------------------------
   Findings/corrective action completed
      (after the previous inspection)                 Interval
------------------------------------------------------------------------
NLG door vibration observed...............  150 flight hours.
(during previous flights).................
No findings...............................  300 flight hours.
Damaged components replaced...............  300 flight hours.
NLG door actuator shaft assembly replaced   600 flight hours.
 by new assembly.
------------------------------------------------------------------------

    (2) For any affected NLG door mechanism actuator shaft assembly: 
Before exceeding 1,800 flight hours accumulated by the NLG door 
shaft of the NLG door mechanism actuator shaft assembly since new, 
or within 60 flight hours after the effective date of this AD, 
whichever occurs later, do a rototest or detailed inspection of the 
NLG door actuator shaft, in accordance with the instructions in 
Airbus Defence and Space AOT AOT-CN235-32-0001, Revision 2, dated 
October 26, 2016; or AOT AOT-C295-32-0001, Revision 2, dated October 
26, 2016; as applicable. Repeat the rototest or detailed inspection 
thereafter at intervals not to exceed those specified in figure 2 to 
paragraph (h)(2) of this AD, depending on the inspection method used 
during the most recent inspection.

Figure 2 to Paragraph (h)(2) of This AD--Repetitive Inspection Intervals
------------------------------------------------------------------------
             Inspection method                        Interval
------------------------------------------------------------------------
Rototest..................................  900 flight hours.
Detailed..................................  600 flight hours.
------------------------------------------------------------------------

(i) Corrective Actions

    (1) During any detailed inspection required by paragraph (h)(1) 
of this AD, if any crack with a length of 18 millimeters (mm) (0.709 
inches) or more is found, or if there is more than one crack with a 
length of less than 18 mm (0.709 inch) found, before further flight, 
replace the cracked component, or replace the NLG door mechanism 
actuator shaft assembly with a serviceable part, in accordance with 
the instructions of Airbus Defence and Space AOT AOT-CN235-32-0001, 
Revision 2, dated October 26, 2016; or AOT AOT-C295-32-0001, 
Revision 2, dated October 26, 2016; as applicable.
    (2) During any detailed inspection required by paragraph (h)(1) 
of this AD, if a single crack with a length of less than 18 mm 
(0.709 inch) is found, within 5 flight cycles after the detailed 
inspection when the crack was found, replace any cracked component, 
or replace the NLG door mechanism actuator shaft assembly with a 
serviceable part, in accordance with the instructions of Airbus 
Defence and Space AOT AOT-CN235-32-0001, Revision 2, dated October 
26, 2016; or AOT AOT-C295-32-0001, Revision 2, dated October 26, 
2016; as applicable.

[[Page 25590]]

    (3) During any detailed or rototest inspection required by 
paragraph (h)(2) of this AD, if any crack is found, before further 
flight, replace the NLG door mechanism actuator shaft with a 
serviceable part, in accordance with the instructions of Airbus 
Defence and Space AOT AOT-CN235-32-0001, Revision 2, dated October 
26, 2016; or AOT AOT-C295-32-0001, Revision 2, dated October 26, 
2016; as applicable.

(j) Replacement not Terminating Action

    Accomplishment of any corrective action on an airplane, as 
required by paragraph (i)(1), (i)(2), or (i)(3) of this AD, as 
applicable, is not terminating action for the repetitive detailed or 
rototest inspections required by paragraphs (h)(1) and (h)(2) of 
this AD, for that airplane.

(k) Optional Terminating Action

    For Model CN-235, CN-235-100, CN-235-200, and CN-235-300 
airplanes: Modification of the NLG door latching mechanism, in 
accordance with the Accomplishment Instructions of Airbus Defence 
and Space Service Bulletin SB-235-32-0031C, dated September 22, 
2016, is terminating action for the repetitive inspections required 
by paragraphs (h)(1) and (h)(2) of this AD, for that airplane.

(l) Parts Installation Limitation

    As of the effective date of this AD, installation of an NLG door 
mechanism actuator shaft assembly having P/N 35-42311-00 or P/N 95-
42315-00, or any of its components, is allowed, provided that the 
part is new; or provided that the assembly or the components, as 
applicable, has passed an inspection; in accordance with the 
instructions of Airbus Space and Defence AOT AOT-CN235-32-0001, 
Revision 2, dated October 26, 2016; or AOT AOT-C295-32-0001, 
Revision 2, dated October 26, 2016; as applicable.

(m) Reporting Not Required

    Although Airbus Space and Defence AOT AOT-CN235-32-0001, 
Revision 2, dated October 26, 2016; and AOT AOT-C295-32-0001, 
Revision 2, dated October 26, 2016; both specify to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

(n) Credit for Previous Actions

    This paragraph provides credit for the initial inspection 
required by paragraph (h)(1) and (h)(2) of this AD, and the 
corrective actions required by paragraphs (i)(1), (i)(2), and (i)(3) 
of this AD, if those actions were performed before the effective 
date of this AD using the applicable service information identified 
in paragraphs (n)(1) through (n)(4) of this AD.
    (1) Airbus Space and Defence AOT AOT-CN235-32-0001, dated 
September 29, 2015.
    (2) Airbus Space and Defence AOT AOT-CN235-32-0001, Revision 1, 
dated February 19, 2016.
    (3) Airbus Space and Defence AOT AOT-C295-32-0001, dated 
September 29, 2015.
    (4) Airbus Space and Defence AOT AOT-C295-32-0001, Revision 1, 
dated February 19, 2016.

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, 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 Section, send it to the attention of 
the person identified in paragraph (p)(2) of this AD. 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 
Section, Transport Standards Branch, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus Space and Defense's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0181, dated September 18, 2017, 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-2018-0493.
    (2) For more information about this AD, contact Shahram 
Daneshmandi, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax 206-231-3220.
    (3) For service information identified in this AD, contact 
Airbus Defense and Space Services/Engineering Support, Avenida de 
Arag[oacute]n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; 
fax +34 91 585 31 27; email [email protected]. You may 
view this service information at the FAA, Transport Standards 
Branch, 2200 South 216th St., Des Moines, WA. For information on the 
availability of this material at the FAA, call 206-231-3195.

    Issued in Des Moines, Washington, on May 23, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-11699 Filed 6-1-18; 8:45 am]
 BILLING CODE 4910-13-P