Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes, 46369-46372 [2018-19183]

Download as PDF Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0493; Product Identifier 2017–NM–141–AD; Amendment 39–19389; AD 2018–18–10] RIN 2120–AA64 Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting 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 AD was prompted by reports that cracks were found on the door mechanism actuator shaft assemblies of the nose landing gear (NLG). This AD requires repetitive inspections of the NLG door mechanism actuator shaft assemblies having certain part numbers, and corrective actions if necessary. This 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 issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective October 18, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 18, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus Defense and Space Services/ Engineering Support, Avenida de Arago´n 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. It is also available on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0493. daltland on DSKBBV9HB2PROD with RULES DATES: Examining the AD Docket You may examine the AD docket on the internet at https:// VerDate Sep<11>2014 17:40 Sep 12, 2018 Jkt 244001 www.regulations.gov by searching for and locating Docket No. FAA–2018– 0493; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Defense and Space S.A. Model CN–235, CN–235–100, CN– 235–200, CN–235–300, and C–295 airplanes. The NPRM published in the Federal Register on June 4, 2018 (83 FR 25587). The NPRM was prompted by reports that cracks were found on the door mechanism actuator shaft assemblies of the NLG. The NPRM proposed to require repetitive inspections of the NLG door mechanism actuator shaft assemblies having certain part numbers, and corrective actions if necessary. The NPRM also proposed to 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 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. 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 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 46369 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0493. Comments We gave the public the opportunity to participate in developing this final rule. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. 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 SB–235–32– 0031C, dated September 22, 2016. This E:\FR\FM\13SER1.SGM 13SER1 46370 Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations 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. Costs of Compliance We estimate that this AD affects 14 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Inspections ........ 21 work-hours × $85 per hour = $1,785 per inspection cycle. Cost per product $0 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 be required based on the results of the inspections. We have no way of Parts cost Cost per product $33,626 $34,476 determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replacement ................................................................. 14 work-hours × $85 per hour = $1,190 ...................... daltland on DSKBBV9HB2PROD with RULES 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. This 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 and associated appliances to VerDate Sep<11>2014 17:40 Sep 12, 2018 Jkt 244001 Parts cost Cost per product $18,720 $19,910 the Director of the System Oversight Division. the FAA amends 14 CFR part 39 as follows: Regulatory Findings PART 39—AIRWORTHINESS DIRECTIVES This AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: (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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 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 adding the following new airworthiness directive (AD): ■ 2018–18–10 Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.): Amendment 39– 19389; Docket No. FAA–2018–0493; Product Identifier 2017–NM–141–AD. (a) Effective Date This AD is effective October 18, 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:\FR\FM\13SER1.SGM 13SER1 Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations (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 46371 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 (flight hours) NLG door vibration observed (during previous flights) ................................................................................................................... No findings ....................................................................................................................................................................................... Damaged components replaced ...................................................................................................................................................... NLG door actuator shaft assembly replaced 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 (flight hours) Rototest ............................ Detailed ............................. 900 600 daltland on DSKBBV9HB2PROD with RULES (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. VerDate Sep<11>2014 17:40 Sep 12, 2018 Jkt 244001 (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. (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 PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 150 300 300 600 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, E:\FR\FM\13SER1.SGM 13SER1 46372 Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations 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 Defense and Space S.A.’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. daltland on DSKBBV9HB2PROD with RULES (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0181, dated September 18, 2017, for related information, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–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) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(3) and (q)(4) of this AD. (q) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Defence and Space AOT AOT– CN235–32–0001, Revision 2, dated October 26, 2016. (ii) Airbus Defence and Space AOT AOT– C295–32–0001, Revision 2, dated October 26, 2016. (iii) Airbus Defence and Space Service Bulletin SB–235–32–0031C, dated September 22, 2016. (3) For service information identified in this AD, contact Airbus Defense and Space Services/Engineering Support, Avenida de Arago´n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 31 27; email MTA.TechnicalService@airbus.com. (4) 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. VerDate Sep<11>2014 17:40 Sep 12, 2018 Jkt 244001 (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on August 23, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–19183 Filed 9–12–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0506; Product Identifier 2018–NM–045–AD; Amendment 39–19378; AD 2018–17–24] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350–941 airplanes. This AD was prompted by the discovery of inadequate corrosion protection in certain areas of the horizontal stabilizer and the rear fuselage cone structure. This AD requires application of sealant and protective treatment on the affected areas of the horizontal stabilizer and the rear fuselage cone structure and, for certain airplanes, modification of the trimmable horizontal stabilizer (THS) torsion box and re-identification of the elevator. We are issuing this AD to address the unsafe condition on these products. 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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0506. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0506; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is Docket Operations, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Kathleen Arrigotti, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218. SUPPLEMENTARY INFORMATION: SUMMARY: Discussion This AD is effective October 18, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 18, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email continuedairworthiness.a350@airbus.com; internet https://www.airbus.com. You may view this service information at the We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus SAS Model A350–941 airplanes. The NPRM published in the Federal Register on June 11, 2018 (83 FR 26882). The NPRM was prompted by the discovery of inadequate corrosion protection in certain areas of the horizontal stabilizer and the rear fuselage cone structure. The NPRM proposed to require application of sealant and protective treatment on the affected areas of the horizontal stabilizer and the rear fuselage cone structure and, for certain airplanes, modification of the THS torsion box and re-identification of the elevator. We are issuing this AD to address reduced structural integrity of the horizontal stabilizer and the rear fuselage cone structure. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018–0036, dated February 7, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus SAS Model A350–941 airplanes. The MCAI states: DATES: PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 E:\FR\FM\13SER1.SGM 13SER1

Agencies

[Federal Register Volume 83, Number 178 (Thursday, September 13, 2018)]
[Rules and Regulations]
[Pages 46369-46372]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-19183]



[[Page 46369]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0493; Product Identifier 2017-NM-141-AD; Amendment 
39-19389; AD 2018-18-10]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting 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 AD was prompted by reports that 
cracks were found on the door mechanism actuator shaft assemblies of 
the nose landing gear (NLG). This AD requires repetitive inspections of 
the NLG door mechanism actuator shaft assemblies having certain part 
numbers, and corrective actions if necessary. This 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 issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective October 18, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 18, 
2018.

ADDRESSES: For service information identified in this final rule, 
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. It is also 
available on the internet at https://www.regulations.gov by searching 
for and locating Docket No. FAA-2018-0493.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0493; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Defense and 
Space S.A. Model CN-235, CN-235-100, CN-235-200, CN-235-300, and C-295 
airplanes. The NPRM published in the Federal Register on June 4, 2018 
(83 FR 25587). The NPRM was prompted by reports that cracks were found 
on the door mechanism actuator shaft assemblies of the NLG. The NPRM 
proposed to require repetitive inspections of the NLG door mechanism 
actuator shaft assemblies having certain part numbers, and corrective 
actions if necessary. The NPRM also proposed to 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 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.
    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 https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0493.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this final rule as proposed, 
except for minor editorial changes. We have determined that these minor 
changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

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 SB-235-
32-0031C, dated September 22, 2016. This

[[Page 46370]]

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.

Costs of Compliance

    We estimate that this AD affects 14 airplanes of U.S. registry.
    We estimate the following costs to comply with this 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 inspection  $24,990 per
                              per hour = $1,785                      cycle.                 inspection cycle.
                              per inspection 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 =           $33,626         $34,476
                                                 $850.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the 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 
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 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 and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 that this AD:
    (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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2018-18-10 Airbus Defense and Space S.A. (Formerly Known as 
Construcciones Aeronauticas, S.A.): Amendment 39-19389; Docket No. 
FAA-2018-0493; Product Identifier 2017-NM-141-AD.

 (a) Effective Date

    This AD is effective October 18, 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.

[[Page 46371]]

(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     Interval (flight
                 previous inspection)                        hours)
------------------------------------------------------------------------
NLG door vibration observed (during previous flights).               150
No findings...........................................               300
Damaged components replaced...........................               300
NLG door actuator shaft assembly replaced by new                     600
 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
------------------------------------------------------------------------
                                                        Interval (flight
                   Inspection method                         hours)
------------------------------------------------------------------------
Rototest..............................................               900
Detailed..............................................               600
------------------------------------------------------------------------

(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.
    (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,

[[Page 46372]]

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 Defense and Space S.A.'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, for related information. This MCAI may be found in the 
AD docket on the internet at https://www.regulations.gov by searching 
for and locating Docket No. FAA-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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(3) and (q)(4) of this AD.

 (q) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Defence and Space AOT AOT-CN235-32-0001, Revision 2, 
dated October 26, 2016.
    (ii) Airbus Defence and Space AOT AOT-C295-32-0001, Revision 2, 
dated October 26, 2016.
    (iii) Airbus Defence and Space Service Bulletin SB-235-32-0031C, 
dated September 22, 2016.
    (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].
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on August 23, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-19183 Filed 9-12-18; 8:45 am]
 BILLING CODE 4910-13-P